c5	c10	c12	c14	c15	c16	c17	c18	c20	c25	c35	c40	c90	c100	c110	c120	c130	c140	c150	c152	c160	c170	c180	c190	c192	c200	c210	c220	c230	c240	c250	c260	c270	c280	c290	c300	c310a	c310b	c310c	c310d	c314a	c314b	c314c	c314d	c320a	c320b	c320c	c324a	c324b	c324c	c330	c332	c340	c350	c360	c370	c380	c390	c400	c410	c420	c430	c440	c450	c460	c490	c510a	c510b	c510c	c510d	c510e	c510f	c602	c604	c606	c608	c610	c612	c614	c616	c620	c640	c652	c654	c660	eof
2000042800023	20000428	00023		2000	4	28	20000428AP005    	4	19980719	G	3140		WARNING SYSTEM  			DORNER	DO32  	DO328100    	2996000	NM  										COCKPIT	ACTIVATED       	A			EQGA	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	19	337PH					3020				FLT 359 - DEN-ASE - CREW BEGAN TAKEOFF ROLL AT 85 KNOTS, RECEIVED A FLIGHT GUIDANCE COMPUTER FAIL CAUTION CHIME AND ASSO	CIATED EICAS MESSAGE.  CREW ABORTED TAKEOFF AS A PRECAUTIONARY MEASURE.  CREW CLEARED RUNWAY AND RESET THE FLIGHT GUIDAN	CE COMPUTER.  FAIL CAUTION AND EICAS MESSAGE CLEARED.  CREW TAXIED BACK TO THE RUNWAY AND MADE AN UNEVENTFUL TAKEOFF.  (	M)			2	H	7	2 	4T			RT	A45NM
2000050800032	20000508	00032	CE  	2000	5	8	20000501SH011    	1	19980831	G	3710	B906	HOSE            			CESSNA	172   	172P        	2072436	CE  										VACUUM SYSTEM	DETERIORATED    	B			PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	65065	2364 				17275681				OWNER/OPERATOR COMPLAINED OF ERRATIC VACUUM PRESSURE AFTER INSTALLATION OF NEW VACUUM PUMP AT ANOTHER FACILITY.  UPON IN	SP OF VACUUM SYSTEM, FOUND ALL IMPERIAL EASTMAN HYTRON REDI-SEAL P/N B906 AND B903 HOSES INSTALLED IN THE VACUUM SYS HAD	 DETERIORATED INTERNALLY.  THIS CONDITION WAS UNDETECTABLE FROM THE OUTWARD APPEARANCE OF THE HOSES.  OF THE FIVE HOSES 	THAT WERE REPLACED, ONLY ONE SHOWED ANY SIGNS OF DRY-ROT OR DETERIORATION.  SUSPECT HOSES WERE ORIGINAL INSTALL BY MFG. 	 SUGGEST ALL ACFT HAVING IMPERIAL EASTMAN HYTRON REDI-SEAL HOSES INSTALLED, HAVE HOSES INSPECTED FOR INTERNAL DETERIORAT	ION OR REPLACE HOSES WITH ANOTHER TYPE HOSE.  AEROQUIP 306 AND 303 TYPE HOSES WERE USED IN REPAIR OF THIS AIRCRAFT. (X)	1	H	7	1 	3O			NT	3A12
2000050800033	20000508	00033	CE  	2000	5	8	20000501SH012    	1	19980831	G	3710	B903	HOSE            			CESSNA	172   	172P        	2072436	CE  										VACUUM SYSTEM	DETERIORATED    	B			PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	65065	2364 				17275681				OWNER/OPERATOR COMPLAINED OF ERRATIC VACUUM PRESSURE AFTER INSTALLATION OF NEW VACUUM PUMP AT ANOTHER FACILITY.  UPON IN	SP OF VACUUM SYSTEM, FOUND ALL IMPERIAL EASTMAN HYTRON REDI-SEAL P/N B906 AND B903 HOSES INSTALLED IN THE VACUUM SYS HAD	 DETERIORATED INTERNALLY.  THIS CONDITION WAS UNDETECTABLE FROM THE OUTWARD APPEARANCE OF THE HOSES.  OF THE FIVE HOSES 	THAT WERE REPLACED, ONLY ONE SHOWED ANY SIGNS OF DRY-ROT OR DETERIORATION.  SUSPECT HOSES WERE ORIGINAL INSTALL BY MFG. 	 SUGGEST ALL ACFT HAVING IMPERIAL EASTMAN HYTRON REDI-SEAL HOSES INSTALLED, HAVE HOSES INSPECTED FOR INTERNAL DETERIORAT	ION OR REPLACE HOSES WITH ANOTHER TYPE HOSE.  AEROQUIP 306 AND 303 TYPE HOSES WERE USED IN REPAIR OF THIS AIRCRAFT. (X)	1	H	7	1 	3O			NT	3A12
2000102400025	20001024	00025	SO  	2000	10	24	20000714SH011    	1	19981213	G	7714		TACHOMETER      			PIPER 	PA28  	PA28181     	7102807	SO  										INSTRUMENT PANEL	INACCURATE      	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			NM	11	6135J	6038 				287690350				PILOT COMPLAINED THAT ENGINE WAS NOT MAKING ENOUGH RPM.  CHECKED TACHOMETER WITH PHOTO TACHOMETER AND FOUND A/C TOOL TO 	BE 120 RPM - 140 RPM LOW THROUGHOUT FULL RANGE OF OPERATION.  UNIT WAS ORIGINAL TO AIRCRAFT.  INSTALLED REPLACEMENT TACH	 - MITCHELL, P/N DA-112-503.   (X)				1	L	7	1 	3O			 	2A13
2000102400042	20001024	00042	SO  	2000	10	24	20000714SH017    	1	19981230	G	2140	37077	HEATER          			PIPER 	PA23  	PA23250     	7102308	SO  											MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	713VS	497  				277405415				FOUND AIR SWITCH STUCK IN CLOSED POSITION.  IF COMBUSTION AIR MOTOR WOULD QUIT, FUEL WOULD STILL COTNINUE IN HEATER CREA	TING FINE HAZARD.  FOUND DURING AD COMPLIANCE. (X)					1	L	7	2 	3O			 	1A10
2000012900259	20000129	00259	EU  	2000	1	29	2000ZZZX245      	1	19980816	G	3340	03004021	GIMBAL ASSY     		SX5         	SNIAS 	350   	AS350B2     	8680813	EU  										SEARCH LIGHT	CORRODED        	B	P		S88R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	4059W	720  			0187	2933				BLACK PROTECTIVE COATING APPARENTLY DID NOT BOND PROPERLY.  AFTER SEPARATION OF THE PROTECTIVE COATING FROM THE PART'S S	URFACE, MOISTURE/WATER WOULD BE ENTRAPPED BETWEEN THE SURFACE OF THE PART AND THE PROTECTIVE COATING, ULTIMATELY CAUSING	 CORROSION.				1	G	7	1 	3U				H9EU
2000020500932	20000205	00932		2000	2	5	2000ZZZX267      	4	19980622	G	2211	501113202	COMPUTER        			LEAR  	35    	35LEAR      	5170600	CE  										COCKPIT	FAILED          	E				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			EA	21	600DT				1642	35017				MACH TRIM FAILED IN-FLIGHT, AIRCRAFT WOULD NOT DESCEND USING PRIMARY TRIM.  CREW HAD TO USE SECONDARY TRIM TO RETURN TO 	DEPARTURE AIRPORT.  AFTER COMPLETING CHECKLIST, CREW WENT BACK TO PRIMARY TRIM.					2	L	7	2 	4F				A10CE
2002071700098	20020717	00098	SO  	2002	7	17	2002FA0000788    	1	19981030	G	7810	654327	FLANGE          			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					EXHAUST SYS	BROKEN          	B			GFVR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	13	CGBCP					468408074	2733264R			PILOT EXPERIENCED LOW MP AT 22K.  SLOWLY BLED DOWN AT CRUISE.  PILOT SAID AT NORMAL 25 INCHES, IT BLED DOWN TO 22 INCHES	 WITH FUEL THROTTLE.  UPON CHECK MECHANIC NOTED EX STAINS ON R/CYL BANK AND DISCOVERED FLANGE COMPLETELY SEPARATED AT TU	RBO FLANGE AREA EXHAUST MANIFOLD.  NEW PART ORDERED AND REPLACED.				1	L	7	1 	3O	3	O	RT	A25SO   	E8CE
1998073100100	19980731	00100		1998	7	31	98UAL900320      	4	19980714	G	2210	106044714	YAW DAMPER      			BOEING	727   	727222      	1384073	NM  	PWA   	JT8   	JT8D15      	52051	NE  					E/E COMPT	FAILED          	A				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			WP	29	7278U					21425				CLIMBING OUT .70 MACH 330 TAS FLIGHT EXPERIENCED UNCONTROLLED MOVEMENT SIMILAR TO ALTERNATELY PUSHING THE LEFT AND RIGHT	 RUDDER PEDALS GIVING THE FLIGHT A COMBINATION OF ROLL AND YAW.  CUT POWER TO IDLE AND APPLIED 15 TO 20 DEGREES RIGHT AI	LERON AND THE AIRCRAFT STABILIZED.  CONTINUED TO OMA.  *S/D*  REPLACED LOWER YAW DAMPER DUE TO FAILED BITE TEST.  SYSTEM	 OPS CHECKS OK.			2	L	7	3 	4F	4	F		A3WE    	E2EA
1998031200101	19980312	00101	NE  	1998	3	12	98ZZZX1000       	2	19980218	G	8530	399359	CYLINDER        			AIRTRC	AT300 	AT301       	0390103	SW  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 2	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	3656C	559  	49   			3010304	419312			THE NR 2 CYLINDER WAS FOUND CRACKED FROM THE REAR SPARK PLUG PORT TO THE FRONT SPARK PLUG PORT ON THE UPPER INTAKE SIDE 	OF THE CYLINDER HEAD.					1	L	7	1 	3R	3	R		A9SW    	5E2
1998031200104	19980312	00104	SO  	1998	3	12	98ZZZX1003       	1	19980201	G	5753	6232400	HINGE BRACKET   			PIPER 	PA28  	PA28180     	7102808	SO  										LT FLAP	CORRODED        	B			BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	7753W	3211 				281758				FOUND MODERATE TO SEVERE CORROSION ON THE INTERIOR OF LEFT FLAP DURING RE-SKIN FOR HAIL DAMAGE.  CORROSION WENT COMPLETE	LY THROUGH THE OUTBOARD RIB ON THE INBOARD HINGE BRACKET.  THE ONLY WAY TO INSPECT THIS AREA IS BY REMOVING THE SKIN.					1	L	7	1 	3O				2A13
1998031200105	19980312	00105	SO  	1998	3	12	98ZZZX1004       	1	19980201	G	5753	6232801	RIB             			PIPER 	PA28  	PA28180     	7102808	SO  										LT FLAP NOSE	CORRODED        	B			BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	7753W	3211 				281758				FOUND MODERATE TO SEVERE CORROSION ON THE INTERIOR OF LEFT FLAP DURING RE-SKIN FOR HAIL DAMAGE.  CORROSION WENT COMPLETE	LY THROUGH THE OUTBOARD RIB ON THE INBOARD HINGE BRACKET.  THE ONLY WAY TO INSPECT THIS AREA IS BY REMOVING THE SKIN.					1	L	7	1 	3O				2A13
1998031200106	19980312	00106	CE  	1998	3	12	98ZZZX1005       	1	19980119	G	3213	5141001202	TRUNNION        			CESSNA	402   	402B        	207590P	CE  										RETRACT EAR	CRACKED         	B			QTVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	7947Q	9346 				402B0397				RETRACT ATTACH EAR CASTING BROKEN.  SPACER P/N S133-4P32 AND BOLT P/N 464 P4-26 REPLACED WITH 1 'AN' 5 BOLT AND OVERTORQ	UED CAUSING UNDO STRESS TO CASTING.					1	L	7	2 	3O				A7CE
1998031200107	19980312	00107		1998	3	12	98ZZZX1006       	4	19980223	G	3424	1394T100	TURN CORRDINATOR			CESSNA	441   	441         	2076020	CE  										COCKPIT	FAILED          	G				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			WP	07	988AE	1611 			8904129	441075				UNDER NORMAL NIGHT FLIGHT OPERATIONS, PILOT SMELLED LIGHT SMOKE IN COCKPIT.  RETURNED TO BASE, FOUND TURN CORRDINATOR IN	OPERABLE.					1	L	7	2 	3T			RT	A28CE
1998031200108	19980312	00108	CE  	1998	3	12	98ZZZX1007       	1	19980212	G	3010	261903311	TRANSITION DUCT 			LEAR  	35    	35A         	5170602	CE  										WING ANTI-ICE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	400DN	8962 				551				WING LEADING EDGE ANTI-ICE DUCT IS COLLAPSED BLOCKING AIRFLOW TO THE RIGHT WING ANTI-ICE.  TT:  8,961.8 HOURS.						2	L	7	2 	4F				A10CE
1998031200109	19980312	00109	EU  	1998	3	12	98ZZZX1008       	1	19980121	G	6320	350A32011000	EPICYCLIC       			SNIAS 	350   	AS350B2     	8680813	EU  										M/R	SCORED          	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		3021 			M267					EPICYCLIC SENT IN FOR MODERATE SCORING ON INNER RACE OF THREE GEARS AND SLIGHT PITTING ON ONE GEAR.						1	G	7	1 	3U				H9EU
1998031200110	19980312	00110	SW  	1998	3	12	98ZZZX1009       	1	19980225	G	6320	212040001141FM	GEARBOX         			BELL  	212   	212         	1181420	SW  										M/R	BINDING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	5017H	5715 	2844 		ABW40173	30930				GEARBOX BINDING AND MAKING NOISE WHEN TURNED BY HAND.  NON-METALIC CONTAMINATION FOUND ON OIL PUMP INLET SCREEN AND IN S	UMP AND INTERNAL FILTER.					1	G	7	1 	4U				H4SW
1998031200115	19980312	00115	CE  	1998	3	12	98ZZZX1013       	1	19980213	G	3246	D30260	WHEEL           			CESSNA	172   	172M        	2072418	CE  										MLG	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	6814H	3114 				17265594				INSPECTION FOUND WHEEL CRACKED IN THE TYPICAL LOCATION.   CRACKS EMANATING FROM EDGE OF FLANGE HOLES.						1	H	7	1 	3O			NT	3A12
1998031200707	19980312	00707	SO  	1998	3	12	98ZZZX1017       	1	19980227	G	3213	7803300	LINK ASSY       		62211       	PIPER 	PA28  	PA28140     	7102802	SO  										RT MLG	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			EA	03	4842T					287225222				STUDENT REPORT HARD LANDING.  UPON INSPECTION, FOUND RT MLG TORQUE LINKS SEPARATED AND THE EARS WERE SHEARED FROM UPPER 	CYLINDER RT MAIN GEAR.  SUSPECT STUDENT CAME IN HOT AND SIDEWAYS LANDING ON RT MAIN GEAR.					1	L	7	1 	3O				2A13
1998031200708	19980312	00708	CE  	1998	3	12	98ZZZX1018       	1	19980212	G	5330		SKIN            			CESSNA	182   	182P        	2075816	CE  										BELLY	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	8480M	3985 				18264618				FOUND CORROSION UNDER FACTORY INSTALLED BLACK INSULATION PADS BONDED TO FUSELAGE BELLY SKINS UNDER CABIN FLOORS.  RECOMM	END REMOVAL OF INSULATION PADS AND TREAT CORROSION IAW SM AND AC 43-13-1A.					1	H	7	1 	3O			NT	TA13
1998031200709	19980312	00709	CE  	1998	3	12	98ZZZX1019       	1	19980224	G	5330		SKIN            			CESSNA	182   	182Q        	2072732	CE  										BELLY	CORRODED        	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	367BT	2045 				18267390				FOUND CORROSION UNDER FACTORY INSTALLED BLACK INSULATION PADS BONDED TO FUSELAGE BELLY SKINS UNDER CABIN FLOOR AND FUSEL	AGE SIDE SKINS.  RECOMMEND REMOVAL OF ALL PADS AND TREAT CORROSION IAW SM AND AC 43-13-1A.					1	H	7	1 	3O			NT	3A13
1998031200710	19980312	00710	EA  	1998	3	12	98ZZZX1020       	2	19980227	G	7414	M3975	COIL            	SLICK       	M4381       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE MAG	FAILED          	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	09	97428	500  				15285774				MAG COIL AT 500 HOURS BURNED THROUGH ON THE OPPOSITE SIDE OF HIGH TENSION LEAD.  HAVE TO PULL COIL OUT TO SEE DAMAGED SP	OT.  ENGINE LOST POWER, TOOK MORE MANIFOLD PRESSURE TO MAINTAIN SAME RPM.					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998031200712	19980312	00712	CE  	1998	3	12	98ZZZX1022       	1	19980201	G	2820		HOSE            			CESSNA	172   	172R        	2072401	CE  										LT WING TANK	MISINSTALLED    	B	L		G2AR	K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			NE	01	406ES	26   				17280213				A FUEL HOSE WHICH CONNECTS THE LEFT WING TANK TO THE LEFT FUEL SUPPLY LINE AT THE WING ROOT WAS FOUND IMPROPERLY INSTALL	ED AND LEAKING.  THIS WAS DISCOVERED DURING A REGULAR OIL CHANGE WHEN A FUEL STAIN WAS NOTICED ON THE WING ROOT AND FUSE	LAGE.  FURTHER INVESTIGATION UNCOVERED THE SOURCE OF THE LEAK AS THE FUEL SUPPLY HOSE WHICH WAS INSTALLED WITH THE CLAMP	 AND HOSE END OUTBOARD OF THE BEAD OF THE TUBE.			1	H	7	1 	3O			NT	3A12
1998031200713	19980312	00713	CE  	1998	3	12	98ZZZX1023       	1	19980126	G	3230	NAS561F412	ROLL PIN        			CESSNA	210   	210D        	2073414	CE  										GEAR CONT	FAILED          	B	S	A	WTXR	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NM	07	3929Y					21058429				ROLL PIN BACKED OUT OF GEAR CONTROL VALVE AT GEAR UP SELECTION, NO FURTHER GEAR SELECTION WAS POSSIBLE AT THIS TIME.  CE	SSNA PARTS SHEET SHOWS AFFECTED PIN (ITEM NR 27).  SUBMITTER RECOMMENDS GEAR POWER PACK SELECTOR ROLL PINS BE SAFETIED A	ND CHECKED EACH ANNUAL/100-HOUR INSPECTION.				1	H	7	1 	3O				3A21
1998031200715	19980312	00715	CE  	1998	3	12	98ZZZX1025       	1	19980105	G	5520	9561001215	BRACKET         			BEECH 	58    	58P         	1152744	CE  										ELEV HINGE	CRACKED         	B		A	OACR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	58VB	2086 				TJ260				DURING REPLACEMENT OF ELEVATOR INBOARD BEARINGS (WHICH WERE BOTH UNSERVICEABLE), THE UPPER RT CORNER OF BRACKET WAS FOUN	D CRACKED.  A DYE-PENN INSP WAS PERFORMED AND TWO OTHER CRACKS WERE NOTED.  WHEN BRACKET/HINGE WAS REMOVED AND CLEANED, 	THE BACK SIDE SHOWED MINOR TO MODERATE CORROSION AND CRACKS EXTENDING FROM TOP RIGHT BOLT HOLE UP AND AROUND EDGE, ALSO,	 ON LOWER RT FROM BOLT HOLE AND DOWN AND AROUND.  REASON FOR OCCURRENCE, POSSIBLE METAL FATIGUE/OVERTORQUING OF BOLTS (I	F PART WAS REPLACED, ALSO, TO MAKE SURE BEVELED WASHER UNDER BOLT HEAD (IS INSTALLED PROPERLY).  CAREFULLY INSPECT ANNUA	LLY, REMOVE PAINT IF IN DOUBT OF CRACK OR NOT.	1	L	7	2 	3O				A23CE
1998032500001	19980325	00001	GL  	1998	3	25	98ZZZX1026       	2	19980210	G	7323	2539034	FLYWEIGHT BUSH  	BENDIX      	23057870    	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					N2 GOVERNOR	WORN            	H			JP0M	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	01	50AP		1052 		24224	1090585D	832359			PILOT EXPERIENCED DROOP OF N2 RPM (ROTOR) TO 100 PERCENT.  BEEFED UP TO 102 PERCENT, THEN N2 RPM WENT UP TO 104 PERCENT.	   ERRATIC OPERATION NOTICED.  RETURNED GOVERNOR TO REPAIR STATION FOR REPAIR AND REINSTALLED.   PROBLEM CORRECTED.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998031200716	19980312	00716	WP  	1998	3	12	98ZZZX1027       	1	19980227	G	2810	269A832919	STRAP           			HUGHES	269   	269C        	4470504	WP  										FUEL TANK	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	61415	1143 				0018				DURING A ROUTINE PRE-FLIGHT INSPECTION, THE PILOT DISCOVERED THE INBOARD FUEL TANK STRAP WAS LOOSE.  CLOSER INSPECTION R	EVEALED THE STRAP WAS BROKEN.  THE BREAK WAS ACROSS TWO SPOT WELDS MADE DURING MANUFACTURE.  					1	G	7	1 	3O			 	4H12
1998031200718	19980312	00718	EU  	1998	3	12	98ZZZX1029       	1	19980307	G	6410	22208BC0500012L	SCREW           		355A1200408 	SNIAS 	350   	AS350B1     	8680811	EU  										T/R BLADE BAL	FAILED          	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	2FOR				5098	2296				DURING REMOVAL OF T/R BLADE TIP SCREW, THE SCREW BROKE.  SCREW IS LOCATED AT THE TIP OF TAIL ROTOR BLADE TO HOLD THE BAL	ANCE WEIGHTS.  THIS SCREW IS IN ALLOYED STEEL (CODE BC- STEEL 35NC6).  REMOVING THE SCREW FROM THE TIP OF THE TAIL ROTOR	 BLADE IN FOR A NORMAL BALANCING CHECK, THE SCREW BROKE WITH A PART OF IT IN THE BLADE TIP.  WHEN REMOVING THE SCREW AN 	EXTRACTOR BROKE ALSO IN THE BLADE TIP.  THE BREAKING OF SCREW WAS DUE TO CORROSION.  THERE IS NO WAY TO PREVENT CORROSIO	N OF THIS SCREW INDICATED IN THE MM OF ASE350 AND MM AS355.  AT THE INSTALLATION OF THE SCREW AS PRESCRIBED IN MM, IT IS	 PROHIBITED TO PROTECT THE SCREW WITH GREASE, MASTINOX, ETC.	1	G	7	1 	3U				H9EU
1998031200719	19980312	00719	GL  	1998	3	12	98ZZZX1030       	2	19980224	G	7313	47086	FILTER          		6890917     	AGUSTA	A109  	A109A       	0260109	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	COLLAPSED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23			1284 				CAE831751			FUEL NOZZLE FILTER IS PARTIALLY COLLAPSED DUE TO FOREIGN OBJECT INSERTED INTO INLET.						1	G	7	2 	3U	3	U		H7EU    	E4CE
1998031200720	19980312	00720	NE  	1998	3	12	98ZZZX1031       	2	19980216	G	8530		CYLINDER        			BEECH 	18    	E18S        	1151006	CE  	PWA   	R985  	R985AN14B   	52008	NE  					NR 4	SEPARATED       	D				E				ENGINE SHUTDOWN         				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	5611D		70   			BA316	437424			THE CYLINDER HEAD SEPARATED FROM THE BARREL COMPLETELY THREE COOLING FINS DOWN FROM THE SPARK PLUG HOLE.  THE CYLINDER R	EMAINS IN PLACE.  DUE TO ENGINE ROUGHNESS, A PRECAUTIONARY SHUT DOWN WAS PERFORMED.  AD 78-08-07 APPLIES TO THIS CONDITI	ON.  SUBMITTER RECOMMENDED INSPECTION FOR BLOW-BY BEFORE EACH FLIGHT INSTEAD OF THE 100-HOUR INTERVAL PER AD.				1	L	7	2 	3R	3	R		A765    	5E1
1998031200721	19980312	00721	EA  	1998	3	12	98ZZZX1032       	2	19980206	G	8550	CH48103	FILTER          	CHAMPION    		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE OIL	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	9VZ	50   			F0214281	448195002				FILTER WAS REMOVED FOR A 100-HOUR INSPECTION.  PRIOR TO CUTTING THE FILTER OPEN, A FOREIGN MATERIAL WAS VISIBLE ON THE O	PENING OF THE FILTER.  FURTHER INSPECTION REVEALED THE FOREIGN MATERIAL WAS A SEAL USED BETWEEN THE TOP OF THE FILTER CA	N AND THE ELEMENT.  AS A RESULT, UNFILTERED OIL COULD BE RETURNING TO THE ENGINE ALONG WITH THIS LOOSE MATERIAL.				1	L	7	2 	3O	3	O		A19S0   	E286
1998031200722	19980312	00722	CE  	1998	3	12	98ZZZX1033       	1	19980227	G	7931	530010816	LINE            			CESSNA	340   	340A        	2076405	CE  										ENG OIL PRESSURE	CORRODED        	G				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	02	2741R	4642 				340A0922				PILOT EXPERIENCED LOSS OF OIL PRESSURE.  UPON INVESTIGATION, FOUND RT ENGINE OIL PRESSURE LINE CORRODED THROUGH AT THE L	OCATION UNDER THE FLOORBOARDS ON THE RIGHT SIDE OF AIRCRAFT WHERE LINE GOES OVER PRESSURIZATION DUCT.  SUBMITTER FELT IT	 WAS DUE TO CONDENSATION AT THE POINT THE LINE AND DUCT INTERSECTED.				1	L	7	2 	3O				3A25
1998031200723	19980312	00723	EA  	1998	3	12	98ZZZX1034       	1	19980302	G	3246	55584	FITTING         			DHAV  	DHC2  	DHC2*       	2800108	EA  										FLOAT STRUT	CRACKED         	E	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	108H					732				ONLY WHEN SPREADER BAR IS REMOVED CAN THE FLOAT ATTACH FITTINGS BE VIEWED.  BOTH FRONT FITTINGS WERE CRACKED THROUGH THE	 TAPER PIN HOLE.  SUBMITTER BELIEVES THE PLATE IN THE SPREADER BAR HAD SOME PLAY AND SOMEONE PUT EXTRA WASHERS AT THE BO	TTOM OF THE TAPER PIN PULLING IT TOO FAR DOWN INTO THESE CASTINGS.				1	H	7	1 	3R				A806
1998031200725	19980312	00725	NE  	1998	3	12	98ZZZX1036       	2	19980213	G	7310	4034260	FUEL VALVE      	WOODWARD    	8062550     	BOEING	757   	757*        		NM  	RROYCE	RB211 	RB211535E437	54555	NE  					REPAIR BUSHING	DISBONDED       	B		A	UU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		18365	11480							WOODWARD RB211-535 CONTROL SN WYG 2328482  RETURNED DUE TO IN-FLIGHT SHUT DOWN (IFSD).  INVEST CONFIRMED AN FFG MALFUNCT	ION WAS THE CAUSE OF THE IFSD AND MALFUNCTION CAUSED BY DISBONDMENT OF A REPAIR BUSHING WHICH HAD BEEN PERFORMED ON THE 	FUEL VALVE HOUSING WHEN NEW IN 1991.  THIS EPOXY REPAIR WAS CONSIDERED PERMANENT.  THE CAUSE OF DISBONDMENT IS UNDER INV	EST.  TO DATE, A SEARCH OF WOODWARD RECORDS INDICATES ONE OTHER FUEL VALVE HOUSING CONTAINS THIS IDENTICAL REPAIR.  IMME	DIATE CORRECTIVE ACTION WILL BE FOR WOODWARD TO REQUEST 'RETURN FOR INSPECTION' OF OTHER S/N IN ORDER TO FURTHER ASSESS 	REPAIR.  DETAILS REGARDING INCORPORATION OF A LONG TERM CORRECTIVE ACTION FOR THIS ISSUE WILL BE COORDINATED WITH RR.	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
1998031200726	19980312	00726	GL  	1998	3	12	98ZZZX1037       	2	19980121	G	7320	50575	ADAPTER         			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					START NOZZLE	WORN            	B			CSLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	195ME	1408 				5250110	1240			DURING ROUTINE INSPECTION CHECK 2, START NOZZLE ADAPTER WAS INSPECTED PER WILLIAMS ROLLS ROYCE FJ44-1A MM FOR DEFECTS. F	RETTING WEAR OF .025 INCH WAS NOTED IN ZONE B(TIP) OF START NOZZLE, .020 INCH IS MAX SERVICE LIMIT FOR WEAR IN THIS AREA	.  INITIAL DISCOVERY OF WEAR WAS AT LAST ENGINE CHECK 1 INSPECTION.  NO PREVIOUS WEAR NOTED PRIOR.  CYCLES, 1,566.				1	L	7	2 	4F	4	F	RT	A1WI    	E3GL
1998031200727	19980312	00727	NE  	1998	3	12	98ZZZX1038       	2	19980217	G	7311	10718FAE	FUEL HEATER     								PWA   	118   	PW118       		NE  					FILTER BOWL STUD	DEFECTIVE       	B			VKUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07		11731			308					DURING INSPECTION AT OVERHAUL, THREE STUDS WERE FOUND LOOSE AROUND THE FILTER BOWL AREA (APPARENTLY 'WALLOWED OUT' DURIN	G HOURS IN SERVICE).  SITUATION COULD LEAD TO POSSIBLE FUEL LEAKAGE IF STUDS PULLED OUT.  PART WAS INSPECTED IAW STEWART	 WARNER CMM 73-10-06.									4	T			E20NE
1998031200728	19980312	00728	NE  	1998	3	12	98ZZZX1039       	2	19980226	G	7311	10718D	FUEL HEATER     	STWARNER    	1518        						PWA   	118   	PW118       		NE  					FILTER BOWL STUD	DEFECTIVE       	B			VKUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07		15220								DURING INSPECTION AT OVERHAUL ONE STUD WAS FOUND LOOSE AROUND THE FILTER BOWL AREA (APPARENTLY 'WALLOWED OUT' DURING HOU	RS IN SERVICE).  SITUATION COULD LEAD TO POSSIBLE FUEL LEAKAGE IF STUD PULLED OUT.  PART WAS INSPECTED IAW STEWART WARNE	R CMM 73-10-06									4	T			E20NE
1998031200729	19980312	00729	NE  	1998	3	12	98ZZZX1040       	3	19980203	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		12773	4292 		1829NR			HJ247A		INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998031200730	19980312	00730	NE  	1998	3	12	98ZZZX1041       	3	19980121	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4574 			2519			HJ4459		INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FOUR CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998031200731	19980312	00731	CE  	1998	3	12	98ZZZX1042       	1	19980205	G	8010	KSR	RELAY           		1293800161  	BEECH 	1900  	1900C       	1154161	CE  										DC POWER PANEL	BURNED          	C				D				RETURN TO BLOCK         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			GL	17	1128M	3062 			0178	UC139				DURING TAXI, CREW NOTICED 90 PERCENT LOAD ON LEFT GENERATOR AND RIGHT GENERATOR LOAD ZERO PERCENT.  TRIED TO RESET RIGHT	 GENERATOR, BUT COULD NOT RESET.  TURNED OFF LEFT GENERATOR AND AIRCRAFT GEN-TIES OPENED AND BATTERY BUS TIES OPENED.  C	OULD NOT RESET LEFT GENERATOR.  RETURNED TO HANGAR.  SUBMITTER SUSPECTED RIGHT START RELAY CONTACTS WELDED CLOSED.  REPL	ACED DC POWER PANEL AND  SYSTEMS RETURNED TO NORMAL.			2	L	7	2 	4T			RT	A24CE
1998031200732	19980312	00732	SO  	1998	3	12	98ZZZX1043       	1	19980226	G	6120	7854175	HOUSING         		78249046    	EMB   	120   	EMB120ER    	3260203	SO  										PROP CONTROL	CRACKED         	B			BN4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	05	294SW		1270 		900333	120321				REFERENCE:  FW06347.   REASON FOR REMOVAL:  LEAKING AROUND MOUNTING CLAMP AREA.  POSSIBLE CAUSE:  TBD.  RECOMMENDATIONS:	  HOUSING TO BE SENT TO HAMSTD FOR METALLURGICAL EVALUATION.  CUSTOMER:  SKYWEST A/L.					2	L	7	2 	4T			RT	A31SO
1998031200733	19980312	00733	NE  	1998	3	12	98ZZZX1044       	2	19980203	G	8530		CYLINDER        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 5	FAILED          	G				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			SW	11	5831B		5    			42100882	350920			WHILE IN CRUISE FLIGHT, THE FLIGHT CREW NOTICED OIL COMING FROM THE ENGINE VENT.  THE ENGINE WAS SECURED AND THE PROPELL	ER FEATHERED.  AN UNEVENTFUL LANDING WAS MADE.  INSPECTION FOUND CYLINDER NR 5 WITH NO COMPRESSION.  CYLINDER TO BE REMO	VED AND FURTHER TROUBLESHOOTING DONE IF THE CYLINDER IS NOT THE PROBLEM.				2	L	7	2 	4R	4	R		A669    	5E4
1998031200734	19980312	00734	NM  	1998	3	12	98ZZZX1045       	1	19980202	G	5330		SKIN            			BOEING	737   	737222      	1384473	NM  										BS 616-639	CORRODED        	B			EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	603DJ	58   				19955				FOUR CRACKS WERE FOUND AT UPPER FUSELAGE BETWEEN BS 616 AND BS 639 BETWEEN STR 1 AND STR 2 RT IN THE BODY SKIN.  IT APPE	ARS TO BE THE FIRST TIME FOR A CRACK IN THIS AREA PER BOEING FAX COO-SJO-98-0057RR DATED 1-22-98.  THE SUSPECT CAUSE OF 	THIS DAMAGE IS STRESS CORROSION.				2	L	7	2 	4F				A16WE
1998031200736	19980312	00736	NE  	1998	3	12	98ZZZX1046       	2	19980215	G	7230		BLADES          			BOEING	747   	747273C     	1384896	NM  	PWA   	JT9   	JT9*        	52054	NE  					ENGINE N1	DAMAGED         	B			GK4Y	K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			WP	03	470EV					20653				ON ARRIVAL NADI, FOUND FOUR N1 BLADES ON NR 1 ENGINE SEVERELY DAMAGED.  SUSPECT CAUSE:  INGESTION OF FOREIGN OBJECTS ON 	RUNWAY 02 CAUSED BY GEMINI AIR CARGO DC10-30F BLOWN WHEELS THAT LANDED EARLIER.					2	L	7	4 	4F	4	F		A20WE   	E20EA
1998031200737	19980312	00737	WP  	1998	3	12	98ZZZX1047       	1	19980215	G	3244		TIRE            			DOUG  	DC10  	DC1030F     	3023504	WP  										WHEELS 5-6	BLOWN           	B			GK4Y	K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	03	604GC					47924				ON ARRIVAL NADI, FOUND LEFT MAIN LANDING GEAR AFT WHEELS (5 AND 6) BLOWN.  BOTH AFT WHEEL HUBS SEVERELY DAMAGED.  LT INB	OARD T/E FLAPS SUSTAINED CRACKS, DENTS, AND PUNCTURES ON UNDER SURFACE IN SEVERAL PLACES.  MINOR DAMAGES WERE NOTED ON L	EFT BOGIE HYDRAULIC LINE BRACKETS, LT OUTBOARD FLAP, LT INBOARD AILERON, NR 1 ENGINE NACELLE, AND COWLING.  LT INBOARD S	LATS, FUSELAGE SKIN FORWARD OF LT WING ROOT AND NR 1 ENGINE TAIL CONE.  SUSPECT AN ANTI-SKID FAILURE THAT CAUSED THE TIR	ES TO RUPTURE.		2	L	7	3 	4F			RT	A22WE
1998031200738	19980312	00738	NE  	1998	3	12	98ZZZX1048       	2	19980209	G	7230		VANES           			BOEING	757   	757236      		NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					RT ENG COMP	DAMAGED         	B			GJPY	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			WP	33	769BE	18985	5223 			24118	30669			FLT CZ23556 - DURING APPROACH SHENZHENG AT 600M, RT ENGINE MADE SLIGHT SURGING SOUND AND LATER, ELECTRICAL POWER TRANSFE	RRED.  A LOT OF EICAS MESSAGES APPEARED.  RT ENGINE UNCOMMANDED SHUT DOWN, ACFT SAFELY LANDED.  CHECKED BVCU AND FOUND '	04' CODE, TPU HAD '40' CODE.  BORESCOPED ENGINE PER MM 72-00-00-601 AND FOUND 6 PIECES OF VANES IN THE THIRD STAGE OF TH	E HIGH PRESSURE COMPRESSOR DAMAGED, HOWEVER, DAMAGE WAS WITHIN LIMIT.  GROUND RAN AND TESTED THE ANTI-SURGE SYSTEM, OK. 	 PUSHED UP THROTTLE TO EPR 1.63, RT ENGINE SURGED.  ON 2-8, REPLACED RIGHT ENGINE.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
1998031900253	19980319	00253	CE  	1998	3	19	98ZZZX1049       	1	19980124	G	3233	12810013	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	115HM	7181 				172RG0490				DURING A 100-HOUR INSPECTION, BOTH  MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET I	NSPECTION RESULTING WITH ONE HOUSING FOUND CRACKED IN THE AREA JUST BELOW THE BEARING PN S1997C7-8. THE ACTUATOR WAS REP	LACED.				1	H	7	1 	3O				3A17
1998031900254	19980319	00254	SO  	1998	3	19	98ZZZX1050       	1	19980212	G	3230	9582900	LINK ASSY       			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG DOWNLOCK	DEFECTIVE       	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	18TP	5174 				347970431				DOWNLOCK SPRING WEAK, CAUSED DOWNLOCK KNUCKLE TO NOT GO TO OVER-CENTER LOCK POSITION.  PIN HAD WEAR OF .005 INCH.  COUPL	E THIS WITH WEAK SPRING AND PLAY, ENOUGH TO ALLOW NLG TO COLLAPSE ON ROLL-OUT.  FAA RECORDS SHOW SAME TYPE ACCIDENT 1974	 - IN A SENECA I AIRCRAFT.				1	L	7	2 	3O				A7SO
1998031900255	19980319	00255	SO  	1998	3	19	98ZZZX1051       	1	19980201	G	5710	082200	WING ASSY       			LUSCOM	8     	8A          	8190104	SO  										LT/RT WING	DAMAGED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2227K	2500 				4954				AIRCRAFT OPENED FOR ANNUAL AND FOUND SEVERAL RAT NESTS AND URINE DAMAGE IN BOTH WINGS (NORMALLY SEALED).  LARGE RAT NEST	 AND URINE DAMAGE IN RT WING TRAILING EDGE.  WASP/MUD DAUBER NEST IN RT LEADING EDGE ATTACHED TO SPAR CABLES.  BIRD NEST	 IN LT WING.  LUSCOMBE WING HAS NO ACCESS FOR ROUTINE INSPECTIONS.  FOUND NESTS WHILE INSTALLING DLAHF INSPECTION ACCESS	 KIT.			1	H	7	1 	3O				A694
1998031900256	19980319	00256		1998	3	19	98ZZZX1052       	4	19980122	G	2210	KA132	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	INTERMITTENT    	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	3527U	198  			3458	317952141				ACCELERATOR SWITCH TESTS INERMITTENTLY IN AUTOPILOT SYSTEM ESPECIALLY IN COLD WEATHER.						1	L	7	2 	3O				A20SO
1998031900257	19980319	00257	CE  	1998	3	19	98ZZZX1053       	1	19980129	G	3233	98820153	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4634V	4100 			5830	172RG0344				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900258	19980319	00258	CE  	1998	3	19	98ZZZX1054       	1	19980129	G	3233	98820153	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	4634V	4100 			5837	172RG0344				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900259	19980319	00259	CE  	1998	3	19	98ZZZX1055       	1	19980119	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5177R	5500 			3965	172RG0045				DURING A 100-HOUR INSPECTION, THE RIGHT MAIN LANDING GEAR ACTUATOR ASSEMBLY PN 9882015-2 ATTACH BOLT WAS FOUND LOOSE WHI	CH ALLOWED THE ACTUATOR TO HAVE MOVEMENT DURING RETRACTION AND EXTENSION.  UPON FURTHER INSPECTION OF THE ACTUATOR HOUSI	NG PN 1281001-3, A CRACK WAS FOUND UNDER THE BEARING CUPS PN S1997C-8 ON BOTH SIDES OF THE HOUSING.  INSPECTION OF THE L	EFT MAIN GEAR ACTUATOR REVEALED SIMILAR CRACKS; THUS, REQUIRING REPLACEMENT OF BOTH ACTUATORS WITH SERVICEABLE UNITS.			1	H	7	1 	3O				3A17
1998031900260	19980319	00260	CE  	1998	3	19	98ZZZX1056       	1	19980119	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5177R	5500 			3967	172RG0045				DURING A 100-HOUR INSPECTION, THE RIGHT MAIN LANDING GEAR ACTUATOR ASSEMBLY PN 9882015-2 ATTACH BOLT WAS FOUND LOOSE WHI	CH ALLOWED THE ACTUATOR TO HAVE MOVEMENT DURING RETRACTION AND EXTENSION.  UPON FURTHER INSPECTION OF THE ACTUATOR HOUSI	NG PN 1281001-3, A CRACK WAS FOUND UNDER THE BEARING CUPS PN S1997C-8 ON BOTH SIDES OF THE HOUSING.  INSPECTION OF THE L	EFT MAIN GEAR ACTUATOR REVEALED SIMILAR CRACKS; THUS, REQUIRING REPLACEMENT OF BOTH ACTUATORS WITH SERVICEABLE UNITS.			1	H	7	1 	3O				3A17
1998031900262	19980319	00262	CE  	1998	3	19	98ZZZX1058       	1	19980123	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B		A	CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	6398V	4700 			7212	172RG0660				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900263	19980319	00263	CE  	1998	3	19	98ZZZX1059       	1	19980123	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	6398V	4700 			7203	172RG0660				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900264	19980319	00264	SO  	1998	3	19	98ZZZX1060       	2	19980205	G	8550		BREATHER        			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	LTSIO360E   	17025	SO  					LT ENG OIL	FROZEN          	B		A	RMMR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CE	01	9284R	232  				3449005				PILOT REPORTED LOW OIL PRESSURE WARNING SOUNDED LEFT ENGINE, AND GAUGE INDICATED ZERO OIL PRESSURE AT APPROXIMATELY 'GEA	R-UP' TIME OF TAKEOFF.  LANDING WITHOUT INCIDENT.  TROUBLESHOOTING DETERMINED TO BE FROZEN BREATHER.  THIS SYSTEM HAS AI	R/OIL SEPARATOR.  PIPER IS IN PROCESS OF MODIFYING SYSTEM.  ALL OPERATORS OF SENECA V AIRCRAFT SHOULD C/W THIS MODIFICAT	ION WHEN AVAILABLE.  ROUTING OF LT ENGINE BREATHER IS SLIGHTLY DIFFERENT THAN RT DUE TO AIR CONDITIONING COMPRESSOR BEIN	G MOUNTED ON LT ENGINE.  A LARGE PUDDLE OF OIL WAS FOUND AT LOCATION OF GROUND RUN.  OIL WAS BLOWN THROUGH RETURN HOSE F	ROM SEPARATOR TO ENGINE.	1	L	7	2 	3O	3	O		A7SO    	E9CE
1998031900265	19980319	00265	CE  	1998	3	19	98ZZZX1061       	1	19980120	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9303D	5400 			6575	172RG1113				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900266	19980319	00266	CE  	1998	3	19	98ZZZX1062       	1	19980120	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9303D	5400 			3740	172RG1113				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900267	19980319	00267	CE  	1998	3	19	98ZZZX1063       	1	19980120	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9561B	7900 			8933	172RG0881				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900268	19980319	00268	CE  	1998	3	19	98ZZZX1064       	1	19980120	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	B			CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9561B	7900 			8552	172RG0881				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND BOTH HOUSINGS WERE FOUND CRACKED IN THE SAME AREA JUST BELOW THE BEARING PN S1997C7-8.  BOTH ACTUATORS WERE	 REPLACED.				1	H	7	1 	3O				3A17
1998031900271	19980319	00271	EU  	1998	3	19	98ZZZX1065       	1	19980226	G	5610	3430214	WINDOW          			ISRAEL	1124  	1124        	4500102	EU  										COCKPIT OVERHEAD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	1124F	17502								DURING AN A-CHECK INSPECTION, THE COPILOT'S OVERHEAD WINDOW WAS FOUND CRACKED ALONG THE AFT EDGE.  IT HAD THE APPEARANCE	 OF DELAMINATION PROGRESSING AT AN ANGLE THROUGH THE OUTER WINDOW.  AFTER REMOVAL, IT WAS APPARENT THERE WAS A CRACK.  T	HE CRACK STARTED IN THE CORNER OF THE MILLED AREA OF THE WINDOW AND PROGRESSED AT AN ANGLE TOWARD THE INNER SURFACE.  SU	BMITTER STATED THE CAUSE COULD HAVE BEEN A DEFECT IN THE RADIUS OF THE MILLED AREA OR A SCRATCH THAT COULD HAVE BEEN PUT	 THERE DURING SEALANT REMOVAL.		2	M	7	2 	4F				A2SW
1998031900272	19980319	00272	SO  	1998	3	19	98ZZZX1066       	1	19980213	G	2720	159C1031413	BRACKET         			GULSTM	G159  	G159        	3952202	SO  										RUD BELLCRANK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	5VX	12360				007				WHILE INSPECTING THE RUDDER CONTROL SYSTEM REFERENCING CUSTOMER BULLETIN NR 235A DATED 5-21-73, DISCOVERED A CRACK IN TH	E RUDDER CONTROL BELLCRANK SUPPORT BRACKET AND ITS ATTACHMENT ANGLE.  THE BRACKET IS MOUNTED TO THE TOP OF THE TAIL COMP	ARTMENT BETWEEN FRAME NR 669 AND NR 690.				2	L	7	2 	4T				1A17
1998031900273	19980319	00273	CE  	1998	3	19	98ZZZX1067       	1	19980120	G	7910	77128251	TANK            			BEECH 	36    	A36         	1151604	CE  										ENGINE OIL	CRACKED         	B			CSLR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	5RZ	400  				E1579				PILOT COMPLAINED OF OIL DRIPPING ON HANGAR FLOOR.  INSPECTION REVEALED APPROXIMATELY .1250 INCH LONG CRACK IN THE SIDE O	F THE OIL TANK.  THERE WERE TWO CREASES IN THE TANK RUNNING IN A VERTICAL DIRECTION ON BOTH THE FORE AND AFT SIDE OF THE	 TANK.  THE CRACK ORIGINATED AT THE TOP OF THE FORWARD CREASE.  THIS OIL TANK IS PRESSURIZED AND EVEN THIS SMALL TANK CR	ACK CAUSED A SUBSTANTIAL AMOUNT OF OIL TO BE LOST.			1	L	7	1 	3O				3A15
1998031900274	19980319	00274	WP  	1998	3	19	98ZZZX1068       	1	19980223	G	5350		FAIRING         			DOUG  	DC10  	DC1030F     	3023504	WP  										AFT CARGO DOOR	DAMAGED         	B			GK4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	604GC					47924				GROUND EQUIPMENT DAMAGED FIBERGLASS FAIRING FORWARD OF AFT CARGO DOOR OPENING.  DAMAGE IS 2.5 INCHES BY 1.5 INCHES BY 0.	5 INCH DEEP.  TERMPORARY REPAIR CARRIED OUT BY GEMINI.					2	L	7	3 	4F			RT	A22WE
1998031900275	19980319	00275	CE  	1998	3	19	98ZZZX1069       	1	19980303	G	3231	NAS3544240	ROD             			CESSNA	650   	650         	2076802	CE  										MLG DOOR	FAILED          	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	606AT					6500225				THE MLG UPPER DOOR ROD P/N NAS 354-4-240 HAS BROKEN 2 TIMES.  SUSPECT DUE TO EXCESSIVE AIR LOAD FOR THE ROD SIZE OR DEFE	CTIVE RODS.  TAT:  1661.  LANDING:  1,055.					2	L	7	2 	4F				A9NM
1998031900277	19980319	00277	WP  	1998	3	19	98ZZZX1070       	2	19980302	G	7314	30706391	PUMP            			LKHEED	1329  	132923D     	5263108	SO  	GARRTT	TFE731	TFE7313     	01518	WP  					ENGINE FUEL	FAILED          	B	S		GW4R	O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SO	11	731L					5091	P75226			FUEL PUMP DRIVE SPLINE WORN TO THE POINT THAT THE SPLINES NO LONGER MADE CONTACT CAUSING THE ENGINE TO SHUT DOWN.						2	L	7	4 	4J	4	F		2A15    	E6WE
1998031900280	19980319	00280	CE  	1998	3	19	98ZZZX1073       	1	19980123	G	3233	98820152	ACTUATOR        		12810013    	CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B	S		CE8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	40960	5498 			6745	172RG0540				DURING A 100-HOUR INSPECTION, BOTH MAIN LANDING GEAR ACTUATOR HOUSINGS PN 1281001-3 WERE INSPECTED AS PART OF A FLEET IN	SPECTION AND ONE HOUSING WAS FOUND CRACKED IN THE AREA JUST BELOW THE BEARING PN S1997C7-8.  THE ACTUATOR WAS REPLACED.					1	H	7	1 	3O				3A17
1998031900585	19980319	00585	WP  	1998	3	19	98ZZZX1076       	1	19980119	G	5342		FITTING         			RHNFLU	EXT300	EXTRA300    	05616CV	WP  										HORIZONTAL STAB	CRACKED         	B	P	A	BD6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	317N	540  				017				AIRFRAME WAS BEING STRIPPED OF FABRIC.  HORIZONTAL STABILIZER AREA WOULD NORMALLY NOT BE VISIBLE AS THIS FABRIC IS GLUED	 AROUND THE TUBING IN THIS AREA.  THIS ITEM IS COVERED UNDER SB 300-2-95.					1	M	7	1 	3O			NC	EXPA1M71
1998031900586	19980319	00586		1998	3	19	98ZZZX1077       	1	19980119	G	3230	42000800	CONTROL VALVE   	PACIFICSCIEN																BLOW DOWN BOTTLE	WRONG PART      	B			P94R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										BLOW DOWN BOTTLE - VALVE IS OF UNKNOWN MANUFACTURE AND NOT OF PACIFIC SCIENTIFIC MANUFACTURE.  FOUND DURING OEM SERVICIN	G (PACIFIC SCIENTIFIC) SEE PRR 0125283.  UNAPPROVED MANUFACTURE OF PART BY UNKNOWN SOURCE OR MIS-INSTALLATION OF PART ON	 WRONG UNIT.
1998031900587	19980319	00587	CE  	1998	3	19	98ZZZX1078       	1	19980305	G	2410	640922A	DRIVE COUPLING  			BEECH 	58    	58          	1152740	CE  										ALTERNATOR	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	100QD	5000 			9422	TH619				SUBMITTER STATED ALTERNATOR DRIVE HAS NO TBO AND ON FAILURE OF THIS UNIT THE INTERNAL GEAR AND ENGINE OIL SUPPLY ARE FOU	LED WITH METAL AND DEBRIS WHICH COULD CAUSE A CATASTROPHIC ENGINE FAILURE.  PART SHOULD HAVE LIFE-LIMIT.  MEL SHOULD NOT	 ALLOW OPERATION WITHOUT INSPECTION.				1	L	7	2 	3O				3A16
1998031900588	19980319	00588	EA  	1998	3	19	98ZZZX1079       	2	19980305	G	8530		VALVE GUIDE     			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A5    	41532	EA  					CYL 1-4 EXH	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6039P					241135	L102840			CHECKED VALVE GUIDE CLEARANCE IAW SB 388B AND FOUND EXHAUST VALVES GUIDES IN CYLINDERS 1 AND 4 TO BE OUT OF SPECIFICATIO	NS.  THE INTAKE AND EXHAUST VALVES IN BOTH CYLINDERS ALSO WERE BELOW MANUFACTURER'S SPECIFICATIONS.					1	L	7	1 	3O	3	O		1A15    	E295
1998031900589	19980319	00589	SO  	1998	3	19	98ZZZX1080       	1	19980305	G	5347		RAIL SUPPORT    			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1A5    	41532	EA  					PILOT SEAT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6039P					241135	L102840			PILOT SEAT RAIL SUPPORT BRACKET CRACKED AT STA 77 AND STA 87.  THE CRACKS WERE FOUND UNDER THE LEFT HAND SEAT RAIL IN TH	E FLANGE AREA AROUND THE NUT PLATES.					1	L	7	1 	3O	3	O		1A15    	E295
1998031900590	19980319	00590	EA  	1998	3	19	98ZZZX1081       	2	19980201	G	7414	M3333	IMPULSE COUPLING	SLICK       	6351        	PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE MAG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8216T				95070029	328206037	L1795348A			MAG IMPULSE COUPLING FAILED.  REMOVED FROM ENGINE AT 469.8 HOURS SINCE NEW.						1	L	7	1 	3O	3	O		A3SO    	1E4
1998031900591	19980319	00591	SO  	1998	3	19	98ZZZX1082       	2	19980227	G	8500		ENGINE          			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					POWER SECTION	FAILED          	B			LJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	6948S	2660 				15067648				ENGINE ASSY PRODUCING EXCESSIVE AMOUNTS OF METAL - MAIN OIL SCREEN.  METAL CONTENT EXCESSIVE STEEL-BRONZE AND ALUMINUM. 	 ENGINE RE-CHECK AFTER TWO ADDITIONAL GROUND RUNS.  EXCESSIVE METAL PRESENT AFTER EACH RUN.  CONTINENTAL ENGINE 0200A, 2	,660.0 HRS TT.				1	H	7	1 	3O	3	O		3A19    	E252
1998031900592	19980319	00592	CE  	1998	3	19	98ZZZX1083       	1	19980217	G	2840	C6695620113	FUEL GAUGE      			CESSNA	150   	152         	2071835	CE  										LT/RT FUEL	ERRORS          	B		A	DSBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	95441	42   				15285896				UPON RETURNING FROM FLIGHT, PILOT COMPLAINED THE ACFT REQUIRED MORE FUEL TO FILL TANKS THAN GAUGES INDICATED.  ASKED MAI	NT TO CHECK GAUGES FOR ACCURACY.  FUEL WAS COMPLETELY DRAINED FROM A/C, AND GAUGES READ ONE-EIGHTH (LT) AND ONE-FOURTH (	RT).  GAUGES WERE INSTALLED IN KIT FORM (SK152-21B) ON 12-18-97, REPLACING ORIG EQUIPMENT.  STEWART-WARNER SYSTEM.  PROB	LEM WAS FOUND AT THE WING ROOT CONNECTORS.  NO APPARENT CORROSION OR DAMAGE WAS EVIDENT, SIMPLY MOVING THE CONNECTORS (W	IGGLING THE 2 HALVES) VARIED THE READING ON THE FUEL GAUGES.  THE CONNECTIONS WERE CLEANED, AND THE GAUGES READ NORMALLY	.	1	H	7	1 	3O			NT	3A19
1998031900593	19980319	00593		1998	3	19	98ZZZX1084       	1	19980225	G	2571		BATTERY BOX     			AMTR  		MINI500     												FIREWALL	NOT GROUNDED    	D				K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			GL	23	120VT					0222				HELICOPTER HAS BATTERY BOX BOLTED TO COMPOSITE FIREWALL.  BATTERY BOX IS NOT GROUNDED TO BATTERY.  A REGULATOR RECTIFIER	 AND STARTER RELAY ARE GROUNDED TO BATTERY BOX.  A SCREWDRIVER WAS ACCIDENTLY DROPPED INSIDE OF BATTERY BOX TOUCHING POS	ITIVE TERMINAL.  SCREWDRIVER THEN GAVE BOX A POSITIVE CHARGE COMPLETING CIRCUIT THROUGH THE NEGATIVE WIRE OF THE REGULAT	OR RECTIFIER AND THIS CAUSED A DEAD SHORT AND WIRES TO CATCH FIRE.						0
1998031900594	19980319	00594	CE  	1998	3	19	98ZZZX1085       	1	19980219	G	7810	1099500001	EXHAUST STACK   			BEECH 	90    	C90A        	1152911	CE  										LT ENG OTBD	CRACKED         	B		A	KO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1568X	39   				LJ1368				INSPECTION FOUND LT ENGINE OUTBOARD EXHAUST STACK CRACKED AT DEICE TUBE.  SECOND EVENT SINCE REPLACEMENT.  PART TT:  39 	HOURS.					1	L	7	2 	3T			RT	3A20
1998031900596	19980319	00596	CE  	1998	3	19	98ZZZX1087       	1	19980113	G	7810	1099500001	EXHAUST STACK   			BEECH 	90    	C90A        	1152911	CE  										LT ENG OTBD	CRACKED         	B			KO1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	1568X	670  				LJ1368				INSPECTION FOUND LT ENGINE OUTBOARD EXHAUST STACK CRACKED AT DEICE TUBE.  REPLACED UNIT.  PART TT 669.9 HOURS.						1	L	7	2 	3T			RT	3A20
1998031900597	19980319	00597	CE  	1998	3	19	98ZZZX1088       	1	19980221	G	3252	63430013	DAMPENER        			CESSNA	525   	525         	2076601	CE  										NLG	SEIZED          	B			IW1R	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	25	741CC	26   			2155	5250227				OPERATOR REPORTED NOSE WHEEL STEERING PULLED TO THE LEFT WHEN INDICATING STRAIGHT (RUDDER PEDALS IN NEUTRAL).  FOUND NOS	E TIRE SEVERELY SCUFFED ON CENTERLINE OF TREAD.  ATTEMPTS TO MANUALLY TURN NOSE WHEEL FOUND SHIMMY DAMPENER FROZEN IN PL	ACE.  REPLACED NOSE TIRE AND SHIMMY DAMPENER, SYSTEM OPERATED NORMALLY.				1	L	7	2 	4F			RT	A1WI
1998031900598	19980319	00598	NE  	1998	3	19	98ZZZX1089       	2	19980305	G	8530	116733CP	CYLINDER        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R183092     	52020	NE  					LT ENG NR 3 CYL	CRACKED         	G				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	11	5831B					42100882	350920			APPROXIMATELY 30 MINUTES AFTER DEPARATURE, FLIGHT CREW NOTICED OIL LEAK IN LEFT ENGINE.  CREW DIVERTED BACK TO AWM.  MAI	NTENANCE FOUND CYLINDER NR 13 HEAD SEPARATING FROM BARREL.					2	L	7	2 	4R	4	R		A669    	5E4
1998031900791	19980319	00791	NM  	1998	3	19	98ZZZX1092       	1	19980302	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908/1016	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	56SW	61936				21721				FUSELAGE SKIN CRACKED AT THE FOLLOWING LOCATIONS, STA 908 STR 10R AND STA 1016 STR 10L AND STR 14R.  REPAIRED PER DALFOR	T AEROSPACE, LP XEA X2-53-205 REV 1 DATED 2-25-98 AND BOEING SRM 53-30-3 FIGURE 42.  FAA FORM 8110-3 DATED 2-25-98.					2	L	7	2 	4F				A16WE
1998031900792	19980319	00792	NM  	1998	3	19	98ZZZX1093       	1	19980302	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908-951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	56SW					21721				NUMEROUS FASTENER HOLES CRACKED IN FUSELAGE SKIN AT STR 14R STA 908 - STA 951.  REPAIRED PER DALFORT AEROSPACE, LP XEA X	2-53-206 DATED 2-25-98.  FAA FORM 8110-3 DATED 2-27-98.					2	L	7	2 	4F				A16WE
1998031900793	19980319	00793	NM  	1998	3	19	98ZZZX1094       	1	19980302	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 915	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	56SW					21721				FUSELAGE SKIN CRACKED AT STA 915 STR 10L.  REPAIRED PER DALFORT AEROSPACE, LP XEA X2-53-207 REV 1, DATED 2-27-98.  FAA F	ORM 8110-3 DATED 2-27-98.					2	L	7	2 	4F				A16WE
1998043001168	19980430	01168	CE  	1998	4	30	98ZZZX1095       	1	19980203	G	3240	8952320875	VALVE           			CESSNA	500   	550         	2076604	CE  										EMERGENCY BRAKE	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	09	6775C				103	5500677				RECEIVED RECENTLY OVERHAULED VALVE FROM SUPPLY.  INSTALLED VALVE, VALVE WOULD NOT PASS OPERATIONAL TEST IN AIRCRAFT.  FO	UND VALVE TO BE FAULTY.  (INTERNALLY BYPASSING PNEUMATIC PRESSURE).  PART WAS OVERHAULED 5-23-97 BY ALLIED SIGNAL AEROSP	ACE EQUIPMENT SYSTEMS.				1	L	7	2 	4F				A22CE
1998043001169	19980430	01169	NE  	1998	4	30	98ZZZX1096       	2	19980307	G	7261		SEAL            			LEAR  	25    	25          	5170506	CE  	GE    	CJ610 	CJ6106      	30006	NE  					OIL FILLER NECK	FAILED          	E				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			GL	23	28CK	6642 				045	211205			RIGHT ENGINE SHUT DOWN IN-FLIGHT DUE TO LOW OIL PRESSURE.  REPLACED FILLER NECK SEAL, INSPECTED OIL FILTER AND CHIP DETE	CTOR.  SERVICED WITH MOBILE JET II.  GROUND RUN, LEAKED CHECKED, AND RETURNED TO SERVICE.					2	L	7	2 	4J	4	J		A10CE   	1E16
1998043001170	19980430	01170	CE  	1998	4	30	98ZZZX1097       	1	19980206	G	8011	03601018	BEARING         			RAYTHN	DH125 	HAWKER800XP 		CE  										GEN FWD DRV END	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	1910H	416  				258318				NR 2 ENGINE STARTER FAILED TO DISENGAGE AUTOMATICALLY AT END OF START SEQUENCE.  FOUND STARTER/GENERATOR FORWARD DRIVE E	ND BEARING HAD FAILED ALLOWING SPEED PICKUP GEAR TO CONTACT SPEED SENSOR.					2	L	7	2 	4F			RT	A3EU
1998043001171	19980430	01171	CE  	1998	4	30	98ZZZX1098       	1	19980306	G	3240	400003	LAMP            			BEECH 	MU300 	400A        	1155402	CE  										BEACON	SHORTED         	B			AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	400SH					RK100				CREW SAID BEACON LIGHT CIRCUIT BREAKER TRIPPED.  FOUND FILAMENT OF BEACON LAMP BROKEN AND AT THE BOTTOM OF THE LAMP BASE	.  CREW REPORTED SOME INVERTER PROBLEMS.  SUBMITTER STATED THE 3RD AIRCRAFT FOUND WITH THIS PROBLEM.					2	H	7	2 	4F			RT	A16SW
1998043001172	19980430	01172	NM  	1998	4	30	98ZZZX1099       	1	19980225	G	3097		WIRE            			DOUG  	MD11  	MD11        	3023602	NM  										NAC ANTI ICE	SHORTED         	H				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	03	103EV	12574				48415				FAILURE OF THIS ENGINE NACELLE ANTI-ICE SYSTEM HAS CAUSED THE ENGINE TO SHUT DOWN IN FLIGHT EN ROUTE.  REPAIR STATION (Q	OCY3497) FOUND ONE WIRE PI-8032 WAS SHORT TO GROUND AND REPAIRED THE FAILED WIRE IAW WDM 3022-02, WDM 2010-02, AND MM 20	-30-05.				2	L	7	3 	4F			RT	A22WE
1998043001173	19980430	01173	NE  	1998	4	30	98ZZZX1100       	3	19980227	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		12821	4420 		1669NR			HJ22A		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TH	REE CRACKS.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998032600280	19980326	00280	CE  	1998	3	26	98ZZZX1101       	1	19980302	G	5730	5011002593	SKIN            			BEECH 	300   	B300C       		CE  										RT WS 124.6	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	82324					FM7				RIGHT WING UPPER SURFACE JUST OUTBOARD OF WING ATTACH BETWEEN FRONT AND REAR SPARS, WS 124.6 WAS FOUND WRINKLED AND CRAC	KED DURING A PHASE 2 INSPECTION.  LOG BOOK HISTORY SHOWS A WRINKLE WAS FIRST NOTICED (10-27-93) (TT 151 HOURS) AND WAS F	OUND OK FOR SERVICE BY A BEECH REP.  THE SECOND LOG BOOK ENTRY WAS JULY OF 1995 AND AGAIN OK BY A BEECH REP.  NOW, 3-2-9	8 DURING A PHASE 2 INSPECTION, THE WRINKLE WAS FOUND CRACKED ABOUT 1 INCH LONG.			2	L	7	2 	4T			RT	A24CE
1998032600283	19980326	00283	EA  	1998	3	26	98ZZZX1104       	2	19980302	G	7420		HARNESS         	SLICK       		CESSNA	182   	182S        	2072701	CE  	LYC   	O540  	IO540*      	41532	EA  					ENGINE IGNITION	DAMAGED         	D				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	974SG	35   				18280083				DURING TROUBLESHOOTING, ROUGH MAG DROP DISCOVERED DURING RUN-UP.  DISCOVERED NYLON TIE WRAPS HOLDING IGNITION HARNESS LE	ADS TOGETHER IN BUNDLES SO TIGHT THE LEADS WERE DISTORTED.  IGNITION LEADS WERE DISCOVERED STRETCHED TIGHT BETWEEN ENGIN	E AND MOUNT.  FAULT DISCOVERED TO BE WHERE A NYLON TIE WRAP HAD CHAFED THROUGH SHIELDING AND BROKEN INNER INSULATION OF 	ONE IGNITION LEAD ALLOWING LEAD TO SHORT DURING OPERATION.  OTHER LEADS DISCOVERED DAMAGED.  SUBMITTER FEELS SERIOUS PRO	BLEM EXISTS SINCE LEAD FAILED WITH EXTREME LOW TIME IN SERVICE.		1	H	7	1 	3O	3	O	NT	3A13    	1E4
1998032600284	19980326	00284	SO  	1998	3	26	98ZZZX1105       	1	19980223	G	7820	6751700	MUFFLER         			PIPER 	PA28  	PA28181     	7102807	SO  										ENGINE	FAILED          	B			MOGR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			GL	25	2558M	3592 				287890256				DURING ANNUAL INSPECTION, ENGINE FOUND RUNNING RICH AND WOULD NOT DEVELOP FULL POWER.  TROUBLESHOOTING REVEALED MUFFLER 	TAILPIPE 50 PERCENT BLOCKED BY FAILED BLAST TUBE.  MUFFLER WAS REMOVED,					1	L	7	1 	3O				2A13
1998032600285	19980326	00285	SO  	1998	3	26	98ZZZX1106       	1	19980223	G	3246	04008602	WHEEL           			PIPER 	PA28  	PA28181     	7102807	SO  										MLG	GOUGED          	B			MOGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	2558M	3592 				287890256				WHILE CHANGING TIRE, FOUND AREAS BELOW TIRE BEAD AREAS SEVERELY GOUGED BY SHARP TOOL.  WHEEL WAS REPLACED WITH NEW.						1	L	7	1 	3O			 	2A13
1998032600286	19980326	00286	SO  	1998	3	26	98ZZZX1107       	1	19980223	G	3246	04008602	WHEEL           			PIPER 	PA28  	PA28181     	7102807	SO  										MLG	CRACKED         	B			MOGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	2558M	3592 				287890256				WHILE CHANGING TIRE, FOUND WHEEL CRACKED AT BOLT HOLE.  HOLE APPEARED TO BE DRILLED OFF-CENTER.  ALSO, AREA BELOW TIRE B	EAD GOUGED PREVIOUSLY BY SHARP OBJECT USED TO BREAK TIRE LOOSE.  WHEEL REPLACED WITH NEW.					1	L	7	1 	3O			 	2A13
1998032600287	19980326	00287		1998	3	26	98ZZZX1108       	1	19980217	G	2910		FITTING         			AMTR  		GLASAIRIII  												NLG HYDRAULIC	LOOSE           	G		A		O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			WP	27	56GJ	282  				3141				PILOT REPORTED UNSAFE NOSE LANDING GEAR UPON FINAL APPROACH.  UPON TOUCHDOWN, NLG COLLAPSED.  INVEST REVEALED A LOOSE HY	D FITTING UNDER THE FLOOR PANEL HAD LEAKED HYD FLUID WITH SUBSEQUENT LOSS OF HYD PRESSURE.  IT APPEARS THE NOSE GEAR NEV	ER ACHIEVED CENTER, ALTHOUGH THE MAIN GEAR INDICATED DOWN AND LOCKED.  FURTHER INVEST REVEALED SB 103, NOSE GEAR OVERCEN	TER SPRING, HAD NOT BEEN ACCOMPLISHED AND SB 100, CHECK OF LANDING GEAR OVERCENTER CONDITION, WAS NOT UTILIZED TO ITS FU	LLEST.  THE LOOSE HYD FITTING WAS INITIALLY CAUSAL.  THIS INCIDENT MAY HAVE BEEN AVOIDED IF SB 103 HAD BEEN ACCOMPLISHED	 AND LANDING GEAR RIGGING ACCOMPLISHED IAW SB 100.				0
1998032600288	19980326	00288	EA  	1998	3	26	98ZZZX1109       	2	19980305	G	8520	5015	STUD            			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					NR 2 CYL BASE	FAILED          	B			Q2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	73N					230	L2345951A			DURING 100-HOUR INSPECTION, NR 2 CYLINDER BASE STUD FOUND BROKEN.  SUBMITTER SUGGESTED POSSIBLY CAUSED BY ENGINE TOTAL T	IME.					1	H	7	2 	3O	3	O		A31EU   	1E10
1998032600289	19980326	00289	CE  	1998	3	26	98ZZZX1110       	1	19980309	G	3230	08421211	TUBE ASSY       			CESSNA	310   	310P        	2074238	CE  										NLG	FAILED          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5092P	7451 				310P0057				NOSE GEAR ROD END ASSY FAILED.  THE BEARING WAS FREE AND NOT SEIZED.						1	L	7	2 	3O				3A10
1998032600291	19980326	00291	CE  	1998	3	26	98ZZZX1112       	1	19980309	G	5312	081107510	SUPPORT         			CESSNA	320   	320A        	2074506	CE  										AFT CABIN	BUCKLED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3038R	13   				320A0038				DURING ANNUAL INSPECTION, FOUND REAR CABIN BULKHEAD SUPPORT (PN 0811075-10) BUCKLED.  UPON FURTHER DISASSEMBLY, FOUND FI	TTING SEVERELY CORRODED.					1	L	7	2 	3O				3A25
1998032600292	19980326	00292	CE  	1998	3	26	98ZZZX1113       	1	19980309	G	5711	08112763	FITTING         			CESSNA	320   	320A        	2074506	CE  										SPAR AFT CABIN	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3038R	13   				320A0038				DURING ANNUAL INSPECTION, FOUND REAR CABIN BULKHEAD SUPPORT (PN 0811075-10) BUCKLED.  UPON FURTHER DISASSEMBLY, FOUND FI	TTING SEVERELY CORRODED.					1	L	7	2 	3O				3A25
1998032600293	19980326	00293	NM  	1998	3	26	98ZZZX1114       	1	19980316	G	2434	02035	ALTERNATOR      	ELECTROSYS  		PIPER 	PA60  	PA60601P    	7106012	NM  											FAILED          	H				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NM	03	727MB		9    			61P079680634				OVERHAULED ALTERNATOR FROM ELECTROSYSTEMS FAILED 3 HOURS INTO FIRST FLIGHT AFTER INSTALLING.  (INTERNAL FAILURE).						1	M	7	2 	3O			RT	A17WE
1998032600295	19980326	00295	WP  	1998	3	26	98ZZZX1115       	1	19980122	G	6710	C5851	SHAFT           			ROBSIN	R44   	R44         	7640120	WP  										CYCLIC CONTROL	WORN            	G		A		O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			SO	19	972SA	63   				0394				ROTORCRAFT EXPERIENCED A PARTIAL CYCLIC CONTROL FAILURE WHILE LANDING.  PILOT WAS UNABLE TO ROLL LEFT USING CYCLIC INPUT	.  INVESTIGATION REVEALED THAT LATERAL TRIM ACTUATOR ASSEMBLY SHAFT, PN C585-1, HAD A STEP WORN IN IT WHICH ALLOWED THE 	TRIM ACTUATOR TO JAM.  THREE ADDITIONAL AIRCRAFT INSPECTED REVEALED THE SAME PROBLEM.  LATERAL TRIM ACTUATOR ASSEMBLY WA	S REPLACED ON ALL 4 AIRCRAFT.  SAFETY RECOMMENDATIONS SUBMITTED.  AD 98-04-12 ISSUED TO INSPECT AND CORRECT THIS PROBLEM	 ON ALL R44 HELICOPTERS.		1	G	7	1 	3O				H11NM
1998032600296	19980326	00296		1998	3	26	98ZZZX1116       	4	19980215	G	3120	V23154C0721GB104	RELAY           			SNIAS 	350   	AS350B2     	8680813	EU  										HOBBS METER	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	4055L					2916				DISCREPANCY IN THE HOUR METER.  TIME WAS LESS THAN ACTUAL FLIGHT TIME.  T/S OF THE METER REVEALED THERE WAS NO POWER AVA	ILABLE TO HOBBS METER.  DISCOVERED THE RELAY WAS HALF FILLED WITH WATER AND THE PINS IN THE SOCKET HAD RUSTED OFF.  UPON	 EVALUATING THE FAILURE NOTED THE RELAYS ARE NOT SEALED, AND EACH RELAY IS INSERTED IN A SOCKET WHICH CONTRIBUTES TO POO	R CONTACT AND THE POTENTIAL FOR CORROSION.  THE LOCATION OF THE RELAYS IS SUCH THAT THE AIR CONDITIONING CONDENSATION WI	LL AMOST CERTAINLY DRIP ON THE RELAYS.  SOLUTION WOULD BE TO INSTALL HERMETICALLY SEALED RELAYS J2K-4730-107P OR EQUIVAL	ENT AND MOUNT THEM TO THE PANEL NEXT TO THE HOUR METER.	1	G	7	1 	3U				H9EU
1998032600297	19980326	00297	NE  	1998	3	26	98ZZZX1117       	2	19980201	G	7230	1B5130C	BEARING         								PWA   	2037  	PW2037      		NE  					ENG NR 1 MAIN	FAILED          	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		5398 								ENGINE REMOVED FOR METAL IN CHIP COLLECTORS, NRS 1, 2, AND 3.  DISASSEMBLY INSPECTION REVEALED FAILED NR 2 MAIN BEARING.	  ONE BALL SPALLED AND BEARING CAGE MUSHROOMED ON OD, SILVER PLATE WORN OFF ONLY AT SPALLED BALL AREA.  BEARING FORWARDE	D TO PRATT & WHITNEY EAST HARTFORD FOR INVESTIGATION.									4	F			E17NE
1998032600298	19980326	00298	SO  	1998	3	26	98ZZZX1118       	1	19980201	G	2810		FUEL TANK       			PIPER 	PA28  	PA28235     	7102810	SO  										LT/RT MAIN	MISINSTALLED    	D				K				NONE                    				W	 		INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	8777W					2810321				FOUND LT AND RT MAIN FUEL TANKS INSTALLED WITH AN 526-C NON-STRUCTURAL SCREWS OF ASSORTED WRONG LENGTHS.  THIS INSTALLAT	ION CALLS FOR 60 EACH MS 27039C-8-12 (OR EQUIVALENT) STRUCTURAL SCREWS ALONG THE SPAR, TOP AND BOTTOM, AND 80 EACH MS 27	039C-8-9 SCREWS ALONG THE SIDES OF THE TANKS.  THESE TANKS WERE REPAIRED AND INSTALLED IN JANUARY, 1997 (BY OWNER RECOLL	ECTION).  AIRCRAFT RECORDS NOT AVAILABLE FOR EXACT DATES AND TIMES.			1	L	7	1 	3O			 	2A13
1998032600299	19980326	00299	SW  	1998	3	26	98ZZZX1119       	1	19980303	G	7603	31402	CONTROL CABLE   			BBAVIA	7     	7ECA        	21101NN	SW  										THROTTLE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5169X	2487 				676				THROTTLE CABLE BROKE APPROXIMATELY 1.5 INCHES FROM THROTTLE LEVER.  OLDER AIRCRAFT USED QQ-2-470 MUSIC WIRE .090 INCH DI	AMETER.  INNERGRANULAR CORROSION WAS NOTED IN THE BROKEN AREA.  SUBMITTER RECOMMENDED CABLE BE REPLACED WITH 20253-P2 PI	N MATERIAL OR UPGRADE AIRCRAFT TO LATE MODEL CABLE SYSTEM.				1	H	7	1 	3O			 	A759
1998032600300	19980326	00300	CE  	1998	3	26	98ZZZX1120       	1	19980304	G	2140		FUEL LINE       		8259JR2     	CESSNA	310   	310R        	2074245	CE  										HEATER	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	2644U				673	310R1811				DURING ANNUAL INSPECTION AND BY C/W AD 81-09-09 BY VISUAL INSPECTION, CORROSION WAS FOUND ON THE FORWARD FUEL INLET LINE	 AFT OF THE HEATER PUMP VALVE.  SUBMITTER STATED THIS IS THE THIRD LINE FOUND WITH THIS PROBLEM ON THREE DIFFERENT 310R'	S.				1	L	7	2 	3O				3A10
1998040100002	19980401	00002		1998	4	1	98ZZZX1121       	4	19980128	G	3425	329B7A	GYRO HORIZON    	COLLINS     		SWRNGN	SA226 	SA226AT     	8780405	SW  										FLT DIRECTOR	FAILED          	B	L	A	EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	59TP				2490	T26161				WHEN RECEIVED, THE PRESENTATION WAS SHOWING AN ATTITUDE OF 70 DEGREES UP WHEN ENERGIZED.  IT SHOULD HAVE BEEN SHOWING ZE	RO ATTITUDE.  THE PROBLEM WAS TRACED TO THE PITCH SYNCHRO.  THIS SYNCHRO HAD LOCKED UP DUE TO THE LAMINATION IMPREGNATIN	G MATERIAL GETTING INTO THE VERY SMALL AIR GAP BETWEEN THE ROTOR AND STATOR OF THE SYNCHRO.  ONLY ONE SET SCREW WAS USED	 TO HOLD THE SYNCHRO DRIVE GEAR ON THE SYNCHRO SHAFT, THEREFORE, WHEN THE SYNCHRO LOCKED UP, THE GEAR SLIPPED ON THE SHA	FT ALLOWING THE SYNCHRO TO GIVE THE WRONG INFORMATION TO THE PRESENTATION.  AFTER ELIMINATING THE CONTAMINATION PROBLEM 	IN THE SYNCHRO, A FLAT WAS MACHINED ON THE SYNCHRO SHAFT.  TWO SET SCREWS WERE USED TO SECURE SYNCHRO DRIVE GEAR.	2	L	7	2 	4T			RT	A5SW
1998032600301	19980326	00301	CE  	1998	3	26	98ZZZX1122       	1	19980212	G	7120	57510061	MOUNT           			CESSNA	441   	441         	2076020	CE  										LT ENG INBD	CRACKED         	B	S	A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	441W	5039 			368	4410181				WHILE INVESTIGATING A ROUGH ENGINE, FOUND AN ENGINE MOUNT TUBE CRACKED THROUGH ON LT ENGINE INBOARD, UPPER CLUSTER, LOWE	R TUBE.  INSTALLED DIFFERENT REPAIRED TRUSS.					1	L	7	2 	3T			RT	A28CE
1998032600302	19980326	00302	SO  	1998	3	26	98ZZZX1123       	1	19980305	G	2140	B405065D722	HEATER          			PIPER 	PA31  	PA31350     	7103110	SO  										FORWARD	FAILED          	H		A		H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	01	63ND	362  			12771058	317852098				DURING FLIGHT, THE COCKPIT FILLED WITH A GREENISH, YELLOW SMOKE EMANATING FROM THE DEFROST AND HEATER DUCTS.  PILOT SHUT	 DOWN THE FORWARD HEATER AND EVACUATED THE SMOKE FROM THE CABIN.  THE FLIGHT CONTINUED TO THE ORIGINAL DESTINATION.  THE	 AIRCRAFT WAS INSPECTED AND FOUND UNDAMAGED.  THE FORWARD HEATER HAD OVERHEATED.  WITHOUT FURTHER INSPECTION OF THE HEAT	ERS, THE DAMAGE AND SYMPTOMS ARE CONSISTENT WITH A PERFORATED BURNER CAN.  THIS COMBUSTION HEATER HAD A PRESSURE DECAY T	EST IAW AD 96-20-07 ON 1-18-98, AND HAD ACCUMULATED 62.4 HEATER HOURS OF OPERATION SINCE THAT DATE.		1	L	7	2 	3O				A20SO
1998032600303	19980326	00303	SO  	1998	3	26	98ZZZX1124       	1	19980310	G	2750	6282000	SPRING          			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP RETURN	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		4400 								DURING PRE-FLIGHT INSPECTION, PILOT PUSHED DOWNWARD ON FULLY EXTENDED FLAPS, HEARD SNAPPING NOISE AND NOTICED FLAPS EXTE	NDED AN ADDITIONAL 5 DEGREES BEYOND FULL EXTENDED POSITION AND LOCKED.  FLAPS COULD NOT BE RAISED WITH FLAP CONTROL HAND	LE.  MAINTENANCE INVESTIGATION REVEALED THAT FLAP RETURN SPRING HAD BROKEN WHERE IT ATTACHES TO FLAP TORQUE TUBE SPROCKE	T CHAIN ALLOWING CHAIN TO DROP ONTO SPROCKET AND JAM BETWEEN LOWER FLAP INPUT CHAIN AND SPROCKET.  SYSTEM IS DESIGNED SO	 THAT SPROCKET TOOTH AND SPRING ATTACH END ARE FORCED TO SHARE THE SAME CHAIN LINK WHENEVER FLAP CONTROL HANDLE IS PULLE	D FULL AFT.  THIS NICKS SPRING AT ATTACH POINT AND EVENTUALLY CAUSES BREAKAGE.	1	L	7	1 	3O				2A13
1998032600304	19980326	00304	SO  	1998	3	26	98ZZZX1125       	2	19980201	G	7324	5200106101	LINE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					FLOW DIVIDER	FAILED          	G				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			GL	27	3246M					402C0294				FUEL REF LINE FROM FLOW DIVIDER TO BAFFLE BROKE CAUSING A ROUGH RUNNING ENGINE.  AIRCRAFT LANDED WITHOUT INCIDENT.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998032600305	19980326	00305	SO  	1998	3	26	98ZZZX1126       	1	19980224	G	2434	ALX9425B	ALTERNATOR      	PRESTOLITE  		PIPER 	PA34  	PA34200T    	7103406	SO  										BRUSH HOLDER	FAILED          	B			ONFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	22382				7110041	347870459				ALTERNATOR FAILED AFTER 2 MINUTES OF OPERATION.  FOUND OPEN FIELD CIRCUIT.  FOUND RED SILICONE SEALANT TYPE MATERIAL ARO	UND BRUSH HOLDER PREVENTING BRUSH SEATING ON SLIP RING.  CAME FROM OVERHAUL  THIS WAY.					1	L	7	2 	3O			 	A7SO
1998032600308	19980326	00308		1998	3	26	98ZZZX1129       	1	19980305	G	2520	SL0191200	ACTUATOR        	PORTER      	SL0230019   															SEAT RECLINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05										SEAT BACK RECLINE ACTUATOR CRACKED.  CRACK EXTENDS FROM SPLINED FIBERNUT TO TIP OF HYDROLOK.  SUSPECT CAUSE, STRESS CRAC	K.
1998032600309	19980326	00309	GL  	1998	3	26	98ZZZX1130       	3	19980227	G	6114	C93	HUB             			CESSNA	414   	414A        	2075907	CE  						MCAULY	3AF32C	3AF32C93    	GL  	NR 2 SOCKET	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	6624C					414A0034		7710518		AFTER TEAR-DOWN, A CRACK WAS FOUND IN NR 2 BLADE SOCKET ON THE ENGINE SIDE.						1	L	7	2 	3O				A7CE    		5	C	P22EA
1998032600310	19980326	00310	EA  	1998	3	26	98ZZZX1131       	2	19980310	G	7314	RG9080J4A	PUMP            			PIPER 	PA46  	PA46350P    	       	SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE FUEL	LEAKING         	B			ODAR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	37AT	17   				4636135	L990661A			OWNER NOTICED FUEL STAIN ON BELLY OF NEW AIRCRAFT.  AFTER INVESTIGATION, FOUND THAT ENGINE DRIVEN FUEL PUMP SEAL HAD EXT	RUDED AND FUEL WAS LEAKING.  LOG BOOKS INDICATED THE SCREWS HOLDING THE CAP AND SEAL IN PLACE HAD BEEN TORQUED IAW LYCOM	ING SB 529.  ALL SCREWS WERE LYCOMING SAFTIED, BUT SCREWS WERE FOUND FINGER TIGHT.  NEW FUEL PUMP WAS INSTALLED CORRECTI	NG PROBLEM.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1998032600311	19980326	00311	CE  	1998	3	26	98ZZZX1132       	1	19980126	G	5753	0523920	BEARING         			CESSNA	210   	T210L       	2073449	CE  										FLAP ROLLER	SEIZED          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	94035	1960 				21060487				DURING AN ANNUAL INSPECTION TO CHECK FLAP BEARINGS AFTER A FAILURE ON A CE-172, FOUND 10 OUT OF 12 BEARINGS WITH THE NEE	DLE BEARINGS SEIZED.  NO VISUAL SIGN OF WEAR.  CLEANED, LUBED, REINSTALLED.  SUBMITTER RECOMMENDED 1,000-HOUR INSPECTION	S REQUIRING REMOVAL.				1	H	7	1 	3O				3A21
1998032600312	19980326	00312	CE  	1998	3	26	98ZZZX1133       	1	19980126	G	5753	0523921	BEARING         			CESSNA	210   	T210L       	2073449	CE  										FLAP ROLLER	SEIZED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	94035	1960 				21060487				DURING AN ANNUAL INSPECTION TO CHECK FLAP BEARINGS AFTER A FAILURE ON A CE-172, FOUND 10 OUT OF 12 BEARINGS WITH THE NEE	DLE BEARINGS SEIZED.  NO VISUAL SIGN OF WEAR.  CLEANED, LUBED, REINSTALLED.  SUBMITTER RECOMMENDED 1,000-HOUR INSPECTION	S REQUIRING REMOVAL.				1	H	7	1 	3O				3A21
1998032600313	19980326	00313	CE  	1998	3	26	98ZZZX1134       	1	19980113	G	5753	0523920	BEARING         			CESSNA	172   	172N        	2072434	CE  										RT OUTER AFT	FAILED          	H		A		O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			NM	03	4642J	7200 				17273658				DURING TOUCH AND GO PRACTICE, RT FLAP OUTER AFT BEARING FAILED DURING RETRACTION.  THE FAILURE CAUSED THE FLAP TO BIND A	ND TRIP CIRCUIT BREAKER, BUT NOT UNTIL AFTER THE RT FLAP HAD BEEN DAMAGED BY THE BINDING.  THE FLAP SKINS AND SPAR WERE 	DAMAGED OUTBOARD OF PUSH/PULL ROD.  DAMAGED ENOUGH TO WARRANT REPAIR OF FLAP.  THE AIRCRAFT WAS INSPECTED PER A 100-HOUR	 45 HOURS BEFORE WITH NO DEFECTS FOUND.			1	H	7	1 	3O			NT	3A12
1998032600314	19980326	00314	CE  	1998	3	26	98ZZZX1135       	1	19980215	G	5711	0411131	SPAR BLOCK      			CESSNA	120   	120         	2071402	CE  										FRONT SPAR	CORRODED        	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	77412	4626 				11853				BLOCK 5 ( 4, NR 0411129) REMOVED.  CHECKED INSIDE OF FRONT AND REAR SPARS.  SLIGHT CORROSION FOUND.  CLEANED AND PAINTED	 WITH ZINC CHROMATE.  MOST BOLTS FROZEN INTO BLOCKS.  BOLTS HAD TO BE POUNDED OR DRILLED OUT.  RECOMMEND THAT BLOCKS BE 	REMOVED IF WINGS ARE TAKEN OFF FOR ANY REASON TO CHECK INSIDE OF SPARS.				1	H	7	1 	3O				A768
1998032600315	19980326	00315	CE  	1998	3	26	98ZZZX1136       	1	19980215	G	5711	0411476	SPAR BLOCK      			CESSNA	120   	120         	2071402	CE  										REAR SPAR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	77412	4626 				11853				BLOCK 5 ( 4, NR 0411129) REMOVED.  CHECKED INSIDE OF FRONT AND REAR SPARS.  SLIGHT CORROSION FOUND.  CLEANED AND PAINTED	 WITH ZINC CHROMATE.  MOST BOLTS FROZEN INTO BLOCKS.  BOLTS HAD TO BE POUNDED OR DRILLED OUT.  RECOMMEND THAT BLOCKS BE 	REMOVED IF WINGS ARE TAKEN OFF FOR ANY REASON TO CHECK INSIDE OF SPARS.				1	H	7	1 	3O				A768
1998032600316	19980326	00316	CE  	1998	3	26	98ZZZX1137       	1	19980215	G	5520	042215	BEARING         			CESSNA	120   	120         	2071402	CE  										ELEVATOR HINGE	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	77412	4626 				11853				INSPECTION FOUND INNER RACE ELEVATOR HINGE BEARING INSIDE DIAMETER WORN EXCESSIVELY.  REPLACED BEARING AND BOLT.						1	H	7	1 	3O				A768
1998032600317	19980326	00317	CE  	1998	3	26	98ZZZX1138       	1	19980310	G	5312	12128582	BULKHEAD        			CESSNA	210   	210G        	2073430	CE  										BS 230.187	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	5837F					21058837				BULKHEAD FOUND CRACKED DURING ANNUAL INSPECTION PER AD 72-07-09.  EFFECTIVE DATE 4-1-72.						1	H	7	1 	3O				3A21
1998032600318	19980326	00318	GL  	1998	3	26	98ZZZX1139       	3	19980303	G	6114	C1579C1	HUB             													MCAULY	2A36C	2A36C1      	GL  	NR 1 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					561124			561124		PROPELLER RECEIVED FOR OVERHAUL.  DURING HUB INSPECTION, A CRACK WAS FOUND IN THE NR 1 BLADE SOCKET, 1 THREAD IN, 5.00 T	O 9.30 POSITION, 4 INCHES LONG.  CRACK WAS DISCOVERED USING A 10X MICROSCOPE.															5	C	P880
1998032600319	19980326	00319	GL  	1998	3	26	98ZZZX1140       	3	19980303	G	6114	D6608C88	HUB             													MCAULY	3A32C	D3A32C88    	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	90WS	2432 	534  					761752		PROPELLER RECEIVED DISASSEMBLED FOR OVERHAUL.  DURING THE INSPECTION OF THE HUB USING A 10X POWER MICROSCOPE, A CRACK WA	S DISCOVERED IN NR 2 BLADE SOCKET BETWEEN 6 TO 7 O'CLOCK POSITION, 4 THREADS IN ABOUT 1 INCH IN LENGTH.															5	C	P21EA
1998032600320	19980326	00320		1998	3	26	98ZZZX1141       	1	19980213	G	2436	51539007A	GCU             	LUCAS       																DC SYSTEM	FAILED          	B			AY55	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03					1066C					DC GENERATOR CONTROL RECEIVED FROM CUSTOMER FOR REPAIR.  DURING INSPECTION, FOUND UNIDENTIFIABLE MODIFICATION ON CIRCUIT	 BOARD NR 51539-1081 REV E AND CIRCUIT BOARD NR 51539-1061 REV D WHEN THERE ARE NO MODIFICATIONS FOR THESE BOARDS OTHER 	THAN REPLACEMENT.  DC GCU MFG DATE:  8-82.  NOTIFIED CUSTOMER, GREEN TAG ATTACHED TO COMPONENT, AND RETURNED TO CUSTOMER	.
1998032600321	19980326	00321	EA  	1998	3	26	98ZZZX1142       	2	19980212	G	8550	MILH6000	LINE            			GULSTM	AA1   	AA1C        	0631214	SO  	LYC   	O235  	O235L2C     	41505	EA  					OIL BREATHER	BLOCKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	39058					AA1C0206				ENGINE BEGAN LEAKING OIL AT CYLINDER THRU STUD LOCATIONS.  AT SAME TIME, FUEL PRESSURE ROSE APPROX 2 POUNDS.  FOUND BREA	THER LINE MIL-H-6000, .75 INCH TUBE, BLOCKED APPROX 95 PERCENT.  BLOCKAGE APPEARS TO BE DETERIORATED INNER HOSE MATERIAL	.  HOSE MFG'D IN 1973.  ACFT MFG'D IN 1978.  HOSE WAS OLD AT TIME OF INSTALLATION.  SUBMITTER RECOMMENDED CHANGING ALL R	UBBER HOSES EVERY 5 YEARS AND INSPECTING ID OF BREATHER HOSE AT ANNUAL.  PRESS BUILD-UP IN THE CRANKCASE CAN CAUSE LOSS 	OF ENGINE PROPELLLER NOSE SEAL AND SUBSEQUENT LOSS OF ALL ENGINE OIL.  HIGHER THAN NORMAL FUEL PRESSURE CAN CAUSE FLOODI	NG OF CARBURATED ENGINE.  POOR CRANKCASE BREATHING CAN ALSO CONTRIBUTE TO ACCELERATED CORROSION.	1	L	7	1 	3O	3	O		A11EA   	E223
1998032600322	19980326	00322	CE  	1998	3	26	98ZZZX1143       	1	19980216	G	5412	56560061	HEAT SHIELD     			CESSNA	340   	340A        	2076405	CE  										LT FIREWALL	BURNED          	B	L		XM8R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17	340TS					340A0999				AFTER REMOVAL OF THE LEFT NACELLE COVER AND FUEL CELL, SEVERE CORROSION WAS FOUND.  ALSO, AFT SIDE OF LT FIREWALL DISCOL	ORED FROM HEAT AND THE FUEL CELL HEAT SHIELD IS BURNED THROUGH.  THE HEAT DAMAGE IS BELIEVED TO BE CAUSED BY A PREVIOUS 	EXHAUST FAILURE.  THIS AIRCRAFT IS WELL MAINTAINED, HANGARED MOST OF THE YEAR, AND NOT HIGH TIME.  SUBMITTER BELIEVES TH	IS IS A SERIOUS PROBLEM THAT MAY GO UNDETECTED ON MANY SIMILAR AIRCRAFT.			1	L	7	2 	3O				3A25
1998032600323	19980326	00323	CE  	1998	3	26	98ZZZX1144       	1	19980216	G	5700	562010023	NACELLE         			CESSNA	340   	340A        	2076405	CE  										LT WING ASSY	CORRODED        	B	P	A	XM8R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17	340TS	2095 				340A0999				FUEL LEAKING FROM RT WING FND COMING FROM RT NACELLE FUEL CELL.  REMOVED NACELLE ACCESS COVER, FUEL CELL LINER, HEAT SHI	ELD, AND FUEL CELL.  SEVERE CORROSION FND ON UPPER WING SKIN AND STRS.  FUEL CELL LINER  CORRODED (EXFOLIATED).  ALSO, L	T NACELLE INSPECTED FOR SIMILAR CONDITION.  AFTER REMOVAL OF LT NACELLE COVER AND FUEL CELL, SEVERE CORROSION FND.  UPPE	R WING SKIN, STRINGERS AND UPPER SPAR CAP ARE ALL EXFOLIATED.  AFT SIDE OF LT FIREWALL DISCOLORED FROM HEAT AND FUEL CEL	L HEAT SHIELD IS BURNED THROUGH.  HEAT DAMAGE MAY BE CAUSED BY A PREVIOUS EXH FAILURE.  ACFT IS WELL MAINTAINED, HANGARE	D MOST OF THE YEAR AND NOT HIGH TIME.  SUBMITTER BELIEVES THIS IS A PROBLEM THAT MAY GO UNDETECTED ON SIMILAR ACFT.	1	L	7	2 	3O				3A25
1998032600324	19980326	00324	CE  	1998	3	26	98ZZZX1145       	1	19980216	G	5700	562010022	NACELLE         			CESSNA	340   	340A        	2076405	CE  										RT WING ASSY	CORRODED        	B	P		XM8R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17	340TS	2095 				340A0999				FUEL LEAKING FROM RT WING FND COMING FROM RT NACELLE FUEL CELL.  REMOVED NACELLE ACCESS COVER, FUEL CELL LINER, HEAT SHI	ELD, AND FUEL CELL.  SEVERE CORROSION FND ON UPPER WING SKIN AND STRS.  FUEL CELL LINER  CORRODED (EXFOLIATED).  ALSO, L	T NACELLE INSPECTED FOR SIMILAR CONDITION.  AFTER REMOVAL OF LT NACELLE COVER AND FUEL CELL, SEVERE CORROSION FND.  UPPE	R WING SKIN, STRINGERS AND UPPER SPAR CAP ARE ALL EXFOLIATED.  AFT SIDE OF LT FIREWALL DISCOLORED FROM HEAT AND FUEL CEL	L HEAT SHIELD IS BURNED THROUGH.  HEAT DAMAGE MAY BE CAUSED BY A PREVIOUS EXH FAILURE.  ACFT IS WELL MAINTAINED, HANGARE	D MOST OF THE YEAR AND NOT HIGH TIME.  SUBMITTER BELIEVES THIS IS A PROBLEM THAT MAY GO UNDETECTED ON SIMILAR ACFT.	1	L	7	2 	3O				3A25
1998032600325	19980326	00325	SW  	1998	3	26	98ZZZX1146       	1	19980220	G	3213	601051001	SADDLE          		058321300   	BELL  	206   	OH58A       	1181579	SW  										HI SKID GEAR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	701MP	5    				7221270				WHILE GROUND HANDLING HELICOPTER, SKID EAR BROKE OFF.  EAR MIGHT BE HARDENED TOO MUCH CAUSING IT TO BE BRITTLE.						1	G	7	1 	3U				H2SW
1998032600327	19980326	00327	GL  	1998	3	26	98ZZZX1147       	2	19980223	G	7322	252464429	FUEL CONTROL    	BENDIX      	23057344    	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	D	L			K				NONE                    				X			ENGINE FLAMEOUT           			IN	INSP/MAINT     	1			WP	23	550JM				310785	0013E	CAE834981			ENGINE STILL HAVING DELAYED STARTS.  ENGINE FLAMED OUT AT IDLE.  RESTARTED WITH THE START PUMP ON, AND FLAMED OUT DURING	 THE START SEQUENCE.  RESTARTED AGAIN, MADE IT TO IDLE, BUT FLAMED OUT AGAIN.  REMOVED THE FUEL CONTROL AND INSTALLED A 	DASH 28 UNIT.  NO FURTHER PROBLEMS.  TIME ON FUEL CONTROL SN 310785 WAS 1237.5 HOURS TSO, AND 31.6 HOURS SINCE REPAIR.				1	G	7	1 	3U	3	U		H3WE    	E4CE
1998032600602	19980326	00602	CE  	1998	3	26	98ZZZX1161       	1	19980225	G	3213	5141001213	STRUT           			CESSNA	340   	340A        	2076405	CE  										LOWER LINK LUG	WORN            	B			A19R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4104G	4400 				340A0279				INSPECTION OF LOWER GEAR STRUT ASSY FOUND LUG HOLES ELONGATED IN LINE WITH LOWER TORQUE LINK.  SUSPECT CORROSION INDUCED	 WEAK DUE TO POOR LUBE HISTORY AND EXTREME CLIMATE.					1	L	7	2 	3O				3A25
1998032600603	19980326	00603	SW  	1998	3	26	98ZZZX1162       	1	19980302	G	5740		ANGLE           			AIRTRC	AT500 	AT502A      	0390306	SW  										WING ATTACH OTBD	CRACKED         	B		A	Q2AR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	438RJ	1241 				502A0345				DURING ANNUAL INSPECTION AND C/W WING ATTACH ANGLE BOLT INSPECTION, OUTBOARD WING ATTACHMENT ANGLE FOUND CRACKED.						1	L	7	1 	3T			NC	A17SW
1998032600605	19980326	00605	WP  	1998	3	26	98ZZZX1164       	1	19980312	G	6710	C0561	SPRING ASSY     		C5811       	ROBSIN	R44   	R44         	7640120	WP  										LATERAL TRIM	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	159RP	199  				0342				WHILE PERFORMING INSPECTION FOR AD 98-06-12, FOUND LATERAL TRIM SPRING ASSY PULLED COMPLETELY OUT OF MOUNTING BLOCK AND 	DANGLING AGAINST BELLY SKIN.  TRIM MOTOR ARM P/N C581-1 FROZEN ON SPRING SHAFT.  SUBMITTER STATED HAD THIS UNIT FAILED I	N-FLIGHT, LOSS OF CONTROL WOULD HAVE BEEN POSSIBLE.  THE REPLACEMENT SPRING ASSY LOWER BEARING IS STAKED INTO THE MOUNTI	NG BLOCK, YET THIS IS NOT THE CAUSE OF THE AD.  SUBMITTER RECOMMENDED REVISION OF AD 98-04-12 TO REQUIRE IMMEDIATE REPLA	CEMENT OF AFFECTED SPRING ASSY REGARDLESS OF SHAFT WEAR.		1	G	7	1 	3O				H11NM
1998032600606	19980326	00606	NE  	1998	3	26	98ZZZX1165       	2	19980307	G	7200		ENGINE          			LEAR  	25    	25D         	5170514	CE  	GE    	CJ610 	CJ6106      	30006	NE  					RT ENGINE	FAILED          	E				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			GL	23	95CK	10490	6684 			248	211032A			RIGHT ENGINE FLAMED OUT.  ADJUSTED FUEL DENSITY.  GROUND RUN SATISFACTORY.  PERFORMED ALTITUDE ACCELERATION CHECK, ENGIN	E DID NOT PASS.  REPLACED ENGINE WITH SERVICEABLE UNIT.					2	L	7	2 	4J	4	J		A10CE   	1E16
1998032600607	19980326	00607	EU  	1998	3	26	98ZZZX1166       	1	19980103	G	2432	RG390E	BATTERY         	CONCORDEBATT		BRAERO	DH125 	BAE125800A  	1500285	EU  										DC SYSTEM	RUPTURED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	601RS	343  			276425	258018				BATTERY WAS MAKING NOISE BUBBLING AND CRACKING.  WHEN ON CHARGE, BATTERY CAME UP TO 29 VOLTS.  REMOVED BATTERY FOR TEST,	 OPEN CIRCUIT VOLTS 25.7.  PUT LOAD ON BATTERY, 200 AMPS.  WHEN SWITCH WAS TURNED ON, BATTERY BLEW HOLE IN THE SIDE.  TE	ST WAS DONE IN AERO BATTERY SHOP.  SUPPORT SLEEVE WAS UP AT THE TIME.  CYCLES:  242.				2	L	7	2 	4F			RT	A3EU
1998032600608	19980326	00608	EU  	1998	3	26	98ZZZX1167       	1	19980223	G	2432	RG390E	BATTERY         			BRAERO	DH125 	HS125700A   	4230170	EU  										DC SYSTEM	RUPTURED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	74B	463  				NA0209				BATTERY SUPPORT SLEEVE ON OUTSIDE OF BATTERY SLIDES DOWN 2 INCHES AND THE SIDE BLEW OUT A 2 INCH BY 6 INCH HOLE.  DATE O	F MFG:  3-96.  INSTALLED:  3-28-96.  REMOVED:  2-24-98.  FLIGHT HRS:  463.  CYCLES:  319.					2	L	7	2 	4F				A3EU
1998032600609	19980326	00609	EU  	1998	3	26	98ZZZX1168       	1	19980209	G	3010	3D248501	TIMER           			STBROS	SD3   	SD360       	8100606	EU  										TAIL DEICE	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	13	601CA					SH3623				THE TAIL DE-ICE BOOTS WERE INOPERABLE DURING THE FLIGHT.  THE DE-ICE TIMER WAS REPLACED.  OPS CHECK GOOD.						2	H	7	2 	4T				A41EU
1998032600611	19980326	00611	SW  	1998	3	26	98ZZZX1169       	1	19980313	G	2430		GROUND CONNECT  			GULSTM	560   	560         	0141402	SW  										START/GENERATOR	LOOSE           	D		A		K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	03	19PV	514  				560416				PILOTS REPORTED A PARALLELING PROBLEM WITH THE GENERATORS.  INSPECTION REVEALED BOTH STARTER/GENERATOR GROUND CONNECTION	S WERE LOOSE.  MINOR ARCING WAS NOTED ON LEFT GROUND.  BOTH CONNECTIONS WERE CLEANED AND RESEATED.  THIS CONDITION RESUL	TED FROM IMPROPER TORQUE OF ATTACHING HARDWARE.				1	H	7	2 	3O				6A1
1998032600612	19980326	00612	CE  	1998	3	26	98ZZZX1170       	1	19980303	G	3340	34022601091	LAMP            	WHELEN      		BEECH 	MU300 	400A        	1155402	CE  											SHORTED         	B	L		AKGR	H				DEACTIVATE SYST/CIRCUITS				F	H		FLT CONT AFFECTED         	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CE	05	768TA					RK168				AIRCRAFT TT:  122.6 HOURS.  CREW IN-FLIGHT HAD YAW DAMPER, BOTH HSI FLAGS AND THEN NOTED BOTH INVERTERS FALLING OFF.  CE	RTIFICATED REPAIR STATION DISCOVERED THE TAIL BEACON LAMP FILAMENT AT THE BASE OF THE LAMP SHORTING IT OUT.  THIS MIGHT 	BE SETTING UP SOME KIND OF RADIO SIGNAL GETTING INTO THE INVERTERS KNOCKING THEM OFF-LINE.  TURNING THE BEACON POWER OFF	, THE PROBLEM WILL GO AWAY.  SUBMITTER STATED THIS IS THE SECOND AIRCRAFT SEEN WITH THIS PROBLEM.			2	H	7	2 	4F			RT	A16SW
1998032600614	19980326	00614	SO  	1998	3	26	98ZZZX1172       	1	19980318	G	5711		SPAR CAP        			PIPER 	PA28  	PA28140     	7102802	SO  										AFT SPAR CAP	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	600AA	4577 				2825102				DURING WING INSPECTION, FOUND EVERY WHERE THAT SOUNDPROOF INSULATION COMES IN CONTACT WITH THE FERROUS AFT SPAR CAP, THA	T CORROSION SETS IN DUE TO THE MOISTURE THAT THE INSULATION HOLDS.					1	L	7	1 	3O				2A13
1998032600616	19980326	00616	CE  	1998	3	26	98ZZZX1174       	1	19980225	G	2510		BRACKET         			CESSNA	402   	402B        	207590P	CE  										PILOT SEAT BACK	FAILED          	C		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AL	03	87144					402B0933				PILOT SEAT BACK RECLINED IN-FLIGHT.  BRACKET ON RIGHT SIDE OF SEAT BROKEN.  CASTING APPEARS TO HAVE BEEN CRACKED PRIOR T	O FAILURE.					1	L	7	2 	3O				A7CE
1998032600617	19980326	00617	CE  	1998	3	26	98ZZZX1175       	1	19980316	G	3246	AN365	NUT             			CESSNA	185   	A185E       	2072818	CE  										LT MLG	STRIPPED        	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	4535F					1851021				DURING SMOOTH LANDING, LEFT WHEEL/TIRE ASSY DEPARTED AIRCRAFT.  TIRE/WHEEL ASSY WAS PROPERLY FAA APPROVED, BUT OVERSIZE.	  NAS BOLTS HOLDING AXLE TO GEAR LEG STRIPPED THROUGH THE AN365 NUTS.  RECOMMEND THIS INSTALLATION FOR GRAVEL RUNWAY USE	 ONLY.				1	H	7	1 	3O				3A24
1998032600618	19980326	00618	SO  	1998	3	26	98ZZZX1176       	2	19980301	G	7314	6467592	FUEL PUMP       			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					STOP PIN	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	736XB	2000 				R1722860	355353			IN-FLIGHT MIXTURE CONTROL WOULD STICK AND WOULD NOT GO BACK TO FULL RICH MIXTURE.  PREVIOUSLY, MOISTURE STIFF BUT WOULD 	MOVE, AND INSPECTION FOUND NO PROBLEMS.  AFTER LAST 'STICK', INSPECTION FOUND THAT IDLE CUT-OFF STOP PIN WAS LOOSE IN IT	S HOLE AND FREE TO MOVE IN AND OUT OF ITS HOLE FAR ENOUGH TO BLOCK MIXTURE LEVER.  REPLACED PUMP WITH NEW PART.				1	H	7	1 	3O	3	O		3A17    	E1CE
1998032600619	19980326	00619	SO  	1998	3	26	98ZZZX1177       	1	19980212	G	6120	4090500	BRACKET         			PIPER 	PA31  	PA31310     	7103103	SO  										PROPELLER CABLE	FAILED          	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			SW	05	112AG	11740				31698				UPON TRYING TO REDUCE TO CLIMB POWER, THE RIGHT PROP CONTROL WAS STIFF WHEN MORE PRESSURE APPLIED.   THE CONTROL BROKE F	REE, BUT THE RPM DID NOT CHANGE.  FOUND PROP CABLE HOLD-DOWN BRACKET BROKEN AND CABLE STIFF.  FREED UP CABLE AND REPLACE	D BRACKET.  OPERATIONAL CHECK OK.  SUGGEST STIFF CABLES BE REPORTED AND CORRECTED TO PRECLUDE BREAKING OF KEEPER WITH LO	SS OF CONTROL EFFECTIVITY.			1	L	7	1 	3O			RT	A20SO
1998032600620	19980326	00620	CE  	1998	3	26	98ZZZX1178       	1	19980305	G	5312	07126161	BULKHEAD        			CESSNA	182   	182L        	2072726	CE  										RT RUD STOP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	42279	4208 				18258940				BULKHEAD FOUND CRACKED AT RIGHT RUDDER STOP APPROXIMATELY .50 INCH LONG.  REMOVED AND REPLACED BULKHEAD ASSY.  THIS REPO	RT SUBMITTED IN C/W AD 72-07-09.					1	H	7	1 	3O			NT	3A13
1998032600622	19980326	00622		1998	3	26	98ZZZX1180       	4	19980318	G	6113	453978	BULKHEAD        			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	22JL					347250198		LAU3797		AFTER FAILURE OF PROPELLER SPINNER BULKHEAD ON SIMILAR MODEL AIRCRAFT, CLOSE INPSECTION COMPLETED WITH DYE PENETRANT, FO	UND CRACKS PROGRESSING FROM PROP SPINNER BULKHEAD MOUNTING  BOLT HOLES.  SUSPECT REASON FOR PREMATURE FAILURE IS WRONG L	ENGTH OF SCREW USED ON SPINNER.  IF NEXT SIZE LONGER SCREW IS USED OTHER THAN CALLED FOR, IT WILL RESULT IN PRELOADING S	PINNER BULKHEAD TO ENGINE DAMPENER DYNAMIC BALANCER) WHERE IT BOTTOMS OUT.  RECOMMEND INSPECTING FOR CORRECT LENGTH OF S	CREWS AND USING EITHER MAGNIFYING GLASS OR DYE PENETRANT FOR INSPECTION.  CRACKS WERE FOUND ON BOTH RIGHT AND LEFT PROPS	.	1	L	7	2 	3O				A7SO    		5	C	P920
1998032600623	19980326	00623	CE  	1998	3	26	98ZZZX1181       	1	19980308	G	2731		ELEV TAB        			CESSNA	414   	414A        	2075907	CE  										ELEV TRIM	MISRIGGED       	H	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	PHECA	3700 				0321				DURING A 1,000 HR INSP ON  RUD-AIL, AND ELEV TRIM IAW CE 414 SM, REV 31, FOUND ELEV TRIM TAB TRAVEL WAS 12 DEG UP/21 DEG	 DOWN.  CHECKED MANUAL FOR TRAVELS OF TRIM TABS AND FOUND IN MM, REV 31, RIGGINGS FOR ELEV TRIM TAB UP:  5 DEG AND DOWN:	  30 DEG.  DOUBLE CK MM REV HISTORY, FOUND ELEV TRIM TAB TRAVELS ALTERED WITH MM REV 31, DATED 2-3-97.  (OLD TRAVELS WER	E:  12 DEG UP AND 20 DEG DOWN, TOL. +1 DEG).  DURING INSTALL, SET TRAVELS IAW MM REV 31:  5 DEG UP AND 30 DEG DOWN.  FIR	ST FLIGHT (TRIM NEUTRAL) ACFT EXPERIENCED A NOSE UP AT TAKE OFF THAT COULD NOT BE CORRECTED BY TRIMMING THE ELEV; IT WAS	 AGAINST ITS 'NOSE DOWN' STOP, AND FORCE HAD TO BE IMPOSED UPON COLUMN TO KEEP ACFT IN LEVEL FLIGHT.	1	L	7	2 	3O				A7CE
1998040200004	19980402	00004	CE  	1998	4	2	98ZZZX1241       	1	19980220	G	3213	51411091	BEARING         			CESSNA	310   	310Q        	2074242	CE  										RT MLG STRUT	WORN            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	11	101DF	2285 				3120Q0828				REMOVED RMLG STRUT TO REPAIR LEAKING SEALS.  FOUND INNER BEARING, WHICH HAD BEEN REPLACED IN C/W AD 90-02-13, WORN APPRO	XIMATELY .037 INCH.  BRASS SHAVINGS MAY HAVE CAUSED SEALS TO FAIL.					1	L	7	2 	3O				3A10
1998040200005	19980402	00005	SO  	1998	4	2	98ZZZX1242       	1	19980201	G	3340	6743604	POTENTIOMETER   			PIPER 	PA28  	PA28R201    	7102816	SO  										NAV LIGHTS	SHORTED         	G		A		O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	11	47839					28R7837006				CUSTOMER RENTED AIRCRAFT AND EXPERIENCED SMOKE IN COCKPIT.  TROUBLESHOT AND FOUND TERMINAL LUG ON POTENTIOMETER HAD CHAF	ED THROUGH HOT LEAD AND CAUSED DIRECT SHORT.  INSULATED TERMINAL LUGS WITH SHRINK TUBE.					1	L	7	1 	3O				2A13
1998040200006	19980402	00006	CE  	1998	4	2	98ZZZX1243       	1	19980206	G	2140	3555011523	SHAFT           			BEECH 	33    	F33A        	1151425	CE  										HEAT/VENT VALVE	FAILED          	B			IYOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	1566P					CE1294				UPON INSTALLING VALVE ASSY ON THE A/C HEAT VENT, THE ARM PORTION OF THE SHAFT ASSY BROKE OFF.  INVESTIGATION FOUND THE W	ELD AT THE BOTTOM OF THE ARM POSITION MISSING WHEN COMPARED TO THE ORIGINAL ASSY.  THE TOP PORTION APPEARED TO HAVE BEEN	 WELDED AND GROUND DOWN WITH LITTLE OR NO PENETRATION OF THE WELD.  THIS WAS 1 OF 4 UNITS BOUGHT AS SPARES, ALL WITH THE	 SAME PROBLEM.  THE MANUFACTURE DATES WERE ALL JUNE 29, 1997 AND INSPECTED BY 870.			1	L	7	1 	3O				3A15
1998040200007	19980402	00007	EU  	1998	4	2	98ZZZX1244       	1	19980302	G	2730		IDLER SUPPORT   			SUKHOI	SU26  	SU26M       	980102 	EU  										ELEV CONTROL	CRACKED         	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	12SU					0102				PILOT OWNER REPORTS SNAP ROLLS WERE NOT CRISP.  UPON INSPECTION OF ELEVATOR CONTROL SYSTEM, THE ELEVATOR IDLER SUPPORT M	EMBER WAS FOUND CRACKED IN HALF AT THE FACTORY WELDMENT.  THE SU26M SUKHOI IS CAPABLE OF UNLIMITED AEROBATICS, AND IT IS	 NOT UNCOMMON TO SEE +/- 10G ON THE METERS.  SUBMITTER SUGGESTED CAUSE OF THIS FAILURE AS THE HIGH G-LOADNG ON PILOT'S S	EATBACK AGAINST THE MEMBER DURING HIGH POSITIVE G-MANEUVERS.			1	L	7	1 	3R			NC	USSR
1998040200013	19980402	00013	CE  	1998	4	2	98ZZZX1245       	1	19980225	G	2121	762811	SWITCH          		99101135    	CESSNA	650   	650         	2076802	CE  										BLOWER VANE ASSY	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	510SD		719  		1217	6500161				BLOWER BECAME NOISY. FOUND 5 EACH FAN BLADES MISSING (P/N 2100900-25).  REMOVED BLOWER FROM AUX HEATER (P/N 6214434-53).	  FOUND BLADES IN AUX HEATER, ALSO FOUND AIRFLOW SWITCH VANE.  SUSPECTED THE VANE CAME OFF THE AIRFLOW SWITCH ASSY CAUSI	NG THE BLADES TO BREAK OFF OF THE FAN/BLOWER ASSY.  SUBMITTER STATED THE VANE TO SWITCH ATTACHMENT SHOULD BE OF A BETTER	/STRONGER DESIGN.			2	L	7	2 	4F				A9NM
1998040200014	19980402	00014	WP  	1998	4	2	98ZZZX1246       	2	19980310	G	7240	8939735	COMBUSTION CASE 			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					LT ENG PLENUM	FAILED          	B		A	YRRD	A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			M	O		OVER TEMP                 	OTHER                     		TO	TAKEOFF        	1			SW	05	66804					BE82	P27165			DURING T/O, PILOT HEARD A 'POOF' SOUND.  NOTICED THE COWLING PAINT DISCOLORED AND THE OIL FILLER DOOR OPEN.  TAKEOFF ABO	RTED, AND ENG EMERG SHUTDOWN.  INVEST DETERMINED THE LT ENG COMBUSTION CASE (PLENUM)  HAD FAILED.  ENG REMOVED FOR REPAI	R, ENG COMPARTMENT DAMAGE REPAIRED.  ENG DISASSEMBLED FOR INSPECT AND IT APPEARED THE PLENUM HAD FAILED AT/AROUND THE P-	3 FITTING BOSS.  ENG MFG CONTACTED TO ESTABLISH IF THE PLENUM WAS AN ORIGINAL COMPONENT FOR THE ENG.  MFG REPLIED PLENUM	 P/N AND S/N WERE NOT IN THE FACILITIES DATA BASE, AND A NON-MFG REPAIR CODE WAS EVIDENT.  SUBMITTER RECOMMENDED TO PREV	ENT RECURRENCE, INSPECT P-3 FITTING BOSS/CUSTOMER AIR PAD AREA OF THE COMBUSTION CASE (PLENUM) CLOSELY AT INSPECTIONS.	1	L	7	2 	4T	4	T		A14CE   	E2WE
1998040200413	19980402	00413	SW  	1998	4	2	98ZZZX1247       	1	19980206	G	5313	206030128165B	LONGERON        		212030100111	BELL  	412   	412         	1182202	SW  										LOWER LT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2071S					33046				DISCOVERED ON REMOVAL OF LEFT TAIL BOOM PANEL DURING ROUTINE MAINTENANCE.  LONGERON WAS CRACKED IN THREE PLACES.  SUSPEC	T CAUSE INDICATES LACK OF PROPER DEBURRING AT RIVET HOLES IN SEVERAL PLACES.  PREPPED COMPLETELY PRIOR TO INSTALLATION.					1	G	7	2 	4U				H4SW
1998040200414	19980402	00414	SW  	1998	4	2	98ZZZX1248       	1	19980206	G	7810	3026934	DUCT ASSY       		3017600     	BELL  	412   	412         	1182202	SW  										EXHAUST FLANGE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2071S					33046				DURING MAJOR REPAIR OF TAIL BOOM, FOUND EXIT DUCT ASSY VERTICAL CRACK APPROXIMATELY 1.25 INCHES LONG ON FORWARD SIDE OF 	FLANGE.  SUSPECT CAUSED BY VIBRATION FROM SEVERE CRACK ALONG EXHAUST EJECTOR 12 INCHES LONG ALONG WELDED BEAD FROM FORWA	RD TO AFT SIDE OF EJECTOR.  LIMIT THE NUMBER OF WELDS TO EJECTOR AND LENGTH.				1	G	7	2 	4U				H4SW
1998040200416	19980402	00416	GL  	1998	4	2	98ZZZX1250       	2	19980122	G	7240	23062750	NOZZLE SHIELD   		6898735     	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMBUST SECTION	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	352TT	1123 			5964	S59	CAE270093			UPON DISASSEMBLY OF TURBINE FOR REPAIR DUE TO BLOWING OIL OUT OF EXHAUST, FOUND DOME AND SHIELD HAD HEAVY OIL STAINS AND	 DOME PART SEPARATED FROM INNER BAND AND CRACKED.  SUBMITTER SUGGESTED POSSIBLY DUE TO TIGHT FIT TO NEW NR 1 FLOATING DI	APHRAGM NOZZLE AND POSSIBLE VIBRATION.  (FIRST RUN ON THE NOZZLE).  ASSURE NR 1 NOZZLE SHIELD HAS SNUG TO LIGHT LOOSE FI	T TO ALL NR 1 NOZZLES.  EXTREME TIGHT FIT AT TANGS TO SADDLE COULD CAUSE THIS PROBLEM.			1	G	7	2 	3U	3	U		H3EU    	E4CE
1998040200417	19980402	00417	NE  	1998	4	2	98ZZZX1251       	1	19980211	G	6520	SB3202A2	BEARING CONE    			SKRSKY	S76   	S76A        	8143006	NE  										INPUT GEARBOX	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL	15370	2416 			760002				ON GROUND RUN UP, HAD BEARING FAILURE IN INPUT QUILL ASSEMBLY.  COMPONENT P/N 7635705000041.						1	G	7	2 	3U				H1NE
1998040200418	19980402	00418	NE  	1998	4	2	98ZZZX1252       	1	19980211	G	6520	SB3202B	BEARING CUP     			SKRSKY	S76   	S76A        	8143006	NE  										INPUT GEARBOX	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL	15370	2416 			760002				ON GROUND RUN UP, HAD BEARING FAILURE IN INPUT QUILL ASSEMBLY.  COMPONENT P/N 7635705000041.						1	G	7	2 	3U				H1NE
1998040200419	19980402	00419	SW  	1998	4	2	98ZZZX1253       	1	19980212	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R SHAFT NR 5	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL				RNRS7539	53141				DURING 25-HOUR INPSECTION, FOUND ONE DISC IN PACK ASSEMBLY CRACKED.  IT WAS THE NR 1 DISC IN THE PACK.						1	G	7	1 	3U			O	H2SW
1998040200420	19980402	00420	SW  	1998	4	2	98ZZZX1254       	1	19980118	G	6510		DISC PACK       		407030801101	BELL  	407   	407         		SW  										T/R DRIVE SHAFT	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL				53142	53141				ON PHASE NR 1 INSPECTION WHILE DOING AD 97-24-17 100-HOUR BLOWER INSPECTION, FOUND DISC NR 1 OF 10, TOTAL, CRACKED  (STA	RTING FRONT TO BACK).					1	G	7	1 	3U			O	H2SW
1998040200421	19980402	00421	EU  	1998	4	2	98ZZZX1255       	1	19980123	G	6322	VT1604012	STATOR          		355A34010800	AEROSP	AS355 	AS355F      	8680806	EU  										COOLER BLOWER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5773X	3946 	1505 		709	5004				DURING PHASE INSPECTION, FOUND OIL COOLER BLOWER STATOR MOUNTING POINTS CRACKED.						1	G	7	2 	3U				H11EU
1998040200422	19980402	00422	EU  	1998	4	2	98ZZZX1256       	1	19980115	G	6220	350A31190703	STARFLEX        			AEROSP	AS355 	AS355F1     	8680810	EU  										M/R HEAD	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5775H				M3881	5025				DISCOVERED DURING DAILY INSPECTION, FOUND 2 EACH STARFLEX ARMS SPLINTERED.						1	G	7	2 	3U				H11EU
1998040200426	19980402	00426	SW  	1998	4	2	98ZZZX1260       	1	19980130	G	6320	L15231487	PACKING         		206040004101	BELL  	206   	206L1       	1182107	SW  										QUILL	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03										AFTER ASSEMBLY OF TRANSMISSION AFTER 4,500 HOUR OVERHAUL AT PRESSURE CHECK, FOUND THE L-1523-1487 O-RING PACKING CHANGED	 APPROX 4 TIMES TO STOP THE INPUT QUILL FROM LEAKING.  UPON EXAMINATION OF SEVERAL NEW PACKINGS, FOUND SOME PACKING APPR	OX 0.022 INCH THICKER THAN THE PACKING THAT LEAKED.  INSTALLED THE THICKER PACKING, THE LEAK STOPPED.  SUBMITTER STATED 	HAVE HAD THIS PROBLEM WITH 3 OTHER TRANSMISSIONS.  WHEN USING THE THICKER PACKING, THE LEAK STOPS.			1	G	7	1 	3U				H2SW
1998040200427	19980402	00427	NE  	1998	4	2	98ZZZX1261       	2	19980128	G	7200		ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 1	FAILED          	B			VE3R	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			WP	23	18LA	2220 				36043	63393			ON FINAL APPROACH TO HOSPITAL ROOF TOP HELIPORT, RPM WARNING HORN ACTIVATED FOLLOWED BY 15 TO 20 SECONDS OF POPPING AND 	GRINDING NOISES FROM NR 1 ENGINE.  AFTER GAINING AIRSPEED, ENGINE WAS SECURED AND AN OEI LANDING WAS MADE AT BURBANK AIR	PORT.  SUBSTANTIAL DAMAGE TO NR 1 ENGINE INTERIOR WAS FOUND, CAUSE UNKNOWN AT THIS TIME.  COMPLETE TWIN-PAC BEING SENT T	O PRATT & WHITNEY FOR EVALUATION.			1	G	7	2 	4U	4	U		H4SW    	E22EA
1998040200431	19980402	00431	SW  	1998	4	2	98ZZZX1264       	1	19980121	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B	L		ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2654				5392	45482				INSPECTION FOUND DRIVE LINK ASSY WITH EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3 FIG 62-21.  ON TEAR DOWN, FOUND BEA	RINGS AND SPACERS WORN BEYOND LIMITS.  TOTAL TIME OF PARTS, LESS THAN 1,000 HRS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998040200433	19980402	00433	SW  	1998	4	2	98ZZZX1266       	1	19980202	G	2822		DOUBLER         			BELL  	206   	206B3       	1181506	SW  										BOOST PUMP MT	CORRODED        	B		A	ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	212LA					3957				FUEL BOOST PUMP MOUNTING FLANGE BECAME DEBONDED ALLOWING THE BOOST PUMPS TO FLEX WITH THE FUEL CELL.  REMOVAL OF THE FUE	L CELL REVEALED EXTENSIVE CORROSION OF THE ALUMINUM MOUNTING FLANGE.   SUBMITTER SUGGESTED A POSSIBLE CAUSE OF FAILURE W	AS MOISTURE TRAPPED BETWEEN THE FUEL CELL AND MOUNTING FLANGE AND POSSIBLY INSUFFICIENT ADHESIVE USED TO BOND THE FLANGE	 TO THE FUSELAGE IN THE FUEL CELL CAVITY.			1	G	7	1 	3U				H2SW
1998040200437	19980402	00437	SW  	1998	4	2	98ZZZX1270       	1	19980305	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R DRIVE	DAMAGED         	B			VE3D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	58236	748  				53069				INSPECTING HELICOPTER PER AD 97-22-15.  FOUND 2 EACH TAIL ROTOR DRIVE DISC BOLTS LOOSE AND DISC PACK BEYOND DAMAGE LIMIT	.  TT 789.0 HOURS.					1	G	7	1 	3U			O	H2SW
1998040200438	19980402	00438	SW  	1998	4	2	98ZZZX1271       	1	19980105	G	6320	206040562101	SUN GEAR        		206040004101	BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2621	3009 	2844 		BMC00180	45400				SUN GEAR AND GEARSHAFT WORN BEYOND LIMITS.  TIME SINCE INSPECTED AND REPACKED, 1,379.4 HOURS.  TT:  3,008.8 HOURS.  SUBM	ITTER STATED REPACKED 4-27-91.  GREASE OVER 6 YEARS OLD.  SUGGEST PUTTING CALENDER TIME LIMIT ON SUN GEAR INSPECTION AND	 REPACK OF 3 YEARS OR 1,500 HOURS WHICHEVER COMES FIRST.				1	G	7	1 	3U				H2SW
1998040200439	19980402	00439	GL  	1998	4	2	98ZZZX1272       	2	19980309	G	7320	68774210	CASE HALF       			HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C20      	03013	GL  					COMP MODULE	ERODED          	B			CK2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	13WD					685	CAE822169			A SLIGHT RUB WAS HEARD IN THE COMPRESSOR WHEN THE N1 WAS ROTATED.  UPON CASE HALF REMOVAL FOR INSPECTION, SEVERE VANE ER	OSION WAS FOUND.  THE CHORD OF ONE VANE WAS SO THIN AS TO CAUSE THE VANE TO BEND AND RUB ON THE COMPRESSOR ROTOR.  SUBMI	TTER SUSPECTS CASE HALF INSPECTIONS FOR OPERATION IN AN EROSIVE ENVIRONMENT WERE NOT CARRIED OUT PER THE MM.				1	G	7	1 	3U	3	U		H3WE    	E4CE
1998040200440	19980402	00440	GL  	1998	4	2	98ZZZX1273       	2	19980309	G	7230	6876655	WHEEL BLADE     			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR NR 5	MISSING         	B			CK2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	105HH		1722 			S339	CAE830493			UPON COMPRESSOR DISASSEMBLY FOR OVERHAUL, FOUND ONE BLADE MISSING FROM 5TH STAGE COMPRESSOR WHEEL.  BLADE APPEARS TO HAV	E EXITED THROUGH BLEED VALVE AS NO DOWNSTREAM DAMAGE OCCURRED.  NO IN-SERVICE DIFFICULTY WAS REPORTED.  THE COMPRESSOR W	HEEL EXHIBITS EVIDENCE OF A CORROSION PIT HALF WAY THROUGH CHORD OF BLADE AT BREAK POINT.				1	G	7	2 	3U	3	U		H3EU    	E4CE
1998041000028	19980410	00028	NM  	1998	4	10	98ZZZX1275       	1	19980223	G	5754	114N4003172	SLAT            			BOEING	757   	75728A      	1384976	NM  										RT NR 9 LE	DAMAGED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	701LF	32708	619  		A2183	24367				AFTER ARRIVAL, INSPECTION FOUND DAMAGES TO SLAT NR 9 LEADING EDGE.  AIRCRAFT WAS GROUNDED DUE TO UNAIRWORTHY CONDITION. 	 INCIDENT UNDER INVESTIGATION.					2	L	7	2 	4F			RT	A2NM
1998041000029	19980410	00029	WP  	1998	4	10	98ZZZX1276       	2	19980217	G	7200		ENGINE          			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					RT ENGINE	SEIZED          	B			N81R	A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			GL	09	108EB	5418 	1848 			BE108	P27075			RIGHT ENGINE INSTALLATION AFTER REPAIRS FOR BIRD INGESTION AND COMPLETION OF HSI.  AIRCRAFT WAS ON A FLIGHT CHECK FOR TH	E REQUIRED IN-FLIGHT NTS CHECK.  ENG WAS SHUT DOWN AND ON RESTART, SPOOLED TO ABOUT 20 PERCENT WHEN ENG SEIZED.  (SEIZUR	E APPEARS TO BE FROM INTERNAL SHAFT WARPAGE).  DURING ATTEMPTED RESTART WHEN ENG SEIZED, THE LOAD ON STARTER WENT EXCESS	IVE AND CAUSED STARTER TO OVERHEAT (LIGHT SMOKE FROM RT SIDE, NO FIRE) AND THE 325 RT BUSS CURRENT LIMITER BLEW.  THE BL	OWN CURRENT LIMITER SHUT DOWN ALL ELECTRICAL POWER TO THE RT SIDE.  A SAFE LANDING WAS MADE AND UPON LT ENGINE SHUT DOWN	, LT 325 CURRENT LIMITER BLEW.  AIRCRAFT TOWED BACK TO MAINTENANCE HANGAR.  REPORT IN C/W FAR 135.415 REQUIREMENT.	1	L	7	2 	4T	4	T		A14CE   	E4WE
1998041000030	19980410	00030	NM  	1998	4	10	98ZZZX1277       	1	19980306	G	2740	69778551	SPRING          			BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		17774								STABILIZER TRIM GEARBOX SPRINGS P/N 69-77855-1 ARE BROKEN.  SUSPECT IMPROPER HEAT TREAT OR INCORRECT ALLOY.  SUBMITTER R	ECOMMENDATIONS:  SPRINGS P/N 69-77855-1 SHOULD BE REPLACED WITH P/N 69-77855-2 SPRINGS.					2	L	7	2 	4F			RT	A16WE
1998041000031	19980410	00031	NM  	1998	4	10	98ZZZX1278       	1	19980218	G	3231	2672232	VALVE BODY      	PARKERHANFIN	2670296     	BOEING	747   	747121      	1384871	NM  										NLG DOOR SEQ	LEAKING         	B	S		IU6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01					321					NLG SEQUENCE VALVE LEAKING FROM PIN HOLE IN BODY.						2	L	7	4 	4F				A20WE
1998041000033	19980410	00033	NM  	1998	4	10	98ZZZX1280       	1	19980219	G	2730	401606223	HOUSING         		401602723   	BOEING	737   	737*        		NM  										ELEV FEEL COMP	PITTED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2108					ELEVATOR FEEL COMPUTER HAS EXCESSIVE PITTING AT SEALING, THREADED, AND INTERIOR SURFACES.						2	L	7	2 	4F			RT	A16WE
1998041000034	19980410	00034	CE  	1998	4	10	98ZZZX1281       	1	19980312	G	2750	S20832	CONTROL CABLE   			CESSNA	182   	R182        	2072734	CE  										FLAP FOLLOW-UP	SEIZED          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	6136S	9693 				R18201622				DURING EXTENSION OF WING FLAPS, THE FLAP CIRCUIT BREAKER WOULD TRIP.  INSPECTION REVEALED THE FLAP FOLLOW-UP CABLE SEIZE	D AT THE TOP END.  THIS WAS CAUSED BY THE INTERNAL CABLE CUTTING A GROOVE IN THE OUTER HOUSING FROM CONSTANT RUB DUE TO 	SLIGHT MIS-ALIGNMENT FROM FACTORY SET BRACKET FOR ATTACHING UPPER CABLE.  THE WEAR LOOKED INNOCENT, BUT IT REALLY CAUSES	 THE FLAP ACTUATOR TO WORK HARD TO OVERCOME THIS RESISTANCE.			1	H	7	1 	3O			RT	3A13
1998041000035	19980410	00035	CE  	1998	4	10	98ZZZX1282       	1	19980311	G	5753	0523920	BEARING         			CESSNA	206   	TU206F      	2073353	CE  										FLAP ROLLER	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	1002V	2952 				U20602387				AFTER FINDING A FAILURE OF FLAP BEARING THAT BOUND FLAP IN FLAP TRACK ON A 172, INSPECTION HAS BECOME PART OF ANNUAL INS	PECTIONS.  ON THIS MODEL 206, ONE BEARING WAS FOUND TO HAVE THE 'CAGE' DETERIORATED AND ONE HAD NEEDLE BEARINGS BROKEN. 	 THE ONLY METHOD OF DETECTION IS REMOVAL FROM FLAP AND REMOVING BEARING BUSHING.  SUBMITTER SUGGESTED 1,000-HOUR INSPECT	ION, CLEANING, AND REPACKING WITH GREASE.			1	H	7	1 	3O				A4CE
1998041000036	19980410	00036	SO  	1998	4	10	98ZZZX1283       	1	19980324	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	3581C	325  			1590	318052091				PILOT REPORTS TO MAINTENANCE THAT WHEN LANDING GEAR WAS SELECTED UP, UNSAFE LIGHT STAYED ON AND GEAR HANDLE WOULD NOT AU	TOMATICALLY RETURN TO THE NEUTRAL POSITION.  GEAR SELECTED DOWN.  PILOT OBSERVED THREE GREEN LIGHTS.  MAINTENANCE FOUND 	THAT RT ENGINE DRIVEN HYDRAULIC PUMP LEAKING HYDRAULIC FLUID BY SEAL AROUND DRIVE END AND FLUID COMING FROM DRAIN.  HYDR	AULIC RESERVOIR 80 PERCENT DEPLETED.  THIS PUMP INSTALLED 11-12-97, MFG BY HOWDEN FLUID SYSTEMS.			1	L	7	2 	3O				A20SO
1998041000037	19980410	00037	CE  	1998	4	10	98ZZZX1284       	1	19980323	G	2820	050042354	FUEL LINE       			CESSNA	172   	172P        	2072436	CE  										RUDDER CABLE	CUT             	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	07	66717					17275991				IMPROPERLY INSTALLED FUEL LINE RUBBING ON RUDDER CABLE CAUSING MAIN FUEL SUPPLY TO BE CUT COMPLETELY OFF.  SUBMITTER STA	TED INSTALLATION APPEARS TO BE FACTORY.					1	H	7	1 	3O			NT	3A12
1998041000038	19980410	00038	CE  	1998	4	10	98ZZZX1285       	1	19980312	G	2897	EB5	WIRE            		C6680020301 	CESSNA	150   	152         	2071835	CE  										FUEL QTY SENSOR	SHORTED         	D		A		O				OTHER                   				A			FLAME/FIRE                			NR	NOT REPORTED   	1			SW	05	25053	8490 				15280517				PILOT REPORTED FIRE ERUPTED FROM THE FUEL VENT IN-FLIGHT.  AIRCRAFT LANDED SAFELY WITH NO VISIBLE DAMAGE.  TROUBLESHOT C	AUSE TO SENDING UNIT POWER WIRE CHAFING AT LT WING ROOT RIB.  REPLACED WIRING FROM SENDING UNIT TO GAUGE.					1	H	7	1 	3O			NT	3A19
1998041000039	19980410	00039	CE  	1998	4	10	98ZZZX1286       	1	19980320	G	2410	635796	DRIVE           	PRESTOLITE  		CESSNA	337   	O2A         		CE  										ALTERNATOR	WORN            	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5151A				633	68873				C/W SB 95-3A TCM ALT/GEN DRIVE INSPECTION.  FOUND BOTH ALT ONE-PIECE DRIVES WORN.  INSIDE BORE WORN OUT OF ROUND.  WOODR	UF KEY SLOT TWICE AS WIDE AS KEY.  KEY NEARLY WORN IN TWO.  FOUND WEAR STEP AND EVIDENCE OF FATIGUE CRACKING ON BOTH SHA	FTS NEITHER SHAFT SERVICEABLE.				1	H	7	2 	3O				A6CE
1998041000040	19980410	00040	CE  	1998	4	10	98ZZZX1287       	1	19980320	G	2410	635796	DRIVE           	PRESTOLITE  		CESSNA	337   	O2A         		CE  										ALTERNATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	5151A				962	68873				C/W SB 95-3A TCM ALT/GEN DRIVE INSPECTION.  FOUND BOTH ALT ONE-PIECE DRIVES WORN.  INSIDE BORE WORN OUT OF ROUND.  WOODR	UF KEY SLOT TWICE AS WIDE AS KEY.  KEY NEARLY WORN IN TWO.  FOUND WEAR STEP AND EVIDENCE OF FATIGUE CRACKING ON BOTH SHA	FTS NEITHER SHAFT SERVICEABLE.				1	H	7	2 	3O				A6CE
1998041000041	19980410	00041	EU  	1998	4	10	98ZZZX1288       	1	19980205	G	2810		FUEL SYSTEM     			ISRAEL	1125  	ASTRASPX    	4500205	EU  										FUEL BAY	CONTAMINATED    	B			JGVR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CE	09	918MK	400  				089				CUSTOMER REPORTED FUEL BYPASS LIGHT ILLUMINATED IN-FLIGHT.  SUBMITTER STATED CAUSE WAS DETERMINED TO BE FUEL BAY CONTAMI	NATION FROM MANUFACTURER.					2	L	7	2 	4F			RT	A16NM
1998041000042	19980410	00042	EU  	1998	4	10	98ZZZX1289       	1	19980309	G	3411	257FN179	STATIC DRAIN    			BRAERO	DH125 	BAE125800A  	1500285	EU  										FUSELAGE RT FWD	CORRODED        	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	84FA					258047				STATIC DRAIN LEAK AT 24 MONTH CERTIFICATION.  COULD NOT REMOVE DRAIN RESERVOIR BODY TO CHANGE O-RING P/N 100-011-8810. R	EMOVED STATIC DRAIN PLATE AND FOUND CORROSION ON PLATE BETWEEN PLATE AND AIRCRAFT SKIN.					2	L	7	2 	4F			RT	A3EU
1998041000043	19980410	00043	EU  	1998	4	10	98ZZZX1290       	1	19980201	G	3411		DRAIN LINE      			BRAERO	DH125 	BAE125800A  	1500285	EU  										FUSELAGE	MISINSTALLED    	B	P	A	JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	84FA					258047				TWO STATIC DRAIN ASSEMBLIES HAVE BEEN COMPLETELY COVERED WITH A PRC SEALANT.  THIS IS CONTRARY TO RAYTHEON INSTALLATION 	DRAWINGS.					2	L	7	2 	4F			RT	A3EU
1998041000044	19980410	00044	CE  	1998	4	10	98ZZZX1291       	1	19980312	G	8011	PM2401	STARTER         	LAMAR       		CESSNA	182   	182S        	2072701	CE  										DRIVE	FAILED          	B			LJER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	182MA	25   			85001542	18280047				WHEN THE PILOT ATTEMPTED TO START THE AIRCRAFT, A SPINNING NOISE WAS HEARD WITH NO ENGAGEMENT.  TROUBLESHOOTING FOUND FA	ILED BENDIX DRIVE.  REMOVED STARTER AND INSTALLED NEW.  PILOT REPORTED NO UNUSUAL STARTING CHARACTERISTICS PRIOR TO THE 	FAILURE.				1	H	7	1 	3O			NT	3A13
1998041000045	19980410	00045	CE  	1998	4	10	98ZZZX1292       	1	19980213	G	3230	NAS464P426	BOLT            		504100112   	CESSNA	310   	310R        	2074245	CE  										RT MLG DOWNLOCK	SHEARED         	D		A		K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			EA	25	1545G					310R1220				DURING LANDING ROLL-OUT, GEAR HORN CAME ON, RT GEAR COLLAPSED.  FOUND DOWNLOCK BELLCRANK PIVOT BOLT HEAD SHEARED OFF AND	 DOWNLOCK ADJUSTING SCREWS BROKEN, BELLCRANK PIVOT LUGS ON TRUNNION BROKEN OFF.  DURING REPAINT AND RIGGING, NOTICED PUS	H ROD TO DOWNLOCK BELLCRANK WAS INSTALLED UPSIDE DOWN AND BINDING ON BELLCRANK WHEN IN RETRACT POSITION.  RIVET TAIL MUS	T BE UP TO PREVENT BINDING.  SUBMITTER STATED FOUND ONE OTHER ROD INSTALLED THIS WAY IN FLEET OF SEVEN 310'S.			1	L	7	2 	3O			 	3A10
1998041000046	19980410	00046	SO  	1998	4	10	98ZZZX1293       	1	19980318	G	5711	0822031	SPAR            			LUSCOM	8     	8A          	8190104	SO  										WING ROOT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2013B	3599 				6440				DURING C/W AD 96-24-17R (AMEND NR 39-10229 EFF 1-27-97), INTERGRANULAR CORROSION WAS FOUND ON THE LOWER WEB OF THE RT RE	AR SPAR AFT FACE APPROXIMATELY 17 INCHES FROM THE WING ATTACH POINT.  THE CORROSION HAD CAUSED A BULGE IN THE MATERIAL A	ND WAS APPROXIMATELY 50 PERCENT THROUGH THE THICKNESS OF THE SPAR.  THE CORROSION WAS APPROXIMATELY 3 INCHES LONG AND 1.	25 INCHES TALL.  NO OTHER CORROSION FOUND.  NO FOREIGN MATERIAL FOUND AGAINST THE SPAR.			1	H	7	1 	3O				A694
1998041000047	19980410	00047		1998	4	10	98ZZZX1294       	1	19980318	G	2434	3656624	ALTERNATOR      	CHRYSLER    																STATOR	FAILED          	B			IC2R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SW	15					49962					ALTERNATOR FAILED IN-FLIGHT. TEAR DOWN FOUND STATOR CHAFED AGAINST ROTOR DUE TO WRONG HOUSING BEING INSTALLED.
1998041000048	19980410	00048		1998	4	10	98ZZZX1295       	1	19980313	G	8120		HOUSING         																	TURBOCHARGER	DEFECTIVE       	B			RB9R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										BEARING HOUSING HAS BEEN FLAME SPRAYED.  THE DEGREE OF FLAME SPRAY WAS UNKNOWN UNTIL WELDING.  IT WAS THEN THE SEPARATIO	N STARTED OCCURRING.  THIS PART IS REJECTED FROM SERVICE.  ALUMINUM AND BRASS ARE NOT COMPATIBLE.  FLAME SPRAY REPAIRS G	REATLY SHORTEN THE LIFE OF THIS PART.  THIS IS AN UNRELIABLE REPAIR.  SUBMITTER RECOMMENDED THIS TYPE OF REPAIR ON THESE	 PARTS BE STOPPED.  THERE IS NO PREVIOUS REPAIR STATION IDENTIFIER ON THIS PART.
1998041000049	19980410	00049		1998	4	10	98ZZZX1296       	4	19980319	G	2561	KS12	LIFE VEST       	EAAEROMARINE																EMERG EQUIP	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					C17412					LIFE VEST FAILED THE MANUFACTURER'S 2 PSI TEST IAW 25-60-1.
1998041000050	19980410	00050		1998	4	10	98ZZZX1297       	4	19980310	G	2561	KSD35HCZ	LIFE VEST       	EAAEROMARINE																EMERG EQUIP	FAIL TEST       	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					FK5556					LIFE VEST FAILED THE MANUFACTURER'S 2 PSI TEST IAW 25-60-7.
1998041000051	19980410	00051		1998	4	10	98ZZZX1298       	1	19980313	G	8120		BEARING HOUSING 	ROTOMASTER  																TURBOCHARGER	DETERIORATED    	B			RB9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					600533					BEARING HOUSING HAS BEEN REPAIRED BEFORE USING A PROCESS KNOWN AS FLAME SPRAY.  THIS IS A PROCESS IN WHICH SUPERHEATED B	RASS AND THEN ALUMINUM ARE SPRAYED ON THE PART.  THIS PART IS SHOWING SIGNS OF COMPLETE SEPARATION BETWEEN THE ORIGINAL 	BASE METAL AND THE FLAME SPRAY.  IT IS UNREPAIRABLE AND REJECTED FROM SERVICE.
1998041000052	19980410	00052		1998	4	10	98ZZZX1299       	1	19980313	G	8120		BEARING HOUSING 	ROTOMASTER  																TURBOCHARGER	DETERIORATED    	B			RB9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										TURBOCHARGER VISUAL INSPECTION SHOWS A PREVIOUS REPAIR USING FLAME SPRAY.  THE ENTIRE ALIGNMENT RING IS ERODED AWAY AND 	MELTED DOWN.  THE SEAL BORE AREA IS ALSO MELTED DOWN. THIS PART IS UNREPAIRABLE AND REJECTED FROM SERVICE.  THE EROSION 	AND SEPARATION OF PIECES ON THIS PART IS ENTIRELY DUE TO FLAME SPRAY.  THIS IS AN UNRELIABLE REPAIR AND DETERMINED TO BE	 UNSAFE.
1998041000053	19980410	00053		1998	4	10	98ZZZX1300       	1	19980313	G	8120		BEARING HOUSING 	ROTOMASTER  																TURBOCHARGER	DETERIORATED    	B			RB9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										TURBOCHARGER VISUAL INSPECTION, ERODED FLAME SPRAY IS APPARENT.  THIS PART IS UNREPAIRABLE AND REJECTED FROM SERVICE.  E	ROSION OF THE FLAME SPRAY FROM THE BASE METAL HAS BEGUN.  IT HAS BEEN DETERMINED THAT COMPLETE SEPARATION OF THE FLAME S	PRAY FROM THE BASE METAL WOULD HAVE BEEN IMMINENT.
1998041000054	19980410	00054		1998	4	10	98ZZZX1301       	1	19980310	G	8120	3AV2ME60H2	TURBOCHARGER    	ROTOMASTER  																EXHAUST HOUSING	CRACKED         	B		A	IC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					221724					ON TEAR-DOWN OF TURBOCHARGER, SN 21761, OIL EVIDENCED IN THE EXHAUST HOUSING.  REMOVAL OF EXHAUST HOUSING AND CLEANING S	HOWED CRACKS IN THE VOLUTE THROAT BEYOND SERVICEABLE LIMITS.  ALSO NOTED WERE CRACKS ACROSS MOUNTING FLANGE.  TURBINE WH	EEL SHOWED DAMAGE IN BEARING JOURNALS FROM CONTAMINATION IN LUBE OIL.  TURBOCHARGER SN 221274 SHOWED CRACKS IN THE EXHAU	ST HOUSING BEYOND SERVICEABLE LIMITS AND ACROSS MOUNTING FLANGE.  TURBINE WHEEL ALSO SHOWED DAMAGE IN JOURNALS FROM META	L IN OIL.  TTSO NOT KNOWN.  THE HISTORY OF RAJAY TURBOS DEMONSTRATES A SHORT LIFE OF EXHAUST HOUSING DUE TO HEAT CRACKS 	IN THE GREY IRON CASTINGS.  THIS PROBLEM IS PREVALENT IN AEROSTAR AIRCRAFT.
1998041000055	19980410	00055		1998	4	10	98ZZZX1302       	1	19980310	G	8120	3AU2MD60H2	TURBOCHARGER    	ROTOMASTER  																EXHAUST HOUSING	CRACKED         	B			IC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					221761					ON TEAR-DOWN OF TURBOCHARGER, SN 21761, OIL EVIDENCED IN THE EXHAUST HOUSING.  REMOVAL OF EXHAUST HOUSING AND CLEANING S	HOWED CRACKS IN THE VOLUTE THROAT BEYOND SERVICEABLE LIMITS.  ALSO NOTED WERE CRACKS ACROSS MOUNTING FLANGE.  TURBINE WH	EEL SHOWED DAMAGE IN BEARING JOURNALS FROM CONTAMINATION IN LUBE OIL.  TURBOCHARGER SN 221274 SHOWED CRACKS IN THE EXHAU	ST HOUSING BEYOND SERVICEABLE LIMITS AND ACROSS MOUNTING FLANGE.  TURBINE WHEEL ALSO SHOWED DAMAGE IN JOURNALS FROM META	L IN OIL.  TTSO NOT KNOWN.  THE HISTORY OF RAJAY TURBOS DEMONSTRATES A SHORT LIFE OF EXHAUST HOUSING DUE TO HEAT CRACKS 	IN THE GREY IRON CASTINGS.  THIS PROBLEM IS PREVALENT IN AEROSTAR AIRCRAFT.
1998041000056	19980410	00056	GL  	1998	4	10	98ZZZX1303       	3	19980313	G	6111	V8433NB	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	RETAIN AREA	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01			840  		E43841			BJ1339		PROPELLER DISASSEMBLED, CLEANED, INSPECTED FOR AD COMPLIANCE.  AD 97-18-02. BLADE SN E43841, CRACKED IN RETENTION AREA. 	 FOUND WITH EDDY CURRENT, PERIODIC INSPECTION SHOULD ALWAYS BE DONE.  EDDY CURRENT INSPECTION SHOULD BE DONE AT 1,000 HO	UR INTERVALS.														5	C	P6EA
1998041000057	19980410	00057	GL  	1998	4	10	98ZZZX1304       	3	19980313	G	6111	V8433NB	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	RETAIN AREA	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01					E43823			BJ1339		PROPELLER DISASSEMBLED, CLEANED, AND INSPECTED FOR AD COMPLIANCE, AD 97-18-02.  BLADE SN E43823 CRACKED IN RETENTION ARE	A.  FOUND WITH EDDY CURRENT.  PERIODIC INSPECTIONS SHOULD ALWAYS BE DONE.  EDDY CURRENT INSPECTION SHOULD BE DONE AT 1,0	00-HOUR INTERVALS.														5	C	P6EA
1998041000058	19980410	00058	GL  	1998	4	10	98ZZZX1305       	3	19980313	G	6111	V8433NB	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	RETAIN AREA	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01			840  		E43786			BJ1339		PROPELLER DISASSEMBLED, CLEANED, AND INSPECTED FOR AD COMPLIANCE.  AD 97-18-02, BLADE SN E43786 CRACKED IN RETENTION ARE	A.  FOUND WITH EDDY CURRENT.  CORROSION ALSO FOUND IN SHOT-PEENED AREA.  PERIODIC INSPECTIONS SHOULD ALWAYS BE DONE.  ED	DY CURRENT INSPECTION SHOULD BE DONE AT 1,000 HOUR INTERVALS.														5	C	P6EA
1998041000059	19980410	00059	GL  	1998	4	10	98ZZZX1306       	3	19980313	G	6111	V8733NB	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	RETAIN AREA	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01			840  		E43821			BJ1340		PROPELLER DISASSEMBLED, CLEANED, AND INSPECTED FOR AD COMPLIANCE AD 97-18-02.   BLADE SN E43821 CRACKED IN RETENTION ARE	A.  FOUND WITH EDDY CURRENT.  PERIODIC INSPECTION SHOULD ALWAYS BE DONE.  EDDY CURRENT INSPECTION SHOULD BE DONE AT 1,00	0 HOURS.														5	C	P6EA
1998041000060	19980410	00060	GL  	1998	4	10	98ZZZX1307       	3	19980313	G	6111	V84337	BLADE           													HARTZL	HCA2V	HCA2V*      	GL  	RETAIN AREA	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01			1500 		A21004			J323		PROPELLER DISASSEMBLED, CLEANED, AND INSPECTED FOR AD COMPLIANCE AD 97-18-02.  BLADE SN A21004 CRACKED IN RETENTION AREA	.  FOUND WITH EDDY CURRENT.  CORROSION ALSO FOUND.  PERIODIC INSPECTION SHOULD ALWAYS BE DONE.  EDDY CURRENT INSPECTION 	SHOULD BE DONE AT 1,000 HOUR INTERVALS.														5	C	P24EA
1998041000061	19980410	00061	GL  	1998	4	10	98ZZZX1308       	3	19980313	G	6111	V8433NB	BLADE           													HARTZL	HCA3V	HCA3VK2     	GL  	RETAIN AREA	CRACKED         	B			RF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01			840  		E43779			BJ1340		PROPELLER DISASSEMLBED, CLEANED, AND INSPECTED FOR AD COMPLIANCE.  AD 97-18-02.  BLADE SN E43779 CRACKED IN RETENTION AR	EA.  FOUND WITH EDDY CURRENT.  PERIODIC INSPECTION SHOULD ALWAYS BE DONE.  EDDY CURRENT INSPECTION SHOULD BE DONE AT 1,0	00 HOUR INTERVALS.														5	C	P6EA
1998041000062	19980410	00062	SO  	1998	4	10	98ZZZX1309       	2	19980216	G	8530	636697	VALVE SEAT      								CONT  	O520  	GTSIO520L   	17032	SO  					CYLINDER NR 3	DEFECTIVE       	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19		5    					608715			FACTORY NEW CYLINDER REMOVED FROM THE NR 3 POSITION DUE TO LOW COMPRESSION.  UPON DISASSEMLBY, NOTED THE INTAKE VALVE SE	AT WAS NOT SEATED PROPERLY IN THE CYLINDER HEAD.  SUSPECT CAUSE:  DURING ASSEMBLY AT FACTORY, SEAT WAS NOT INSTALLED INT	O THE MACHINED PORTION OF THE CYLINDER HEAD PROPERLY.  SUBMITTER SUGGESTED A CLOSE INSPECTION OF THE INTAKE AND EXHAUST 	VALVE SEAT BE PERFORMED DURING CYLINDER ASSEMBLY.  CYLINDER MFG DATE:  12-97.								3	O			E7CE
1998041000064	19980410	00064	SO  	1998	4	10	98ZZZX1311       	1	19980319	G	3230	4178900	FORK            			PIPER 	PA31  	PA31350     	7103110	SO  										MLG LOCK ROD	BROKE           	H	S	A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			WP	07	209TA					317405211				AFTER TAKEOFF AND GEAR SELECTED UP, THE LEFT MAIN GEAR DID NOT RETRACT.  GEAR WAS SELECTED DOWN AND AIRCRAFT RETURNED TO	 AIRPORT.  INSPECTION REVEALED THE MAIN GEAR LOCK ROD FORK BROKE COMPLETELY THROUGH ON SHAFT.  SUSPECT CAUSE:   FATIGUE.	  RECOMMEND TIME CHANGE 1,000 HOURS.				1	L	7	2 	3O				A20SO
1998041000065	19980410	00065		1998	4	10	98ZZZX1312       	4	19980316	G	6113	075263717	BULKHEAD        			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	21042	401  				18261375		740201		DURING ANNUAL INSPECTION, THE SPINNER BULKHEAD WAS FOUND CRACKED AROUND 5 OF THE 6 ATTACHING POINTS.  THIS AREA IS SUPPO	RTED WITH A DOUBLER.  TWO OF THE 6 ATTACHING POINTS WERE FOUND COMPLETELY BROKEN, AND NO LONGER PROVIDING SUPPORT OF SPI	NNER.  A REVIEW OF AIRCRAFT RECORDS REVEALED TWO PREVIOUS FALURES OF THIS PART.  FAILED PART REVEALS SEVERAL ELONGATED B	OLT HOLES.  SUSPECT CAUSE, IMPROPER TORQUE OF ATTACHING HARDWARE, AND/OR POSSIBLE PROPELLER OR ENGINE VIBRATION.  THE FA	ILED PART WAS INSTALLED 12-93 WITH 400 HOURS TIS.		1	H	7	1 	3O			NT	TA13    		5	C	P3EA
1998041000066	19980410	00066	SO  	1998	4	10	98ZZZX1313       	1	19980323	G	2710	6276600	CONTROL ROD     			PIPER 	PA32  	PA32RT300T  	7103216	SO  										AILERON	BROKEN          	B		A	NUTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2148B	2335 				32R7987030				DURING ANNUAL INSPECTION, FOUND ROD END BEARINGS IN AILERON CONTROL ROD WORN.  AFTER REMOVAL, FOUND INNER ROD END ACTUAL	LY BROKEN IN THREADED AREA.  A SMALL HOLE WAS DRILLED THROUGH THE ROD ASSEMBLY ITSELF, AND THROUGH THE ROD END, AND THEN	 SECURED WITH ROLL PIN.  DEFECTIVE AREA WAS AROUND DRILLED HOLE.  TOTAL TIME ON PART WAS THE SAME AIRFRAME TOTAL TIME. I	NSPECTION OF OTHER SIDE DID NOT SHOW DISCREPANCY.  NEW PORT INSTALLED.			1	L	7	1 	3O				A3SO
1998041000067	19980410	00067	SO  	1998	4	10	98ZZZX1314       	1	19980316	G	2460		CONNECTOR       			PIPER 	PA38  	PA38112     	7103812	SO  										LT SIDEWALL PNL	CHARRED         	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			GL	09	2593P					3879A0866				'HOT WIRE' SMELL IN-FLIGHT AT NIGHT.  STALL HORN CONTINUOUSLY ON.  STROBES INOPERATIVE.  (WING TIPS).  UPON UNEVENTFUL L	ANDING, NOTICED STALL HORN BECOMES 'NORMAL' IF PITOT LT SWITCH IS TURNED ON.  CONNECTOR 2 CARRIES CIRCUITS OF NAV LIGHTS	, STROBES, PT HEAT, AND STALL WARNING.				1	L	7	1 	3O				A18SO
1998041000070	19980410	00070	CE  	1998	4	10	98ZZZX1317       	1	19980301	G	3240		BRAKES          	GERDES      		CESSNA	170   	170B        	2072306	CE  										MLG	LOCKED          	D	L			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	01	4522C					25466				THE AIRCRAFT NOSED OVER ON LANDING CAUSED BY BOTH BRAKES BEING LOCKED ON TOUCHDOWN.  PRIOR TO LANDING (SHORT FINAL) THE 	PILOT HAD TO USE FULL RUDDER DEFLECTION.  WHEN THE AIRCRAFT TOUCHED DOWN THE AIRPLANE NOSED OVER.  THE BRAKES WERE FOUND	 LOCKED, WHEN FULL RUDDER TRAVEL USED, THE LOCKPLATE CONTACTS THE FIREWALL AND LOCKS THE BRAKES.  SUBMITTER STATED THIS 	IS A KNOWN CONDITION, BUT NO AD HAS BEEN ISSUED.			1	H	7	1 	3O				A799
1998041000071	19980410	00071		1998	4	10	98ZZZX1318       	4	19980318	G	6113	453978	BULKHEAD        			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	15156					PA347350028		AU1814		AFTER A FAILURE OF PROPELLER SPINNER BULKHEAD OF A SIMILAR MODEL AIRCRAFT, INSPECTION WAS MADE WITH DYE PENETRANT.  REVE	ALED CRACKS BEGINNING AT MOUNT HOLE FOR BULKHEAD.  RECOMMEND CLOSE INSPECTION OF THESE AREAS.  ALSO, CHECK FOR CORRECT L	ENGTH OF SCREW ON SPINNER AS THE NEXT SIZE LONGER SCREW THAN IS CALLED FOR IN PARTS MANUAL COULD RESULT IN PRELOADING SP	INNER BULKHEAD ON ENGINE DAMPENER (DYNAMIC BALANCER).			1	L	7	2 	3O				A7SO    		5	C	P920
1998041000072	19980410	00072	EU  	1998	4	10	98ZZZX1319       	1	19980301	G	2820	702000	FUEL VALVE      			MUDRY 	10    	CAP10B      		EU  										FUEL SYSTEM	MALFUNCTIONED   	G	L			A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	03	80TP	785  				188				REFERENCE:  P/N 70-20-00 (91752) INVERTED FUEL VALVE WAS FOUND TO BE INTERMITTENT (HANGS UP).  DISASSEMBLY AND INSPECTIO	N FOUND A 'WEAR MARK' ON HOUSING - POSSIBLY CAUSED BY THE SHUTTLE VALVE.					1	L	7	1 	3O				A36EU
1998041000073	19980410	00073		1998	4	10	98ZZZX1320       	4	19980318	G	6113		BULKHEAD        			PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2158E							AU5870		AS THE RESULT OF SPINNER BULKHEAD FAILURES ON MODEL PA34-200, DETAIL INSPECTION WAS MADE ON THIS MODEL.  FOUND ONE BULKH	EAD CRACKING AT MOUNTING HOLE APPROXIMATELY .50 INCH LONG.  THIS MODEL DOES NOT HAVE DYNAMIC BALANCER AS MODEL PA 34-200	 DOES, WHERE LENGTH OF SPINNER SCREWS CAN HAVE ADVERSE AFFECTS ON SPINNER BULKHEAD CRACKING.  SUBMITTER RECOMMENDED DETA	ILED INSPECTION AT REGULAR SCHEDULED MAINTENANCE.			1	L	7	2 	3O				A19S0   		5	C	P920
1998041000001	19980410	00001		1998	4	10	98ZZZX1321       	4	19980310	G	6113	055023613	SPINNER         			CESSNA	172   	172P        	2072436	CE  										PROPELLER	CRACKED         	H			CE8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	5451K					17274117				DURING A 100-HOUR INSPECTION, THE SPINNER PN 0550236-13, WAS FOUND CRACKED AT THE BLADE OUTLET JUST AFT OF THE FORWARD B	ULKHEAD, PN 0550321-4.  NO OTHER DEFECTS NOTED.					1	H	7	1 	3O			NT	3A12
1998041000002	19980410	00002		1998	4	10	98ZZZX1322       	4	19980310	G	6113	055023613	SPINNER         			CESSNA	172   	172P        	2072436	CE  										PROPELLER	CRACKED         	H			CE8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	54203					17274915				DURING A 100-HOUR INSPECTION, THE SPINNER, PN 0550236-13, WAS FOUND CRACKED AT THE BLADE OUTLET JUST AFT OF THE FORWARD 	BULKHEAD, PN 0550321-4.  FURTHER INSPECTION REVEALED THE FORWARD BULKHEAD HAD SEVERAL CRACKS UNDER THE MOUNTING BOLT HEA	D WASHERS.				1	H	7	1 	3O			NT	3A12
1998041000006	19980410	00006	CE  	1998	4	10	98ZZZX1326       	1	19980303	G	5711	51221103	RIB ASSY        			CESSNA	421   	421C        	2076016	CE  										LT WS 58.94	BUCKLED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	98437	5917 				421C0040				DURING PHASE INSPECTION, RIB AT LT WS 58.94 WAS FOUND BUCKLED.  DAMAGE EXTENDED FROM 2.50 INCHES AFT OF MAIN SPAR AT TOP	 TO 7 INCHES AFT OF MAIN SPAR AT BOTTOM.  SUSPECT CAUSED BY HARD LANDING.  MANUFACTURER HAS BEEN CONTACTED FOR RECOMMEND	ATIONS.				1	L	7	2 	3O				A7CE
1998041000010	19980410	00010	CE  	1998	4	10	98ZZZX1330       	1	19980303	G	7111	NAS76A3028	BUSHING         			CESSNA	182   	182S        	2072701	CE  										COWL FLAP HANDLE	MISSING         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	9874F	60   				18280037				BUSHING P/N NAS 76A3-028 WAS OMITTED AT MANUFACTURE WHICH CAUSED DIFFICULTY OF ENGAGING COWL FLAP HANDLE STOP PIN IN THE	 VARIOUS ADJUSTMENT HOLES.  BUSHING IS LOCATED IN THE PIVOT POINT OF THE COWL FLAP HANDLE.  SUBMITTER SUGGESTED MAKING I	NSPECTION OF NEWLY MANUFACTURED 182S AIRCRAFT AND TO DETERMINE PRESENCE OR ABSENCE OF BUSHING.				1	H	7	1 	3O			NT	3A13
1998041000011	19980410	00011	CE  	1998	4	10	98ZZZX1331       	1	19980315	G	5521	053200114	RIB             			CESSNA	172   	172P        	2072436	CE  										RT STAB 3RD RIB	BUCKLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	54036	8331 				17274852				UNDER SIDE OF RIGHT STABILIZER DAMAGED AT THIRD RIB OUTBOARD OF CENTER OF STABILIZER RESULTING IN RIB BUCKLING AND ALSO 	FORWARD SPAR AT CENTER LIGHTENING HOLE BUCKLED AND CRACKED IN THE WEB.  DAMAGE POSSIBLY CAUSED BY GROUND HANDLING OF AIR	CRAFT.  DAMAGE FOUND DURING AN ANNUAL INSPECTION.				1	H	7	1 	3O			NT	3A12
1998041000012	19980410	00012	CE  	1998	4	10	98ZZZX1332       	1	19980315	G	5511	053200198	SPAR            			CESSNA	172   	172P        	2072436	CE  										HORIZ STAB	BUCKLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	54036	8331 				17274852				UNDER SIDE OF RIGHT STABILIZER DAMAGED AT THIRD RIB OUTBOARD OF CENTER OF STABILIZER RESULTING IN RIB BUCKLING AND ALSO 	FORWARD SPAR AT CENTER LIGHTENING HOLE BUCKLED AND CRACKED IN THE WEB.  DAMAGE POSSIBLY CAUSED BY GROUND HANDLING OF AIR	CRAFT.  DAMAGE FOUND DURING AN ANNUAL INSPECTION.				1	H	7	1 	3O			NT	3A12
1998041000013	19980410	00013	CE  	1998	4	10	98ZZZX1333       	1	19980320	G	5210	334200201	PIN             		33400300629 	BEECH 	33    	F33C        	1151434	CE  										CABIN DOOR	FAILED          	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	58MC	2302 				CJ143				DURING POST-FLIGHT INSPECTION, LOWER HINGE PIN ON THE QUICK RELEASE CABIN DOOR ASSY WAS NOTED OUT OF NORMAL ALIGNMENT. C	LOSE INSPECTION REVEALED THE .1875 INCH BY 1.75 INCH HINGE PIN (PN 33-420020-1) HAD FRACTURED AT THE MACHINED GROOVE IN 	THE MIDDLE OF THE PIN AND THE LOWER HALF OF THE PIN HAD FALLEN OUT OF THE HINGE ONTO THE HANGAR FLOOR.  THE UPPER HALF R	EMAINED IN THE HINGE.  THE PIN HAD FAILED IN-FLIGHT, BUT DID NOT AND COULD NOT FALL OUT IN FLIGHT DUE TO SIDE LOAD ON BO	TH HALVES.  A GROUND TEST SHOWED THE FAILED PIN DID NOT AFFECT THE DOOR RELEASE CAPABILITY.  THE PIN SHOWED NO NOTICEABL	E WEAR DESPITE BEING ORIGINAL EQUIPMENT WITH 2,301.5 HOURS OF SERVICE.	1	L	7	1 	3O				3A15
1998041000014	19980410	00014	CE  	1998	4	10	98ZZZX1334       	1	19980312	G	2721	51152071	ACTUATOR        			CESSNA	402   	402B        	207590P	CE  										RUDDER TRIM	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	60GP	12000				402B0848				DURING PRE-FLIGHT, PILOT FOUND THAT RUDDER TRIM WAS ABNORMAL.  AFTER INVESTIGATION, THE (ACTUATOR SCREW HAD BEEN BENT AN	D CRACKED ON THE LAST TREAD) THE ACTUATOR SCREW BROKE DURING REMOVAL AND WAS SHIPPED AS A CORE.  SUBMITTER STATED CAUSE 	OF FAILURE UNKNOWN, POSSIBLY DUE TO WIND?				1	L	7	2 	3O				A7CE
1998041000015	19980410	00015	SO  	1998	4	10	98ZZZX1335       	2	19980304	G	8520	6419311075	THRU BOLT       			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 6 CYL FLANGE	FAILED          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	60RR	679  				421C0885	292133R			DURING 100-HOUR INSPECTION, FOUND THE NR 6 CYLINDER TOP FORWARD STUD/THRU-BOLT BROKEN AT THE CYLINDER BASE.  TCM TECH RE	P SAYS THAT THERE HAS BEEN A PROBLEM WITH THRU-BOLTS BREAKING EVEN BEFORE THEY LEAVE THE FACTORY.  HYDROGEN EMBRITTLEMEN	T IS THE CAUSE.  SUBMITTER DOESN'T KNOW WHY THIS ONE BROKE.				1	L	7	2 	3O	3	O		A7CE    	E7CE
1998041000016	19980410	00016	SO  	1998	4	10	98ZZZX1336       	1	19980318	G	3230	1742001	TUBE ASSY       			PIPER 	PA23  	PA23250     	7102308	SO  										LT/RT MLG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	63807	3930 				277754131				INVESTIGATION FOUND AFT ATTACH BRACKET CRACKED AT BOLT HOLES ON LEFT AND RIGHT SIDES AND ON BOTH MAIN GEAR ASSEMBLIES.						1	L	7	2 	3O				1A10
1998041000017	19980410	00017	SO  	1998	4	10	98ZZZX1337       	2	19980325	G	7421	RHB32S	SPARK PLUG      	CHAMPION    		CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					ELECTRODE	DELAMINATED     	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	677PC	63   				P21000677				THE SIDE MOUNTED GROUND ELECTRODE   SHOWS SIGNS OF DELAMINATION OR END SPLITS.  PREVIOUS MDR SUBMITTED AND WRITTEN IN AL	ERT 230 SEPT 1997.					1	H	7	1 	3O	3	O		3A21    	E8CE
1998041000018	19980410	00018		1998	4	10	98ZZZX1338       	4	19980317	G	6113	453978	BULKHEAD        			PIPER 	PA34  	PA34200     	7103405	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	FAILED          	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	56187	500  				347350302		DN1629		LEFT PROPELLER SPINNER BULKHEAD FAILED RESULTING IN SPINNER DISINTEGRATION, AND LEAVING AIRCRAFT.  FLEET INSPECTION WAS 	MADE INCLUDING RT PROP BULKHEAD.  FOUND CRACKS BEGINNING AT MOUNTING HOLES FOR BULKHEAD.  AFTER CLOSE INSPECTION, FOUND 	SPINNER SCREWS WERE BOTTOMING OUT ON ENGINE DAMPENER (DYNAMIC BALANCER) RESULTING IN PRE-LOADING SPINNER BULKHEAD.  SUBM	ITTER RECOMMENDED INSPECTION FOR CORRECT SCREWS INSTALLED AND INSPECTION FOR CRACKS WITH DYE PENETRANT OR MAGNIFYING GLA	SS.		1	L	7	2 	3O				A7SO    		5	C	P920
1998041000019	19980410	00019	SO  	1998	4	10	98ZZZX1339       	1	19980317	G	5730	6706201	SKIN            			PIPER 	PA28  	PA28R200    	7102811	SO  										RT WING	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	75139	6588 				28R7635269				INSPECTION FOUND SKIN CRACKED AT BOTTOM, CENTER, RIGHT WING.  SUBMITTER STATED CAUSED BY FATIGUE.						1	L	7	1 	3O				2A13
1998041000020	19980410	00020	CE  	1998	4	10	98ZZZX1340       	1	19980301	G	3230	20410142	SUPPORT         			CESSNA	177   	177RG       	2073709	CE  										MLG ACTUATOR	FAILED          	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	7516V	2432 				177RG813				MAIN LANDING GEAR ACTUATOR SUPPORTS CRACKED.						1	H	7	1 	3O				A20CE
1998041000021	19980410	00021	CE  	1998	4	10	98ZZZX1341       	1	19980301	G	3230	20410141	SUPPORT         			CESSNA	177   	177RG       	2073709	CE  										MLG ACTUATOR	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	7516V	2432 				177RG813				MAIN LANDING GEAR ACTUATOR SUPPORTS CRACKED.						1	H	7	1 	3O				A20CE
1998041000022	19980410	00022	CE  	1998	4	10	98ZZZX1342       	1	19980303	G	5510	12326231	REINFORCEMENT   		1232600203  	CESSNA	206   	U206G       	2073356	CE  										HORZ STAB ATT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	756HK	4880 				U20604102				DURING AN ANNUAL INSPECTION ON THE HORIZONTAL STABILIZER, THE LEFT REAR REINFORCEMENT, PN 1232623-1, WAS FOUND CRACKED. 	 THIS PART IS RIVETED TO THE REAR SPAR.  A NEW P/N 1232624-1 WAS INSTALLED ON BOTH SIDES.  THE NEW PART IS RE-DESIGNED A	ND MADE OF STEEL INSTEAD OF ALUMINUM AS THE OLD PART.  THIS IS THE SECOND CRACKED LEFT REINFORCEMENT FOUND ON A 206.				1	H	7	1 	3O				A4CE
1998041000023	19980410	00023	CE  	1998	4	10	98ZZZX1343       	1	19980212	G	3397		WIRE            			CESSNA	182   	TR182       	2072735	CE  										INST POST LIGHT	SHORTED         	B			DC1R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	07	756WF	4858 				R18201177				PILOT REPORTED SMOKE IN COCKPIT.  GROUND WIRE FOR INSTRUMENT POST- LIGHTS SHORTED OUT ON WIRE LUG TO 60-AMP CIRCUIT BREA	KER FOR ALTERNATOR.  REPLACED GROUND WIRE AND RELOCATED AWAY FROM CIRCUIT BREAKER.  WIRE LUG ON 60-AMP BREAKER REPLACED.	  BOTH SYSTEMS CHECKED OKAY.  NO OTHER DAMAGE FOUND.				1	H	7	1 	3O			 	3A13
1998041000024	19980410	00024	CE  	1998	4	10	98ZZZX1344       	1	19980318	G	3242	AN62302	O-RING          			CESSNA	172   	172R        	2072401	CE  										BRAKE CALIPER	INCORRECT       	B			WIWR	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			WP	07	97100	401  				17280100				INCORRECT O-RING INSTALLED AT FACTORY.  SUBMITTER STATED THERE WAS A POSSIBILITY O-RING SWELLED CAUSING LOSS OF BRAKE PR	ESSURE.					1	H	7	1 	3O			NT	3A12
1998041000124	19980410	00124	SW  	1998	4	10	98ZZZX1347       	1	19980210	G	2550	206072903101	WIRE ROPE       			BELL  	206   	206L4       	1182110	SW  										HOOK RELEASE	FRAYED          	B	L	A	GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	108W	681  				52034				DURING 100-HOUR INSPECTION, CARGO HOOK RELEASE CABLE WAS DISCOVERED SEVERELY FRAYED ON BOTH ENDS OF CABLE INSIDE CABLE H	OUSING.  THIS CABLE WAS PREVIOUSLY REPLACED 2 YEARS AGO AND 681 HOURS ACCRUED ON THIS INSTALLATION BEFORE FAILURE.  WHEN	 PERFORMING EXTERNAL LIFTS, CABLE GETS WORKED CONTINUOUSLY AT SHARP ANGLE WEARING CABLE WITHIN HOUSING END AREAS.  SUBMI	TTER STATED A SEALED CABLE WITH GREASEABLE FITTING WOULD HELP.			1	G	7	1 	3U			NC	H2SW
1998041000125	19980410	00125	GL  	1998	4	10	98ZZZX1348       	1	19980306	G	7603	5545271067	CONTROL CABLE   			ENSTRM	F28   	F28F        	3300412	GL  										THROTTLE	BINDING         	C			PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	890JR	300  				764				THROTTLE CONTROL CABLE INTERNAL BINDING CAUSES PARTIAL TO FULL LOSS OF THROTTLE CONTROL.  UNIT IN SERVICE 20 WEEKS.						1	G	7	1 	3O			 	H1CE
1998041000126	19980410	00126	GL  	1998	4	10	98ZZZX1349       	1	19980325	G	7603	5545271067	CONTROL CABLE   			ENSTRM	F28   	F28F        	3300412	GL  										THROTTLE	BINDING         	C			PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8626S	187  				786				THROTTLE CONTROL CABLE INTERNAL BINDING CAUSES PARTIAL TO FULL LOSS OF THROTTLE CONTROL.  UNIT IN SERVICE 7 WEEKS.						1	G	7	1 	3O			 	H1CE
1998041000127	19980410	00127	GL  	1998	4	10	98ZZZX1350       	1	19980309	G	7603	5545271067	CONTROL CABLE   			ENSTRM	F28   	F28F        	3300412	GL  										THROTTLE	BINDING         	C			PP0M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8624B	603  				752				THROTTLE CONTROL CABLE INTERNAL BINDING CAUSES PARTIAL TO FULL LOSS OF THROTTLE CONTROL.  UNIT IN SERVICE 36 WEEKS.						1	G	7	1 	3O			 	H1CE
1998041000218	19980410	00218	NM  	1998	4	10	98ZZZX1362       	1	19980310	G	2910	AV16B1350	VALVE           			BOEING	727   	727224      	1384076	NM  										HYDRAULIC SOV	FAILED          	B			EB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	69739				M46850009	20667				AIRFCRAFT UNDERGOING 4B CHECK, HYDRAULIC SHUT-OFF VALVE TO NR 2 ENGINE WOULD NOT OPERATE.  WHEN NR 2 ENGINE FIRE PULL T-	HANDLE WAS PULLED, THE CIRCUIT BREAKER FOR THE HYDRAULIC SHUT-OFF VALVE TRIPPED.  TROUBLELSHOOTING REVEALED THE VALVE WA	S STUCK IN THE OPEN POSITION.  THE RED FLAG INDICATOR COULD NOT BE MOVED.  REMOVED AND REPLACED SHUT-OFF VALVE.				2	L	7	3 	4F				A3WE
1998041000219	19980410	00219	NM  	1998	4	10	98ZZZX1363       	1	19980311	G	3230	65B015648	HEAD ASSY       		65B015398   	BOEING	747   	747124      	1384874	NM  										TILT ACTUATOR	PITTED          	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					FT72688					MAIN LANDING GEAR TILT ACTUATOR BEYOND REPAIRABLE LIMITS DUE TO PITTING ON HEAD ASSY.						2	L	7	4 	4F				A20WE
1998041000220	19980410	00220	NM  	1998	4	10	98ZZZX1364       	1	19980311	G	3230	65B015661	BEARING         		65B015398   	BOEING	747   	747124      	1384874	NM  										TILT ACTUATOR	PITTED          	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					FT72688					MAIN LANDING GEAR TILT ACTUATOR BEYOND REPAIRABLE LIMITS.   PITTING ON END BEARING.						2	L	7	4 	4F				A20WE
1998041000221	19980410	00221	NM  	1998	4	10	98ZZZX1365       	1	19980319	G	3230	654458211	HOUSING ASSY    		65445815    	BOEING	737   	737201      	1384454	NM  										HYD MOD PACK	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			39951		1137					HYDRAULIC MODULE PACK HOUSING WALL BETWEEN TWO SHUT-OFF VALVES CRACKED.  HOUSING CRACKED DURING NORMAL OPERATION.  SUBMI	TTER STATED THIS IS A RECURRING PROBLEM AND RECOMMENDED A STRONGER HOUSING BE MANUFACTURED AS A REPLACEMENT.					2	L	7	2 	4F				A16WE
1998041000222	19980410	00222	NM  	1998	4	10	98ZZZX1366       	1	19980309	G	3251	651796120	BARREL ASSY     		651781411   	BOEING	727   	727232      	1384082	NM  										NLG STEERING	PITTED          	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					M1542					NOSE LANDING GEAR STEERING ACTUATOR BEYOND REWORK LIMITS DUE TO HEAVY PITTING.						2	L	7	3 	4F				A3WE
1998041000223	19980410	00223	NM  	1998	4	10	98ZZZX1367       	1	19980309	G	3251	651796120	BARREL ASSY     		651781411   	BOEING	727   	727232      	1384082	NM  										NLG STEERING	PITTED          	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					529					NOSE LANDING GEAR STEERING ACTUATOR BEYOND REWORK LIMITS DUE TO HEAVY PITTING.						2	L	7	3 	4F				A3WE
1998041000224	19980410	00224	NM  	1998	4	10	98ZZZX1368       	1	19980309	G	3251	651796120	BARREL ASSY     		671781411   	BOEING	727   	727232      	1384082	NM  										NLG STEERING	PITTED          	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					0253					NOSE LANDING GEAR STEERING ACTUATOR BEYOND REWORK LIMITS DUE TO HEAVY PITTING.						2	L	7	3 	4F				A3WE
1998041000225	19980410	00225	CE  	1998	4	10	98ZZZX1369       	1	19980223	G	5512	50600001617	SKIN            			BEECH 	90    	C90         	1152913	CE  										LT HOR STAB LE	CRACKED         	B	S		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	601SC	8564 				LJ753				DURING PHASE 1 AND 2 INSPECTIONS FOUND 2 CRACKS APPROXIMATELY 1 INCH LONG EMANATING FROM LT HORIZONTAL STABILIZER INBOAR	D LEADING EDGE RIVETS.					1	L	7	2 	3T				3A20
1998041000226	19980410	00226	SW  	1998	4	10	98ZZZX1370       	1	19980320	G	2750	51003357	PULLEY BRACKET  			GULSTM	690TP 	690B        	7630516	SW  										FLAP MASTER	CRACKED         	B			FJTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	711PB	5140 				11356				DURING 100-HOUR MANUFACTURER'S INSPECTION, FOUND LEFT INBOARD FLAP MASTER PULLEY  BRACKET CRACKED ON INBOARD SIDE.  BRAC	KET IS ACCESSIBLE THROUGH AFT BAGGAGE COMPARTMENT.					1	H	7	2 	3T				2A4
1998041000227	19980410	00227	CE  	1998	4	10	98ZZZX1371       	1	19980309	G	2750	MSZ4166D1	RELAY           			MTSBSI	MU2   	MU2B36A     	5780413	CE  										FLAP DOWN	FAILED          	B		A	IZ2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	777LP	7095 				719SA				PILOT SELECTED FLAPS DOWN 20 DEGREES FOR TAKEOFF.  FLAPS WENT PAST 20 DEGREE POSITION, PAST 40 DEGREE DOWN POSITION, AND	 STOPPED AT THE MECHANICAL STOP.  INVESTIGATION REVEALED FLAP DOWN RELAY FAILED ALLOWING CONTACTS TO TOUCH AT ALL TIMES.	  RELAY REPLACED TO CORRECT PROBLEM AND FLAPS RIGGED.				1	H	7	2 	3T				A10SW
1998041000230	19980410	00230	CE  	1998	4	10	98ZZZX1374       	1	19980225	G	3260	3080070843004	INDICATOR       			BEECH 	B300  	B300        	1159232	CE  										RT MLG	FAILED          	D				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			SO	13	350S	2584 				FL9				RIGHT MAIN GEAR DID NOT INDICATE DOWN AND LOCKED.  PILOT COULD NOT GET INDICATOR OUT OF PANEL TO CHECK FOR BURNED OUT BU	LB.  AN UNEVENTFUL LANDING WAS PERFORMED.  WHEN MAINTENANCE REMOVED THE INDICATOR, ONE LOCKING TAB FELL OUT.  IT APPEARS	 AS IF THE LOCKING TAB HAD THE INDICATOR JAMMED.  THE INDICATOR ASSEMBLY WAS REPLACED AND NO OTHER PROBLEMS HAVE BEEN SE	EN.			2	L	7	2 	4T			RT	A24CE
1998041000231	19980410	00231	NM  	1998	4	10	98ZZZX1375       	1	19980318	G	5330		SKIN            			BOEING	737   	737275      	1384485	NM  										BS 300, STR 24L	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CGWJE	51200				20588				CRACKS IN FUSELAGE SKIN AT STA 300, STR 24L.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-202 DATED 2-12-98, AND 737 	SRM 53-30-3, FIG 42.  REF:  FAA FORM 8110-3 DATED 2-23-98.					2	L	7	2 	4F				A16WE
1998041000232	19980410	00232	NM  	1998	4	10	98ZZZX1376       	1	19980318	G	5330		SKIN            			BOEING	737   	737275      	1384485	NM  										BS 272, STR 19L	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CGWJE	51200				20588				THE LOWER FUSELAGE WAS CRACKED AT STA 272, STR 19L.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-203 REV 1, DATED 2-2	4-98, AND 737 SRM 53-30-3, FIG 42.  REF:  FAA FORM 8110-3 DATED 2-25-98.					2	L	7	2 	4F				A16WE
1998041000233	19980410	00233	NM  	1998	4	10	98ZZZX1377       	1	19980318	G	5330		SKIN            			BOEING	737   	737275      	1384485	NM  										BS 992 TO 1016	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CGWJE	51200				20588				CRACKS WERE FOUND IN THE FUSELAGE SKIN LAP LOWER ROW BETWEEN STA 992 AND STA 1016, STR 14R.  REPAIRED PER DALFORT AEROSP	ACE, L.P. XEA X2-53-208 REV 1, DATED 3-6-98, AND 737 SRM 53-30-3, FIG 42.  REF:  FAA FORM 8110-3 DATED 3-12-98.					2	L	7	2 	4F				A16WE
1998041000234	19980410	00234	NM  	1998	4	10	98ZZZX1378       	1	19980318	G	5330		SKIN            			BOEING	737   	737275      	1384485	NM  										BS 927 TO 951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CGWJE	51200				20588				FUSELAGE SKIN IS CRACKED AROUND SEVERAL FASTENER HOLES IN THE LAP JOINT LOWER ROW AT STR 14R FROM STA 927 TO STA 951.  R	EPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-211 REV 1, DATED 3-16-98, AND BOEING SRM 53-30-3, FIG 42.  REF:  FAA FORM 	8110-3 DATED 3-11-98.				2	L	7	2 	4F				A16WE
1998041000235	19980410	00235	NM  	1998	4	10	98ZZZX1379       	1	19980318	G	5330		SKIN            			BOEING	737   	737275      	1384485	NM  										BS 1016, STR 4L	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CGWJE	51200				20588				NUMEROUS FASTENER HOLES CRACKED IN FUSELAGE SKIN, STA 1016, STR 4L.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-212 	REV 1, DATED 3-20-98, AND SRM 53-30-3, FIG 42.  REF:  FAA FORM 8110-3 DATED 3-20-98.					2	L	7	2 	4F				A16WE
1998041000236	19980410	00236	NM  	1998	4	10	98ZZZX1380       	1	19980318	G	5330		SKIN            			BOEING	737   	737275      	1384485	NM  										BUTT JOINT 1016	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	CGWJE	51200				20588				FUSELAGE SKIN CRACKED AT THE FOLLOWING LOCATIONS, BUTT JOINT 1016 STR 14L AND STR 10R.  REPAIRED PER DALFORT AEROSPACE, 	L.P. XEA X2-53-204 DATED 2-18-98, AND 737 SRM 53-30-3, FIG 42.  REF:  FAA FORM 8110-3 DATED 2-25-98.					2	L	7	2 	4F				A16WE
1998041000237	19980410	00237	WP  	1998	4	10	98ZZZX1381       	1	19980323	G	3251	3766640502	END BARREL      		37666395508 	DOUG  	DC8   	DC863       	302198A	WP  										STEERING CYL	CRACKED         	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					EB0003					END BARREL (CAP) HAS TWO LARGE CRACKS (APPROXIMATELY 1.50 INCH LONG) PER INDICATOR TO THREADS.  CRACKS ARE 180 DEGREES F	ROM EACH OTHER.  END BARREL WAS MANUFACTURED BY AV-MAT FAA-PMA PART.					2	L	7	4 	4F				4A25
1998041000238	19980410	00238	CE  	1998	4	10	98ZZZX1382       	1	19980311	G	2612	1179100531	STAND-OFF       			BEECH 	200   	B200        	1152922	CE  										LT/RT ENG DET	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	909J	249  				BB1579				STAND-OFF FOR FIRE PROTECTION SENSOR FOUND BROKEN ON RT AND LT ENGINES.  STAND-OFF IS BOLTED TO EXHAUST STACK FLANGE BOL	T AND ADEL CLAMP FOR SENSOR.					1	L	7	2 	4T				A24CE
1998041000239	19980410	00239	CE  	1998	4	10	98ZZZX1383       	1	19980324	G	3710	LW12540	ADAPTER         	ARO         	A505CDD     	BEECH 	80    	65B80       	1152812	CE  										AIR PUMP	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	138BA	763  			13660	LD361				WHILE INVESTIGATING AN OIL LEAK ON THE RT ENGINE, DID A DYE PENETRANT INSPECTION OF THE AIR PUMP ADAPTER, AND FOUND IT C	RACKED IN THE AREA OF THE FLANGE THAT MATES WITH THE ENGINE ACCESSORY CASE.  SUBMITTER STATED THEY FIND THIS A COMMON DE	FECT IN FLEET OF 17 QUEEN AIR WITH AT LEAST 8 OCCURRENCES A YEAR USUALLY AROUND THE AREA OF THE ATTACHMENT POINT HOLES O	F THE FLANGE.			1	L	7	2 	3O				3A20
1998041000240	19980410	00240	CE  	1998	4	10	98ZZZX1384       	1	19980320	G	3243	3321211	PISTON ROD      	BENDIX      	33212001    	BEECH 	60    	60          	1153602	CE  										NR 1 PWR BRAKE	FAILED          	B			NVIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	205FX	3136 			9020651	005				AFTER REPLACING WHEEL BRAKE ASSEMBLIES, WENT TO BLEED BRAKE SYSTEM.  NO BRAKE RESPONSE ON PILOT'S LEFT BRAKE.  TROUBLESH	OT TO POWER BRAKE VALVE.  FOUND PISTON ROD BROKEN AND LODGED IN OPERATING LINKAGE.  THE PILOT HAD NOT REPORTED A PROBLEM	 WITH THE BRAKE SYSTEM.  REPLACED POWER BRAKE VALVE WITH NEW PART, BLED SYSTEM, OPERATIONAL CHECKS GOOD.				1	L	7	2 	3O				A12CE
1998041000241	19980410	00241	SO  	1998	4	10	98ZZZX1385       	1	19980319	G	5320	12003029001	LATERAL POST    			EMB   	120   	EMB120RT    		SO  										LT WINDOW	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	217AS					120011				WHILE PERFORMING ATLANTIC SOUTHEAST AIRLINES WORK CONTROL CARD TASK NR 472566, (EO 53-0047 REV A - INSP OF WINDSHIELD/DV	 WINDOW IAW SB 120-53-0010) NUMEROUS CRACKS WERE FOUND IN LT AND RT SKINS AT FWD BOTTOM OF FLT COMPARTMENT SIDE WINDOW O	PENINGS UNDER DOUBLERS (P/N'S 120-36463-005/120-36463-006) WHICH HAD BEEN INCORPORATED UNDER SB 120-53-0010.  ALSO, INDI	CATION OF CRACKS WERE FOUND ON LT AND RT LATERAL POSTS (P/N'S 120-03029-001/120-03029-002).			2	L	7	2 	4T			RT	A31SO
1998041000242	19980410	00242	SO  	1998	4	10	98ZZZX1386       	1	19980319	G	5320	12003029002	LATERAL POST    			EMB   	120   	EMB120RT    		SO  										RT WINDOW	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	217AS					120011				WHILE PERFORMING ATLANTIC SOUTHEAST AIRLINES WORK CONTROL CARD TASK NR 472566, (EO 53-0047 REV A - INSP OF WINDSHIELD/DV	 WINDOW IAW SB 120-53-0010) NUMEROUS CRACKS WERE FOUND IN LT AND RT SKINS AT FWD BOTTOM OF FLT COMPARTMENT SIDE WINDOW O	PENINGS UNDER DOUBLERS (P/N'S 120-36463-005/120-36463-006) WHICH HAD BEEN INCORPORATED UNDER SB 120-53-0010.  ALSO, INDI	CATION OF CRACKS WERE FOUND ON LT AND RT LATERAL POSTS (P/N'S 120-03029-001/120-03029-002).			2	L	7	2 	4T			RT	A31SO
1998041000243	19980410	00243	NM  	1998	4	10	98ZZZX1387       	1	19980304	G	2432	12337028100	CELL            		TX40112     	ISRAEL	1125  	1125        		NM  										BATTERY	FAILED          	B	P		JGVR	K				NONE                    				M			OVER TEMP                 			NR	NOT REPORTED   	1			CE	09	232S				7D	032				NICAD BATTERY CELL HAD THERMAL RUNAWAY.						2	L	7	2 	4F			RT	A16NM
1998041000244	19980410	00244	SO  	1998	4	10	98ZZZX1388       	1	19980301	G	5720		RISER           			GULSTM	G159  	G159        	3952202	SO  										WING PLANK	CORRODED        	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2FOR					119				GULFSTREAM CUSTOMER BULLETIN NR CB 337 REQUIRES X-RAY INSPECTION OF INBOARD LOWER PLANK SPLICES AND ULTRASONIC INSPECTIO	N OF THE ADJACENT RISERS.  SUBSEQUENT DISASSEMBLY FOR REPAIRS REVEALED EXTENSIVE CORROSION IN SPLICES AND RISERS NOT DET	ECTABLE BY THE SPECIFIED TECHNIQUES.  N-NR YV28CP.				2	L	7	2 	4T				1A17
1998041000245	19980410	00245	WP  	1998	4	10	98ZZZX1389       	1	19980306	G	5512	369A3600603	SKIN            			HUGHES	369   	OH6A        		WP  										HORIZ STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6186U	2558 				6916048				DURING INSPECTION, A 1 INCH CRACK WAS FOUND ON TOP OF THE HORIZONTAL STABILIZER.  ALSO, A .25 INCH CRACK WAS FOUND SAME 	AREA, BUT ON BOTTOM SIDE OF HORIZONTAL STABILIZER.  THE PART WAS REMOVED FROM SERVICE.					1	G	7	1 	3U				H3WE
1998041000246	19980410	00246	WP  	1998	4	10	98ZZZX1390       	1	19980306	G	5512	369A3600603	SKIN            			HUGHES	369   	OH6A        		WP  										HORIZ STABILIZER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	5185N	2003 				6817341				DURING AN INSPECTION, A 4 INCH CRACK WAS FOUND ON TOP OF HORIZONTAL STABILIZER INBOARD OF THE HORIZONTAL SUPPPORT BRACKE	T.  THE SKIN OF THE HORIZONTAL STABILIZER WAS REMOVED AND FOUND THE HORIZONTAL STABILIZER SPAR WAS CRACKED ALL THE WAY T	HROUGH.				1	G	7	1 	3U				H3WE
1998041000252	19980410	00252	SW  	1998	4	10	98ZZZX1396       	1	19980116	G	2436	51539005A	GCU             			KAMAN 	K1200 	K1200       	05625F6	SW  										DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	743  			94639	940019				PILOT REPORTED GENENRATOR WILL NOT COME ON-LINE.  REPLACED GENERATOR CONTROL UNIT.  OPERATIONS NORMAL.						1	G	7	1 	4F			NT	TR7BO
1998041000254	19980410	00254	SW  	1998	4	10	98ZZZX1398       	1	19980129	G	7160	K983149001A	CONTROL VALVE   			KAMAN 	K1200 	K1200       	05625F6	SW  										PARTICAL SEP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	1090 			0077	940019				PARTICAL SEPARATOR PURGE VALVE INOPERABLE.  INSTALLED NEW VALVE.						1	G	7	1 	4F			NT	TR7BO
1998041500009	19980415	00009	SW  	1998	4	15	98ZZZX1408       	1	19980114	G	6710	K982100001	LIMITER         			KAMAN 	K1200 	K1200       	05625F6	SW  										COLLECTIVE CRANK	BINDING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	1385 				940019				PILOT REPORTED COLLECTIVE LIMITER BINDING HARD TO MOVE UP OR DOWN:  12 EACH LIMITERS WERE INSTALLED.  AFTER EACH INSTALL	, AIRCRAFT OPERATIONS REPORTED NORMAL.  12-10-97:  COLLECTIVE LIMITER INPUT CRANK FOUND TO HAVE INTERMITTENT BINDING ON 	COLLECTIVE SHAFT AT DISASSEMBLY.  CORROSION FOUND ON SHAFT (STEEL) OUTSIDE DIAMETER AND CRANK (ALUMINUM) 1.0.  AT EACH L	IMITER CHANGE, THE BINDING OF THE CRANK TO THE SHAFT WAS LOOSENED AND OPERATIONS WERE NORMAL FOR A RANGE OF OPERATING HO	URS FROM 34.6 TO 261.4 HOURS.  NO PART NUMBERS ARE LISTED FOR THE CRANK OR SHAFT.  RECOMMEND A MIL SPEC CORROSION INHIBI	TOR AND LUBRICANT BE APPLIED TO THE COLLECTIVE CRANK AND SHAFT.	1	G	7	1 	4F			NT	TR7BO
1998041000265	19980410	00265	SW  	1998	4	10	98ZZZX1410       	1	19980115	G	6210	K915101004	BLADE           			KAMAN 	K1200 	K1200       	05625F6	SW  										M/R	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	473  			64A	940019				NORMAL INSPECTION OF MAIN ROTOR BLADES FOUND DELAMINATED LOWER SURFACE INBOARD AT TIP.  NO BLADE STRIKE.						1	G	7	1 	4F			NT	TR7BO
1998041000266	19980410	00266	SW  	1998	4	10	98ZZZX1411       	1	19980115	G	6210	K915101004	BLADE           			KAMAN 	K1200 	K1200       	05625F6	SW  										M/R	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	313KA	642  			64B	940019				NORMAL INSPECTION OF MAIN ROTOR BLADES FOUND DELAMINATED LOWER SURFACE INBOARD AT TIP.  NO BLADE STRIKE.						1	G	7	1 	4F			NT	TR7BO
1998041000273	19980410	00273	CE  	1998	4	10	98ZZZX1418       	1	19980326	G	6120	10594000011	PROP LEVER      			BEECH 	76    	76          	1153005	CE  										INST PNL BRACE	JAMMED          	B	L	A	BF8R	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			WP	07	3812C					ME390				LEFT PROPELLER WAS FEATHERED IN-FLIGHT FOR TRAINING.  UNABLE TO INITIALLY GET PROPELLER LEVER BACK FORWARD.  FINALLY, WH	EN LEVER BROKE LOOSE, A LOUD SNAP WAS HEARD.  PROPELLER CAME OUT OF FEATHER.  LANDING WAS UNEVENTFUL.  UPON INVESTIGATIO	N, FOUND BOTH PROP LEVERS COULD RIDE UP AND OVER FEATHER DETENT SPRING.  FOUND THE INSTRUMENT PANEL CROSS-BRACE ASSEMBLY	 THE DETENT SPRING ATTACHES TO DEFORMED.  THIS CONDITION ALLOWED THE SPRING POSITION TO CHANGE AND THE PROP LEVERS TO RI	DE UP AND OVER THE SPRING AND JAM IN FEATHER.  TO MAKE SURE THIS WILL NOT OCCUR, SPECIAL ATTENTION SHOULD BE GIVEN DURIN	G ROUTINE INSPECTIONS.	1	L	7	2 	3O				A29CE
1998041000775	19980410	00775	SW  	1998	4	10	98ZZZX1421       	1	19980317	G	6420	206011809109	PITCH HORN      			BELL  	206   	206L1       	1182107	SW  										T/R BLADE	LOOSE           	B		A	LCF2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	600CK					45787				TAIL ROTOR PITCH HORNS TO BLADE ATTACHMENT BOLTS FOUND LOOSE ON POST-FLIGHT WALK AROUND OF HELICOPTER.  SUBMITTER SUGGES	TED PRO SEAL SQUEEZE OUT CAUSING LOSS OF TORQUE ON ATTACHMENT BOLTS.					1	G	7	1 	3U				H2SW
1998041000787	19980410	00787	SW  	1998	4	10	98ZZZX1426       	1	19980107	G	7810	206061300027	EXHAUST STACK   			BELL  	206   	206B        	1181511	SW  										LT EXHAUST	CRACKED         	H			A05L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206TH	49   				4217				DURING A POST-FLIGHT INSPECTION, FOUND LT EXHAUST STACK CRACKED ALONG ENTIRE LENGTH OF TOP WELD SEAM.  REMOVED AND REPLA	CED WITH SERVICEABLE ASSY.					1	G	7	1 	3U				H2SW
1998041000788	19980410	00788	SW  	1998	4	10	98ZZZX1427       	1	19980107	G	6240	222375077119	TRANSMITTER     			BELL  	407   	407         		SW  										ROTOR TORQUE	ERRATIC         	H			A05L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AA	259  			57292184	53167				TORQUE INDICATOR READINGS ERRATIC.  TROUBLESHOT SYSTEM, REPLACED TORQUE TRANSMITTER WITH NEW ASSY, FUNCTIONAL CHECK OK.						1	G	7	1 	3U			O	H2SW
1998041000912	19980410	00912	SW  	1998	4	10	98ZZZX1433       	1	19980318	G	7722	2060751907	INDICATOR       			BELL  	206   	206B        	1181511	SW  										ENGINE TOT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322		1    			1736				TOT INDICATOR OFF FLAG STAYS ON CONTINUOUSLY.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1998041000913	19980410	00913	SW  	1998	4	10	98ZZZX1434       	1	19980325	G	2910	70053H00A100	HOSE            			BELL  	206   	206L3       	1182108	SW  										HYDRAULIC SYSTEM	RUPTURED        	H		A	UWBL	O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			NM	07	937S	4097 				51258				HYDRAULIC HOSE RUPTURED DURING FLIGHT RESULTING IN TOTAL LOSS OF HYDRAULICS.  PILOT LANDED WITHOUT INCIDENCE.  TECHNICAL	 BULLETIN TB206L-97-193 WHICH INCORPORATES A LONGER HOSE TO PREVENT THIS OCCURRENCE HAD NOT YET BEEN ACCOMPLISHED.  NEW 	HOSE P/N 70-061H000T134A HAS BEEN INSTALLED IAW THE BULLETIN.  SUBMITTER SUGGESTED THIS LONGER HOSE BE INSTALLED BY ANYO	NE HAVING THE OLDER SHORTER HOSES TO PREVENT THIS OCCURRENCE.			1	G	7	1 	3U				H2SW
1998041000914	19980410	00914	EU  	1998	4	10	98ZZZX1435       	1	19980317	G	3397		WIRE            			BRAERO	1000  	HAWKER1000  	7450005	EU  										RT LANDING LIGHT	CHAFED          	B		A	DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	552QS	632  				259052				RIGHT LANDING LIGHT INOPERABLE.  FOUND WIRE BUNDLE CHAFING AGAINST FORWARD VENTRAL TANK TRANSFER VALVE ASSEMBLY.  LOCATI	ON IS BETWEEN WIRE BUNGEE 'DF' AND CONNECTOR 'JA-D9'.  UPON REMOVAL OF FORWARD VENTRAL TANK, THE WIRING FOR THE FUEL QUA	NTITY SYSTEM OF THE FORWARD VENTRAL TANK WAS ALSO FOUND CHAFING.  THIS IS THE FIRST KNOWN INCIDENT.				2	L	7	2 	4F			RT	A3EU
1998041000915	19980410	00915	SW  	1998	4	10	98ZZZX1436       	1	19980301	G	6310	206040106001	SPRING          			BELL  	206   	206L1       	1182107	SW  										M/R DRIVE	MISMANUFACTURED 	H		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07										CUSTOMER STATED THE SPRINGS SUBMITTER SUPPLIED WERE 'TOO SHORT'.  THE SPRING HAD BEEN PURCHASED NEW FROM BELL HELICOPTER	S IN FEBRUARY, 1998, AND SHIPPED TO THE CUSTOMER.  SUBMITTER INSPECTED TWO SPRINGS THAT WERE IN STOCK AND FOUND THE SPRI	NGS TO MEASURE 1.838 INCH AND 1.850 INCH, BELOW THE SPECIFIED HEIGHT OF 1.900 PLUS OR MINUS 0.020 INCH PER THE BHT1 206B	 SERIES CR&O, PARA 63-4-22 AND 1.900 INCH PLUS OR MINUS 0.010 INCH PER 206L SERIES CR&O, PARA 63-122-7.  THIS HAS BEEN R	EPORTED TO BELL HELICOPTERS.		1	G	7	1 	3U				H2SW
1998041000916	19980410	00916	SW  	1998	4	10	98ZZZX1437       	1	19980327	G	5302	206030446001F	D RING          		206031044011	BELL  	206   	206B        	1181511	SW  										TAILBOOM	CRACKED         	B		A	RJNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	206BB	6166 			NNJN0662	112				DURING ANNUAL INSPECTION, A CRACK WAS FOUND IN THE T/R GEARBOX SUPPORT D-RING.  THE CRACK ORIGINATED FROM THE LT AFT HOL	E FOR THE TAIL ROTOR GEARBOX MOUNTING STUD AND PROPAGATED FWD TO THE EDGE OF THE D-RING.  THERE WERE NO OTHER DEFECTS NO	TED OF THE PART OF ASSY.  THE TORQUES OF THE GEARBOX MOUNTING STUD NUTS ARE CHECKED EVERY 100 HRS AND NO DEFECTS NOTED H	ERE EITHER.  TAIL ROTOR VIBRATION WAS RULED OUT AS A CAUSE OF THE CRACK, THE LAST MEASURED IPS LEVEL APPROX 200 HRS PREV	IOUSLY WAS .07 IPS.  (.2 IPS IS BELL'S MAX ALLOWABLE).  THE CRACK MAY HAVE FORMED FROM FATIGUE.		1	G	7	1 	3U				H2SW
1998041700086	19980417	00086	EU  	1998	4	17	98ZZZX1438       	1	19980310	G	2435	03601018	BEARING         	LUCAS       	23080005    	BRAERO	DH125 	BAE125800A  	1500285	EU  										START/GENERATOR	FAILED          	B		A	KC2R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	03	621MT		800  		2763	258036				OPERATOR NOTICED VIBRATION ON ENGINE.  STARTER/GENERATOR WAS REMOVED AND INSPECTED. THERE WAS ENOUGH SIDE MOVEMENT OF AR	MATURE THAT THE FAN BLADES RUBBED INSIDE OF COVER.  DISASSEMBLED UNIT AND FOUND BOTH BEARINGS HAD FAILED.  DISASSEMBLED 	END BEARING AND FOUND BALL RETAINER RIVETS HAD SHEARED AND ALLOWED BALLS TO MOVE RANDOMLY ALLOWING ARMATURE TO MOVE OFF 	CENTER.			2	L	7	2 	4F			RT	A3EU
1998041700087	19980417	00087	EU  	1998	4	17	98ZZZX1439       	1	19980301	G	2730	B178008	PULLEY          			BRAERO	1000  	HAWKER1000  		EU  										ELEV CABLE	BINDING         	B		A	DXTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	546QS					259046				CONTROL COLUMN IS STIFF IN MOVEMENT FORE AND AFT.  FOUND ELEVATOR CABLE PULLEY UNDER CHART CASE FLOOR (P/N F46) RUBBING 	FORWARD STATIC LINE.  REPOSITIONED LINE.					2	L	7	2 	4F			RT	A3EU
1998041700088	19980417	00088	WP  	1998	4	17	98ZZZX1440       	1	19980331	G	5553	4918093506	FITTING         			DOUG  	DC9   	DC931       	3022065	WP  										V STAB TIE	CRACKED         	B			JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	969ML	72110				47268				AIRCRAFT UNDERGOING A C-CHECK INSPECTION.  THE VERTICAL TIE FITTING ATTACHING THE VERTICAL STABILIZER TO THE FUSELAGE WA	S FOUND CRACKED IN HALF.					2	L	7	2 	4F				A6WE
1998041700089	19980417	00089	WP  	1998	4	17	98ZZZX1441       	1	19980331	G	5320	9919619503N	SUPPORT         			DOUG  	DC9   	DC931       	3022065	WP  										BS 737 LT	CRACKED         	B			JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	969ML	72110				47268				AIRCRAFT UNDERGOING A C-CHECK INSPECTION.  THE FRAME AT STA 737 WAS FOUND CRACKED IN THE LOWER POCKET OF THE FITTING.						2	L	7	2 	4F				A6WE
1998041700090	19980417	00090	WP  	1998	4	17	98ZZZX1442       	1	19980331	G	5320	9919619502N	SUPPORT         			DOUG  	DC9   	DC931       	3022065	WP  										BS 699 RT	CRACKED         	B			JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	969ML	72110				47268				AIRCRAFT UNDERGOING A C-CHECK INSPECTION.  THE FRAME AT STA 699 RT SIDE OF FUSELAGE WAS FOUND CRACKED IN THE LOWER POCKE	T OF THE FITTING.					2	L	7	2 	4F				A6WE
1998041700091	19980417	00091	WP  	1998	4	17	98ZZZX1443       	1	19980331	G	5320	9919619504N	SUPPORT         			DOUG  	DC9   	DC931       	3022065	WP  										BS 737 RT	CRACKED         	B			JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	969ML	72110				47268				AIRCRAFT UNDERGOING A C-CHECK INSPECTION.  THE FRAME AT STA 737 RT SIDE WAS FOUND CRACKED IN THE LOWER POCKET OF THE FIT	TING.					2	L	7	2 	4F				A6WE
1998041700092	19980417	00092	NM  	1998	4	17	98ZZZX1444       	1	19980331	G	5320	65C232312AA	FITTING         			BOEING	727   	72723       	1384004	NM  										BS 870 RT	CORRODED        	B			JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	992AJ	58776				19428				AIRCRAFT UNDERGOING A C-CHECK INSPECTION.  THE RT WING TERMINAL FITTING STA 870 WAS FOUND CORRODED BEYOND SRM LIMITATION	S.					2	L	7	3 	4F				A3WE
1998041700093	19980417	00093	NM  	1998	4	17	98ZZZX1445       	1	19980331	G	5320	65C812631	FITTING         			BOEING	727   	72723       	1384004	NM  										BS 870 RT	CORRODED        	B			JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	992AJ	58776				19428				AIRCRAFT UNDERGOING A C-CHECK INSPECTION.  THE RT WING TERMINAL FITTING STA 870 WAS FOUND CORRODED BEYOND SRM LIMITATION	S.					2	L	7	3 	4F				A3WE
1998041700094	19980417	00094	NM  	1998	4	17	98ZZZX1446       	1	19980325	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 938 STR 10R	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	57SW	61376				21722				THE FUSELAGE SKIN FOUND CRACKED IN THE SKIN LAP LOWER ROW AT STA 938, STR 10R, AT SEVERAL FASTENER HOLES.  THIS REPAIR I	S ADJACENT TO THE AFT GALLEY DOOR UPPER HINGE CUT OUT.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-213 DATED 3-17-98	.  REF:  FAA FORM 8110-3 DATED MARCH 24, 1998.				2	L	7	2 	4F				A16WE
1998041700095	19980417	00095	SO  	1998	4	17	98ZZZX1447       	1	19980301	G	3260	451823	ACTUATOR ARM    		8640902     	PIPER 	PA44  	PA44180     	7104402	SO  										NLG DOWNLOCK	FAILED          	D				K				NONE                    				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			WP	09	3020M	4064 				447995220				NO DOWN AND LOCK INDICATION ON NOSE GEAR.  FOUND DOWN AND LOCK SWITCH ACTUATOR ARM BROKEN, NOT MAKING SWITCH CONTACT.  S	USPECT CAUSE METAL FATIGUE.  SUBMITTER SUGGESTED REPLACING ACTUATOR AT REASONABLE TIME INTERVALS.					1	L	7	2 	3O				A19S0
1998041700096	19980417	00096	EA  	1998	4	17	98ZZZX1448       	2	19980318	G	8530		VALVE SEAT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 3 CYL EXH VLV	DAMAGED         	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	54048	4627 	505  			17274857	L1223939A			DURING AIRCRAFT RUN-UP, THE PILOT NOTICED THE ENGINE WAS RUNNING ROUGH.  THE MECHANIC PULLED A COMPRESSION CHECK AND FOU	ND THAT NR 3 CYLINDER HAD NO COMPRESSION.  FURTHER INVESTIGATING AND CYLINDER REMOVAL SHOWED THE EXHAUST VALVE SEAT INSI	DE THE CYLINDER HAD SLIPPED OUT FROM ITS GROOVE; THUS, NOT ALLOWING FOR PROPER VALVE SEATING.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998041700097	19980417	00097	CE  	1998	4	17	98ZZZX1449       	1	19980403	G	2820	1580016D0112	HOSE            	STRATOFLEX  		CESSNA	182   	R182        	2072734	CE  										FUEL	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	757ME	354  				R18201247				FUEL HOSE FAILED AFTER 2 YEARS AND 254 HOURS OF OPERATION.  THE TAG ON THE HOSE HAS A DATE OF MANUFACTURE, 6-4-96.						1	H	7	1 	3O			RT	3A13
1998041700098	19980417	00098	SO  	1998	4	17	98ZZZX1450       	1	19980317	G	5712	7847504	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  										WS 49.25 LT WING	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	75139	6588 				28R7635269				WING STA 49.25 RIB CRACKED.  CRACK NOT VISIBLE UNTIL BRACE STUD ATTACH WAS REMOVED.						1	L	7	1 	3O				2A13
1998041700099	19980417	00099	SO  	1998	4	17	98ZZZX1451       	1	19980317	G	5712	7847505	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  										RT WS 49.25	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	75139	6588 				28R7635269				RIGHT WING STA 49.25 RIB CRACKED.  CRACK NOT VISIBLE UNTIL BRACE STUD ATTACH REMOVED.						1	L	7	1 	3O				2A13
1998041700100	19980417	00100	EA  	1998	4	17	98ZZZX1452       	2	19980401	G	8530	LW14995	RETAIN SPRING   			PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					SHROUD TUBE	BROKEN          	B			CQVR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	2204A	79   				287911006	L2050340A			FOUND OIL LEAKING FROM COWL.  REMOVED COWL.  FOUND NR 6 CYLINDER EXHAUST PUSH ROD MOVED INTO UPPER CYLINDER.  REMOVED RO	CKER COVER.  FOUND SHROUD TUBE RETAINING SPRING BROKEN.  EXAMINED OTHER 5 CYLINDERS.  FOUND ONE MORE BROKEN SPRING AND 2	 CRACKED SPRINGS.  REPLACED ALL SPRINGS WITH NEW.  EITHER LYCOMING HAS ANOTHER PROBLEM OR THESE SPRINGS WERE MISSED BY L	YCOMING SB 519.			1	L	7	1 	3O	3	O		2A13    	E295
1998041700102	19980417	00102	SO  	1998	4	17	98ZZZX1454       	2	19980330	G	8530	653191	GASKET          			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					CYL NR 3 ROCKER	LEAKS           	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	9438M	9    				U20604546				A SMALL OIL LEAK ON NR 3 CYLINDER WAS REPAIRED BY INSTALLING A NEW P/N 653191 ROCKER COVER GASKET.  NINE HOURS LATER,  A	 LARGE OIL LEAK WAS EVIDENT, CYLINDER NR 3.  UPON PULLING COVER, FOUND GASKET HAD SHRUNK CAUSING OIL LEAK WHERE THE GASK	ET WENT STRAIGHT BETWEEN TWO SCREWS.				1	H	7	1 	3O	3	O		A4CE    	E8CE
1998041700598	19980417	00598	SO  	1998	4	17	98ZZZX1456       	2	19980227	G	8520	641931981	BOLT            								CONT  	O470  	IO470K      	17026	SO  					CASE THRU BOLT	BROKE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17							861591K			THRU-BOLT BROKE AFTER 14 HOURS.  ENGINE NEVER RAN BEFORE BOLT BROKE.											3	O			3E1
1998041700600	19980417	00600	GL  	1998	4	17	98ZZZX1458       	1	19980323	G	7714	207100051C	CONTROL CABLE   			DIAMON	DA20  	DA20A1      	2990000	GL  										TACHOMETER	FAILED          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	520SS	584  				10075				DURING RUN-UP PRIOR TO TAKEOFF, TACH WENT TO ZERO.  FOUND THAT CABLE END SWAGE/NUT ON TACH INDICATOR END HAD PULLED OFF 	THE CABLE HOUSING.  NEITHER CABLE END WAS SWAGED TIGHT TO CABLE OUTER SHEATH.  NEW CABLE INSTALLED.  NEW CABLE APPEARED 	TO BE SWAGED THE SAME AMOUNT.  SUGGEST A TIGHTER SWAGE IF CABLE SHEATH WILL ALLOW IT.				1	L	7	1 	3O			NT	TA4CH
1998041700601	19980417	00601	GL  	1998	4	17	98ZZZX1459       	1	19980323	G	6120	2076000112	CABLE           			DIAMON	DA20  	DA20A1      	2990000	GL  										PROP CONTROL	FAILED          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	558ND	492  				10129				PILOT REPORTED PROPELLER CONTROL CABLE LOST TENSION DURING RUN-UP.  FOUND CABLE CORE WIRE BROKEN WHERE CABLE CONNECTS TO	 GOVERNOR.  ROUTING OF CABLE HAD PLACED A BENDING PRELOAD ON CABLE.  SUBMITTER SUGGESTED STRAIGHTER ROUTING AND A ROD EN	D TYPE CABLE INSTEAD OF SINGLE CORE WIRE TYPE.				1	L	7	1 	3O			NT	TA4CH
1998041700602	19980417	00602	CE  	1998	4	17	98ZZZX1460       	1	19980318	G	2150	203SZZ	BEARING         		585550137   	BEECH 	58    	58          	1152740	CE  										LT ENG AIR COND	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	3255U	308  				TH1750				DURING RANDOM CHECK FOR AIRCRAFT CONDITION, FOUND AIR CONDITIONING TENSIONING PULLEY BEARING DISINTEGRATED.  PULLEY WAS 	HELD IN PLACE BY BELT.  ALL BEARING BALLS WERE GONE.  ONLY INNER AND OUTER RACE REMAINED.  THIS IS SECOND PULLEY TO FAIL	 ON THIS AIRCRAFT IN 307.8 HOURS.  PREVIOUS BEARING TIME UNKNOWN.  INSTALLED NEW ASSY.				1	L	7	2 	3O				3A16
1998041700603	19980417	00603	CE  	1998	4	17	98ZZZX1461       	1	19980319	G	7120	051313210	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENG MT UPPER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	7288M	3565 				55588				LOWER RIGHT FIREWALL ENGINE MOUNT BRACKET FOUND CRACKED INTO TWO PIECES.  UPPER LEFT AND RIGHT BRACKETS FOUND TO HAVE SI	MILAR CRACKS, BUT NOT AS EXTENSIVE.  AREA IS DIFFICULT TO INSPECT AS ENGINE MOUNT BOLTS NEED TO BE REMOVED AND BRACKETS 	ARE OFTEN COVERED UP BY INSULATION.  NEW PARTS ARE .010 INCH THICKER THAN ORIGINAL.				1	H	7	1 	3O			NT	3A17
1998041700604	19980417	00604	CE  	1998	4	17	98ZZZX1462       	1	19980319	G	7120	051313211	BRACKET         			CESSNA	175   	175         	2072502	CE  										ENG MT LOWER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	7288M	3565 				55588				LOWER RIGHT FIREWALL ENGINE MOUNT BRACKET FOUND CRACKED INTO TWO PIECES.  UPPER LEFT AND RIGHT BRACKETS FOUND TO HAVE SI	MILAR CRACKS, BUT NOT AS EXTENSIVE.  AREA IS DIFFICULT TO INSPECT AS ENGINE MOUNT BOLTS NEED TO BE REMOVED AND BRACKETS 	ARE OFTEN COVERED UP BY INSULATION.  NEW PARTS ARE .010 INCH THICKER THAN ORIGINAL.				1	H	7	1 	3O			NT	3A17
1998041700605	19980417	00605	CE  	1998	4	17	98ZZZX1463       	1	19980318	G	3221	AN526A	BOLT            			CESSNA	180   	180         	2072602	CE  										TAIL WHEEL	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	9345C					31743				DURING AN ANNUAL INSPECTION, THE TWO TAIL WHEEL ATTACHMENT BOLTS WERE REMOVED FOR INSPECTION.  BOTH BOLTS WERE FOUND COR	RODED APPROXIMATELY 50 PERCENT OF THE BOLT DIAMETER.  THIS CONDITION HAS ALSO BEEN NOTED ON SEVERAL OTHER TAIL WHEEL AIR	CRAFT.				1	H	7	1 	3O			NC	5A6
1998041700606	19980417	00606	CE  	1998	4	17	98ZZZX1464       	1	19980318	G	7120	051313211	BRACKET         			CESSNA	175   	175A        	2072504	CE  										ENG MT UPPER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	90045					56603				CRACK RADIATING FROM ENGINE MOUNT BOLT HOLE.  THIS IS THE SECOND CESSNA 175 SUBMITTER FOUND WITH CRACKED BRACKETS.  VISU	AL INSPECTION IS SATISFACTORY TO IDENTIFY CRACKS, BUT GAINING ACCESS TO BRACKET MAY REQUIRE REMOVAL OF ENGINE MOUNT BOLT	/NUT AND WASHERS.				1	H	7	1 	3O				3A17
1998041700607	19980417	00607	CE  	1998	4	17	98ZZZX1465       	1	19980318	G	7120	051313209	BRACKET         			CESSNA	175   	175A        	2072504	CE  										ENG MT RT LOWER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	90045					56603				CRACK RADIATING FROM ENGINE MOUNT BOLT HOLE.  THIS IS THE SECOND CESSNA 175 SUBMITTER FOUND WITH CRACKED BRACKETS. VISUA	L INSPECTION IS SATISFACTORY TO IDENTIFY CRACKS, BUT GAINING ACCESS TO BRACKET MAY REQUIRE REMOVAL OF ENGINE MOUNT BOLT/	NUT AND WAHSERS.				1	H	7	1 	3O				3A17
1998041700608	19980417	00608	CE  	1998	4	17	98ZZZX1466       	1	19980318	G	7120	051313210	BRACKET         			CESSNA	175   	175A        	2072504	CE  										ENG MT LT LOWER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	90045					56603				CRACK RADIATING FROM ENGINE MOUNT BOLT HOLE.  THIS IS THE SECOND CESSNA 175 SUBMITTER FOUND WITH CRACKED BRACKETS. VISUA	L INSPECTION IS SATISFACTORY TO IDENTIFY CRACKS, BUT GAINING ACCESS TO BRACKET MAY REQUIRE REMOVAL OF ENGINE MOUNT BOLT/	NUT AND WAHSERS.				1	H	7	1 	3O				3A17
1998041700609	19980417	00609	CE  	1998	4	17	98ZZZX1467       	1	19980401	G	2701		YOKE            			CESSNA	182   	182F        	2072714	CE  										COCKPIT	FAILED          	D	P			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	03	3374U					18254774				CONTROL YOKE FAILURE ON LANDING.  CONTROL YOKE BROKE, FAILED IN UPPER LEFT SIDE.  AIRCRAFT MANUFACTURED IN 1963.  SUSPEC	T CAUSE EXTREME AGE OF PLASTIC PART.  AIRCRAFT AND CONTROL YOKE TT 2,800 HOURS.					1	H	7	1 	3O			NT	3A13
1998041700610	19980417	00610	CE  	1998	4	17	98ZZZX1468       	1	19980401	G	3242		BRAKE DISC      	PARKERHANFIN		CESSNA	172   	172N        	2072434	CE  										MLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4725D					17272340				THREE CRACKS RADIATING OUT ACROSS THE DISC.  CRACKS EXTENDED THROUGH THE DISC AND WERE FOUND BY VISUAL INSPECTION.  THIS	 IS THE THIRD DISC FOUND CRACKED LIKE THIS IN THE LAST YEAR.					1	H	7	1 	3O			NT	3A12
1998041700611	19980417	00611	CE  	1998	4	17	98ZZZX1469       	1	19980403	G	5730	12212212	SKIN            			CESSNA	210   	P210N       	2073454	CE  										LT WING TOP INBD	CRACKED         	B	S		KQ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	67JK					P21000684				CRACKS AT RIVET HOLES ON TOP OF BOTH WINGS FROM .25 INCH TO .75 INCH AT TRAILING EDGE BETWEEN WS 110.00 AND WS 124.00 AN	D ON WS 110.00.  PRECISE FLIGHT, INC., SPEED BRAKES INSTALLED UNDER STC 2602NM ON 8-10-90 BETWEEN WS 124.00 AND WS 138.0	0.  TOTAL TIME SINCE INSTALLATION, 449.5 HOURS.  ESTIMATE 20.0 HOURS USING SPEED BRAKES.  VIBRATION OF THE SPEED BRAKES 	WHEN EXTENDED COULD BE THE CAUSE.  SUBMITTER SUGGESTED INSPECTING THIS AREA AT EVERY PRE-FLIGHT, 50, 100, AND ANNUAL INS	PECTION, OR DISCONTINUE USING SPEED BRAKES UNTIL THIS PROBLEM IS RESOLVED.		1	H	7	1 	3O				3A21
1998041700612	19980417	00612	CE  	1998	4	17	98ZZZX1470       	1	19980403	G	5730	12212222	SKIN            			CESSNA	210   	P210N       	2073454	CE  										RT WING TOP INBD	CRACKED         	B	S		KQ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	67JK					P21000684				CRACKS AT RIVET HOLES ON TOP OF BOTH WINGS FROM .25 INCH TO .75 INCH AT TRAILING EDGE BETWEEN WS 110.00 AND WS 124.00 AN	D ON WS 110.00.  PRECISE FLIGHT, INC., SPEED BRAKES INSTALLED UNDER STC 2602NM ON 8-10-90 BETWEEN WS 124.00 AND WS 138.0	0.  TOTAL TIME SINCE INSTALLATION, 449.5 HOURS.  ESTIMATE 20.0 HOURS USING SPEED BRAKES.  VIBRATION OF THE SPEED BRAKES 	WHEN EXTENDED COULD BE THE CAUSE.  SUBMITTER SUGGESTED INSPECTING THIS AREA AT EVERY PRE-FLIGHT, 50, 100, AND ANNUAL INS	PECTION, OR DISCONTINUE USING SPEED BRAKES UNTIL THIS PROBLEM IS RESOLVED.		1	H	7	1 	3O				3A21
1998041700613	19980417	00613	EA  	1998	4	17	98ZZZX1471       	2	19980408	G	8530		ROCKER SHAFT    			CESSNA	172   	172R        	2072401	CE  	LYC   	O360  	O360F1A6    	41514	EA  					NR 3 EXH-INT	LOOSE           	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	15		2    								A DEAD CYLINDER CAUSED AIRCRAFT TO LAND. TROUBLESHOOTING FOUND NR 3 CYLINDER DEAD.  WHEN REMOVING THE VALVE COVER, FOUND	 THE INTAKE AND EXHAUST ROCKER SHAFTS LOOSE AND ONE RETAINING NUT WAS INSIDE THE VALVE COVER.  THE ACFT HAD JUST BEEN RE	TURNED TO SERVICE 2 TACK HOURS EARLIER, THE LOG BOOK SHOWED THAT ALL PUSH ROD SEALS WERE REPLACED DUE TO OIL LEAKS.  THE	 OIL SEALS WERE REPLACED BUT UPON RE-INSTALLATION OF THE ROCKER SHAFT, THE MECHANIC USED STAR WASHERS TO SECURE THE PLAI	N NUTS INTO PLACE.  THE CONTINENTAL ENGINE MANUALS CALLS FOR A LOCK P/N 50186.  NEW LOCKS INSTALLED (24 EACH) ON ALL ROC	KER SHAFT RETAINING NUTS AND CRIMP LOCKED AS REQUIRED.  NO HARM WAS DONE AND GROUND RUN-UP WAS SATISFACTORY.	1	H	7	1 	3O	3	O	NT	3A12    	E286
1998041700614	19980417	00614	CE  	1998	4	17	98ZZZX1472       	1	19980301	G	5551	NAS13064	ATTACH BOLT     			CESSNA	414   	414         	2075908	CE  										RT FWD H STAB	MISSING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8BL					4140098				DURING AN ANNUAL INSPECTION, HORIZ STAB MOVED UP AND DOWN FROM THE RT SIDE.  AN EXCESSIVE AMOUNT OF MOVEMENT WAS NOTED. 	 DUIRNG CLOSER INSPECTION, FOUND BOLT, P/N NAS1306-4, MISSING FROM THE RT FORWARD ATTACH POINT.  INSIDE THE STABILIZER A	FT OF THE FORWARD SPAR, BOLT WAS FOUND.  FORWARD OF THE AFT SPAR IN THE AFT TAILCONE, FOUND 2 HALVES OF NUT, P/N MS21044	N6.			1	L	7	2 	3O			RT	A7CE
1998041700615	19980417	00615	EU  	1998	4	17	98ZZZX1473       	1	19980318	G	6210	601741	BEARING         			BOLKMS	117   	BK117A1     	5626010	EU  										BLUE M/R BLADE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	128HH					7036				NOTICED BLUE M/R BLADE PENDULUM ABSORBER SOUNDED ROUGH ON PRE-FLIGHT INSPECTION.  SUSPECT CAUSE, LACK OF LUBRICATION.						1	G	7	2 	3U				H13EU
1998041700618	19980417	00618	NE  	1998	4	17	98ZZZX1475       	2	19980330	G	7250	411101007	NOZZLE          		410100038   						LYC   	LTS101	LTS101600A3 	41560	NE  					GP MODULE	BURNT           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	13					C400		LE43177CE			GP NOZZLE WAS INSTALLED ON ENGINE THAT WAS SURGING.  DURING INVESTIGATION, FOUND THE NEWLY OVERHAULED GP NOZZLE TO HAVE 	BURNED VANES. THERE ARE OTHER NOZZLES WITH SIMILAR DEFECTS NOTED ON OTHER INSTANCES.  INVESTIGATION OF THIS MATTER IS ON	GOING.									3	U			E5NE
1998041700619	19980417	00619	SO  	1998	4	17	98ZZZX1476       	2	19980303	G	7322	9944	PLUG            	FACET       	MA45        	CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470P       	17026	SO  					CARBURETOR BOWL	MISSING         	D	L	A		A				UNSCHED LANDING         				A			FLAME/FIRE                			CL	CLIMB          	1			WP	23	9109G	1752 			BD175233	18260649	21119771R			FOLLOWING TAKEOFF, ENGINE RUNNING ROUGH AND FIRE ERUPTED.  AFTER LANDING, INSPECTION FOUND FIRE IN ENGINE COMPARTMENT DU	E TO MISSING DRAIN PLUG FROM CARBURETOR BOWL.  NO SAFETY WIRE EVIDENT.					1	H	7	1 	3O	3	O	NT	3A13    	E273
1998041700620	19980417	00620		1998	4	17	98ZZZX1477       	4	19980219	G	2210	KAP140	AUTOPILOT SYS   			CESSNA	172   	172R        	2072401	CE  										COCKPIT	MALFUNCTIONED   	B			HX1R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			EA	25	118ET	262  			1029	17280019				DURING FLIGHT, AUTOPILOT (WHICH WAS OFF) TURNED ITSELF ON AND COULD NOT BE TURNED OFF WITH THE ON/OFF BUTTON.  THE INDIC	ATOR LIGHTS BEGAN TO FLASH RANDOMLY.  AFTER SEVERAL MINUTES, THE UNIT SHUT ITSELF OFF.  ACFT LANDED WITHOUT INCIDENT.  T	HE AUTOPILOT BOX WAS REMOVED AND RETURNED TO MANUFACTURER.  IT WAS NOTED THE AUTOPILOT CIRCUIT BREAKER WAS NOT THE PULL 	OFF TYPE. THE ONLY WAY THE POWER TO THE AUTOPILOT COULD HAVE BEEN TURNED OFF WOULD HAVE BEEN TO TURN OFF THE AVIONIC MAS	TER; THUS, LOSING ALL NAVIGATION AND COMMUNICATION CAPABILITIES.  FURTHER INVEST, REVEALED THE AUTOPILOT MFG CLEARLY CAL	LED OUT IN ITS INSTALL MANUAL, THE SYMBOL FOR A PULL OFF TYPE CB.  THIS INSTALLATION PERFORMED BY THE AIRFRAME MFG.	1	H	7	1 	3O			NT	3A12
1998041700737	19980417	00737	CE  	1998	4	17	98ZZZX1478       	1	19980406	G	3244		TIRE            			BEECH 	80    	65B80       	1152812	CE  										WEEP HOLES	LEAK            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	131BA				4055N00589	LD297				SUBMITTER STATED OPERATION HAS BEEN HAVING PROBLEMS WITH TIRES LEAKING FROM WEEP HOLES AFTER HAVING BEEN RETREADED BY RE	PAIR STATION NR BX3R4131.  WE MARK THE TIRES AND RETURN THEM TO THE COMPANY.  THEY RETREAD THEM AND SEND THEM BACK AND T	HEY STILL LEAK.  THE WEEP HOLES ARE ON THE SIDES AND THE RETREADING DOES NOT GO DOWN THAT FAR.				1	L	7	2 	3O				3A20
1998041700739	19980417	00739		1998	4	17	98ZZZX1480       	1	19980220	G	3246	6A0129001	TUNNEL CAP      	WIPLINEINC  	6000        															FLOAT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										NEW PART MADE FROM A MACHINED ALUMINUM BLOCK WAS INSPECTED BEFORE INSTALLATION.  A VOID SURFACE WAS FOUND ON ONE FACE WI	TH PITTING ON THE OTHER SIDE IN SAME LOCATION.  THE ANODIZING DID NOT APPEAR TO HAVE TAKEN IN THE VOID.  THIS PART IS IN	 A MOIST ENVIRONMENT, OFTEN SALTWATER, AND WOULD HAVE CORRODED THROUGH QUICKLY.  IT APPEARS DEFECT WAS PRESENT IN ORIGIN	AL BLOCK OF ALUMINUM BEFORE MACHINING.  RETURNED PART TO WIPLINE FOR REPLACEMENT.
1998041700740	19980417	00740	NM  	1998	4	17	98ZZZX1481       	1	19980217	G	8011	480388	BENDIX DRIVE    	PRESTOLITE  	MZ4218      	CHILD 	S2    	S2APITTS    	0110201	NM  										STARTER	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			SO	15	32TP				9861018	2179				WHILE MANEUVERING IN A FLAT SPIN, THE PILOT EXPERIENCED AN ENGINE OUT.  AN ATTEMPT TO RESTART COULD NOT BE MADE BECAUSE 	THE BENDIX FAILED TO RE-ENGAGE.					1	Q	7	1 	3O				A8SO
1998041700741	19980417	00741	NM  	1998	4	17	98ZZZX1482       	1	19980217	G	2810	26502013	FUEL SYSTEM     			CHILD 	S2    	S2APITTS    	0110201	NM  										FUEL FLOP TUBE	CONTAMINATED    	G				O				OTHER                   				Y			ENGINE STOPPAGE           			AB	AEROBATIC      	1			SO	15	32TP					2179				WHILE MANUEVERING IN A FLAT SPIN, THE PILOT EXPERIENCED AN ENGINE OUT.  AN ATTEMPT TO RESTART FAILED BECAUSE THE BENDIX 	FAILED TO ENGAGE.  DURING THE ACCIDENT INVESTIGATION, IT WAS NOTED THE FUEL FILTER HAD NUMEROUS METAL PARTICLES.  SUBMIT	TER STATED BY PLACING A TEFLON RING AROUND THE FLOP TUBE, WOULD KEEP THE FLOP TUBE FROM SCRAPING THE METAL AND WOULD ELI	MINATE METAL PARTICLES FROM ENTERING THE FUEL FILTER.			1	Q	7	1 	3O				A8SO
1998041700742	19980417	00742	SO  	1998	4	17	98ZZZX1483       	1	19980402	G	7120	6711957	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  										ENGINE	MAGNETIZED      	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	6367C					28R7837162				WHILE SWINGING THE COMPASS ADJUSTMENTS, WOULD NOT COMPENSATE ANY CLOSER THAN 18 DEGREES ON AN EAST HEADING.  FOUND THE E	NGINE MOUNT TO BE MAGNETIZED ON THE UPPER RIGHT AND CENTER FIREWALL ATTACH POINTS.  SUBMITTER SUSPECTS THIS OCCURRED WHE	N THE MOUNT WAS REPAIRED WITH AN ARC WELDER.  THE PROBLEM WAS ELIMINATED BY REMOVING THE MOUNT AND PASSING IT THROUGH A 	DEGAUSSING COIL.			1	L	7	1 	3O				2A13
1998041700743	19980417	00743	CE  	1998	4	17	98ZZZX1484       	1	19980327	G	7120	04112815	BRACKET         			CESSNA	150   	150G        	2071816	CE  										ENGINE MOUNT	DISPLACED       	B			MOGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	8311J	3384 				15066211				FOUND LEFT LOWER ENGINE MOUNT BRACKET DISPLACED FROM NORMAL POSITION.  THIS MAY HAVE OCCURRED DURING UNDOCUMENTED REPAIR	 IN AREA BY PERSONS UNKNOWN.					1	H	7	1 	3O			 	3A19
1998041700744	19980417	00744	CE  	1998	4	17	98ZZZX1485       	1	19980325	G	7603	99103213	CONTROL CABLE   			CESSNA	441   	441         	2076020	CE  										LT ENG PWR CONT	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911ER	7806 			595	4410249				LEFT ENGINE POWER CONTROL CABLE BROKE ABOUT 3.25 INCHES INSIDE HOUSING AT COCKPIT CONSOLE.						1	L	7	2 	3T			RT	A28CE
1998041700746	19980417	00746	EA  	1998	4	17	98ZZZX1487       	3	19980323	G	6111		BLADE           			AMTR  	WAG   	WAGARO      	05655YX	GL  						SNSNCH	76E	76EM8S5     	EA  	PROPELLER	SEPARATED       	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	19	9244B					2				APPROXIMATELY 40 INCHES OF PROPELLER SEPARATED.  DEFINITE 'SHADOW' OF DIFFERENT COLOR IN METAL IN CROSS-SECTION OF CHORD	.  'SHADOW' OCCUPIED ONE-THIRD OF CROSS-SECTION.  NO APPARENT CAUSE FOR FACTURE.					1	H	7	1 	3O			NC	EXPA1H71		5	N	P4EA
1998041700748	19980417	00748	EU  	1998	4	17	98ZZZX1489       	1	19980406	G	5510	453005509	HINGE FITTING   			ISRAEL	1124  	1124        	4500102	EU  										AFT SPAR SPLICE	CRACKED         	H			GQFG	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	1621	8364 				275				INSPECTION FOUND CRACKS IN HORIZONTAL STABILIZER AFT SPAR SPLICE HINGE FITTING.  TAT:  8,363.6 HOURS.  LANDINGS:  5,993.						2	M	7	2 	4F				A2SW
1998041700749	19980417	00749	NE  	1998	4	17	98ZZZX1490       	2	19980406	G	7321	105970	NOZZLE          		JFC3123     	BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R     	41580	NE  					FCU PUMP	FRACTURED       	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	05		12803	920  		F10956					FUEL CONTROL FAILURE.  ENGINE SHUT DOWN IN-FLIGHT.  SUSPECT CAUSE:  PUMP NOZZLE IS FRACTURED CAUSING SEVERE CONTAMINATIO	N.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998041700750	19980417	00750	CE  	1998	4	17	98ZZZX1491       	1	19980323	G	7930	45AS410AA001	SWITCH          			BEECH 	MU300 	400A        	1155402	CE  										FILTER BYPASS	FAILED          	B			KI2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	01	85CR					RK22				OIL FILTER BYPASS SWITCH FAILED.  REASON FOR REJECTION, NEW SWITCH WAS ALSO INTERNALLY SHORTED.  ACCORDING TO RAYTHEON, 	VENDOR HAD A MANUFACTURING PROBLEM.  REPLACED TWO SWITCHES AND BOTH HAD THE SAME PROBLEM.					2	H	7	2 	4F			RT	A16SW
1998041700751	19980417	00751		1998	4	17	98ZZZX1492       	4	19980330	G	3457	0110005400	GPS             	GARMIN INTL 	GPS150      	BELL  	206   	206B3       	1181506	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	9907K					2040				GPS WAS RETURNED FROM OVERHAUL.  BATTERY LOW LIGHT STAYED ON.  UNIT WOULD NOT PICK UP SATELLITES.						1	G	7	1 	3U				H2SW
1998041700752	19980417	00752	SW  	1998	4	17	98ZZZX1493       	1	19980331	G	6210	206010154003	WASHER          			BELL  	206   	OH58A       	1181579	SW  										BLADE RETAIN	BROKEN          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	54AG					7120721				DURING PRE-FLIGHT INSPECTION, PILOT FOUND THE WASHER UNDER THE NUT OF THE BLADE RETENTION BOLT WAS CRACKED.  UPON REMOVA	L OF NUT, IT WAS FOUND COMPLETELY BROKEN.  WASHER WAS REPLACED AND AIRCRAFT RELEASED FOR FLIGIHT.					1	G	7	1 	3U				H2SW
1998041700753	19980417	00753	GL  	1998	4	17	98ZZZX1494       	2	19980330	G	7314	3865005	FUEL PUMP       			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC	2502 			T107446	290456D				FAILED BYPASS CHECK AT 100 HOUR INSPECTION.  FUEL PUMP REMOVED AND SENT FOR OVERHAUL EVALUATION.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998041700754	19980417	00754	WP  	1998	4	17	98ZZZX1495       	1	19980301	G	6210		BLADE           			HUGHES	369   	369E        	4470707	WP  										M/R	UNBONDED        	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	46EE	2792 				0406E				DURING SCHEDULED INSPECTION, FOUND LOWER ROOT FITTING TO DOUBLER BOND LINE ADHESIVE MISSING.  AREA OF MISSING ADHESIVE W	AS APPROXIMATELY 1 INCH LONG AND .100 INCH UNDER ROOT FITTING.  BLADE WAS SENT TO BLADE REPAIR FACILITY AND FOUND TO BE 	UNREPAIRABLE.  BLADE WAS SCRAPPED.  AREA OF DEFECT WAS ON LEADING SIDE OF LOWER ROOT FITTING.  INSTALLED NEW BLADE.				1	G	7	1 	3U				H3WE
1998042400087	19980424	00087	EA  	1998	4	24	98ZZZX1518       	2	19980301	G	8550		OIL PUMP        			GULSTM	AA1   	AA1A        	0630710	SO  	LYC   	O235  	O235C2C     	41505	EA  					ENGINE OIL	WRONG GEARS     	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	7255L					AA1A0455	L1139615			ANNUAL INSPECTION RECORD CHECK FOUND AD 75-08-09 C/W NOV 1976.  REPLACED GEARS 6-7-78.  ENGINE OVERHAULED, NO DETAILS GI	VEN.  6-30-79 - ENGINE REMOVED AND STORED.  TT 697.4 HOURS.  6-30-84.  ENGINE INSTALLED IN N 7255L.  AD 81-18-04R2.  SIG	NED OFF ON AD LIST AS DUE AT 2,000 HRS OR OVERHAUL.  IN C/W AD 96-09-10, ENGINE REMOVED AND GEARS INSPECTED AND FOUND TO	 BE SINTERED IRON.  BOTH GEARS REPLACED WITH HARDENED STEEL.			1	L	7	1 	3O	3	O		A11EA   	E223
1998042400088	19980424	00088	EA  	1998	4	24	98ZZZX1519       	2	19980306	G	8520		STUD            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 1 CYLINDER	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	13	4108D	3713 				318352018	L890061A			95.3 HOURS SINCE OVERHAUL:  PILOT REPORTED ROUGH RUNNING ENGINE. INSPECTION SHOWED NR 1 CYLINDER, 2 EACH, TOP CYLINDER S	TUDS AND, 2 EACH, AFT STUDS BROKEN.  FUEL INJECTOR LINE BROKEN, INTAKE TUBE DAMAGED.  .3750 INCH STUDS, P/N 38-13.  .50 	INCH STUDS, P/N 50-15.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998042400089	19980424	00089	EA  	1998	4	24	98ZZZX1520       	2	19980320	G	8520		STUD            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 4 CYLINDER	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	13	4108D	5145 				318352018	L43068A			108.9 HOURS SINCE OVERHAUL:  PILOT REPORTED ROUGH RUNNING NR 4 CYLINDER ALL STUDS BROKEN, FUEL INJECTOR LINE AND EXHAUST	 PIPE BROKEN, AND CASE CRACKED.  THIS ENGINE IS BEING REMOVED FOR REPAIR.  .3750 INCH STUDS, P/N 38-13.  .50 INCH STUDS,	 P/N 50-15 THROUGH STUD, P/N 76220.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998042400090	19980424	00090	CE  	1998	4	24	98ZZZX1521       	1	19980323	G	7110		COWL            			CESSNA	206   	U206F       	2073333	CE  						HARTZL	HCC3Y	HCC3Y*      	GL  	NOSE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1198V					U20602509				DURING ANNUAL INSPECTION, FOUND THE NOSE COWL WITH HOLES RUBBED THROUGH FROM AFT SPINNER BULKHEAD.  THIS IS A STC SA685A	L INSTALLATION, AND THE THIRD AIRCRAFT KNOWN TO HAVE THIS PROBLEM.  TOTAL TIME SINCE PROPELLER INSTALLED 50:1.  COWL TO 	BULKHEAD CLEARANCE IS .1250 INCH, BUT NEEDS MORE CLEARANCE DUE TO COWL GROWTH FROM AIR PRESSURE.				1	H	7	1 	3O				A4CE    		5	C	P25EA
1998042400091	19980424	00091	EA  	1998	4	24	98ZZZX1522       	2	19980227	G	7230	230064802	PLATE           		210193006   						LYC   	ALF502	ALF502*     	41580	EA  					NR 2 BEARING	MISMARKED       	B			C7GR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	13										FACE PLATE WAS IDENTIFIED AS 2-300-649-02, PART WAS ACTUALLY 2-300-648-02.  ASSEMBLY WAS RETURNED BY CUSTOMER FOR HAVING	 WRONG P/N INSTALLED.  NOTIFIED MANUFACTURER OF MIS-IDENTIFICATION TO INITIATE CORRECTIVE ACTION.  PERFORMED STOCK SWEEP	, NO OTHERS FOUND MISIDENTIFIED.  NOTIFIED CENTRAL DISTRIBUTION CENTER IN PHOENIX TO PERFORM STOCK SWEEP FOR SAME.									4	F			E6NE
1998042400092	19980424	00092	NE  	1998	4	24	98ZZZX1523       	2	19980224	G	7250	410106013	IMPELLER SHROUD 		410100027   						LYC   	LTS101	LTS101750B2 	41560	NE  					GP MODULE	SEPARATION      	B			C7GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13					86B066		W88B008			USCG ENGINE SURGED.  UPON TROUBLESHOOTING OF THE ENGINE, FOUND ABRADABLE (PLASMA) COATING SEPARATED AT INTERFACE.											3	U			E5NE
1998042400093	19980424	00093	NE  	1998	4	24	98ZZZX1524       	2	19980326	G	7230	410100641	AXIAL ROTOR     		410102050   						LYC   	LTS101	LTS101650B1 	41560	NE  					BLADE ROOT	SEPARATION      	B			C7GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13		787  			105244		LE41116AE			AXIAL BLADE SEPARATION AT BLADE ROOT AREA - ENGINE FAILURE.  INVESTIGATION ONGOING.  CORRECTIVE ACTION IN PROGRESS.											3	U			E5NE
1998042400094	19980424	00094	GL  	1998	4	24	98ZZZX1525       	2	19980330	G	7230	6896024	EJECTOR NOZZLE  								ALLSN 	250C  	250C28B     	03013	GL  					NR 1	BROKEN          	B			XZNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07							CAE860172			EJECTOR TUBE ASSY HAD TOP TUBE BROKEN OFF CAUSING DAMAGE TO IMPELLER REQUIRING IMPELLER TO BE SCRAPED, PIECES OF TUBE WE	RE FOUND IN COMBUSTOR AND TURBINE NR 1 NOZZLE.  TUBE ROUTED TO ALLISON ENGINE CO. FOR ANALYSIS.  OPERATOR ROUTED ENGINE 	TO REPAIR STATION FOR FOREIGN OBJECT DAMAGE REPAIR.									3	U			E1GL
1998042400095	19980424	00095	NE  	1998	4	24	98ZZZX1526       	2	19980326	G	7240	213139003	COMBUSTION LINER		91C242      						LYC   	LF507 	LF5071F     		NE  					ENGINE	DISTORTED       	B			C7GR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13			458  				LF7367			UPON TEARDOWN OF THE ENGINE FOR AN UNRELATED ISSUE, IT WAS DISCOVERED THE COMBUSTION LINER WAS DISTORTED DUE TO BLOCKED 	COOLING HOLES.  SUSPECT PLASMA COATING OVERSPRAY DURING OVERHAUL.  INVESTIGATION IS ONGOING.  SERVICE BULLETIN IS PENDIN	G.									4	F			E6NE
1998042400096	19980424	00096	CE  	1998	4	24	98ZZZX1527       	1	19980331	G	5210	NAS3544240	DOOR ROD        			CESSNA	650   	650         	2076802	CE  										SECONDARY DOOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	606AT					6500225				THIS IS THE THIRD SECONDARY DOOR ROD INSTALLED ON THIS AIRCRAFT.  SUBMITTER SUGGESTED THERE ARE TWO SUSPECT CAUSES FOR T	HESE FAILURES.  ROD DIAMETER IS TOO SMALL FOR THE LOADS ENCOUNTERED OR DEFECTIVE RODS.					2	L	7	2 	4F				A9NM
1998042400097	19980424	00097	EU  	1998	4	24	98ZZZX1528       	1	19980307	G	5314		KEEL            			HWKSLY	DH125 	DH1251A     	4230106	EU  										STR 19 RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	105HS	7959 				25031				DISCOVERED DURING 2 YEAR INSPECTION, .25 INCH LONG CRACK LOCATED STRINGER LINE 19 OF KEEL AREA BETWEEN FRAMES 10 AND 11 	RT.					2	L	7	2 	4J				A3EU
1998042400098	19980424	00098	EA  	1998	4	24	98ZZZX1529       	1	19980410	G	2430	12XRP12A1	CIRCUIT BREAKER 	GE          		DHAV  	DHC6  	DHC6300     		EA  										BATTERY	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11	143Z				SWW03	437				INSTALLED 'OVERHAULED' REVERSE CURRENT CIRCUIT BREAKER ON AIRCRAFT.  PLACED BATTERY SWITCH AND MASTER TO 'ON'.  BATTERY 	WOULD NOT COME ON LINE.  TROUBLESHOT SYSTEM AND FOUND AN 'OPEN' BETWEEN THE 'GENERATOR FIELD SWITCH TERMINALS'; THUS, NO	T ALLOWING THE BATTERY RELAY TO BE ENERGIZED.				1	H	7	2 	3T				A9EA
1998042400325	19980424	00325	SW  	1998	4	24	98ZZZX1530       	1	19980403	G	3150	209075325045	CAUTION PANEL   			BELL  	212   	212         	1181420	SW  										INST PANEL	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F		228  			30920				INTERMITTENTLY COMPLETELY CUT OFF AND WILL NOT LIGHT MASTER CAUTION.  UNIT REMOVED AND SENT FOR OVERHAUL.  SUBMITTER CON	TROL NR 98-4-1.					1	G	7	1 	4U				H4SW
1998042400326	19980424	00326	WP  	1998	4	24	98ZZZX1531       	1	19980408	G	2841	369D29630521	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										FUEL QUANTITY	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				FUEL GAUGE INTERMITTENT AND CHANGES WHEN GENERATOR TURNED ON.  UNIT REMOVED AND SENT FOR REPAIR.  SUBMITTER CONTROL NR 9	8-4-4.					1	G	7	1 	3U				H3WE
1998042400327	19980424	00327	SW  	1998	4	24	98ZZZX1532       	1	19980403	G	7931	209070262	INDICATOR       			BELL  	212   	212         	1181420	SW  										OIL PRESS/TEMP	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F	496  				30920				ENGINE OIL PRESSURE INDICATOR READS ABOVE RED LINE AND READS 40 PSI WITH POWER OFF.  REMOVED AND SENT FOR OVERHAUL.  SUB	MITTER CONTROL NR 98-4-3.					1	G	7	1 	4U				H4SW
1998042400328	19980424	00328	SW  	1998	4	24	98ZZZX1533       	1	19980403	G	7714	212070108007	INDICATOR       			BELL  	212   	212         	1181420	SW  										NR 2 ENG TACH	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530F		783  			30920				NR 2 ENGINE TACH NEEDLE STICKS AT 80 PERCENT.  UNIT REMOVED AND SENT FOR OVERHAUL.  SUBMITTER CONTROL NR 98-4-2.						1	G	7	1 	4U				H4SW
1998042400329	19980424	00329	EU  	1998	4	24	98ZZZX1534       	1	19980317	G	6220	117775P	BALL JOINT      			SNIAS 	350   	AS350BA     	8680817	EU  										M/R HEAD	WORN            	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	350BA	268  				2788				BALL JOINT WOULD NOT PASS WEAR CRITERIA PER MWC.  REPLACED 3 EACH.						1	G	7	1 	3U			NC	H9EU
1998042400330	19980424	00330	GL  	1998	4	24	98ZZZX1535       	3	19980305	G	6111		BLADE           			GULSTM	500   	500B        	0141106	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	V-GROOVE	CRACKED         	B			RV3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					E74881			BJ1252		PROPELLER BLADE INSPECTION FOUND CRACK IN V-GROOVE ON SHANK.						1	H	7	2 	3O				6A1     		5	C	P6EA
1998042400331	19980424	00331	GL  	1998	4	24	98ZZZX1536       	3	19980408	G	6111		BLADE           			GULSTM	500   	500B        	0141106	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	V-GROOVE	CRACKED         	B			RV3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					E89471			BJ342		PROPELLER BLADE INSPECTION FOUND CRACK IN V-GROOVE ON SHANK.						1	H	7	2 	3O				6A1     		5	C	P6EA
1998042400332	19980424	00332	GL  	1998	4	24	98ZZZX1537       	3	19980409	G	6111		BLADE           			GULSTM	500   	500B        	0141106	SW  						HARTZL	HCA3V	HCA3VK2     	GL  	V-GROOVE	CRACKED         	B			RV3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					E98611			BJ342		PROPELLER BLADE INSPECTION FOUND CRACK IN V-GROOVE ON SHANK.						1	H	7	2 	3O				6A1     		5	C	P6EA
1998042400333	19980424	00333	SW  	1998	4	24	98ZZZX1538       	1	19980331	G	2435		BEARING         	LUCAS       	23085004    	GULSTM	560   	560         	0141402	SW  										LT START/GEN	FAILED          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			SO	03	94TX		594  		974	5600247				PILOTS REPORTED A VIBRATION IN THE LEFT ENGINE AFTER TAKEOFF.  THEY RETURNED TO THE AIRPORT WITH NO FURTHER PROBLEM.  IN	SPECTION REVEALED THE LT STARTER/GENERATOR ANTI-DRIVE END BEARING WAS BEGINNING TO FAIL.  THE GENERATOR WAS STILL OPERAT	ING; HOWEVER, PIECES OF THE BEARING CAGE WERE FOUND UPON REMOVAL INDICATING IMMINENT CATASTROPHIC FAILURE.				1	H	7	2 	3O				6A1
1998042400334	19980424	00334	CE  	1998	4	24	98ZZZX1539       	1	19980409	G	2750	602EN166	SWITCH          			CESSNA	500   	S550        	2076607	CE  										LT FLAP LIMIT	SHORTED         	D				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			EA	25	98QS					S5500098				PILOT REPORTED FLAP CONTROL CIRCUIT BREAKER TRIPPED WHEN FLAPS SELECTED UP.  C/B WOULD NOT RESET.  MAINTENANCE FOUND FLA	P LIMIT SWITCH ON LT FLAP ACTUATOR INTERNALLY SHORTED TO GROUND.  INSTALLED NEW SWITCH, P/N 602EN16-6, AND ADJUSTED AND 	SAFETIED IAW CESSNA S550 MM.  PERFORMED OPERATIONAL CHECK OF FLAP SYSTEM AFTER RESETTING C/B, NO DEFECTS.  FLAP SYSTEM N	OW OPERATING NORMALLY.  REF:  CESSNA CITATION S550 MM CH 27-51-OU FOR REMOVAL AND REPLACEMENT PROCEDURES OF SWITCH.   SU	SPECT HIGH TIME PART LED TO FAILURE.		1	L	7	2 	4F			RT	A22CE
1998042400335	19980424	00335	SW  	1998	4	24	98ZZZX1540       	1	19980327	G	5751		SPAR            			GULSTM	690TP 	690B        	7630516	SW  										LT AILERON	CRACKED         	B			FTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	307CL	5803 				11508				INSPECTION FOUND AILERON SPARS CRACKED.  LOCATION:  INBOARD HINGE BRACKET ATTACH POINT.  LT AILERON HAD .75 INCH CRACK. 	 RT AILERON HAD 2.25 INCH CRACK.  CAUSE COULD BE RELATED TO TOTAL TIME.					1	H	7	2 	3T				2A4
1998042400336	19980424	00336	SW  	1998	4	24	98ZZZX1541       	1	19980327	G	5751		SPAR            			GULSTM	690TP 	690B        	7630516	SW  										RT AILERON	CRACKED         	B		A	FTKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	307CL	5803 				11508				INSPECTION FOUND AILERON SPARS CRACKED.  LOCATION:  INBOARD HINGE BRACKET ATTACH POINT.  LT AILERON HAD .75 INCH CRACK. 	 RT AILERON HAD 2.25 INCH CRACK.  CAUSE COULD BE RELATED TO TOTAL TIME.					1	H	7	2 	3T				2A4
1998042400337	19980424	00337	EA  	1998	4	24	98ZZZX1542       	1	19980323	G	3222	200811218	AXLE            	ROTOL       		CNDAIR	CL600 	CL6002A12   	1900304	EA  										NLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	120MP	4713 			DCL168	3034				UPON DISASSEMBLY OF THE NLG AXLE FROM THE SLIDING TUBE, CORROSION WAS NOTICED.  AFTER CLEANING TO DETERMINE THE DEPTH OF	 THE DAMAGE, IT WAS DETERMINED BY DOWTY THAT THE PART WAS SCRAP BECAUSE THE DAMAGE WAS GREATER THAN .005 INCH DEEP IN ON	E AREA.  THE CORROSION WAS IN THE INNER BORE OF THE AXLE HOUSING.  LANDINGS, 3,402.				2	L	7	2 	4F			RT	A21EA
1998042400338	19980424	00338	CE  	1998	4	24	98ZZZX1543       	1	19980409	G	5210	551123516	HINGE ASSY      			CESSNA	500   	550         	2076604	CE  										CABIN DOOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	26496	4137 				5500607				CABIN DOOR REMOVED TO CHANGE BEARING ASSYS IN DOOR HINGE AND CORROSION DAMAGE WAS DISCOVERED IN HINGE. THIS IS MADE OF M	AGNESIUM AND THE CORROSION DAMAGE WOULD NOT BE REMOVED WITHOUT COMPROMISING THE HINGE INTEGRITY.  REASON FOR CORROSION W	AS LACK OF LUBRICATION IN THE BEARINGS.  THE LUBRICATION WAS NOT CALLED OUT IN THE INSPECTION GUIDE ALTHOUGH LUBE FOR LA	NDING GEAR TORQUE LINKS IS.  THIS CAUSED THE LUBE TO BE OVERLOOKED UNTIL IT WAS TOO LATE.			1	L	7	2 	4F				A22CE
1998042400339	19980424	00339	SO  	1998	4	24	98ZZZX1544       	2	19980323	G	8530		ROCKER BOSS     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					NR 2 CYL EXHAUST	FAILED          	D				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CL	CLIMB          	1			GL	13	21477	2766 	1315 			18261657	22281572R			ABOUT 4 MINUTES AFTER TAKEOFF, ENGINE RAN ROUGH.  A NORMAL LANDING WAS MADE.  REMOVED COWL, NR 2 VALVE COVER HAD A 1 INC	H HOLE IN IT.  REMOVED VALVE COVER AND FOUND BOTH ROCKER SHAFT FORGED BOSSES BROKEN FOR EXHAUST ROCKER SHAFT.  VALVE WAS	 NOT STUCK.  PUSH ROD WAS NOT BENT.  OLD AGE?				1	H	7	1 	3O	3	O	NT	TA13    	E273
1998050200002	19980502	00002		1998	5	2	98ZZZX1545       	4	19980306	G	6122	192103	FLYWEIGHT RING  	WOODWARD    	C210769     															GOVERNOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		1800 			1995461					PILOT COMPLAINT, COULD NOT MAINTAIN RPM'S.  UPON BENCH, FOUND THAT GOVERNOR WOULD GO 200 RPM'S ABOVE SPECS.  DISASSEMBLY	 REVEALED THAT THE RING HAD BROKEN AND ALLOWED THE FLY PIN TO COME OUT RESULTING IN ONE SIDE OF THE FLYWEIGHT TO BE STUC	K AND DISLOGED AND LAYING IN FLYWEIGHT CUP.  NO METAL WAS FOUND IN GEAR POCKETS, BUT ANY FURTHER OPERATION WOULD HAVE MU	LTIPLIED THE SEVERITY OF THIS PROBLEM.
1998042400341	19980424	00341	GL  	1998	4	24	98ZZZX1547       	3	19980409	G	6114		HUB             			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	23NC					402B0419		799902		BLADE SOCKET NR 1 HAS AN EDDY CURRENT INDICATION IN EXCESS OF MANUFACTURER'S SPECS.						1	L	7	2 	3O				A7CE    		5	C	P22EA
1998042400342	19980424	00342	EA  	1998	4	24	98ZZZX1548       	2	19980410	G	8520	11B200511DL	CRANKCASE       			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					NR 2 CYLINDER	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	2773V	3900 	1300 			177RG0694	L1537951A			DISCOVERED 5.50 INCH LONG CRACK ON CRANKCASE BELOW NR 2 CYLINDER FLANGE.  CRACK WAS APPROXIMATELY 1 INCH BELOW BOTTOM FL	ANGE OF CYLINDER AND FOLLOWED ENTIRE BOTTOM CIRCUMFERENCE OF CYLINDER.  CRACK WAS DISCOVERED AFTER PILOT REPORT OF A LAR	GE OIL LEAK FROM FORWARD LEFT SIDE OF COWLING AND STREAKING UNDER AIRCRAFT BELLY.				1	H	7	1 	3O	3	O		A20CE   	1E10
1998042400343	19980424	00343	CE  	1998	4	24	98ZZZX1549       	1	19980312	G	3230	081330046	TORQUE TUBE     			CESSNA	320   	320A        	2074506	CE  										NLG UPLOCK	FAILED          	G		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			EA	17	3038R	12920				320A0038				LANDING GEAR WAS RETRACTED.  40 MINUTES INTO FLIGHT, PILOT HEARD LOUD BANG.  AIRCRAFT LANDED WITH MAINS EXTENDED AND LOC	KED.  NOSE GEAR PARTIALLY RETRACTED.  UPON INSPECTION, FOUND UPLOCK TORQUE TUBE END STUD BROKEN OFF (.25 INCH - 28 STUD.	  NEW VERSIONS HAVE .3125 INCH STUD).  SUBMITTER RECOMMENDED INSTALLING BEEFIER UNIT.				1	L	7	2 	3O				3A25
1998042400344	19980424	00344		1998	4	24	98ZZZX1550       	4	19980331	G	6113	87325	BULKHEAD        			PIPER 	PA28  	PA28161     	7102803	SO  						SNSNCH	74D	74DM        	EA  	PROP SPINNER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	38581					287716270		A50509		PROPELLER SPINNER FRONT BULKHEAD CRACKED, TWO PLACES.						1	L	7	1 	3O				2A13    		5	N	P88614
1998042400345	19980424	00345	SO  	1998	4	24	98ZZZX1551       	1	19980326	G	7120	8401002	MOUNT           			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					FIREWALL RT	CRACKED         	B		A	BONR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	40PM	1664 				4608005	273699R			DURING ANNUAL INSPECTION, FOUND ENGINE MOUNT CRACKED ON RT SIDE.  CRACK IS LOCATED WHERE NLG HYDRAULIC ACTUATOR ATTACHES	 TO MOUNT.  DESIGN REQUIRES ACTUATOR TO BE POSITIONED SUCH THAT IT STRESSES THE MOUNT.					1	L	7	1 	3O	3	O		A25SO   	E8CE
1998042400348	19980424	00348	CE  	1998	4	24	98ZZZX1554       	1	19980301	G	3710	B904	HOSE            			CESSNA	172   	172P        	2072436	CE  										VACUUM SYSTEM	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	54413	7211 				17274970				VACUUM SYSTEM HOSE BELIEVED TO BE FACTORY INSTALLED HAD A VACUUM LEAK.  TROUBLESHOOTING, HOSE APPEARED OK UNTIL WIGGLED 	BY HAND.  CRACKS IN HOSE APPEARED AND INTERNAL HOSE MATERIAL DISINTEGRATED.					1	H	7	1 	3O			NT	3A12
1998042400349	19980424	00349	CE  	1998	4	24	98ZZZX1555       	1	19980327	G	5511	16962000159	SPAR            		169620001603	BEECH 	23    	C23         	1151242	CE  										STAB HINGE ATT	CRACKED         	B	S	A	AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6014F	6404 				M2107				CRACKS IN STABILATOR MAIN SPAR ADJACENT TO FUSELAGE HINGE ATTACHMENT FITTINGS.  AIRCRAFT USED FOR FLIGHT TRAINING.  CRAC	KS DUE TO FATIGUE.  SUBMITTER RECOMMENDED DETAILED INSPECTION OF THIS AREA AT EACH INSPECTION INTERVAL.					1	L	7	1 	3O				A1CE
1998042400350	19980424	00350	CE  	1998	4	24	98ZZZX1556       	1	19980406	G	2750	51220465	BRACKET         			CESSNA	414   	414A        	2075907	CE  										LT FLAP PULLEY	CORRODED        	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911LD	5129 				414A0461				OUTBOARD FLAP BELLCRANK BRACKET BOLT HOLE IS CORRODED AND ELONGATED.  BRACKET IS NEAR EXHAUST SLIP STREAM AND POSSIBLE R	EASON FOR THIS FAILURE.					1	L	7	2 	3O				A7CE
1998050200003	19980502	00003	CE  	1998	5	2	98ZZZX1559       	1	19980404	G	3246	D301185	WHEEL           			CESSNA	185   	A185F       	2072821	CE  										MLG	FAILURE         	D		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			AL	03	9620Q	1432 				18503780				DURING LANDING, THE ALUMINUM WHEEL BROKE CAUSING A COMPLETE FAILURE OF THE WHEEL AND BRAKE ASSEMBLY.  REASON FOR FAILURE	 IS UNKNOWN.  SUBMITTER RECOMMENDED A THOROUGH VISUAL INSPECTION OF THE WHEEL HALVES AND CHECK FOR PROPER TORQUE ON THE 	WHEEL BOLTS DURING AN ANNUAL INSPECTION.				1	H	7	1 	3O				3A24
1998042400353	19980424	00353	SW  	1998	4	24	98ZZZX1560       	1	19980225	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  										LT FLAP	BROKEN          	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	8638V					16275				DURING ANNUAL INSPECTION, LEFT AND RIGHT FLAP CABLES WERE FOUND WITH NUMEROUS BROKEN STRANDS WHERE THEY PASS OVER THE P/	N 1-2395 PULLEYS AT THE LEFT AND RIGHT WING ROOTS.  THE LEFT CABLE HAD BEEN REPLACED (DUE TO BREAKING AT THIS LOCATION) 	APPROXIMATELY 800 HOURS PREVIOUSLY IN 1993.  CAUSE OF THIS DEFECT APPEARS TO BE DUE TO THE STIFFNESS OF THE CABLE COUPLE	D WITH RIGGING OVER A SMALL DIAMETER (APPROX .75 INCH GROOVE DIA) PULLEY.			1	H	7	1 	3O			 	A21CE
1998042400354	19980424	00354	SW  	1998	4	24	98ZZZX1561       	1	19980225	G	2750	19023	CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  										RT FLAP	BROKEN          	B		A	AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	8638V					16275				DURING ANNUAL INSPECTION, LEFT AND RIGHT FLAP CABLES WERE FOUND WITH NUMEROUS BROKEN STRANDS WHERE THEY PASS OVER THE P/	N 1-2395 PULLEYS AT THE LEFT AND RIGHT WING ROOTS.  THE LEFT CABLE HAD BEEN REPLACED (DUE TO BREAKING AT THIS LOCATION) 	APPROXIMATELY 800 HOURS PREVIOUSLY IN 1993.  CAUSE OF THIS DEFECT APPEARS TO BE DUE TO THE STIFFNESS OF THE CABLE COUPLE	D WITH RIGGING OVER A SMALL DIAMETER (APPROX .75 INCH GROOVE DIA) PULLEY.			1	H	7	1 	3O			 	A21CE
1998042400768	19980424	00768	CE  	1998	4	24	98ZZZX1581       	1	19980413	G	5741		BOLT            			BEECH 	65    	65          	1152802	CE  										LT WING PANEL	CORRODED        	B	L		UE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	9546Q	1100 				LC231				IN C/W AD 85-22-05, WING BOLT REJECTED DUE TO MINUTE GALLING CORROSION SPOT IN THE INNER RADIUS.  BOLT REMOVED FROM THE 	LT LOWER FORWARD OUTER WING PANEL ATTACHMENT.					1	L	7	2 	3O				3A20
1998042400769	19980424	00769	SO  	1998	4	24	98ZZZX1582       	2	19980408	G	8530		CYLINDER        								CONT  	O520  	TSIO520H    	17040	SO  					NR 2	SEPARATION      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		1100 					506111			INSPECTION FOUND NR 2 CYLINDER SEPARATED BETWEEN BORE AND HEAD.											3	O			E8CE
1998042400770	19980424	00770		1998	4	24	98ZZZX1583       	4	19980411	G	2561	S8200	LIFE VEST       	SWITLIK     																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					8117411					LIFE VEST FAILED 2 PSI TEST.
1998042400771	19980424	00771		1998	4	24	98ZZZX1584       	4	19980411	G	2561	P0201101	LIFE VEST       	EAAEROMARINE																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					D04209					LIFE VEST FAILED 2 PSI TEST.
1998042400772	19980424	00772		1998	4	24	98ZZZX1585       	4	19980411	G	2561	AD7	LIFE VEST       	AIRCRUISERS 																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					4893					LIFE VEST FAILED 2 PSI TEST.
1998042400773	19980424	00773		1998	4	24	98ZZZX1586       	4	19980411	G	2561	H2L8	LIFE VEST       	PATTENPAN   																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					12086					LIFE VEST MFG DEC 1975, MATERIAL DRY, ROTTEN.  FAILED 2 PSI TEST.
1998042400774	19980424	00774		1998	4	24	98ZZZX1587       	4	19980411	G	2561	5MV2102	LIFE VEST       	JCRIND      																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					110					LIFE VEST FAILED 2 PSI TEST.
1998042400775	19980424	00775		1998	4	24	98ZZZX1588       	4	19980411	G	2561	P0201105	LIFE VEST       	EAAEROMARINE																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					G03467					LIFE VEST FAILED 2 PSI TEST.
1998042400776	19980424	00776		1998	4	24	98ZZZX1589       	4	19980411	G	2561	5MV2102	LIFE VEST       	JCRIND      																	FAILED          	B			KQ1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	07					106					LIFE VEST FAILED 2 PSI INFLATION TEST.
1998042400777	19980424	00777	EA  	1998	4	24	98ZZZX1590       	2	19980401	G	7310	LW120980140	TUBE ASSY       			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR 1 CYLINDER	BROKEN          	D				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			SO	16	191ER					243252	L2550151A			THE PILOT REPORTED A ROUGH ENGINE AND MADE A PRECAUTIONARY LANDING.  THE NR 1 CYLINDER FUEL INJECTOR LINE WAS BROKEN AT 	THE CYLINDER END.  RAW FUEL WAS BEING SPRAYED ON THE ENGINE AS IT WAS RUNNING.  THERE WAS NO FIRE.  THIS IS A COMMON PRO	BLEM ON THIS INSTALLATION (NR 1 CYL).  AD 93-02-05 IS C/W AT EACH 100-HOUR INSPECTION.				1	L	7	1 	3O	3	O		2A3     	1E10
1998042400778	19980424	00778		1998	4	24	98ZZZX1591       	1	19980311	G	4920	161103101	HOUSING         	SUNDSTRANDEM	T62T40C3A   															APU COMBUSTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25		820  			881811					DURING APU HOT SECTION INSPECTION AND REPAIR DISASSEMBLY, MECHANIC FOUND A 10 INCH CRACK IN THE HOUSING AND 2 OTHERS, .7	50 INCH AND .385 INCH, IN THE SAME PLANE.  CRACKS WERE LOCATED ADJACENT TO THE SPOT WELDS FOR THE AIR EXIT PLENUM DOUBLE	R.  THE APU IS LOCATED IN A CONTAINMENT BOX IN A CITATION III TAIL SECTION.  THE INSTALLATION IS INACCESSIBLE REQUIRING 	36 TO 40 MAN HOURS TO REMOVE AND INSTALL.  THE MANUFACTURER HAS CHANGED THE MATERIAL USED TO MANUFACTURE THIS PART ON OT	HER MODELS, BUT HAS NOT DONE SO ON THIS MODEL.
1998042400779	19980424	00779	CE  	1998	4	24	98ZZZX1592       	1	19980325	G	3260	JE6	ARM             			CESSNA	340   	340A        	2076405	CE  										MLG SWITCH	FAILED          	D				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			SO	15	2681Y	3000 				340A1530				ARM P/N JE6 ACTIVATES GEAR DOWN MICROSWITCH.  LEAF BROKE, UNSAFE GEAR CONDITION SIGNALED, AIRCRAFT LANDED WITHOUT INCIDE	NT AFTER COMPLETING 'UNSAFE GEAR' CHECK LIST.					1	L	7	2 	3O				3A25
1998042400780	19980424	00780	EA  	1998	4	24	98ZZZX1593       	2	19980301	G	7414	4771	MAGNETO         	SLICK       		CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG LT MAG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	269CJ	45   			9603001	17259512	2841827A			MAGNETO WAS INSTALLED AS A NEW UNIT WITH STC SE419CH ON THIS AIRCRAFT ON 4-28-97.  THE STC IS THE UNISON ELECTRONIC IGNI	TION SYSTEM.  DURING THE MAG CHECK WITH THE ENGINE RUNNING AND THE MAG SWITCH IN THE LEFT POSITION, THE ENGINE QUIT.  OP	ERATION WAS NORMAL IN RIGHT MAG OR BOTH POSITIONS.  AFTER CONTACTING UNISON, THEY SENT A NEW MAG AND SUGGESTED CHANGING 	THE UNIT OUT.  AFTER THIS WAS DONE WITH A NEW MAG, THE OPERATIONAL CHECK OF THE SYSTEM WAS NORMAL.  THE UNSERVICEABLE MA	G WAS RETURNED TO UNISON.		1	H	7	1 	3O	3	O	NT	3A12    	E274
1998042400781	19980424	00781	SO  	1998	4	24	98ZZZX1594       	1	19980406	G	8011	MZ4222R	STARTER         	PRESTOLITE  		PIPER 	PA28  	PA28R200    	7102811	SO  										ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3091T				ESI7092299	28R7235312				STARTER MOTOR ATTACHED WITH NON-'AN' HARDWARE TO REDUCTION GEAR ASSY.  ALL  NR 10 ATTACH HARDWARE SHEARED, MOTOR SEPARAT	ED FROM GEAR ASSY.  STARTER FAILED.					1	L	7	1 	3O				2A13
1998042400782	19980424	00782	CE  	1998	4	24	98ZZZX1595       	1	19980330	G	2140	44008	SOLENOID        		B4500       	BEECH 	76    	76          	1153005	CE  										HEATER FUEL	LEAKING         	B		A	BF8R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	3812C	460  			A96100081	ME390				INTERMITTENT HEATER OPERATION FOUND FUEL SOLENOID LEAKING THROUGH SAME HOLE IN SIDE OF SOLENOID THAT THE WIRING COMES OU	T OF.  FUEL PUDDLED UP IN DRAIN PAN, THEN DRAINED OVERBOARD.  FUEL OVERBOARD DRAIN IS LOCATED DIRECTLY IN FRONT OF EXHAU	ST.				1	L	7	2 	3O				A29CE
1998042400783	19980424	00783	SO  	1998	4	24	98ZZZX1596       	1	19980408	G	7120		BOLTS           			PIPER 	PA28  	PA28R201T   	7102813	SO  										ENGINE MOUNT	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	47642					28R7703413				FOUND BOTH LOWER BOLTS THAT SECURE ENGINE MOUNT TO AIRFRAME WERE TIGHTENED ALL THE WAY TO BOLT SHOULDER, BUT LOOSE IN PA	RT.  STILL HAD 'TORQUE SEAL' PAINT ON NUT.  REMOVED BOLTS, INSPECTED, REINSTALLED WITH ADDITIONAL WASHERS.					1	L	7	1 	3O				2A13
1998042400784	19980424	00784	EA  	1998	4	24	98ZZZX1597       	2	19980414	G	8530	SLC10311	CYLINDERS       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	714TG	1578 				15279415	L1740815			WHILE INVESTIGATING AN OIL LEAK, STAINS WERE NOTED ON THE LOWER SIDE OF THE ENGINE CYLINDERS.  THE 4 EACH CYLINDERS WERE	 REMOVED FOR FURTHER INVESTIGATION AND CRACKS WERE NOTED APPROXIMATELY 1.25 INCHES DOWN FROM THE BARREL TO END.  THE CRA	CKS WERE ON THE UPPER SURFACE (PUSH ROD SIDE).  THE CYLINDERS WERE RETURNED TO THE MANUFACTURER FOR FURTHER EVALUATION.				1	H	7	1 	3O	3	O	NT	3A19    	E223
1998042400785	19980424	00785	CE  	1998	4	24	98ZZZX1598       	1	19980328	G	2430		DIODE           			CESSNA	337   	337G        	2075730	CE  										DC POWER SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	72324	1500 				33701561				POWER DIODE FAILED CAUSING DAMAGE TO:  REGULATOR, ALTERNATOR, AUTOPILOT.  RECOMMEND REPLACING BOTH DIODES WITH HEAVIER D	UTY (HIGHER CAPACITY) DIODES.					1	H	7	2 	3O				A6CE
1998042400786	19980424	00786	CE  	1998	4	24	98ZZZX1599       	1	19980402	G	7430	C2925010105	SWITCH          	GERDES      	A510        	CESSNA	210   	210M        	2073450	CE  										IGNITION	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	6265B	2957 				21062727				IGNITION SWITCH, MODEL A-510.  KEY CAN BE REMOVED AND FALLS OUT IN ALL POSITIONS.  RECOMMEND RE-PUBLISHING WARNING FOR M	ECHANICS TO CHECK FOR THIS CONDITION AT EVERY INSPECTION.					1	H	7	1 	3O				3A21
1998042400787	19980424	00787	CE  	1998	4	24	98ZZZX1600       	1	19980327	G	5511	16962000159	SPAR            		16962001603 	BEECH 	23    	C23         	1151242	CE  										STABILATOR HINGE	CRACKED         	B	S		AKGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6349C	3875 				M2371				CRACK IN STABILATOR MAIN SPAR ADJACENT TO FUSELAGE HINGE ATTACH FITTINGS AIRCRAFT USED FOR FLIGHT TRAINING.  CRACK DUE T	O FATIGUE.  SUBMITTER RECOMMENDED DETAILED INSPECTION OF THIS AREA AT EACH INSPECTION INTERVAL.					1	L	7	1 	3O				A1CE
1998042400788	19980424	00788	GL  	1998	4	24	98ZZZX1601       	3	19980402	G	6110		BLADE CONTROL   			PIPER 	PA28  	PA28140     	7102802	SO  						MCAULY	D3A34	D3A34C402   	GL  	PROP NR 2 BLADE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	7327F	38   				2825236		972424		DURING ANNUAL INSPECTION, DISCOVERED NR 2 BLADE CAN BE ROTATED, BY HAND, THROUGH FULL RANGE OF BLADE ANGLES.  MCCAULEY S	USPECTS A LINK OR THE PROP CONTROL MECHANISM MAY BE BROKEN.  MCCAULEY TO INVESTIGATE ONCE THEY RECEIVE PROPELLER INTO SH	OP.				1	L	7	1 	3O				2A13    		5	C	P47GL
1998042400789	19980424	00789	CE  	1998	4	24	98ZZZX1602       	1	19980327	G	2510	S1021Z68	SCREW           		0413034200  	CESSNA	150   	150G        	2071816	CE  										GLOVE BOX	MISSING         	B			MOGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	8311J					15066211				DURING ANNUAL INSPECTION, A SMALL HOLE WAS FOUND IN RIGHT SIDE OF FORWARD FUSELAGE BELOW WINDSHIELD.  PER CESSNA SB SB 6	8-16, THIS BOLT IS FOR SCREW THAT SUPPORTS FORWARD END OF GLOVE BOX.  THIS HOLE WAS PAINTED OVER SHOWING SCREEN HAD BEEN	 MISSING SINCE LAST REPAINT IN 1994.  NOTE:  AD 67-31-04 REQUIRES REMOVAL OF GLOVE BOX.  GLOVE BOX IS INSTALLED WITH FOR	WARD END UNSUPPORTED.  NO LOG ENTRY INDICATING AD HAD EVER BEEN C/W.  NOTIFIED OWNER.			1	H	7	1 	3O			 	3A19
1998042400790	19980424	00790	CE  	1998	4	24	98ZZZX1603       	1	19980327	G	5412	04531142	FIREWALL        		04530012    	CESSNA	150   	150G        	2071816	CE  										ENG MT AREA	BUCKLED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8311J	3384 				15066211				FOUND FIREWALL BUCKLED HEAVILY ALL THE WAY ACROSS APPROXIMATELY 8 INCHES FROM BOTTOM.  ALSO, BUCKLED AT ALL ENGINE MOUNT	 LOCATIONS.  NOTIFIED OWNER.					1	H	7	1 	3O				3A19
1998042400791	19980424	00791	CE  	1998	4	24	98ZZZX1604       	1	19980327	G	2810	04265126	STRAP           			CESSNA	150   	150G        	2071816	CE  										LT WING TANK	FAILED          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8311J	3384 				15066211				DURING ANNUAL INSPECTION, FOUND LEFT FUEL TANK AFT MOUNTING STRAP BROKEN.  NOTIFIED OWNER.						1	H	7	1 	3O				3A19
1998042400792	19980424	00792	CE  	1998	4	24	98ZZZX1605       	1	19980327	G	5412	04531073	ANGLE           		04530012    	CESSNA	150   	150G        	2071816	CE  										FIREWALL LT FWD	FAILED          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8311J	3384 				15066211				DURING ANNUAL INSPECTION, FOUND ANGLE WHICH MOUNTS FIREWALL TO FUSELAGE BUCKLED AND POORLY REPAIRED.  DAMAGE EXTENDED FR	OM 7 O'CLOCK TO 10 O'CLOCK POSITIONS.  THE REPAIR CONSISTED OF AN ANGLE DOUBLER WITH RIVETS PASSING THROUGH BEND RADIUS 	AND ZERO EDGE DISTANCE.  NOTIFIED OWNER.  NO DOCUMENTATION OR REPAIR FOUND.				1	H	7	1 	3O				3A19
1998042400793	19980424	00793	CE  	1998	4	24	98ZZZX1606       	1	19980413	G	2432	RG35XC	BATTERY         			BBAVIA	8     	8KCAB       	2110612	CE  										CASE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	8751V				CBC309557	20075				BATTERY CASE CRACKED ON BOTH SIDES OF CELL BELOW POSITIVE POST.  CRACKS STARTED FROM FACTORY SEAM DOWN ALMOST TO BOTTOM.	  CRACKS APPEAR EQUAL ON BOTH SIDES.  LESS THAN 20 HOURS SINCE NEW.  POSSIBLE INTERNAL SHORT CAUSED EXPLOSION.					1	H	7	1 	3O				A21CE
1998042400794	19980424	00794	EU  	1998	4	24	98ZZZX1607       	1	19980406	G	5753	25WF218AH	FLAP            			HWKSLY	DH125 	DH1253ARA   	423013P	EU  										RT SIDE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	55G		122  			NA709				DURNG A SCHEDULED INSPECTION OF THE AIRCRAFT, THE TOP SKIN OF THE RIGHT FLAP WAS INSPECTED AND THREE CRACKS WERE NOTED F	ROM 3 RIVETS.  THE LOCATION OF THE CRACKS WAS APPROX 103 INCHES FROM THE OTBD EDGE AND APPROX 7 INCHES FROM THE TRAILING	 EDGE.  CAUSE UNKNOWN.  THE CRACKS WERE .1875 INCH, .6250 INCH, AND .75 INCH IN LENGTH.  TO BE REPAIRED IAW SRM.				2	L	7	2 	4J				A3EU
1998042400795	19980424	00795	CE  	1998	4	24	98ZZZX1608       	1	19980226	G	3233	23927005	SEAL            		232710012   	LEAR  	35    	35A         	5170602	CE  										MLG ACTUATOR	FAILED          	H				L	O			ABORTED APPROACH        	OTHER                   			J			WARNING INDICATION        			AP	APPROACH       	1			NM	03	925DM	4708 			3718	486				ACTUATOR SLOW TO LOCK IN (EXTENDED) 'GEAR DOWN' POSITION.  LANDING GEAR POSITION DETERMINED TO BE UNLOCKED DURING APPROA	CH TO LANDING.  SEVERAL CYCLES OF LANDING GEAR WERE ATTEMPTED.  EVENTUALLY, THIS ACTUATOR DID FULLY EXTEND AND INDICATED	 A 'SAFE' CONDITION TO LAND.  GEAR ACTUATOR SENT TO LEARJET FACTORY.  DISCREPANCY WAS CONFIRMED.  SEALS INSIDE ACTUATOR 	WERE FOUND SWOLLEN.  REPLACED SEALS.  FUNCTIONAL CHECKED NORMAL.			2	L	7	2 	4F				A10CE
1998042400796	19980424	00796	CE  	1998	4	24	98ZZZX1609       	1	19980413	G	5400	B300	NACELLE         			BEECH 	B300  	B300        	1159232	CE  										OIL COOLER INT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	227KM				FL91	FL91				SMALL CRACK DISCOVERED AT LOWER RT CORNER OF ENGINE NACELLE AT OIL COOLER INTAKE.  VIBRATION RUB AREA ADJACENT TO CRACK 	WAS DOWN TO BARE METAL.					2	L	7	2 	4T			RT	A24CE
1998042400797	19980424	00797	GL  	1998	4	24	98ZZZX1610       	3	19980403	G	6114	A1891A	PILOT TUBE      			AYRES 	S2    	S2RT34NORMAL	0970106	SO  						HARTZL	HCB3T	HCB3TN3     	GL  	PROP HUB	DISPLACED       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2256L	512  				T34232		BUA20089		REMOVED PROPELLER TO REPLACE BROKEN LINK PIN UNIT.  FOUND CORROSION ON BLADE.  UPON FURTHER INSPECTION, FOUND CORROSION 	ON ALL THREE BLADES AND ANOTHER BROKEN SCREW IN ANOTHER LINK PIN  UNIT.  AFTER DISASSEMBLY, A PILOT TUBE WAS FOUND OUT O	F POSITION.  PROP HUB WAS SENT BACK TO FACTORY FOR REPAIR.  SCREWS LOOK LIKE THEY WERE OVERTORQUED.  THE PILOT TUBE DID 	NOT HAVE ENOUGH PITCH TO HOLD IT IN POSITION.  SUBMITTER STATED MANUFACTURER NEEDS TO CHECK THEIR QUALITY CONTROL AND MA	NUFACTURE ASSY PROCEDURES.		1	L	7	1 	3T				A3SW    		6	C	P15EA
1998042400798	19980424	00798	NM  	1998	4	24	98ZZZX1611       	1	19980414	G	5210	001A521B0501000	HINGE           			DORNER	DO32  	DO328100    	2996000	NM  										PAX DOOR AFT	CRACKED         	B	S		VH2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	328PH	7392 				3006				PASSENGER DOOR HINGE WAS CRACKED APPROXIMATELY .5 INCH THROUGH OUTER LEG FLANGE TO EDGE OF PART.  CRACK OCCURRED AT WEB 	A REA CLOSET TO THE AIRCRAFT AND HINGE ATTACH POINT.					2	H	7	2 	4T			RT	A45NM
1998042400799	19980424	00799	NM  	1998	4	24	98ZZZX1612       	2	19980126	G	7210		TRANSFER TUBE   			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315251K 		NM  					NOSE CASE OIL	BROKEN          	B			HAXR	E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			SW	11	76WA					11342	P06944			CHIP LIGHT CAME ON IN-FLIGHT (VIBRATION).  ENGINE SHUT DOWN IN-FLIGHT.  FOUND METAL IN OIL SAMPLE.  REMOVED NOSE CASE, F	OUND OIL TRANSFER TUBE BROKEN OFF, BROKEN RING GEAR, AND ALL PLANETARY GEARS DAMAGED.  SENT ENGINE TO AIRSEARCH FOR REPA	IR.   188.5 HOURS AFTER GEARBOX INSPECTION.				1	H	7	2 	3T	4	T		2A4     	E2WE
1998050100001	19980501	00001	CE  	1998	5	1	98ZZZX1614       	1	19980327	G	2841	00238100215	SIGHT GAUGE     			BEECH 	36    	B36TC       	1151609	CE  										RT FUEL QTY	STUCK           	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	11	1525M					EA464				RIGHT FUEL TANK SIGHT GAUGE STUCK AT 35 GALLONS.  REMOVED AND REPLACED SIGHT GAUGE.  SUGGEST DURING ANNUAL INSPECTION, C	HECK FOR CORRECT OPERATION OF SIGHT GAUGES.					1	L	7	1 	3O				3A15
1998050100002	19980501	00002	CE  	1998	5	1	98ZZZX1615       	1	19980327	G	2842	58938000113	TRANSMITTER     			BEECH 	36    	B36TC       	1151609	CE  										FUEL QUANTITY	WRONG PART      	D	L	A		A				UNSCHED LANDING         				W	Y		INADEQUATE Q C            	ENGINE STOPPAGE           		CR	CRUISE         	1			GL	11	1525M					EA464				FUEL STARVATION PROBLEM FOUND TO BE DUE TO INCORRECT FUEL QUANTITY TRANSMITTER HAD BEEN INSTALLED.						1	L	7	1 	3O			 	3A15
1998050100003	19980501	00003	SO  	1998	5	1	98ZZZX1616       	1	19980411	G	2910	JH23012	HOSE            			LKHEED	1329  	132923E     	5263116	SO  										NR 1 HYD SYSTEM	FAILED          	D				E				ENGINE SHUTDOWN         				J	K		WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			EA	03	511TS					5101				AIRCRAFT LOST NR 1 HYDRAULIC PRESSURE IN-FLIGHT.  ENGINE SHUT DOWN TO AVOID ANY MORE PROBLEMS TO PUMP.  FOUND HOLE IN LT	 MLG ACT HYD HOSE (EXTEND) WOULD NEVER KNOW SINCE HOSE HAS METAL SLEEVING ON IT.  NO RECORD OF HOSE BEING CHANGED AND NO	 REQUIREMENT IN MM TO CHANGE.  SUSPECT CAUSE IS AGE AND RECOMMEND THIS PART BE CHANGED EVERY 2,000 HOURS OR 3 YEARS.				2	L	7	4 	4J				2A15
1998050100005	19980501	00005	GL  	1998	5	1	98ZZZX1618       	2	19980409	G	7532	2305317	BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			LS1R	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	13	1097J		1360 			900801D	CAE833805			ENGINE WOULD NOT MAKE POWER.  PERFORMANCE RUN FOUND ENGINE RUNNING WITH EXCESSIVELY HIGH TOT.  BLEED VALVE REPLACED, PER	FORMANCE CHECK OK, ACFT RETURNED TO SERVICE.  CNTRL NR 98-4-6.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998050100006	19980501	00006	GL  	1998	5	1	98ZZZX1619       	2	19980409	G	7323	23057870	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					POWER TURBINE	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J		301  			90081D	CAE833805			PT GOVERNOR WAS SURGING BELOW LIMITS.  PT GOVERNOR REPLACED, OPS CHECK OK.  AIRCRAFT RETURNED TO SERVICE.  CNTRL NR 98-4	-5.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998050100007	19980501	00007	GL  	1998	5	1	98ZZZX1620       	2	19980409	G	7322	23056936	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEFECTIVE       	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX		1730 			2872	CAE833239			FUEL CONTROL BEARING - BLUE GREASE WASHED OUT.  SENT FOR REPAIR.  CNTRL NR 98-4-7.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998050100008	19980501	00008	SW  	1998	5	1	98ZZZX1621       	1	19980318	G	6230	206010336005	LINK ASSY       			BELL  	206   	206L1       	1182107	SW  										PYLON	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EXCESSIVE PLAY AT TWO PLACES.  SEE BELL MM L-3 FIG 62.21.  AT TEAR DOWN FOUND LINK ASSY BEARINGS AND SPACERS WORN BEYOND	 LIMITS, TOTAL TIME OF PARTS LESS THAN 1,000 HRS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998050100009	19980501	00009		1998	5	1	98ZZZX1622       	1	19980401	G	2821	0A876299	CARTRIDGE SQUIB 	KIDDE       	89575201    															FIRE EXT	FAILED          	H	P	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	06										CARTRIDGE FAILED RUPTURE DISC, OF FIRE EXTINGUISHER.  SUSPECT CAUSE:  CARTRIDGE FAILED TO RUPTURE DISC BECAUSE OF INSUFF	ICIENT EXPLOSIVE ENERGY IN OVERLAND AVIATION MANUFACTURED CARTRIDGE.  CARTRIGE IS NOT AN APPROVED (OEM) WALTER KIDDE AER	OSPACE COMPONENT.  RECOMMENDATION:  USE ONLY OEM APPROVED PARTS.
1998050100010	19980501	00010	SO  	1998	5	1	98ZZZX1623       	1	19980325	G	3213	67035	HOUSING         			PIPER 	PA28  	PA28R200    	7102811	SO  										LT MLG STRUT	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	9375N					28R35084				ROUTINE LUBE OF GEAR FOUND BROKEN LT LANDING GEAR FORWARD SWIVEL SHAFT.  CASTING SHOULD HAVE LARGE RADIUS AT AREA USING 	A BEARING SPACER WITH A MATCHING INSIDE RADIUS.  CAUSE - HARD LANDINGS/STRESS CONCENTRATION.					1	L	7	1 	3O				2A13
1998050100011	19980501	00011	CE  	1998	5	1	98ZZZX1624       	1	19980408	G	2710	0510105260	CONTROL CABLE   			CESSNA	172   	172P        	2072436	CE  										RT AILERON	FRAYED          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	62348	11700				17275254				DURING INCORPORATION OF SK 172-149 KIT TO C/W SB 97-1, FOUND RT AILERON DIRECT CABLE FRAYED WHERE IT TRAVELS UNDER THE R	T OUTBOARD PULLEY LOCATED AT THE LOWER AFT DOOR FRAME AREA.  THIS IS A VERY DIFFICULT AREA TO INSPECT DURING ROUTINE INS	PECTIONS.  THE FRAYING WAS ONLY VISIBLE ONCE THE PULLEY WAS REMOVED.  AT LEAST 8 BROKEN STRANDS, 16 ENDS, WERE VISIBLE. 	 SUBMITTER RECOMMENDED REMOVING PULLEYS EVERY 5,000 HOURS OR INSTALL INSPECTION PANELS AFT OF THE PULLEY FOR PROPER INSP	ECTION.		1	H	7	1 	3O			NT	3A12
1998050100012	19980501	00012	SO  	1998	5	1	98ZZZX1625       	1	19980413	G	3213	6792617	TRUNNION        			PIPER 	PA28  	PA28R201    	7102816	SO  										RT MLG STRUT	CRACKED         	B			OG5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	170ND	7773 				2837005				PILOT REPORTED FLUID LEAKING FROM RIGHT STRUT ON AFT SIDE OF TRUNNION.  FOUND CRACKED AT LOWER END OF WEB AREA.  CRACK A	PPROXIMATELY .75 INCH LONG RUNNING LATERALLY EACH WAY FROM WEB.  INSTALLED NEW ASSEMBLY.  PLACED WATCH ON OTHER AIRCRAFT	 IN FLEET.				1	L	7	1 	3O				2A13
1998050100013	19980501	00013	EA  	1998	5	1	98ZZZX1626       	2	19980414	G	8510	LW10551	RING GEAR       			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					STARTER	WRONG PART      	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	4149Y	43   				2843128	L3592736A			DURING ROUTINE INSPECTION, MECHANIC NOTICED THERE WAS ABNORMAL AMOUNT OF WEAR ON THE STARTER RING GEAR FOR ONLY HAVING 4	3 HOURS TT ON THE PART.  UPON FURTHER INSPECTION, FOUND THE WRONG P/N RING GEAR INSTALLED.  THE CORRECT RING GEAR IS P/N	 72566 WHICH IS FOR A RT ROTATING ENGINE. THE P/N LW-10551 RING GEAR IS FOR A LT ROTATING ENGINE.  THIS IS EVIDENCED WHI	LE SITTING IN THE PILOT SEAT, THE RING GEAR BEVEL (CHAMFER SIDE) SHOULD BE ON THE RIGHT SIDE FOR RT ROTATION, AND LEFT S	IDE FOR LT ROTATION.  ALTHOUGH THERE WERE WEAR MARKS, SYSTEM OPERATIONS WERE NORMAL.		1	L	7	1 	3O	3	O	 	2A13    	E286
1998050100014	19980501	00014	CE  	1998	5	1	98ZZZX1627       	1	19980119	G	8010	S15771	SOLENOID        			CESSNA	182   	R182        	2072734	CE  										STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	511CC					R18200979				OWNER COMPLAINED OF STARTER BENDIX HARD TO ENGAGE.  ON INSP, TURNED ON MASTER SWITCH AND ENGINE STARTED CRACKING.  START	ER SOLENOID WAS STUCK ENGAGED.  REPLACED STARTER SOLENOID P/N S1577-1.  MASTER SOLENOID LOOKED BURNED, SO IT WAS REPLACE	D WITH P/N S1580-1.  CHECKED BATTERY AND FOUND IT VERY LOW ON WATER, THE CASE WAS WARPED AND THE TERMINALS BLACK AND PAR	TIALLY MELTED.  BELIEVE THE STARTER SOLENOID WAS ENGAGED IN-FLIGHT WHICH CAUSED THE BATTERY TO OVERHEAT.  REPLACED BATTE	RY AND STARTER BENDIX.  THE SOLENOIDS ARE LOCATED CLOSE TO THE RT MUFFLER WHICH SEEMS TO CAUSE EXCESSIVE HEAT ON THEM.		1	H	7	1 	3O			RT	3A13
1998050100015	19980501	00015	CE  	1998	5	1	98ZZZX1628       	1	19980327	G	5511	16962000159	SPAR            		169620001603	BEECH 	23    	C23         	1151242	CE  										H STAB HINGE	CRACKED         	B	S	A	YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	5167M	7987 				M2043				CRACKS IN STABILATOR MAIN SPAR ADJACENT TO FUSELAGE HINGE ATTACHMENT FITTING.  THIS AIRCRAFT IS USED FOR FLIGHT TRAINING	.  CRACKS POSSIBLY DUE TO FATIGUE.  RECOMMEND DETAILED INSPECTION OF THIS AREA AT EACH INSPECTION INTERVAL.					1	L	7	1 	3O				A1CE
1998050100016	19980501	00016	CE  	1998	5	1	98ZZZX1629       	1	19980223	G	5511	04320049	BRACKET         			CESSNA	150   	152         	2071835	CE  										H STAB SPAR AFT	CRACKED         	H		A	D6VV	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	757WN	6500 				15280063				CRACK FOUND DURING ROUTINE 100 HOUR INSPECTION.  CRACK FOUND IN BRACKET ASSY THAT ATTACHES TO REAR SPAR OF HORIZONTAL ST	ABILIZER WHICH ALSO HOUSES FITTING FOR ELEVATOR.  SUBMITTER RECOMMENDATIONS:  CLOSE INSPECTION OF AREA TO POSSIBLY INCLU	DE DYE PENETRANT AFTER PAINT REMOVAL.				1	H	7	1 	3O			NT	3A19
1998050100017	19980501	00017	CE  	1998	5	1	98ZZZX1630       	1	19980324	G	3213	19805	U-BOLT          			BBAVIA	8     	8KCAB       	2110612	CE  										RT MLG LEG	BROKEN          	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	90965	1277 				6073				UPON LANDING, PILOT NOTED RIGHT MAIN LANDING GEAR WHEEL AND GEAR LEG MOVING BACK AND FORTH APPROXIMATELY 12 INCHES.  FOU	ND BROKEN U-BOLT WHERE THE LANDING GEAR LEG COMES OUT OF THE FUSELAGE.  U-BOLT BROKEN AT THE REAR.					1	H	7	1 	3O				A21CE
1998050800004	19980508	00004	NM  	1998	5	8	98ZZZX1633       	1	19980420	G	5312	BOE20030031	SEAL            			BOEING	737   	737322      	1384676	NM  										AFT PRESS BULKHD	FAILED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	13	348UA					24252				AIRCRAFT WOULD NOT HOLD CABIN PRESSURE.  MAINTENANCE FOUND AFT PRESSURE BULKHEAD SEAL THAT SEALS APU BLEED AIR LINE AND 	THE AFT PRESSURE BULKHEAD HAD FAILED.  CAUSE OF FAILURE IS UNKNOWN.  DATE OF SEAL MANUFACTURE, 12-29-87.  SUBMITTER RECO	MMENDED A MANDATORY REPLACEMENT OF THE SEAL BASED ON THE TIME IN SERVICE OF THE SEAL.				2	L	7	2 	4F			RT	A16WE
1998050800005	19980508	00005	CE  	1998	5	8	98ZZZX1634       	1	19980226	G	2730	115610010325	TORQUE TUBE     			BEECH 	99    	C99         	1154006	CE  										ELEVATOR	CRACKED         	B	S	A	EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6645K					U209				ELEVATOR TORQUE TUBE ASSY, P/N 115610010325, INSPECTED PER SB 2145 (RECURRING) DATED APRIL, 1986.  AIRCRAFT HISTORY INDI	CATES NUMEROUS REPLACEMENTS DUE TO CRACKS IN SUPPORT ASSY, P/N 1156100181, OR TORQUE TUBE, P/N 11510010325.					1	L	7	2 	3T				A14CE
1998050800006	19980508	00006	CE  	1998	5	8	98ZZZX1635       	1	19980226	G	2730	1156100181	SUPPORT         		115610010325	BEECH 	99    	C99         	1154006	CE  										ELEV TORQ TUBE	CRACKED         	B	S	A	EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6656N	702  				U213				ELEVATOR TORQUE TUBE SUPPORT IS INSPECTED EACH 1,000 HOUR RECURRING PER SB 2145, DATED APRIL, 1986.  AIRCRAFT HISTORY IN	DICATES NUMEROUS REPLACEMENTS DUE TO CRACKS OF SUPPORT ASSY, P/N 115610181 OR TORQUE TUBE, P/N 115610010325.					1	L	7	2 	3T				A14CE
1998050800013	19980508	00013	CE  	1998	5	8	98ZZZX1636       	1	19980128	G	5511	123262224	SPAR            			CESSNA	210   	210L        	2073448	CE  										STABILIZER	CRACKED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	59063					21060062				CRACKS HAVE BEEN FOUND ON THE REAR STABILIZER SPAR.  SUSPECT CRACKS ARE CAUSED BY IMPROPER USE OF A RIVET SQUEEZER DURIN	G FACTORY INSTALLATION.  SUBMITTER STATED THESE CRACKS AND TOOLING MARKS HAVE BEEN FOUND ON 4 OTHER ASSEMBLIES.  CRACKS 	RANGE IN SIZE FROM .25 INCH TO .50 INCH LONG, AND ARE FOUND ABOVE THE RIVET TAIL.				1	H	7	1 	3O			 	3A21
1998050800014	19980508	00014	EU  	1998	5	8	98ZZZX1637       	1	19980416	G	5753	F10A114261A1	FLAP TRACK      			AMD   	FALC10	FALCON10    	2730101	EU  										LT INBD WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	724DS	8167 				92				WHILE PERFORMING A-CHECK, NOTICED LT INBD FLAP LOOSE.  PERFORMED INSPECTION AND FOUND 4 INCH CRACK IN LOWER RAIL.  REMOV	ED PART FROM SERVICE AND INSTALLED NEW.  PERFORMED NDT INSPECTION ON OTHER FLAP TRACK, NO INDICATIONS.  SUSPECT CAUSE: L	OWERING FLAPS AT EXCESS AIRSPEED.				2	L	7	2 	4F				A33EU
1998050800015	19980508	00015	SW  	1998	5	8	98ZZZX1638       	1	19980203	G	2435	230790001	STARTER         	LEARSIEGLER 		GULSTM	690TP 	695         	7630518	SW  										START/GEN	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	515AM	1023 			3534	95008				UPON REMOVAL OF STARTER/GENERATOR, FOUND MAIN SHAFT BEARING FAILED CAUSING AN INTERNAL SHORT TO STARTER HOUSING.  PER OP	ERATOR, FAILURE WAS NOT ABNORMAL AND DUE TO TIME ON COMPONENT.					1	H	7	2 	3T				2A4
1998050800016	19980508	00016	WP  	1998	5	8	98ZZZX1639       	2	19980402	G	7230	31013731	PLATE LOCK      								GARRTT	TPE331	TPE3312     	01514	WP  					IMPELLER SHROUD	FAILED          	B	S		FTUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	CGHQG						P06697C			BOLTS ATTACHING THE FIRST STAGE IMPELLER SHROUD TO THE IMPELLER HOUSING WERE FOUND LOOSE AND MISSING DURING A ROUTINE EN	GINE INSPECTION.  THESE BOLTS USE A LOCK TAB P/N 3101373-1 TO LOCK A MS9489-19 BOLT AND SPACER IN PLACE.  REPLACEMENT PA	RTS WERE ORDERED AND IT WAS FOUND THE LOCK TABS HAVE A LARGER HOLE THAN THE BOLT IT IS SUPPOSED TO LOCK.  THE LOCK TAB H	OLE MEASURES .224 INCH AND THE BOLT IS .187 INCH.  WHEN THE LOCK TAB IS BENT TO LOCK THE BOLT HEAD, THERE IS ENOUGH ROOM	 FOR THE BOLT TO TURN IF VIBRATION OCCURS. SUGGEST LOCK TAB HOLE DIAMETER IS REDUCED TO PROPERLY LOCK THE BOLT IN PLACE.							3	T			E3WE
1998050800017	19980508	00017	SO  	1998	5	8	98ZZZX1640       	1	19980414	G	5210	12006625001	FITTING         			EMB   	120   	EMB120RT    		SO  										PASSENGER DOOR	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	269AS					120210				WHILE PERFORMING INSPECTION TASK C-95 FOR ATLANTIC SOUTHEAST AIRLINES, A CRACK WAS FOUND IN MACHINED HINGE FITTING FOR A	FT PASSENGER DOOR HINGE MOUNT.  CAUSED BY DOOR NOT SUPPORTED WHILE STOPS WERE REMOVED.  SUBMITTER RECOMMENDED MORE FREQU	ENT INSPECTION OF AREA.				2	L	7	2 	4T			RT	A31SO
1998050800868	19980508	00868	NE  	1998	5	8	98ZZZX1645       	2	19980415	G	7230	360705	COUPLING LOCK   								PWA   	JT8   	JT8*        	52044	NE  					ENGINE COMP	WORN            	B			B97R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							82330013			ENGINE COUPLING LOCK HAS MAX WEAR ON OD .010.  ACTUAL .012.  WEAR EXCEEDS MANUAL LIMITS.  RETURNED TO CUSTOMER.											4	F			E2EA
1998050800869	19980508	00869	NE  	1998	5	8	98ZZZX1646       	2	19980415	G	7230	774407	DISK            								PWA   	JT8   	JT8*        	52044	NE  					ENG C7	PITTED          	B			B97R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13926					S13949			ENGINE C7 DISK VISUAL INSPECTION DISCLOSED PITTING THROUGHOUT PART.  EXCEEDS BLEND LIMITS.  PART SCRAPPED.  TC:  9,762.											4	F			E2EA
1998050800870	19980508	00870	NE  	1998	5	8	98ZZZX1647       	2	19980415	G	7230	772512	DISK            								PWA   	JT8   	JT8*        	52044	NE  					ENG C12	PITTED          	B			B97R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		11786					N81043			ENGINE C12 DISK HAS PITTING ON RADIUS.  NO DAMAGE ALLOWED IN RADIUS BETWEEN WEB AND SNAP DIAMETERS.  INSPECTION 01, SECT	ION 4(B), TASK 72-36-46.  PART RETURNED TO CUSTOMER AS SCRAP.  TC:  10,381.										4	F			E2EA
1998050800871	19980508	00871	CE  	1998	5	8	98ZZZX1650       	1	19980422	G	2810	0526007201	TANK            			CESSNA	172   	172E        	2072412	CE  										BAFFLE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	3799S	5033 				17250999				WHILE MOVING AIRCRAFT A CLICKING SOUND WAS HEARD.  AFTER LOOKING IN THE GAS CAP, A LARGE PART WAS FOUND SLIDING AROUND I	N FUEL TANK.  AFTER A CLOSER LOOK, FOUND BROKEN WELDS ON INTERNAL RIB OR BAFFLE.  CAUSE WAS FUEL MOVEMENT IN TANK, AND R	IB WAS ONLY WELDED ON ONE SIDE OF RIB.  IF WELDED ON BOTH SIDES, IT MAY HAVE NOT BROKEN LOOSE.  IF THE RIB WOULD STICK U	NDER FUEL GAUGE, FLOAT COULD INDICATE MORE FUEL THAN WAS IN TANK.			1	H	7	1 	3O			NT	3A12
1998050800872	19980508	00872	CE  	1998	5	8	98ZZZX1651       	1	19980422	G	2810	05260074	TANK            			CESSNA	172   	172E        	2072412	CE  										BAFFLE	BROKEN WELD     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	3799S	5033 				17250999				WHILE MOVING AIRCRAFT A CLICKING SOUND WAS HEARD.  AFTER LOOKING IN THE GAS CAP, A LARGE PART WAS FOUND SLIDING AROUND I	N FUEL TANK.  AFTER A CLOSER LOOK, FOUND BROKEN WELDS ON INTERNAL RIB OR BAFFLE.  CAUSE WAS FUEL MOVEMENT IN TANK, AND R	IB WAS ONLY WELDED ON ONE SIDE OF RIB.  IF WELDED ON BOTH SIDES, IT MAY HAVE NOT BROKEN LOOSE.  IF THE RIB WOULD STICK U	NDER FUEL GAUGE, FLOAT COULD INDICATE MORE FUEL THAN WAS IN TANK.			1	H	7	1 	3O			NT	3A12
1998050800874	19980508	00874	CE  	1998	5	8	98ZZZX1653       	1	19980406	G	3252	04425121	DAMPENER        			CESSNA	172   	172L        	2072432	CE  										NLG	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	7201Q	4749 				17260501				SHIMMY DAMPENER HAD NO FLUID AND SHAFT WOULD NOT COME OUT FOR OVERHAUL.  INSTALLED NEW PART.						1	H	7	1 	3O			NT	3A12
1998050800875	19980508	00875	CE  	1998	5	8	98ZZZX1654       	1	19980406	G	2731	12600741	ACTUATOR        			CESSNA	172   	172L        	2072432	CE  										ELEVATOR TRIM	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	7201Q	4749 				17260501				HAD EXCESSIVE PLAY. MAXIMUM PLAY .131 - HAS .330 PLAY.  INSTALLED NEW PART.						1	H	7	1 	3O			NT	3A12
1998050800876	19980508	00876	EA  	1998	5	8	98ZZZX1655       	2	19980406	G	7322	105217	CARBURETOR      	FACET       	MA4SPA      	CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					FUEL INLET	WORN            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	33	7201Q	3149 	548  		75008623	17260501	L3287027A			FUEL INLET FITTING HAD STRIPED THREADS OUT OF CARBURETOR HOUSING AND LEAKING FUEL.  INSTALLED REBUILT PART.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998050800877	19980508	00877	GL  	1998	5	8	98ZZZX1656       	3	19980408	G	6114		HUB             													MCAULY	3AF32C	3AF32C87    	GL  	NR 1 SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17								716260		NR 1 BLADE SOCKET HAD AN EDDY CURRENT INDICATION IN THE 7TH THREAD DOWN BETWEEN 1 AND 2 O'CLOCK.  INDICATION WAS APPROXI	MATELY 1.25 INCHES LONG.  THIS PROPELLER WAS IN FOR REPAIR DUE TO A PROP STRIKE.															5	C	P22EA
1998050800879	19980508	00879		1998	5	8	98ZZZX1658       	4	19980313	G	3454	6222080011	RECEIVER        	COLLINS     		BEECH 	58    	58          	1152740	CE  										COCKPIT NAV	BURNED          	I				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			EA	09	216HA	10186			24138	TH733				AIRCRAFT DEPARTED RIC.  EN ROUTE, CREW NOTED BURNED ODOR AND THE NAV UNIT EMITTED SMOKE (A WHISP).  CREW PULLED THE CIRC	UIT BREAKER OF THE AFFECTED UNIT AND RETURNED TO RIC.					1	L	7	2 	3O				3A16
1998050800880	19980508	00880	SO  	1998	5	8	98ZZZX1659       	1	19980410	G	3213	0831192	GEAR LEG        			LUSCOM	8     	8A          	8190104	SO  										RT MLG	FAILED          	D	L	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	05	2750K	1710 				5477				CORROSION INTERNALLY.  FRACTURE ABOVE WELD BELOW BRAKE PULLEY.  TOTAL GEAR FAILURE ON RIGHT GEAR ON LANDING.  SEE LUSCOM	BE NEW LETTER NR 113.					1	H	7	1 	3O				A694
1998050800881	19980508	00881	SO  	1998	5	8	98ZZZX1660       	2	19980401	G	8550	AN9171D	T-FITTING       			CESSNA	182   	182F        	2072714	CE  	CONT  	O470  	O470R       	17026	SO  					TURBO LT SIDE	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03	3341U					18254741	843463R4			INSPECTION FOR AN OIL LEAK FOUND THE T-FITTING THAT FEEDS OIL PRESSURE TO BOTH TURBOS WAS CRACKED.  THE FITTING IS LOCAT	ED JUST AFT OF THE LEFT TURBO.  IF THE LEAK HAD GONE UNNOTICED, THERE IS A SUBSTANTIAL POSSIBILITY OF AN ENGINE FIRE.  R	ECOMMEND USING BRASS OR STEEL FITTING NEAR TURBOCHARGERS INSTEAD OF ORIGINAL ALUMINUM ONES CALLED OUT FOR IN RAJAY TURBO	 CONVERSION.			1	H	7	1 	3O	3	O	NT	3A13    	E273
1998050800883	19980508	00883	CE  	1998	5	8	98ZZZX1662       	1	19980318	G	7810	991030130	EXHAUST STACK   			CESSNA	335   	335         	2075601	CE  										LT ENG INBD	WORN            	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	335PC					3350053				DURING A ROUTINE ENGINE CHANGE, THE EXHAUST COMPONENTS WERE INSPECTED AND THE LEFT ENGINE, INBOARD EXHAUST STACK (ELBOW)	 WAS FOUND WITH 2 LARGE HOLES CAUSED BY CONTACT FROM THE HEAT SHIELDS MOUNTED ABOVE THE ELBOW.  THE HEAT SHIELDS ALSO HA	D HOLES IN THEM AND WERE BURNED BY THE ESCAPING EXHAUST GASSES.  ROUTED DIRECTLY ABOVE THE HEAT SHIELDS IS THE MAIN WIRE	 BUNDLE CONTAINING ALL NECESSARY WIRING FROM THE LEFT ENGINE.  SEVERAL WIRES SHOWED SIGNS OF HEAT DAMAGE TO THE INSULATI	ON AND ONE WIRE WAS BURNED COMPLETELY IN HALF.		1	L	7	2 	3O				3A25
1998050800884	19980508	00884	WP  	1998	5	8	98ZZZX1663       	1	19980401	G	7160	BA4101	GASKET          	BRACKETT    		VARGA 	2150  	2150AMORISY 	9350102	WP  										CARB HEAT BOX	DETERIORATED    	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	4631V					VAC8777				DURING ANNUAL INSPECTION, FOUND CARBURETOR HEAT BOX GASKET P/N BA-4101 (BRACKETT) IN A DETERIORATED CONDITION.  ON VARGA	 MODEL 2150A  THERE ARE TWO BA-4101 GASKETS.  ONE BETWEEN THE AIR VARGA P/N 30020-31 DUCT ASSY, AND ONE BETWEEN DUCT ASS	Y AND VARGA P/N 30020-32  CARBURETOR HEAT BOX.  THE GASKET BETWEEN THE CARB AIR BOX AND DUCT ASSY IS THE SAME GASKET THA	T AD 96-09-06 APPLIES.  AIRCRAFT TT 1,526.0 HOURS, TT ON PART UNKNOWN.			1	L	7	1 	3O				4A19
1998050800887	19980508	00887	CE  	1998	5	8	98ZZZX1666       	1	19980416	G	2720		RUDDER BAR      			CESSNA	182   	R182        	2072734	CE  										RT RUDDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	5545S	3147 				R18201604				RIGHT HAND RUDDER BAR ASSEMBLY, WELDED ON FITTING THAT CONNECTS TO NOSE GEAR STEERING AND CONTROLS RUDDER TRIM, BROKE AW	AY FROM RUDDER BAR ASSY.  UPON INSPECTION OF WELDED FITTING, IT APPEARS TO HAVE BEEN A COLD WELD.					1	H	7	1 	3O			RT	3A13
1998050800888	19980508	00888	SO  	1998	5	8	98ZZZX1667       	1	19980415	G	3230	400235	BOLT            		1619800     	PIPER 	PA23  	PA23250     	7102308	SO  										NLG DRAG BRACE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	51ME					277854066				UPPER NOSE GEAR DRAG BRACE BOLT FAILED.  FAILURE OCCURRED ON BOLT UNDER DRAG BRACE BUSHING.  METAL FATIGUE IS SUSPECTED 	REASON FOR FAILURE.  SUBMITTER SUGGESTED REMOVING AND VISUALLY INSPECTING BOLT AND/OR PERFORM NDT OF BOLT.					1	L	7	2 	3O				1A10
1998050800889	19980508	00889	EU  	1998	5	8	98ZZZX1668       	1	19980319	G	5210	TB1025042102	GUIDE           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										RT DOOR FWD CAB	FAILED          	B	L	A	FO6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	51TB	1628 				488				WHILE TROUBLESHOOTING AN AIR LEAK ON THE RT DOOR, DISCOVERED THE FWD DOOR LATCH WAS NOT OPERATING DUE TO A BROKEN LOWER 	LATCH GUIDE.  FURTHER INVESTIGATION REVEALED THE BROKEN LATCH GUIDE WAS A P/N TB1025042100 GUIDE MADE OF PLASTIC INSTEAD	 OF THE PROPER P/N TB1025042102 GUIDE MADE OF MACHINED ALUMINUM.  A CHECK OF THE OTHER DOOR LATCHES ON THE RT AND LT DOO	RS ALSO FOUND IMPROPER P/N GUIDES INSTALLED.  THERE WAS NO RECORD OR INDICATIONS THAT THE GUIDES HAD BEEN PREVIOUSLY REP	LACED.  RECOMMEND INSPECTION OF DOOR LATCHES AND REPLACEMENT OF IMPROPER PARTS.		1	L	7	1 	3O			RT	A51EU
1998050800890	19980508	00890	CE  	1998	5	8	98ZZZX1669       	1	19980319	G	3211	S21381	BOLT            			CESSNA	172   	172N        	2072434	CE  										LT MLG MOUNT	FAILED          	B		A	VT3R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	09	6360D	9401 				17272746				DURING ROLL-OUT, PILOT LOST DIRECTIONAL CONTROL AND AIRCRAFT VEERED OFF RUNWAY INTO THE DIRT.  AFTER CONTACTING UNEVEN T	ERRAIN, THE LT MLG STRUT COLLAPSED AFT CAUSING DAMAGE TO LT MLG FAIRINGS, FUSELAGE, AND LT STABILIZER/ELEVATORS.  INSPEC	TION SHOWED THE P/N S2138-1 BOLT HAD BROKEN INSIDE STRUT ALLOWING STRUT TO ROTATE AFT.  METALLURGICAL ANALYSIS DETERMINE	D THE BOLT WAS PREVIOUSLY CRACKED.  SUBMITTER RECOMMENDED A SAFE LIFE LIMIT BE ESTABLISHED.			1	H	7	1 	3O			NT	3A12
1998050800891	19980508	00891	SO  	1998	5	8	98ZZZX1670       	2	19980414	G	8520		CRANKCASE       			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 6 CYL STUD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	756QP	580  				U20604274	564851			THE CRANKCASE SPLIT FROM NR 6 CYLINDER HOLE TO OIL FILLER HOLE ON TOWARD TO THE FRONT OF THE CASE.  THIS OCCURRED IN CON	JUNCTION WITH THE CYLINDER MOUNTING STUD IN THIS IMMEIDATE AREA FAILING.  THE CIRCUMSTANCES UNDER WHICH IT OCCURED WERE 	'NORMAL OPERATION'.  SUSPECT CAUSE - OVERTORQUEING OF SAID CYLINDER STUD BOLT.				1	H	7	1 	3O	3	O		A4CE    	E5CE
1998050800892	19980508	00892	CE  	1998	5	8	98ZZZX1671       	1	19980320	G	5753	0523920	ROLLER BEARING  		052390138   	CESSNA	172   	172N        	2072434	CE  										RT OTBD FLAP	WORN            	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	09	738QA					17270144				RT OUTBOARD LOWER FLAP ROLLER JAMMED IN TRACK CAUSING EXTENSIVE FLAP DAMAGE AND INABILITY TO RAISE FLAPS TO FULL UP POSI	TION.  UPON LANDING, FLAP ROLLER FOUND WORN THROUGH TO ATTACH HARDWARE INDICATING IT HAD NOT BEEN ROLLING, BUT SLIDING I	N TRACK.  HAVE FOUND SIMILAR 'STUCK' ROLLERS ON OTHER 172 AIRCRAFT DUE TO IMPROPER INSTALLATION OF WASHER STACK ON BOTH 	SIDES OF ROLLER.			1	H	7	1 	3O			NT	3A12
1998050800893	19980508	00893	SO  	1998	5	8	98ZZZX1672       	1	19980326	G	3213	MS20364624C	AXLE NUT        			PIPER 	PA30  	PA30        	7103002	SO  										NLG	FAILED          	H	P	A		O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	99	7732Y					30821				AXLE NUT P/N MS 20364-624C (PIPER P/N 752-482) WORKED LOOSE AND FELL OFF OF NOSE GEAR AXLE TIE BOLT P/N 20854-00.  THIS 	NUT IS ADJUSTED ONLY TIGHT ENOUGH TO REMOVE FREE PLAY ON NOSE WHEEL BEARINGS.  IT IS NOT TORQUED TO A SPECIFIC TORQUE. W	HEN NUT CAME OFF, THIS ALLOWED TIE BOLT TO SLIDE OUT OF NOSE GEAR TO THE SIDE.  TIE BOLT THEN JAMMED NOSE GEAR IN THE UP	 POSITION.  AFTER 1 HR OF TRYING TO DISLODGE L/G,  ACFT  LANDED WHEELS UP WITH NO INJURIES AND MINOR DAMAGE.  SUBMITTER 	RECOMMENDED REPLACING ANY AXLE TIE BOLT WITH THREAD WEAR AND INSTALL NEW LOCKNUTS AND A SLIGHTLY LONGER TIE BOLT ALLOWIN	G AN363C NUT (NOT THIN TYPE) OR DRILLED TIE BOLT FOR CASTLE NUT AND COTTER PIN ARRANGEMENT.  TT ON ACFT IS 7,300 HRS.	1	L	7	2 	3O				A1EA
1998050800894	19980508	00894	CE  	1998	5	8	98ZZZX1673       	1	19980421	G	3211	0541153	U-BOLT          			CESSNA	182   	182C        	2072708	CE  										LT MLG	FAILED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	8655T	4450 				52555				DURING 100-HOUR INSPECTION, ONE LEG OF THE U-BOLT ON THE LT MAIN GEAR LEG WAS FOUND BROKEN IN THE THREAD AREA.  SUBMITTE	R SUSPECTS IT WAS DUE TO FATIGUE.  A CLOSER LOOK AT THESE BOLTS DURING INSPECTION WOULD BE IN ORDER.					1	H	7	1 	3O			NT	3A13
1998050800895	19980508	00895	SO  	1998	5	8	98ZZZX1674       	1	19980206	G	3260		SWITCH          			PIPER 	PA32  	PA32R301    	7103218	SO  										RT MLG DOWNLOCK	OUT OF ADJUST   	D				O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			NM	09	92877	76   				3246078				GEAR DOWN LIGHT DID NOT COME ON WHEN THE GEAR WAS EXTENDED.  FOUND RT MLG DOWNLOCK LIGHT SWITCH OUT OF ADJUSTMENT.  JACK	ED AIRCRAFT AND ADJUSTED SWITCH.					1	L	7	1 	3O				A3SO
1998050800896	19980508	00896	EA  	1998	5	8	98ZZZX1675       	2	19980409	G	8530		VALVE GUIDE     			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 3 CYL EXH VLV	DEFECTIVE       	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			TO	TAKEOFF        	1			SW	99	9477L		1400 			17276562	L1045839A			ON TAKEOFF, A MOMENTARY ENGINE ROUGHNESS PROMPTED THE PILOT TO ABORT TAKEOFF.  THE AIRCRAFT EXCEEDED RUNWAY LENGTH AND S	TRUCK AN ANTENNA.  INSPECTION OF THE ENGINE REVEALED A BUILD-UP OF CARBON IN THE NR 3 EXHAUST VALVE GUIDE.  NOTE:  ALL E	XHAUST VALVE GUIDES WERE REAMED APPROXIMATELY 650 HRS PRIOR TO INCIDENT.  AFTER INCIDENT, ENGINE RUN-UP WAS NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998050800897	19980508	00897	SO  	1998	5	8	98ZZZX1676       	1	19980401	G	2710	6210200	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										AIL BELLCRANK	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9729W					2823207				AILERON BELLCRANK SUPPORTS BROKEN AT FORWARD ENDS OF SUPPORT.  THE DAMAGE HAS TO BE FOUND WITH A MIRROR.  THE BELLCRANK 	SUPPORTS LOOK SATISFACTORY LOOKING IN THE ACCESS HOLES ORIGINALLY INSTALLED BY PIPER.  THE FRONT FLANGE OF THE AILERON B	ELLCRANK SUPPORT BRACKETS FRONT BOLT HOLES FOR  MOUNTING CRACKED COMPLETELY FROM ONE FLANGE SUPPORT EDGE TO THE OTHER. S	USPECT CAUSED BY HIGH WINDS AND NO AILERON LOCKING PROVISION ON THIS AIRCRAFT.  THE DAMAGE IS HIDDEN BY THE WAY THE SUPP	ORTS' FLANGE IS BENT UP ON THE OUTBOARD EDGE.  THE INBOARD FLANGE THAT IS BOLTED AND RIVETED TO THE RIB IS THE AREA THAT	 CRACKS.	1	L	7	1 	3O				2A13
1998050800898	19980508	00898	SO  	1998	5	8	98ZZZX1677       	1	19980401	G	2710	6210201	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  										AIL BELLCRANK	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9729W					2823207				AILERON BELLCRANK SUPPORTS BROKEN AT FORWARD ENDS OF SUPPORT.  THE DAMAGE HAS TO BE FOUND WITH A MIRROR.  THE BELLCRANK 	SUPPORTS LOOK SATISFACTORY LOOKING IN THE ACCESS HOLES ORIGINALLY INSTALLED BY PIPER.  THE FRONT FLANGE OF THE AILERON B	ELLCRANK SUPPORT BRACKETS FRONT BOLT HOLES FOR  MOUNTING CRACKED COMPLETELY FROM ONE FLANGE SUPPORT EDGE TO THE OTHER. S	USPECT CAUSED BY HIGH WINDS AND NO AILERON LOCKING PROVISION ON THIS AIRCRAFT.  THE DAMAGE IS HIDDEN BY THE WAY THE SUPP	ORTS' FLANGE IS BENT UP ON THE OUTBOARD EDGE.  THE INBOARD FLANGE THAT IS BOLTED AND RIVETED TO THE RIB IS THE AREA THAT	 CRACKS.	1	L	7	1 	3O				2A13
1998050800899	19980508	00899	CE  	1998	5	8	98ZZZX1678       	1	19980419	G	8010	S19911	SOLENOID        			CESSNA	172   	172L        	2072432	CE  										STARTER	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	9898G	2445 				17259798				WHEN AIRCRAFT MASTER SWITCH WAS TURNED ON THE STARTER ENGAGED CAUSING THE PROPELLER TO TURN.  THE SOLENOID P/N S-199-1 W	AS REMOVED AND OPENED UP.  WATER, RUST, AND CORROSION WERE FOUND.  THIS CAUSED THE SOLENOID TO REMAIN IN THE CLOSED POSI	TION.  THIS CONDITION IS A SERIOUS SAFETY CONDITION AND COULD CAUSE INJURY OR DEATH.  A NEW SOLENOID WAS INSTALLED, IT W	AS SEALED WITH EPOXY PRIOR TO INSTALLATION TO PREVENT WATER OR MOISTURE FROM ENTERING IT.  THE LOCATION OF THE SOLENOID 	IN THE COWLING ALLOWS RAIN TO ENTER THE UNIT.		1	H	7	1 	3O			NT	3A12
1998050800900	19980508	00900	SO  	1998	5	8	98ZZZX1679       	1	19980416	G	3060	758243	BRACKET         		758180      	PIPER 	PA23  	PA23250     	7102308	SO  										DEICE BRUSH BLK	CRACKED         	B	L		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09										CUSTOMER RETURNED P/N 758-180 (4E1515-3) PROP DEICE BRUSH BLOCK ASSY BECAUSE BRACKET P/N 758-243 (431514-2) WAS CRACKED 	IN RADIUS OF BEND.					1	L	7	2 	3O				1A10
1998050800901	19980508	00901	SW  	1998	5	8	98ZZZX1680       	1	19980421	G	2822	2C271	PUMP CARTRIDGE  			BELL  	206   	206B3       	1181506	SW  										BOOST PUMP	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY					2871				FORWARD BOOST PUMP INOPERABLE.  REMOVED AND REPLACED BOOST PUMP.  AIRCRAFT RETURNED TO SERVICE.  CONTROL NR 98-4-10.						1	G	7	1 	3U				H2SW
1998050800902	19980508	00902	EU  	1998	5	8	98ZZZX1681       	1	19980427	G	6230	L522110V	BEARING         		350A37000305	SNIAS 	350   	AS350BA     	8680817	EU  										M/R SHAFT	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	398MA	2774 			2495	1856				LOWER MAST BEARING OUTER RACE DETERIORATING, MAKING METAL.  SUBMITTER STATED ENSURE CORRECT MAST BEARING SHIMMING.						1	G	7	1 	3U			NC	H9EU
1998050800903	19980508	00903	GL  	1998	5	8	98ZZZX1682       	2	19980330	G	7250	A6871505	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE NR 5	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	49573	921  				1665	834450			AFTER A NORMAL FLIGHT (EXTERNAL LOAD) AND SHUT-DOWN, THE PILOT REPORTED AN ABNORMAL NOISE WHILE TURNING ROTOR BACKWARDS 	TO TIE-DOWN POSITION.  UPON REMOVAL OF THE TURBINE MODULE, THE FORWARD HALF OF THE NR 5 BEARING INNER CAGE FELL OUT.  (T	HIS IS A 1-PIECE UNIT, NOT 2)  THIS BEARING IS THE SUBJECT OF AD 96-19-01.  THERE HAD BEEN NO PREVIOUS SIGNS OF DISTRESS	, I.E., CHIP LIGHTS, ETC.  ENGINE OIL FILTER REMAINS CLEAN AT REMOVAL OF TURBINE.  SUSPECT THAT BEARING FAILED AFTER SHU	T DOWN IN THAT AT OPERATIONAL SPEED NEAR 60K RPM, MAJOR TURBINE DAMAGE WOULD HAVE OCCURRED IN MILLI-SECONDS.  REPLACED W	ITH OEM BEARING.	1	G	7	1 	3U	3	U		H2SW    	E4CE
1998050800904	19980508	00904	GL  	1998	5	8	98ZZZX1683       	2	19980427	G	7320	704A34130163	CONTROL CABLE   			AEROSP	AS355 	AS355F2     	8680812	EU  	ALLSN 	250C  	250C20F     	03013	GL  					NR 2 N2 CONTROL	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	942MS	99   				5498				CABLE FRAYED AND BEARING WORN OUT CAUSING BINDING OF N2 LINKAGE.  SUBMITTER SUGGESTED INSTALLING A BETTER, MORE RELIABLE	 SYSTEM.					1	G	7	2 	3U	3	U	 	H11EU   	E4CE
1998050800906	19980508	00906		1998	5	8	98ZZZX1685       	4	19980416	G	3457	0110005400	GPS             		GPS150      	BELL  	206   	206B        	1181511	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K	1422 				2040				GPS WILL NOT PICK UP SATELLITE UNIT SENT TO MANUFACTURER FOR REPAIR.  CONTROL NR 984-9.						1	G	7	1 	3U				H2SW
1998050800907	19980508	00907		1998	5	8	98ZZZX1686       	1	19980420	G	6710	0470	NUT             			AMTR  		MINI500     												M/R CONTROL	DETACHED        	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	105WB	108  								ROTOR CONTROL NUT BACKED OFF OF BOLT P/N 0434 DISCONNECTING MAIN ROTOR PITCH CONTROL.  SUBMITTER STATED NUT AND BOLT ASS	Y SHOULD BE DOUBLE-NUTTED OR DRILLED AND COTTER KEYED TO PREVENT SEPARATION.  THERE ARE A TOTAL OF 4 OF THESE ASSEMBLIES	 IN THE CONTROL SYSTEM.							0
1998050800909	19980508	00909	NM  	1998	5	8	98ZZZX1688       	1	19980226	G	3250	1692RA	METERING VALVE  	SARGENT     	1692E41     	BOEING	727   	727224      	1384076	NM  										STEERING	CRACKED         	B			CA5Z	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35					942					WHILE BEING OVERHAULED, AN OCCURRENCE OF CRACKS WERE NOTED IN SEVERAL VALVE BODIES.  THERE ARE NO NDT CHECKS FOR BODY P/	N 1692E41 OTHER THAN X10 MAGNIFICATION VISUAL CHECK IN THE SARGENT OMM 32-50-04.  SUBMITTER SUGGESTED THAT AS A MINIMUM,	 A DYE PENETRANT FLAW DETECTION IS CARRIED OUT ON THIS PART AT EVERY OVERHAUL.				2	L	7	3 	4F				A3WE
1998050800912	19980508	00912	NE  	1998	5	8	98ZZZX1690       	2	19980409	G	7250	6010T32P01	NOZZLE          		GGM020302182	LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					2ND STAGE	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	25HA	7674 	684  			141	251475A			THE SECOND STAGE EXHAUST STATOR HAD A BLADE BURNED THROUGH, CAUSE WAS TRACED TO BAD FUEL FLOW FROM FUEL NOZZLES THAT WER	E POSSIBLY MAGNITIZED BY STARTER MAGNETIC FIELD.  TESTING AND REPAIRS TO PARTS WERE CONDUCTED BY NORTH TEXAS TURBINES.					2	L	7	2 	4J	4	J		A10CE   	1E16
1998050800913	19980508	00913	CE  	1998	5	8	98ZZZX1691       	1	19980331	G	2910	2607003468	LINE            			LEAR  	35    	35A         	5170602	CE  										RT MLG WELL	LEAKING         	B	S	A	DINR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	258G	4365 				443				AFTER NOTING A HYDRAULIC LEAK BY THE RT MAIN GEAR WHEEL WELL, FOUND ALUMINUM HYDRAULIC LINE FOR THE FLAP RETURN SYSTEM W	EEPING FROM A CORROSION PIN HOLE.  THE PIN HOLE IS APPROXIMATELY 1 INCH FROM END OF LINE AND IN THE MIDDLE OF A 90 DEGRE	E BEND.  THE LINE IS DATED 1-30-81, AND LOOKS TO BE ORIGINAL.  THE LINE IS PAINTED WITH ZINC CHROMATE INCLUDING THE AREA	 WITH THE PIN HOLE.  NEW LINE WAS INSTALLED.			2	L	7	2 	4F				A10CE
1998050800914	19980508	00914	CE  	1998	5	8	98ZZZX1692       	1	19980401	G	3233	65412045	STUD            			CESSNA	500   	550         	2076604	CE  										MLG ACTUATOR	FAILED          	B	S	A	GMNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	310AV					5500028				IN PERFORMING 10,000-HOUR MLG INSPECTION AND UPON INSTALLING NUT ON STUD, STUD SHEERED IN HALF AT BASE OF THREADED AREA 	ALLOWING ACTUATOR TO SEPARATE FROM LANDING GEAR.  AIRCRAFT WAS ON JACKS.  UPON INSPECTION OF STUD, DETERMINED IT WAS CRA	CKED AND CORRODED.				1	L	7	2 	4F				A22CE
1998050800915	19980508	00915	CE  	1998	5	8	98ZZZX1693       	1	19980317	G	3240	1013810125	VALVE           			BEECH 	B300  	B300        	1159232	CE  										LT BRAKE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4S	175  			0543	FL107				PILOT REPORTED LEFT BRAKE DEICE INOPERABLE.  MAINTENANCE CHECK-OUT REVEALED SWITCH IN VALVE APPEARS INOPERATIVE AS VALVE	 WAS PHYSICALLY IN THE OPEN POSITION, ON COMMAND.  THIS VALVE WAS INSTALLED ONLY 6 MONTHS.					2	L	7	2 	4T			RT	A24CE
1998050800916	19980508	00916	CE  	1998	5	8	98ZZZX1694       	1	19980124	G	5610	10138402515	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  										PILOT	DELAMINATED     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	4S	1197 				FL107				ON POST-FLIGHT, 1-24-98, WINDSHIELD (PILOT'S) WAS FOUND DELAMINATED IN TOP INBOARD CORNER ALONG CENTER WINDSHIELD POST. 	 AFTER FLIGHT ON 1-26-98, INSPECTION REVEALED DELAMINATED AREA HAD ENLARGED AND CLOSE TO HEATING ELEMENT.  REPLACED WIND	SHIELD WITH NEW WINDSHIELD.				2	L	7	2 	4T			RT	A24CE
1998050800917	19980508	00917	NM  	1998	5	8	98ZZZX1695       	1	19980331	G	3230	400088001	BELLCRANK       			PIPER 	PA60  	PA60600     	7106001	NM  										LT MLG WELL	CRACKED         	B		A	BONR	K				NONE                    				O			OTHER                     			AP	APPROACH       	1			GL	19	60DC	5261 				600797806123				DURING ROUTINE TRAINING FLIGHT, TOWER REPORTED THE LT MLG INBOARD DOOR REMAINED OPEN AFTER LANDING GEAR EXTENSION.  AIRC	RAFT LANDED WITHOUT INCIDENT.  INSPECTED AIRCRAFT AND FOUND LT MLG BELLCRANK P/N 400088-001 BROKEN.  THIS ALLOWED SEQUEN	CE VALVE TO OPEN CAUSING MLG DOOR TO FREEFALL OPEN.  THE SAME PROBLEM OCCURRED IN 1994 TO RT BELLCRANK WITH 4,266.3 HRS 	TT.  THE REPLACEMENT LT BELLCRANK IS SUBSTANTIALLY IMPROVED OVER ORIGINAL PART.  SUBMITTER RECOMMENDED A SERVICE BULLETI	N TO REQUIRE FREQUENT INSPECTIONS OF ORIGINAL PARTS.		1	M	7	2 	3O			RT	A17WE
1998050800919	19980508	00919	GL  	1998	5	8	98ZZZX1697       	2	19980417	G	7414		DRIVE COUPLING  			AMTR  	SONERI	SONERAI2    		GL  	AMTRVW	VOLKS 	VW2200VOLKS 		GL  					ENGINE MAGNETO	FAILED          	G		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	11	247RJ					999				THE CAST ALUMINUM MAGNETO DRIVE COUPLING WHICH IS KEYED TO THE FLYWHEEL BROKE INTO FOUR PIECES.  THE RESULTANT FRICTION 	MELTED AND FUSED A PORTION OF THE BROKEN PIECES OF THE COUPLING TO THE STATIONARY CROSS MEMBER ENGINE MOUNT.  THIS FAILU	RE OF THE MAGNETO COUPLING RESULTED IN THE FAILURE OF THE ENGINE DURING CRUISE AND ULTIMATELY THE ACCIDENT WHICH DESTROY	ED THE AIRCRAFT AND INJURED THE PILOT.  THE COUPLING BROKE AT THE KEYWAYS AND SHOWED EVIDENCE OF PRE-EXISTING CRACKS POS	SIBLY CASTING FLAWS.  SUBMITTER RECOMMENDED THE MAGNETO DRIVE COUPLING BE MILLED FROM A SOLID PIECE OF HIGH GRADE ALUMIN	UM AND ALL EDGES BE RADIUSED TO PREVENT CRACKING.	1	M	7	1 	3O	3	O		EXPA1M71	EXP3O
1998050800920	19980508	00920	SW  	1998	5	8	98ZZZX1698       	1	19980115	G	2710	730048001	CONTROL ROD     			MOONEY	M20   	M20K        	5870220	SW  										RT AILERON	RUSTED          	B	S	A	EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	261CB	3967 				250391				DURING ANNUAL INSPECTION NOTED AILERON ROD RUSTY.  UPON FURTHER INSPECTION, FOUND ROD RUSTED TO THE EXTENT IT COULD BE S	EPARATED IN TWO WITH LIGHT HAND PRESSURE.  SUBMITTER RECOMMENDED INSPECTING AT EACH ANNUAL.					1	L	7	1 	3O				2A3
1998050800922	19980508	00922	SW  	1998	5	8	98ZZZX1700       	1	19980427	G	6220	214010103115	SPINDLE         		214010100207	BELL  	214   	214ST       	1182106	SW  										M/R HUB	CRACKED         	B	L	A	HEER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T				A524	28101				THE MAIN ROTOR SPINDLE WAS CRACKED AT THE TRAILING EDGE TANGS.  BOTH LOWER AND UPPER TANGS WERE CRACKED.  THE CRACK WAS 	DETECTED DURING A DAILY VISUAL INSPECTION BY A COMPANY TECHNICIAN.  SUBMITTER STATED FAILURE OF THIS SPINDLE WOULD HAVE 	CERTAINLY LED TO A CATASTROPHIC ACCIDENT.				2	G	7	2 	4U				H10SW
1998050801160	19980508	01160	SW  	1998	5	8	98ZZZX1705       	1	19980422	G	5302		SKIN            			BELL  	407   	407         		SW  										TAILBOOM	DENTED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL					53054				DURING PRE-FLIGHT INSPECTION, FOUND SHARP DENT IN LT SIDE OF TAILBOOM SKIN APPROXIMATELY 34.8750 INCH FORWARD OF THE AFT	 END OF THE TAILBOOM CAN AND APPROXIMATELY 2.25 INCH IN LENGTH.  THE DENT APPEARS TO HAVE BEEN CAUSED BY A TAIL ROTOR BL	ADE STRIKING THE TAILBOOM WHILE THE ROTORS WERE IN MOTION.				1	G	7	1 	3U			O	H2SW
1998051500261	19980515	00261	CE  	1998	5	15	98ZZZX1709       	1	19980427	G	7714	535634	DOWEL PIN       			CESSNA	414   	414         	2075908	CE  										TACHOMETER DRIVE	SHEARED         	B			ABOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	12ED	988  				4140521				RIGHT ENGINE TACHOMETER INTERMITTENT.  ALWAYS ACTED FINE ON GROUND RUN-UP.  AFTER SOME TROUBLESHOOTING, FOUND THE DOWEL 	PIN THAT HOLDS ONE BEVEL GEAR TO THE TACHOMETER DRIVE GEAR SHEARED.					1	L	7	2 	3O			RT	A7CE
1998051500262	19980515	00262	CE  	1998	5	15	98ZZZX1710       	1	19980427	G	5730	512200426	SKIN            			CESSNA	414   	414A        	2075907	CE  										RT WING INBD	CORRODED        	B			ABOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	650BD	3316 				414A0404				RIGHT WING BOOT DETERIORATED.  UPON REMOVING BOOT AND AFTER REMOVING 1300L, FOUND INBOARD AND UNDERSIDE OF WING SKIN SEV	ERELY CORRODED.  'THIS IS A WET WING' AND CORROSION WAS ABOUT 18 INCHES FROM EXHAUST OUTLET.  SUSPECT THE BOOT HAD BEEN 	DAMAGED OR JUST DRY ROTTED AND WATER GOT THROUGH THE BOOT AND WAS TRAPPED.  BOOTS LOOKED ORIGINAL '1979'.				1	L	7	2 	3O				A7CE
1998051500263	19980515	00263	CE  	1998	5	15	98ZZZX1711       	1	19980425	G	7120	045100336	MOUNT           			CESSNA	150   	152         	2071835	CE  										ENG/NLG MOUNT	CRACKED         	B	S		LJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	24731	5482 				15280344				INSPECTION FOUND ENGINE MOUNT CRACKED AT NLG ATTACH.						1	H	7	1 	3O			NT	3A19
1998051500264	19980515	00264	CE  	1998	5	15	98ZZZX1712       	1	19980423	G	2520	05142201	SEAT            			CESSNA	172   	172R        	2072401	CE  										AFT BENCH	MISDRILLED      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07	255HP	19   				17280308				THE BACK SEAT APPEARS TO HAVE BEEN JIGGED IMPROPERLY DURING MANUFACTURING.  THE BRACKETS THAT ATTACH SEAT TO THE FLOOR A	ND THE ATTACHMENT HOLES IN THE SEAT DO NOT LINE UP.  IT IS POSSIBLE TO LINE UP BACK 2 BRACKETS, BUT FRONT 3 BRACKETS ARE	 UP TO ONE-HALF THE HOLE DIAMETER OUT OF ALIGNMENT.  FOR A REPAIR, THE BRACKETS HAVE BEEN SLOTTED WHERE THE BOLTS GO TO 	HOLD THE BRACKETS TO THE FLOOR.  THIS AIDS BRACKET TO SEAT ALIGNMENT.			1	H	7	1 	3O			NT	3A12
1998051500267	19980515	00267	EA  	1998	5	15	98ZZZX1715       	2	19980323	G	8530	AL75089	PISTON          			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					NR 3 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	29274	498  				287990442	L2657036A			DURING A ROUTINE OIL CHANGE, THE SUMP SCREEN WAS INSPECTED, FOUND A PEA SIZE PIECE OF CAST ALUMINUM.  IT TURNED OUT TO B	E A PIECE OF CYLINDER NR 3 PISTON SKIRT.  ALSO, FROM THIS BROKEN-OUT PIECE, FROM THE CENTER OF THE BREAK, WAS A .50 INCH	 CRACK RADIATING UP TOWARD THE PISTON HEAD.  ENGINE WAS OVERHAULED IN SEPTEMBER, 1994.  TSMOH IS 498.0 HOURS.  BROKEN AR	EA WAS APPROXIMATELY 90 DEGREES TO PISTON PIN BORE.			1	L	7	1 	3O	3	O		2A13    	E286
1998051500268	19980515	00268	EA  	1998	5	15	98ZZZX1716       	2	19980401	G	7314	LW15473	PUMP            			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540S1A5   	41532	EA  					ENGINE FUEL	LOOSE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05	30004					327840120	RL2044548A			UPON VISUAL INSPECTION OF NEWLY OVERHAULED ENGINE, FOUND ALL OF THE BOLTS SECURING THE BOTTOM DIAPHRAGM PLATE TO THE FUE	L PUMP BODY WERE LOOSE, AT LEAST .0312 INCH OF SPACE COULD BE SEEN UNDER BOLT HEAD.  THIS WAS A NEW PUMP INSTALLED BY EN	GINE SHOP.  SUBMITTER ADVISED INSPECTING EVEN NEW PARTS FOR DEFECT.				1	L	7	1 	3O	3	O	 	A3SO    	1E4
1998051500269	19980515	00269	CE  	1998	5	15	98ZZZX1717       	1	19980413	G	3297		WIRE            			CESSNA	310   	310L        	2074230	CE  										MASTER SOLENOID	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	21	3304X					310L0154				LANDING GEAR DID NOT COME DOWN DUE TO A BROKEN WIRE TO MASTER SOLENOID.  REPLACED WIRE WITH NEW AND WILL REPLACE ALL WIR	ING ON MASTER SIDE DUE TO AGE.					1	L	7	2 	3O			 	3A10
1998051500270	19980515	00270		1998	5	15	98ZZZX1718       	3	19980401	G	6112	R320002	BOOT STRAP      			BEECH 	36    	A36         	1151604	CE  										PROP DEICE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	36665					E1696				BOOT RETAINING STRAP BROKE LETTING DEICE LEADS COME IN CONTACT WITH SPINNER ON PROPELLER SHORTING THE SYSTEM OUT.						1	L	7	1 	3O				3A15
1998051500271	19980515	00271	GL  	1998	5	15	98ZZZX1719       	3	19980409	G	6114		HUB             			BEECH 	90    	65A90       	1152908	CE  						HARTZL	HCB3T	HCB3TN3     	GL  	MOUNT FLANGE	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	646AB					LJ224		BU331		DURING RECEIVING INSPECTION, A FOREIGN OBJECT WAS FOUND LODGED/SWAGED INTO THE PROPELLER HUB MOUNTING FLANGE BORE.  THE 	APPEARANCE WAS SIMILAR TO A WHEEL BEARING RACE.  UPON CLOSER EXAMINATION, IT IS SUSPECTED TO BE AN ADAPTER FROM A PROPEL	LER SHOP ARBOR COMMONLY USED TO FUNCTIONAL TEST TURBINE STYLE PROPELLERS.  THE ADAPTER WAS NOT REMOVED AFTER TESTING, AN	D WAS INSTALLED ON THE ENGINE WITH THE PROPELLER, CRUSHING IT AND DAMAGING THE ENGINE OUTSHAFT.  THIS PROPELLER WAS NOTE	D TO HAVE BEEN LEAKING AT THE MOUNTING SHAFT, AND TRACES OF RTU SEALANT WERE FOUND ON THE OUTSIDE DIAMETER OF THE HUB.		1	L	7	2 	3T			 	3A20    		6	C	P15EA
1998051500272	19980515	00272	SO  	1998	5	15	98ZZZX1720       	1	19980416	G	7120	6711957	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  										LOWER LT CLUSTER	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	806ND	6735 				2837009				FOUND CRACK IN CLUSTER JUST BELOW LOWER LEFT ENGINE TO MOUNT ATTACH POINT.  CRACK ORIGINATED FROM UNDERCUT WELD.  MOUNT 	IS ORIGINAL ONE INSTALLED.  INSTALLED NEW MOUNT (MOUNT REMOVED FOR REPAIR).  CRACK FOUND DURING SCHEDULED INSPECTION.					1	L	7	1 	3O				2A13
1998051500273	19980515	00273	SO  	1998	5	15	98ZZZX1721       	1	19980416	G	2910	67700182	LINE            			PIPER 	PA28  	PA28R201    	7102816	SO  										NLG UP	CRACKED         	B			OG5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	810ND	6269 				2837019				NOSE GEAR 'UP' LINE CRACKED WHERE IT PASSES THROUGH STIFFENER JUST BELOW LOWER DOOR FRAME BY COPILOT'S SEAT.  LINE APPEA	RED TO HAVE A SLIGHT BURR FROM RUBBING ON CAT-TRACK IN ROUTING HOLE.  INSTALLED NEW LINE.					1	L	7	1 	3O				2A13
1998051500274	19980515	00274	SO  	1998	5	15	98ZZZX1722       	1	19980409	G	7430	103572001E	SWITCH          			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360*       	41514	EA  					IGNITION	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	81497	1926 				288090227				SUBMITTER STATES AS A STANDARD PRACTICE AT RUN-UP, TEST IGNITION SWITCHES IN THE 'OFF' AND PAST 'OFF' POSITIONS AS STATE	D BY TCM AD 76-07-12 REGARDLESS OF WHETHER IT APPLIES OR NOT. THIS SWITCH DID NOT APPLY, YET FAILED THE PAST 'OFF' TEST.	  IT HAD A 4 NUMBER DATE CODE OF 8148 AND CAME OUT OF A 1980 AIRCRAFT.				1	L	7	1 	3O	3	O		2A13    	E286
1998051500279	19980515	00279	GL  	1998	5	15	98ZZZX1725       	2	19980429	G	7310	47086	FILTER          								ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		1270 					AT17547			FOUND SOME CONTAMINATION ON FILTER WHERE SCREEN ATTACHES TO BASE.  ALSO, BLACK PARTICULATES ON BASE FACING INLET OF FUEL	.  CONTAMINATION CLEANED BY ULTRASONIC METHOD GOOD.										3	U			E4CE
1998051500280	19980515	00280	EA  	1998	5	15	98ZZZX1726       	2	19980428	G	7230	3033481	BEARING         								PWA   	PT6   	PT6A34      	52043	EA  					ENGINE NR 1	DEFECTIVE       	B			TQZR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17					BB977434					DURING COMPRESSOR BUILD-UP AND BALANCING OF ENGINE, A NEW NR 1 BEARING WAS PURCHASED FROM DALLAS AIRMOTIVE AND INSTALLED	 ON THE COMPRESSOR ROTOR ASSY.  WHEN THE COMPRESSOR WAS 'SPUN UP' FOR BALANCING, A LOW RUMBLE/KNOCKING NOISE WAS DETECTE	D AND ISOLATED AS COMING FROM THE NR 1 BEARING.  THE BEARING WAS REMOVED AND INSPECTED AND IT WAS NOTED THAT THE INNER R	ACE SHOWED THE BALLS WERE NOT TRACKING IN ONE PLANE, BUT WANDERED BACK AND FORTH ACROSS THE RACE.  A SECOND NEW BEARING 	WAS PURCHASED FROM THE SAME SOURCE; INSTALLED AND RUN WITH EXACTLY THE SAME RESULTS.  A THIRD NEW BEARING WAS PURCHASED,	 INSTALLED AND RUN...THIS TIME WITH SATISFACTORY RESULTS.						4	T			E4EA
1998051500281	19980515	00281	EA  	1998	5	15	98ZZZX1727       	2	19980428	G	7230	3033481	BEARING         								PWA   	PT6   	PT6A34      	52043	EA  					ENGINE NR 1	DEFECTIVE       	B			TQZR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17					FA9710027					DURING COMPRESSOR BUILD-UP AND BALANCING OF ENGINE, A NEW NR 1 BEARING WAS PURCHASED FROM DALLAS AIRMOTIVE AND INSTALLED	 ON THE COMPRESSOR ROTOR ASSY.  WHEN THE COMPRESSOR WAS 'SPUN UP' FOR BALANCING, A LOW RUMBLE/KNOCKING NOISE WAS DETECTE	D AND ISOLATED AS COMING FROM THE NR 1 BEARING.  THE BEARING WAS REMOVED AND INSPECTED AND IT WAS NOTED THAT THE INNER R	ACE SHOWED THE BALLS WERE NOT TRACKING IN ONE PLANE, BUT WANDERED BACK AND FORTH ACROSS THE RACE.  A SECOND NEW BEARING 	WAS PURCHASED FROM THE SAME SOURCE; INSTALLED AND RUN WITH EXACTLY THE SAME RESULTS.  A THIRD NEW BEARING WAS PURCHASED,	 INSTALLED AND RUN...THIS TIME WITH SATISFACTORY RESULTS.						4	T			E4EA
1998051500282	19980515	00282	SO  	1998	5	15	98ZZZX1728       	1	19980427	G	5210	12026749001	BOLT            			EMB   	120   	EMB120RT    		SO  										ENTRY DOOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	238AS					120053				DURING ATLANTIC SOUTHEAST AIRLINES 'C' CHECK TASK CARD C-95, RUST WAS NOTED AT THE AFT HINGE OF THE PASS/CREW ENTRANCE D	OOR.  THE DOOR WAS REMOVED AND THE ATTACHMENT BOLT WAS FOUND TO HAVE SEVERE PITTING CORROSION.  THE BOLT HAS BEEN REMOVE	D FROM SERVICE.  RECOMMEND BOLT REMOVAL AND INSPECTIONS ON 'C' CHECK INTERVALS.				2	L	7	2 	4T			RT	A31SO
1998051500283	19980515	00283	EU  	1998	5	15	98ZZZX1729       	1	19980424	G	2750	9787320303	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  										LT INBD FLAP	FAILED          	B			LF1R	O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			EA	07	49LM				367	163				PILOT REPORTED FLAPS INOPERATIVE.  INSPECTION REVEALED LT INBOARD FLAP ACTUATOR NOT FULLY RETRACTING.  ICE CHIPPER PREVE	NTED FULL RETRACTION.  REPLACED COMPONENT AND RIGGED SYSTEM IAW PC-12 MM.  THIS CONDITION CAUSED THE FLAP SYSTEM TO MALF	UNCTION, HOWEVER, THEY WERE STILL OPERABLE IN ALTERNATE MODE.				1	L	7	1 	3T			RT	A78EU
1998051500284	19980515	00284	EU  	1998	5	15	98ZZZX1730       	1	19980422	G	2750	9787120301	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  										LT OTBD FLAP	DEFECTIVE       	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	62JT	1329 			272	107				DURING ANNUAL INSPECTION, NOTICED ICE BREAKER ON LEFT OUTBOARD FLAP ACTUATOR SLIDING ON SHAFT.  REPLACED COMPONENT AND R	IGGED SYSTEM IAW PC-12 MM.  THIS CONDITION COULD CAUSE FLAPS TO JAM IF ICE BREAKER BECOMES LODGED IN SCREW.  THERE ARE S	EVERAL REVISIONS ON THIS COMPONENT.				1	L	7	1 	3T			RT	A78EU
1998051500285	19980515	00285	CE  	1998	5	15	98ZZZX1731       	1	19980427	G	7931	1013890235	TRANSDUCER      			BEECH 	90    	C90A        	1152911	CE  										NR 2 ENGINE OIL	FAILED          	G				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SO	03	8022Q				45043134	LJ1314				AIRCRAFT WAS IN CRUISE @ FL 200 WHEN THE PILOT NOTICED THE OIL PRESSURE GAUGE FOR THE NR 2 ENGINE READING ZERO.  PILOT P	ERFORMED A PRECAUTIONARY SHUT DOWN AND LANDED WITHOUT FURTHER INCIDENT.  TROUBLESHOOTING DETERMINED A FAILED OIL PRESSUR	E TRANSDUCER.				1	L	7	2 	3T			RT	3A20
1998051500286	19980515	00286	CE  	1998	5	15	98ZZZX1732       	1	19980428	G	3260		SWITCH          			CESSNA	750   	750         	2076810	CE  										LT MLG UPLOCK	LOOSE           	B			MUCR	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			GL	13	924EJ					7500024				WHEN RETRACTING LANDING GEAR, (GEAR UNLOCKED) LIGHT STAYED ILLUMINATED ON CLIMB-OUT.  INSPECTED LANDING GEAR AND PERFORM	ED FUNCTIONAL HYDRAULIC TEST ON JACKS.  (GEAR UNLOCKED) LIGHT STAYED ILLUMINATED ON FIRST RETRACTION.  TIGHTENED BACKSHE	LL ON LT UPLOCK SWITCH AND LUBRICATED ROLLERS.  ALL SUBSEQUENT RETRACTION CYCLES OPERATED NORMALLY.				2	L	7	2 	4J			RT	T00007WI
1998051500287	19980515	00287	CE  	1998	5	15	98ZZZX1733       	1	19980416	G	5553	AN96046	BOLT            			BEECH 	60    	60          	1153602	CE  										VERTICAL STAB	MISSING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	60UK	2385 				004				DURING A 2400 HOUR INSPECTION, 2 EACH BOLTS WERE FOUND MISSING IN LOWER ATTACH POINT OF VERTICAL STABILZIER.  NO OTHER D	EFECTS FOUND.  INSTALLED NEW BOLTS AN960-416, WASHERS, AND NUTS.					1	L	7	2 	3O				A12CE
1998051500288	19980515	00288	CE  	1998	5	15	98ZZZX1734       	1	19980416	G	5753	262501570511	BRACKET         			BEECH 	60    	60          	1153602	CE  										RT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	60UK	2385 				004				DURING A 2400-HOUR INSPECTION, THE NOSE ROLLER OUTBOARD FORWARD HINGE BRACKET WAS FOUND CRACKED ON LT AND RT FLAPS.  REP	LACED BRACKET WITH NEW.					1	L	7	2 	3O				A12CE
1998051500289	19980515	00289	CE  	1998	5	15	98ZZZX1735       	1	19980416	G	5753	262501569570	BRACKET         			BEECH 	60    	60          	1153602	CE  										LT FLAP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	60UK	2385 				004				DURING A 2400-HOUR INSPECTION, THE NOSE ROLLER OUTBOARD FORWARD HINGE BRACKET WAS FOUND CRACKED ON LT AND RT FLAPS.  REP	LACED BRACKET WITH NEW.					1	L	7	2 	3O				A12CE
1998051500290	19980515	00290	CE  	1998	5	15	98ZZZX1736       	1	19980416	G	5210	541051445	ARM LATCH       			BEECH 	60    	60          	1153602	CE  										CABIN DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	60UK	2385 				004				DURING 2400 HOUR INSPECTION, THE FORWARD AND AFT CABIN DOOR ARM LATCHES WERE FOUND CRACKED DURING EDDY CURRENT REQUIRED 	INSPECTION.  REPLACED ARMS WITH NEW.					1	L	7	2 	3O				A12CE
1998051500291	19980515	00291	CE  	1998	5	15	98ZZZX1737       	1	19980416	G	5314	MS200026	WASHER          			BEECH 	60    	60          	1153602	CE  										KEEL BEAM	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	60UK					004				DURING A 2400 HOUR INSPECTION, THE UPPER RIGHT KEEL BEAM ATTACH BOLT WASHER WAS FOUND MISSING WHICH LET KEEL BEAM BOLT L	OOSE.  NO OTHER DEFECTS NOTED.  INSTALLED NEW WASHER MS20002-6 AND TORQUED TO SPECS.					1	L	7	2 	3O				A12CE
1998051500292	19980515	00292	SW  	1998	5	15	98ZZZX1738       	1	19980424	G	2436	MS18071	REGULATOR       			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	51AG					7120178				VOLTAGE REGULATOR WILL NOT STAY ON LINE AND CANNOT BE ADJUSTED.  REMOVED AND REPLACED AND SENT FOR REPAIR.  CONTROL NR 9	8-4-11.					1	G	7	1 	4U				EXPA1G71
1998051500293	19980515	00293	EA  	1998	5	15	98ZZZX1739       	2	19980418	G	7414	ES103571651	COIL            	BENDIX      		ENSTRM	F28   	F28A        	3300406	GL  	LYC   	O360  	HIO360C1A   	41514	EA  					ENG LT MAG	FAILED          	D				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			NE	01	57SJ	550  				278	L1238751A			COMPLAINT WAS 'MISFIRE' AT CRUISE POWER.  SYMPTOM WAS NOSE YAW AT ERRATIC INTERVALS.  NORMAL PREFLIGHT RUN-UP CHECK SHOW	ED NO PROBLEM.  MAGNETO CHECK AT HOVER POWER CAUSED ENGINE FAILURE WHEN 'LEFT' MAGNETO POSITION WAS SELECTED.  RECORDS I	NDICATE THIS COIL HAS BEEN IN SERVICE AT LEAST SINCE ENGINE MAJOR OVERHAUL IN 1987.				1	G	7	1 	3O	3	O		H1CE    	1E10
1998051500435	19980515	00435	GL  	1998	5	15	98ZZZX1740       	2	19980424	G	7230	6890550	COMPRESSOR      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FOD             	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	369AW	8878 				470117D	CAC33463			COMPRESSOR STALLING.  FOUND 1ST STAGE BEARING LEAKING.  APPEARS THAT COMPRESSOR HAD FOD.  REMOVED FROM AIRCRAFT AND OVER	HAULED COMPRESSOR INSTALLED.  CONTROL NR 98-4-11.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998051500437	19980515	00437	NE  	1998	5	15	98ZZZX1742       	1	19980422	G	6210	641520201048	BLADE           			SKRSKY	S64   	S64F        		NE  										M/R	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	157AC	5234 			64M51625451	64065				MAIN ROTOR SPAR IS CRACKED 72.81 INCHES FROM TIP UNDER THE NR 6 POCKET, CLOSE (APPROXIMATELY .1 INCH) TO THE SPACE BETWE	EN THE NR 6 AND NR 7 POCKETS.  THE CRACK RUNS CHORDWISE BETWEEN THE POCKET LEADING EDGE GROOVE, AND THE BACKWALL RADIUS.	  IT DOES NOT APPEAR TO GO ALL THE WAY TO THE BACKWALL RADIUS.  THE CRACK IS APPROXIMATELY .5 INCH LONG AND LOOKS LIKE I	T MAY HAVE BEEN CAUSED BY CORROSION PITS UNDERNEATH THE ORIGINAL ADHESIVE.  ERICKSON HAD NOT REPLACED THIS POCKET AND IT	 IS UNKNOWN IF THE POCKET HAS EVER BEEN REPLACED.		2	G	7	2 	4U				H6EA
1998051500438	19980515	00438	NE  	1998	5	15	98ZZZX1743       	1	19980415	G	6520	6535807054	CENTER HOUSING  		643566001047	SKRSKY	S64   	S64F        		NE  										TAIL GEARBOX	CRACKED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	178AC	3149 	1146 			64097				TAIL ROTOR GEARBOX WAS REMOVED FROM AIRCRAFT DUE TO A CRACK IN THE TAIL GEARBOX CENTER HOUSING WEB ADJACENT TO THE LOWER	 LEFT GEARBOX ATTACHMENT LUG.  ENGINEERING REQUESTED THE QUALITY DEPARTMENT HELP FIND THE CRACKED AREA BECAUSE IT WAS NO	T MARKED ON THE PART NOR WAS IT VISIBLE TO THE EYE.				2	G	7	2 	4U				H6EA
1998051500667	19980515	00667		1998	5	15	98ZZZX1747       	4	19980412	G	3120	E19559	COUNTER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC					7509				CYCLE COUNTER QUIT OPERATING AFTER APPROXIMATELY 2 MONTHS.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500668	19980515	00668	EU  	1998	5	15	98ZZZX1748       	1	19980307	G	2841	1179405403	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL QUANTITY	INTERMITTENT    	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC				1104	7509				MAIN FUEL INDICATION INTERMITTENTLY DROPS TO 5 GALLONS THEN RETURNS TO NORMAL.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500669	19980515	00669		1998	5	15	98ZZZX1749       	4	19980323	G	3120	E19558	COUNTER         			BOLKMS	BK117 	BK117C1     	5626025	EU  										CYCLE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC					7509				CYCLE COUNTER NEW - NEVER USED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500670	19980515	00670	EU  	1998	5	15	98ZZZX1750       	1	19980323	G	6320	IPT20RT1100080G	TRANSDUCER      			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRANSMISSION	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC				59085312	7509				TRANSDUCER FAILED.  NEVER USED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500671	19980515	00671	EU  	1998	5	15	98ZZZX1751       	1	19980416	G	2430	SP461300	SWITCH          			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAIN PANEL	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC					7509				SWITCH TIES INTERMITTENTLY.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500672	19980515	00672	EU  	1998	5	15	98ZZZX1752       	1	19980313	G	2900	2811T10001	ACTUATOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENG HEATER	FAILED          	B			TI1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	05	117NC				103	7509				HEATER CAUTION LIGHT COMES ON WITH BOTH ENGINE HEATERS SELECTED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500673	19980515	00673	EU  	1998	5	15	98ZZZX1753       	1	19980320	G	7931	IPT70RT11000250	TRANSDUCER      			BOLKMS	117   	BK117A3     	5626015	EU  										OIL PRESSURE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH	230  			58939A388	7061				OIL PRESSURE TRANSDUCER FLUCTUATES AND DROPS TO ZERO.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998051500675	19980515	00675	SW  	1998	5	15	98ZZZX1755       	1	19980328	G	3150	222375010131	ANNUNCIATOR PNL 			BELL  	222   	222U        	1182140	SW  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	222HX				155	47533				ANNUNCIATOR PANEL NR 2 ENGINE FUEL VALVE CAUTION AND NR 2 FUEL LOW LIGHTS INOPERATIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW
1998051500676	19980515	00676	EU  	1998	5	15	98ZZZX1756       	1	19980405	G	6420	1053170023	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BEARING HAS PLAY.  SCRAPPED ON SIGHT.						1	G	7	2 	3U			NC	H13EU
1998051500677	19980515	00677	EU  	1998	5	15	98ZZZX1757       	1	19980405	G	6420	1053170023	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BEARING HAS PLAY.  SCRAPPED ON SIGHT.						1	G	7	2 	3U			NC	H13EU
1998051500678	19980515	00678	EU  	1998	5	15	98ZZZX1758       	1	19980401	G	6720	11731822	PITCH LINK      			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R CONT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BEARINGS WORN.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H13EU
1998051500679	19980515	00679	EU  	1998	5	15	98ZZZX1759       	1	19980405	G	5412	117601131	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FIREWALL CRACKED AT LOWER LEFT HAND CORNER.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500680	19980515	00680	EU  	1998	5	15	98ZZZX1760       	1	19980408	G	6220	10513144	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				ROD END BEARING PLAY.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U			NC	H13EU
1998051500681	19980515	00681	EU  	1998	5	15	98ZZZX1761       	1	19980408	G	6220	10513143	ROD END         			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				ROD END BEARING PLAY.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U			NC	H13EU
1998051500682	19980515	00682	EU  	1998	5	15	98ZZZX1762       	1	19980402	G	6330	1171120301	ROD ASSY        			BOLKMS	BK117 	BK117C1     	5626025	EU  										M/R XMSN MT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	2236 			0444	7505				ROD ASSY BEARINGS SPINNING IN LINK.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500683	19980515	00683	EU  	1998	5	15	98ZZZX1763       	1	19980421	G	8200	CT16120	CONTROLLER      			BOLKMS	BK117 	BK117C1     	5626025	EU  										WATER ALCOHOL	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				S785243E08J	7505				FLASHES '8'S' ON DISPLAY UPON INITIAL INSTALLATION.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500684	19980515	00684		1998	5	15	98ZZZX1764       	4	19980413	G	3416	10222011886	ALTIMETER       			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENCODE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				144203	7505				ENCODE ALTIMETER REPORTS WRONG ALTITUDE INTERMITTENTLY.  FOUND AIR INLET SCREEN OFF AND ROLLING AROUND INSIDE OF UNIT AT	 REMOVAL.  REMOVED AND REPLACED.					1	G	7	2 	3U			NC	H13EU
1998051500685	19980515	00685		1998	5	15	98ZZZX1765       	4	19980401	G	3452	066011410101	TRANSPONDER     			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				11246	7505				TRANSPONDER INTERMITTENTLY SENDS OUT FAULTY ENCODING.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500686	19980515	00686		1998	5	15	98ZZZX1766       	4	19980401	G	2211	11788292	COMPUTER        			BOLKMS	BK117 	BK117C1     	5626025	EU  										SPAS	FAILED          	B			TI1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	317MC				1191238	7505				SPAS WILL NOT SELF-TEST.  ACTUATOR VOLTAGE POLARITY IS REVERSED ON PIN 7 WITH 140 KNOTS AIRSPEED INDICATED.  REMOVED AND	 REPLACED.					1	G	7	2 	3U			NC	H13EU
1998051500687	19980515	00687		1998	5	15	98ZZZX1767       	4	19980401	G	3455	066107204	RECEIVER        		KR87        	BOLKMS	BK117 	BK117C1     	5626025	EU  										ADF	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				61022	7505				ADF INTERMITTENTLY LOSES SIGNAL LOCK.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500688	19980515	00688		1998	5	15	98ZZZX1768       	4	19980401	G	2211	391110002	ACTUATOR        			BOLKMS	BK117 	BK117C1     	5626025	EU  										PITCH BIAS	FAILED          	B			TI1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	317MC				430	7505				SPAS WILL NOT SELF-TEST.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500689	19980515	00689	EU  	1998	5	15	98ZZZX1769       	1	19980326	G	5412	117600651	COVER           			BOLKMS	BK117 	BK117C1     	5626025	EU  										LT FORWARD	SEPARATED       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				BOOT SEPARATED FROM SCREEN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500690	19980515	00690	EU  	1998	5	15	98ZZZX1770       	1	19980228	G	2822	1176415103	BOOST PUMP      			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC				172085	7505				BOOST PUMP FUNCTIONS INTERMITTENTLY.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500691	19980515	00691	EU  	1998	5	15	98ZZZX1771       	1	19980410	G	5412	1176625501	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				FIREWALL CRACK AT WELDS.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500693	19980515	00693	SW  	1998	5	15	98ZZZX1773       	1	19980407	G	6230	204011402021	INNER RING      			BELL  	212   	212         	1181420	SW  										SWASHPLATE	CRACKED         	B	S		ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	XAIUR		1000 		RE0400	30938				SWASHPLATE WAS REMOVED FOR 1,000 HOUR INSPECTION AND UPON DISASSEMBLY, EAR WAS FOUND CRACKED AT BOLT HOLE.						1	G	7	1 	4U				H4SW
1998051500932	19980515	00932	SW  	1998	5	15	98ZZZX1777       	1	19980409	G	7130	23009594	FIRESHIELD      			BELL  	206   	206L1       	1182107	SW  										ENGINE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	400SL					45235				VERTICAL FIRE SHIELD CRACKED.  WELD REPAIR MARKED AREA.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1998051500933	19980515	00933	EU  	1998	5	15	98ZZZX1778       	1	19980330	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										TRIPLE TACH	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X				426	S7038				TRIPLE TACH NR 2 ENGINE RPM INTERMITTENT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998051500934	19980515	00934	SW  	1998	5	15	98ZZZX1779       	1	19980301	G	6320	1223328	SEAL            			BELL  	230   	230         	1182149	SW  										M/R GEARBOX	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	4UV					23019				SEAL CHIPPED AND LEAKING.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500935	19980515	00935	SW  	1998	5	15	98ZZZX1780       	1	19980318	G	6330	222331618105	ISOLATION MOUNT 			BELL  	230   	230         	1182149	SW  										XMSN MOUNT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				BR1056	23019				ISOLATION MOUNT BEARING WORN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500936	19980515	00936	SW  	1998	5	15	98ZZZX1781       	1	19980422	G	6220	222310503101	PAD BEARING     			BELL  	230   	230         	1182149	SW  										M/R	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				LK0005	23019				PAD BEARING DEBONDED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500937	19980515	00937	SW  	1998	5	15	98ZZZX1782       	1	19980422	G	2430	1820300150	SHUNT           			BELL  	230   	230         	1182149	SW  										DC SYSTEM	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				WORN SHUNT.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U			NC	H9SW
1998051500938	19980515	00938	SW  	1998	5	15	98ZZZX1783       	1	19980302	G	2432	39563001	BATTERY         			BELL  	230   	230         	1182149	SW  										STANDBY IND	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				9303476	23019				STANDBY ATTITUDE INDICATOR BATTERY WILL NOT CHARGE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500939	19980515	00939	SW  	1998	5	15	98ZZZX1784       	1	19980223	G	6410	222016001123	BLADE           			BELL  	230   	230         	1182149	SW  										T/R	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1207 			A1135	23019				T/R BLADE CRACKED ON TRAILING EDGE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500940	19980515	00940	SW  	1998	5	15	98ZZZX1785       	1	19980322	G	3150	065001580102	PANEL           		KCP520      	BELL  	230   	230         	1182149	SW  										COCKPIT	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV				P1008	23019				WARNING PANEL POSSIBLE 'NO AUDIO WARNING WITH AN AUTOPILOT DISCONNECT'.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500941	19980515	00941	SW  	1998	5	15	98ZZZX1786       	1	19980410	G	6400	222012711107	LINK ASSY       			BELL  	230   	230         	1182149	SW  										T/R COUNTERWT	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				BEARINGS WORN ON T/R COUNTERWEIGHT ASSY.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500942	19980515	00942	SW  	1998	5	15	98ZZZX1787       	1	19980410	G	6720	230312001101	PITCH LINK      			BELL  	230   	230         	1182149	SW  										T/R	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				BEARINGS WORN ON T/R PITCH LINK.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998051500943	19980515	00943	GL  	1998	5	15	98ZZZX1788       	2	19980401	G	7250	6851531	NOZZLE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					NR 4	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF	182  			ER20738	S663				CRACKED DIAPHRAGM.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998051500944	19980515	00944	GL  	1998	5	15	98ZZZX1789       	2	19980401	G	7250	6878498	NOZZLE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20      	03013	GL  					NR 2	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF	182  			X46696	S663				NR 1 BLADE PATH BREAKING OUT NOZZLE NR 2.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998051500969	19980515	00969	CE  	1998	5	15	98ZZZX1814       	1	19980412	G	3246	12881003011	WHEEL           			BEECH 	MU300 	400A        	1155402	CE  										MLG	DAMAGED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	25	768TA	242  				RK168				BOTH MAIN TIRES BLOWN, BOTH WHEELS OVERHEATED, RIGHT WHEEL GROUND DOWN APPROXIMATELY 3 INCHES, BOTH BRAKES ASSEMBLIES OV	ERHEATED, ROTORS FUSED TOGETHER WITH THE STATORS, BOTH WHEEL SPEED TRANSDUCERS OVERHEATED, LEFT ONE HARD TO SPIN, RIGHT 	ONE HAD THE WINDINGS SHORTED.  SUSPECT ACFT LANDED WITH THE BRAKES LOCKED.  FOUND EMERGENCY BRAKE BREAKAWAY WIRE BROKEN 	AND EMERGENCY BRAKE NITROGEN BOTTLE LOW.  DUE TO THE LOCATION OF THE EMERGENCY BRAKE HANDLE, IT MAY BE POSSIBLE TO ACCID	ENTALLY ACTIVATE IT WITH THE COPILOT'S LEFT KNEE.		2	H	7	2 	4F			RT	A16SW
1998051500970	19980515	00970	CE  	1998	5	15	98ZZZX1815       	1	19980412	G	3240	400800297	BRAKE           			BEECH 	MU300 	400A        	1155402	CE  										MLG	DAMAGED         	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	25	768TA	242  				RK168				BOTH MAIN TIRES BLOWN, BOTH WHEELS OVERHEATED, RIGHT WHEEL GROUND DOWN APPROXIMATELY 3 INCHES, BOTH BRAKES ASSEMBLIES OV	ERHEATED, ROTORS FUSED TOGETHER WITH THE STATORS, BOTH WHEEL SPEED TRANSDUCERS OVERHEATED, LEFT ONE HARD TO SPIN, RIGHT 	ONE HAD THE WINDINGS SHORTED.  SUSPECT ACFT LANDED WITH THE BRAKES LOCKED. FOUND EMERGENCY BRAKE BREAKAWAY WIRE BROKEN A	ND EMERGENCY BRAKE NITROGEN BOTTLE LOW.  DUE TO THE LOCATION OF THE EMERGENCY BRAKE HANDLE, IT MAY BE POSSIBLE TO ACCIDE	NTALLY ACTIVATE IT WITH THE COPILOT'S LEFT KNEE.		2	H	7	2 	4F			RT	A16SW
1998051500971	19980515	00971	EU  	1998	5	15	98ZZZX1816       	1	19980327	G	7810	117651121	TAIL PIPE       			BOLKMS	117   	BK117A1     	5626010	EU  										CONE STRUT	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					ADS735301					FOUND TAIL PIPE HAS TWO CRACKS INSIDE CONE ON CROSS STRUTS.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998051500972	19980515	00972		1998	5	15	98ZZZX1817       	4	19980408	G	3421	4021541671	GYRO            			BOLKMS	117   	BK117B2     	5626013	EU  										HORIZ	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					82070909					WHEN INSTALLED IN AIRCRAFT, GYRO DOES NOT STAY ERECT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998051500973	19980515	00973		1998	5	15	98ZZZX1818       	4	19980324	G	2211	11788292	COMPUTER        			BOLKMS	117   	BK117B1     	5626012	EU  										SPAS	FAILED          	B			TI1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	05					018803150					FAILED INITIAL TESTS - SPAS LIGHT STAYS ON.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998051500974	19980515	00974	SW  	1998	5	15	98ZZZX1819       	1	19980408	G	6710	222010408113	LEVER           			BELL  	222   	222         	1182122	SW  										CYCLIC	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05		1315 			EA339					RECEIVED OVERHAULED FROM BELL.  LINK FROM LEVER TO SWASHPLATE WILL NOT FIT LEVER.  LEVER END BUSHING NOT MILLED RIGHT. R	EMOVED AND REPLACED.					1	G	7	2 	3U				H9SW
1998051500975	19980515	00975	EU  	1998	5	15	98ZZZX1820       	1	19980327	G	7332	10593910	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					DIFF PRESS	FAILED          	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					2201					DIFFERENTIAL PRESSURE SWITCH DEFECTIVE.  INSTALLED ON AIRCRAFT AND DID NOT FUNCTION.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998051500976	19980515	00976		1998	5	15	98ZZZX1821       	4	19980401	G	2211	11788292	COMPUTER        			BOLKMS	117   	BK117B1     	5626012	EU  										SPAS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					0189108					SPAS WILL NOT SELF-TEST.  ACTUATOR VOTLAGE IS REVERSED ON PIN 7 WITH 140 KNOT INDICATED AIRSPEED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998051500977	19980515	00977	GL  	1998	5	15	98ZZZX1822       	2	19980330	G	7321	25490923	FUEL CONTROL    			SKRSKY	S76   	S76         	8143010	NE  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					85140002					FUEL CONTROL OUT OF STOCK OVERHAUL.  ENGINE WOULD NOT GO ABOVE 30 PERCENT OR 500 DEGREES CELSIUS.  HANGS.  REMOVED AND R	EPLACED.					1	G	7	2 	3U	3	U		H1NE    	E1GL
1998052200001	19980522	00001	EU  	1998	5	22	98ZZZX1823       	1	19980109	G	2820	1176413401	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL CROSSTUBE	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - SCRAPPED 4 ON SITE.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U			NC	H13EU
1998052200002	19980522	00002	EU  	1998	5	22	98ZZZX1824       	1	19980109	G	2820	1176415801	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - SCRAPPED ON SITE.  REMOVED AND REPLACED 4 EACH.						1	G	7	2 	3U			NC	H13EU
1998052200003	19980522	00003	EU  	1998	5	22	98ZZZX1825       	1	19980109	G	2820	1176415601	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEAL USED TO REPAIR FUEL LEAK - SCRAPPED ON SITE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998052200004	19980522	00004	EU  	1998	5	22	98ZZZX1826       	1	19980109	G	2820	1176415603	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEAL USED TO REPAIR FUEL LEAK - SCRAPPED ON SITE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998052200005	19980522	00005	EU  	1998	5	22	98ZZZX1827       	1	19980109	G	2820	1176415901	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - SCRAPPED ON SITE.  REMOVED AND REPLACED 2 EA.						1	G	7	2 	3U			NC	H13EU
1998052200006	19980522	00006	EU  	1998	5	22	98ZZZX1828       	1	19980109	G	2820	1176415903	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEAL USED TO REPAIR FUEL LEAK - SCRAPPED ON SITE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998052200007	19980522	00007	EU  	1998	5	22	98ZZZX1829       	1	19980109	G	2820	1176415701	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - 7 SCRAPPED ON SITE.						1	G	7	2 	3U			NC	H13EU
1998052200008	19980522	00008	EU  	1998	5	22	98ZZZX1830       	1	19980109	G	2820	1176415703	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - 2 SCRAPPED ON SITE.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H13EU
1998052200009	19980522	00009	EU  	1998	5	22	98ZZZX1831       	1	19980109	G	2820	1176415501	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - 2 SCRAPPED ON SITE.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H13EU
1998052200010	19980522	00010	EU  	1998	5	22	98ZZZX1832       	1	19980109	G	2820	1176415503	SEAL            			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUEL SYSTEM	LEAK            	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	117NC					7509				SEALS USED TO REPAIR FUEL LEAK - 2 SCRAPPED ON SITE.  REMOVED AND REPLACED 2 EACH.						1	G	7	2 	3U			NC	H13EU
1998052200011	19980522	00011	SW  	1998	5	22	98ZZZX1833       	1	19980129	G	6710	121810064603	TRIM SWITCH     			HUGHES	500N  	500N        	3027374	SW  										PILOT CYCLIC	FAILED          	C		A	PO7M	K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	523FB	598  				LN003				CYCLIC TRIM SWITCH RUNS AWAY TO RIGHT SIDE.						1	G	7	1 	3U			NC	H3WE
1998052200026	19980522	00026	SW  	1998	5	22	98ZZZX1848       	1	19980427	G	7722	2060751907	INDICATOR       			BELL  	206   	206B        	1181511	SW  										TOT	ERROR           	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K					2040				INSTALLED, TESTED, AND FOUND 10 PERCENT OFF ON THE LOW SIDE, ALL RANGES.  SENT BACK TO OVERHAUL SHOP.  TEST PROCEDURE IN	DICATES A 10 MINUTE WARM-UP PERIOD IS REQUIRED.  INDICATOR WAS REINSTALLED IN AIRCRAFT.  WARMED UP FOR 10 MINUTES AND TE	STED.  FOUND TO BE ACCURATE.  CONTROL NR 98-4-13.				1	G	7	1 	3U				H2SW
1998052200027	19980522	00027	SO  	1998	5	22	98ZZZX1849       	1	19980318	G	2436	VR371	REGULATOR       	ELECTRODELTA		PIPER 	PA28  	PA28180     	7102808	SO  										ALTERNATOR CONT	NOISY           	B			ACOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	9790J	100  			4092819	283992				ADF WOULD NOT POINT BELOW 500 HKZ DUE TO ELECTRICAL NOISE GENERATED BY ALTERNATOR SYSTEM.  FOUND THIS TYPE UNIT CAUSED I	NTERFERENCE DUE TO SWITCHING FREQUENCY OF REGULATION SYSTEM.  ELEIMINATED PROBLEM BY RETURNING ALTERNATOR CONTROL SYSTEM	 TO OLDER LOW FREQUENCY REGULATOR SYSTEM.				1	L	7	1 	3O				2A13
1998052200028	19980522	00028	WP  	1998	5	22	98ZZZX1850       	1	19980401	G	7830	5958782503	LINK            			DOUG  	DC9   	DC9*        		WP  										THRUST REV	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										THREE LINKS FOUND CRACKED USING DOUGLAS NDT 8-1 INSPECTION.  THESE LINKS ARE NEW.  LINKS ARE AFFECTED BY AD 96-10-11, DO	UGLAS SB 78-66.  THIS HAS BEEN REPORTED TO DOUGLAS ON 5-5-98.					2	L	7	2 	4F				A6WE
1998052200029	19980522	00029		1998	5	22	98ZZZX1851       	4	19980427	G	2562	AK450	ELT             	AMERIKING   																ANTENNA	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										SUBMITTER REPORTS A DIFFICULTY WITH AMERIKING ELT MODEL AK450 ANTENNAS SLIDING OUT OF CLIPS LOCATED ON THE SIDE OF ELT B	RACKET.  SUBMITTER CORRECTED DEFECT BY WRAPPING ANTENNA WITH ELECTRICAL TAPE.
1998052200030	19980522	00030	SO  	1998	5	22	98ZZZX1852       	2	19980430	G	7322	30764	FLOAT           	FACET       	10396512    	CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470L       	17026	SO  					CARBURETOR	DETACHED        	B			KZ3R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	9208T	925  			H236694	50708	804379L4			WEAR WHERE CARBURETOR FLOAT NEEDLE RIDES.  PIVOT POINT VERY LOOSE.  FLOAT DETACHED.  PRECISION HAS NEW FLOAT THAT IS COM	POSITE.  THE ONLY INDICATION WAS THAT THE CARBURETOR WAS DRIPPING AFTER A FLIGHT.					1	H	7	1 	3O	3	O		5A6     	E273
1998052200031	19980522	00031	SO  	1998	5	22	98ZZZX1853       	1	19980504	G	2430	455211	CONTACTOR       			PIPER 	PA31  	PA31350     	7103110	SO  										BATTERY	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	20LX					317552121				WENT TO SERVICE BATTERY AND FOUND BATTERY RELAY BROKEN AND WIRES BURNED.  THE SYSTEM STILL WORKED, BUT SUBMITTER DOES NO	T KNOW HOW LONG RELAY EAR HAD BEEN BROKEN OFF.  IT SEEMS THAT EVEN THOUGH THE EAR ON THE CONTACTOR HAD BROKEN OFF, IT WA	S STILL ABLE TO MAKE CONTACT, BUT SINCE THERE WAS HIGH RESISTANCE, IT CREATED A LOT OF HEAT AND BURNED THE WIRES.  THIS 	IS THE ORIGINAL CONTACTOR MFG 1975 BY CUTLER-HAMMER 200 AMP SP-ST 28V.  SUBMITTER SUSPECTS PART MIGHT HAVE BROKEN FROM A	GE		1	L	7	2 	3O				A20SO
1998052200032	19980522	00032		1998	5	22	98ZZZX1854       	4	19980212	G	2562	SHARC7	ELT             	LEIGH       		PIPER 	PA32  	PA32300     	7103212	SO  										ANTENNA	MISINSTALLED    	B			ACOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05	4057R					3240361				FOUND AND REMOVED RIGHT ANGLE CONNECTOR ADAPTER TERMINATED WITH A 50 OHM RESISTOR AT ANTENNA CONNECTOR OF ELT.  RADIATED	 OUTPUT POWER FROM ELT WOULD HAVE BEEN REDUCED BY AT LEAST 75 PERCENT.					1	L	7	1 	3O			 	A3SO
1998052200033	19980522	00033	EA  	1998	5	22	98ZZZX1855       	2	19980430	G	8520	L18639	GEAR LOCKPLATE  		LW17281     	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360A1H     	41514	EA  					CRANKSHAFT	BROKEN          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	191ND	2206 	296  			4495003	LW2269136A			DURING SCHEDULED ENGINE INSPECTION, CRANKSHAFT LOCK TAB WAS FOUND IN THE OIL SUMP SCREEN.  REMOVED SUMP AND ACCESSORY HO	USING TO VERIFY.  TAB ON BOLT WAS CONFIRMED BROKEN.  CRANKSHAFT GEAR BOLT WAS FOUND TO HAVE MINIMAL TORQUE REMAINING.  (	LESS THAN 100 INCH/POUND).  NEW BOLT AND LOCKPLATE INSTALLED PER LYCOMING INSTRUCTIONS AND RE-ASSEMBLED ENGINE.  ENGINE 	HAS 295.6 HOURS SINCE FACTORY OVERHAUL ON 10-21-97.			1	L	7	2 	3O	3	O		A19S0   	E286
1998052200034	19980522	00034	CE  	1998	5	22	98ZZZX1856       	2	19980224	G	8530	649263	INTAKE TUBE     			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					NR 3	CRACKED         	B			OVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	252BS	554  				251107	317110			INTAKE TUBE CRACKED AT FLANGE.  SUBMITTER STATED RESEARCH OF AIRCRAFT RECORDS DETERMINED THIS WAS THE THIRD INDUCTION TU	BE IN THIS LOCATION THAT HAD CRACKED IN 1,100 HOURS.  PART MISALIGNED WITH INDUCTION PLENUM.					1	L	7	1 	3O	3	O		2A3     	E9CE
1998052200036	19980522	00036	EA  	1998	5	22	98ZZZX1858       	2	19980506	G	8520		CAMSHAFT        			CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					LOBES	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6341S		1482 			R18201662	L2152240A			ENGINE HAS LOW POWER.  REMOVED CYLINDERS FOR TOP OVERHAUL AND FOUND CAM HAD BAD LOBES.  TBO ON THIS ENGINE IS 2,000 HOUR	S.					1	H	7	1 	3O	3	O		3A13    	E295
1998052200037	19980522	00037	SO  	1998	5	22	98ZZZX1859       	2	19980401	G	8530	626146	PISTON          			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300*      	17022	SO  					RING GROOVE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	6954E		680  			56454	55048A			AIRCRAFT WAS IN SHOP FOR ANNUAL INSPECTION, CHECKING COMPRESSIONS.  FOUND 3 CYLINDERS WITH BELOW ACCEPTABLE COMPRESSION 	READINGS.  PULLED CYLINDERS TO EXAMINE.  FOUND BROKEN RINGS IN 2 CYLINDERS AND CRACKED PISTONS.  DECISION WAS MADE TO RE	MOVE THE 3 OTHER ACCEPTABLE CYLINDERS.  OUT OF 6 CYLINDERS, 5 PISTONS WERE CRACKED STARTING FROM AN OIL RETURN HOLE AT T	HE 4 RING GROOVE UP.  OUT OF 5 PISTONS WITH CRACKS, 2 OUT OF 5 HAD BROKEN RINGS ALSO WHICH RENDERED THE BARRELS OF CYLIN	DERS UNSERVICEABLE AND SCRAP.		1	H	7	1 	3O	3	O		3A17    	E298
1998052200039	19980522	00039	SO  	1998	5	22	98ZZZX1861       	2	19980411	G	8520	626168	CONNECTING ROD  			CESSNA	175   	175         	2072502	CE  	CONT  	O300  	GO300A      	17022	SO  					CYL NR 2	FAILED          	D				O				OTHER                   				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			SO	06	7111M	1233 				55411	101631AR			CONNECTING ROD BROKE AT PISTON PIN AREA.  REMAINING POSTION OF ROD PUNCHED HOLE IN CRANKCASE, DAMAGED PISTON, AND RESULT	ED IN ENGINE SHUT DOWN.					1	H	7	1 	3O	3	O	NT	3A17    	E298
1998052200040	19980522	00040	EA  	1998	5	22	98ZZZX1862       	2	19980429	G	8530	SL10302A21P	CYLINDER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 VALVE SEAT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	714TG					15279415	L1740815			INSTALLED NEW CYLINDER ASSEMBLIES.  HAD NO COMPRESSION NR 1 CYLINDER.  REMOVED, FOUND METAL CHIP UNDER VALVE.  SUSPECT C	AUSE - IMPROPER CLEANING PROCEDURE PRIOR TO ASSEMBLY.  SUBMITTER RECOMMENDATION - MORE USEFUL INSPECTION (QC).					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998052200041	19980522	00041	SW  	1998	5	22	98ZZZX1863       	1	19980507	G	2133	1036484	OUTFLOW VALVE   			GULSTM	560   	560         	0141402	SW  										CABIN PRESS	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	777KY	900  				5600108				OPERATOR HAD PRESSURIZATION PROBLEM ON CESSNA 560.  THIS INFORMATION MAY BE PREMATURE, BUT HE HAS NOT HEARD BACK FROM CE	SSNA OR ALLIED-SIGNAL ON THE PROBLEM.  SUBMITTER SUSPECTS THAT AD 96-17-10 SHOULD HAVE INCLUDED MORE DASH NUMBERS.  OUTF	LOW VALVE WAS A 103648-14.  THE BEECHCRAFT AD TOOK IN 103648-1 THROUGH 13-I.  SUBMITTER STATED THERE IS NO AD ON THE CIT	ATIONS.			1	H	7	2 	3O				6A1
1998052200042	19980522	00042	SO  	1998	5	22	98ZZZX1864       	1	19980429	G	7120	6711957	MOUNT           			PIPER 	PA28  	PA28R201    	7102816	SO  										ENGINE	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	810ND	6319 				2837019				FOUND ENGINE MOUNT CRACKED AT LOWER LEFT MOUNT RING JUST BELOW LORD MOUNT.  CRACK IS ALONG WELD WHERE DIAGONAL TUBE FROM	 FIREWALL MOUNT POINT JOINS MOUNT AT RING.					1	L	7	1 	3O				2A13
1998052200045	19980522	00045	SO  	1998	5	22	98ZZZX1867       	1	19980501	G	3250	1159SCH4033	VALVE           			GULSTM	G1159 	GIV         	3980115	SO  										STEERING SOV	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2610	278  			353A	1094				DURING LINE OP CHECK JUST PRIOR TO DEPARTURE, CREW OBSERVED 'STEER-BY-WIRE FAIL' MESSAGE ON CASDU AND ALSO FOUND NR 1 AN	D NR 2 STEERING CONTROL CIRCUIT BREAKERS TRIPPED.  BREAKERS WOULD NOT RESET.  AIRCRAFT TAXIED BACK TO RAMP WITH DIFFEREN	TIAL BRAKING.  MAINTENANCE FOUND STEERING SYSTEM NR 1 SOLENOID SHUT-OFF VALVE CAUSING FAULT AND REPLACED SAME AND RETURN	ED AIRCRAFT TO SERVICE.			2	L	7	2 	4F			RT	A12EA
1998052200046	19980522	00046	CE  	1998	5	22	98ZZZX1868       	1	19980430	G	5610	10138402517	WINDSHIELD      			BEECH 	300   	300BEECH    	1152930	CE  										PILOTS	SHATTERED       	B			TUDR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	13	300PE					FA27				PILOT'S WINDSHIELD SHATTERED AT 29,000 FEET.  PILOT REPORTED THIS TO BE SECOND WINDSHIELD FAILURE IN ABOUT A ONE-YEAR TI	ME SPAN.					2	L	7	2 	4T				A24CE
1998052200047	19980522	00047	CE  	1998	5	22	98ZZZX1869       	1	19980423	G	2460		CONNECTION      			CESSNA	650   	650         	2076802	CE  										AUX DC J-BOX	LOOSE           	D				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	09	313QS	7009 				650013				PILOT REPORTED AFT J-BOX CB ANNUNCIATOR ILLUMINATED IN-FLIGHT.  FOUND BAGGAGE HEAT AND APU AUX HYD PUMP CONTROL CB'S LOC	ATED IN AUX DC J-BOX TRIPPED.  USED AN INSP MIRROR AND FOUND NO OBVIOUS WIRING DEFECTS.  AFTER SEVERAL HRS OF SYS T/S AF	T J-BOX CB ANNUNCIATOR ILLUMINATED.  SMOKE WAS EMITTING FROM AUX J-BOX, ALL SYSTEMS WERE SHUT DOWN, FIRE WAS EXTINGUISHE	D.  DURING AUX J-BOX REMOVAL, THE SELF-LOCKING NUT SECURING TERMINAL LUG OF MAIN POWER CABLE WAS FOUND LOOSE.  HEAT GENE	RATED FROM ADDED RESISTANCE TRIPPED CB'S AND CAUSED FIRE.  AUX J-BOX PREVIOUSLY REMOVED 1-97 TO ACCOMPLISH SB 29-9.  PHA	SES 1-5 COMPLETED 2-98.	2	L	7	2 	4F				A9NM
1998052200048	19980522	00048		1998	5	22	98ZZZX1870       	4	19980310	G	3455	BT06A1210S	CONNECTOR       		KDF805      	BEECH 	90    	C90         	1152913	CE  										ADF LOOP CABLE	FAILED          	B			ACOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4449Q	3140 				LJ895				WIRES BROKE INSIDE CABLE AT FACE OF HARD EPOXY POTTING COMPOUND.  CONNECTOR HAD NO STRAIN RELIEF.  BOTH SYSTEMS HAD SIMI	LAR FAILURE.  CABLES WERE REPAIRED BY CUTTING OFF CONNECTORS AND POTTED AREA OF CABLES, RETERMINATING SHIELDS, AND INSTA	LLING NEW CONNECTORS WITH STRAIN RELIEF CLAMPS.				1	L	7	2 	3T				3A20
1998052200050	19980522	00050	EU  	1998	5	22	98ZZZX1872       	1	19980429	G	7830	54535213	LATCH ACTUATOR  			BRAERO	DH125 	BAE125800A  	1500285	EU  										LT THRUST REV	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	527M	4773 			33	258054				INSPECTION FOUND LT THRUST REV INBD LATCH ACTUATOR CRACKED.						2	L	7	2 	4F			RT	A3EU
1998052200051	19980522	00051	EU  	1998	5	22	98ZZZX1873       	1	19980325	G	5522		SKIN            			ISRAEL	1124  	1124        	4500102	EU  										LT ELEVATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	727AT	6594 				284				PIN HOLE CORROSION WAS FOUND ON UPPER SKIN.  FURTHER INVESTIGATION REVEALED SEVERE INTERIOR CORROSION.  THE PART WAS REP	LACED WTIH AN OVERHAULED ELEVATOR.					2	M	7	2 	4F				A2SW
1998052200054	19980522	00054	NE  	1998	5	22	98ZZZX1875       	2	19980505	G	7250	804131	CASE            		804127      						PWA   	JT8   	JT8D217A    	52053	NE  					ENGINE	CRACKED         	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					NX7298		717369			ENGINE REMOVED FROM SERVICE DUE TO TURBINE FAILURE.  DISASSEMBLY REVEALED HPC AND TURBINE FAILURE DUE TO C-8 SHELF CRACK	 FAILURE.										4	F			E9NE
1998052200582	19980522	00582	SW  	1998	5	22	98ZZZX1876       	1	19980505	G	6730	2040760551	VALVE           			BELL  	204   	UH1H        	1181407	SW  										LT SERVO	LEAKS           	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	52AG	4834 				7015746				LEFT SERVO VALVE LEAKS AT CAP, P/N 42596-2B.  CONTROL NR 98-5-1.						1	G	7	1 	4U				EXPA1G71
1998052200583	19980522	00583	SW  	1998	5	22	98ZZZX1877       	1	19980430	G	5312	20603240002	BULKHEAD        			BELL  	206   	206L1       	1182107	SW  										T/B ATTACH	CRACKED         	B			KBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5746N	7631 				45461				BULKHEAD FOUND CRACKED 1.6 INCHES RUNNING CIRCUMFERENTIALLY OUTBOARD OF LOWER LEFT HAND TAILBOOM ATTACH HOLE.  7 INCHES 	LONG.					1	G	7	1 	3U				H2SW
1998052200584	19980522	00584	SW  	1998	5	22	98ZZZX1878       	1	19980429	G	6220	206011149105	YOKE            			BELL  	206   	206B3       	1181506	SW  										M/R HEAD	WORN            	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6358S	1166 			H4394	4392				M/R HEAD YOKE ASSEMBLY WORN.  REPLACED WITH NEW YOKE AND DISC SET FROM BELL HELICOPTER.						1	G	7	1 	3U				H2SW
1998052200585	19980522	00585	SW  	1998	5	22	98ZZZX1879       	1	19980429	G	6220	327211	DISC SET        			BELL  	206   	206B3       	1181506	SW  										M/R HEAD	WORN            	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6358S	1166 				4392				M/R HEAD YOKE ASSEMBLY WORN.  REPLACED WITH NEW YOKE AND DISC SET FROM BELL HELICOPTER.						1	G	7	1 	3U				H2SW
1998052200586	19980522	00586	WP  	1998	5	22	98ZZZX1880       	1	19980402	G	6510	369A30103	DAMPENER SUPPORT			HUGHES	369   	OH6A        		WP  										T/R DRIVE SHAFT	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	6638R	2050 				6716198				DURING A 300-HOUR INSPECTION, A CRACK WAS NOTICED ON THE TAIL ROTOR DRIVE SHAFT DAMPENER SUPPORT.  AFTER REMOVING TAIL B	OOM, THE CRACK WAS ABOUT .75 INCHES LONG AND WAS FOUND ON TOP RIGHT PART OF BRACKET.					1	G	7	1 	3U				H3WE
1998052200587	19980522	00587	EU  	1998	5	22	98ZZZX1881       	1	19980120	G	6240	DL43638	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	FLUCTUATES      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	495LF				940	645				HIGH M/R RPM WARNING WAS BEING CAUSED BY A DEFECTIVE RPM WARNING BOX AND FLUCTUATING TRIPLE TACH INDICATOR.  BOTH UNITS 	WERE REPLACED AND A/C RETURNED TO SERVICE.					1	G	7	2 	3U				H3EU
1998052200588	19980522	00588	EU  	1998	5	22	98ZZZX1882       	1	19980120	G	6240	DKW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										M/R RPM	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	495LF				092	645				HIGH M/R RPM WARNING WAS BEING CAUSED BY A DEFECTIVE RPM WARNING BOX AND FLUCTUATING TRIPLE TACH INDICATOR.  BOTH UNITS 	WERE REPLACED AND A/C RETURNED TO SERVICE.					1	G	7	2 	3U				H3EU
1998052200589	19980522	00589	EU  	1998	5	22	98ZZZX1883       	1	19980424	G	7714	430106202	SENSOR          			BOLKMS	117   	BK117A3     	5626015	EU  										NG PICKUP	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911MZ				82A0194	7098				INDICATION FAILURE.  TROUBLESHOOT TO NG PICKUP.  INSTALLED NEW PICKUP, OPS CHECK GOOD.						1	G	7	2 	3U				H13EU
1998052200590	19980522	00590	EU  	1998	5	22	98ZZZX1884       	1	19980427	G	3310	1179203103	CONTROL         			BOLKMS	117   	BK117A3     	5626015	EU  										INST LIGHTS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	118LL					7097				INTERNAL FAILURE OF INSTRUMENT LIGHTS' CONTROL UNIT.  CAUSE UNKNOWN.						1	G	7	2 	3U				H13EU
1998052200591	19980522	00591	WP  	1998	5	22	98ZZZX1885       	1	19980402	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				EXHAUST STACK CRACKED AROUND FLANGE MOUNT.  REMOVED AND REPLACED.  CONTROL NR 98-4-16.						1	G	7	1 	3U				H3WE
1998052200593	19980522	00593	SW  	1998	5	22	98ZZZX1887       	1	19980430	G	7120	206064105102	MOUNT           			BELL  	206   	206L1       	1182107	SW  										ENG RT LEG ASSY	CRACKED         	B			KBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2233F	8137 				45739				ENGINE MOUNT LEG BROKEN.  DURING PRE-FLIGHT INSPECTION, PILOT FOUND CORROSION FROM INSIDE/OUT 5.1 INCHES FROM BOTTOM. RE	COMMENDED FOR PREVENTION:  EPOXY POLYAMIDE PRIMER AND CORROSION PREVENTATIVE COMPOUND INSIDE DIAMETER DURING ASSY.  AFTE	R ASSY, SEAL END FASTENERS AND END FITTINGS.				1	G	7	1 	3U				H2SW
1998052200594	19980522	00594	EU  	1998	5	22	98ZZZX1888       	1	19980403	G	6320	6607A2114	SWITCH          			BOLKMS	105   	BO105LSA3   	5626020	EU  										GEARBOX PRESS	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV					2033				GEARBOX OIL PRESSURE MALFUNCTION IS COMMON DUE TO PRESSURE SWITCH.  SUBMITTER STATED THE SYSTEM NEEDS A PRESSURE GAUGE T	O VERIFY LIKE THE ENGINE OIL SYSTEM.					1	G	7	2 	3U				H3AU
1998052200595	19980522	00595	SW  	1998	5	22	98ZZZX1889       	1	19980506	G	2510	FDC2700	BELT            			BELL  	206   	206B        	1181511	SW  										COCKPIT	CORRODED        	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	614					1200				BELT BUCKLE IS SEVERELY CORRODED ON THE MALE FITTING AT THE WEBBING ATTACHMENT.  THE PLATING HAS BEEN EATEN AWAY FROM TH	E AREA UNDER THE WEBBING.  SURFACE CORROSION IS STARTING ON THE BOTTOM OF THE BUCKLE.  SUBMITTER STATED IT IS BELIEVED T	HAT IMPROPER CLEANING OF THE BELTS MAY HAVE ACCELERATED THE CORROSION UNDER THE WEBBING.				1	G	7	1 	3U				H2SW
1998052200597	19980522	00597	EU  	1998	5	22	98ZZZX1891       	1	19980324	G	6720	109013304101	LINK            			AGUSTA	A109  	A109C       	0260118	EU  										T/R CONT	MISRIGGED       	D		A		O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			GL	15	911D	110  				7637				PILOT REPORTED RT T/R CONTROL PEDAL HIT FULL STOP DURING RT DESCENDING TURN.  HELICOPTER COULD NOT BE TRIMMED.  DESCENT 	WAS SHALLOWED AND TRIM WAS ACHIEVED.  MECH PERFORMED T/R RIGGING CHECK AND FOUND THE FOLLOWING:  FULL LT PEDAL READING O	N T/R BLADES = 24.5 DEGREES; LIMIT PER MFG MM IS 21 DEGREES 10'.  FULL RT PEDAL READING WAS -4.75 DEGREES; LIMIT IS A RE	FERENCE OF -7 DEGREES.  INVEST REVEALED THE T/R SHORT PITCH LINKS P/N 109-0133-04-101 HAD BEEN REPLACED BY AGUSTA AEROSP	ACE CORP WITH P/N 109-0133-04-105 LINKS.  NO RIGGING CHECK WAS CALLED FOR IN THE MM AND NONE WAS PERFORMED.  P/N 109-013	3-04-105 LINKS ARE 3 MM SHORTER THAN -101 LINKS.	1	G	7	2 	3U				H7EU
1998052200599	19980522	00599	EU  	1998	5	22	98ZZZX1892       	1	19980506	G	7830	54535213	ACTUATOR        			BRAERO	DH125 	BAE125800A  	1500285	EU  										LT THRUST REV	FAILED          	C				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			SW	99	527M	4773 			33	258054				THE FAILURE OCCURRED DURING A FLIGHT CREW TRAINING FLIGHT CONSISTING OF 3 FULL STOP LANDINGS, AND TAKEOFFS.  ON THE 3RD 	LANDING, THE AIRCRAFT WAS CLEAR OF THE RUNWAY AND WAS TAXIING TO THE DEPARTURE END OF THE RUNWAY.  IDLE REVERSE THRUST W	AS BEING USED, AS NEEDED, TO CONTROL GROUND SPEED.  WHEN BOTH HYDRAULIC LOW PRESSURE WARNING LIGHTS CAME ON THE ENGINES 	WERE THEN SHUT DOWN AND THE AIRCRAFT WAS TOWED TO THE FBO FOR TROUBLESHOOTING BY THE FLIGHT CREW AND LOCAL MAINTENANCE P	ERSONNEL.  IT WAS FOUND THAT WHEN THE LEFT THRUST REVERSER WAS DEPLOYED, HYDRAULIC FLUID WOULD FLOW FROM THE LEFT INBOAR	D ACTUATOR FAIRING.  THE FAIRING WAS REMOVED.  THRUST REVERSER WAS AGAIN DEPLOYED AND THE ACTUATOR WAS FOUND LEAKING.	2	L	7	2 	4F			RT	A3EU
1998052200600	19980522	00600	GL  	1998	5	22	98ZZZX1893       	2	19980501	G	7310	47086	FILTER          		6890917     						ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	DIRTY           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23					1YF03504		CAT24382			FOUND SOME CONTAMINATION AT BASE OF FILTER SCREEN WHERE IT IS BRAZED TO MOUNTING BASE.  ABOUT 5 PERCENT OF FILTER CLOGGE	D WITH LIGHT TAN TO WHITE FLAKES AND FIBEROUS SUBSTANCE SLIGHTELY LARGER THAN SCREEN MESH.										3	U			E4CE
1998053000007	19980530	00007	EU  	1998	5	30	98ZZZX1894       	1	19980405	G	3250	242374	SHUTTLE         	VALCOR      	893954      	FOKKER	F27   	F27MK400    	4990626	EU  										STEERING VALVE	FAILED          	D	S			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	05	2MIL		631  		447	10652				UPON LANDING ROLL-OUT, PILOT NOTICED A LACK OF STEERING RESPONSE TO THE RIGHT.  AIRPLANE COULD BE TAXIED (USING REG STEE	RING CONTROL) ONLY TO THE LEFT.  DIFFERENTIAL POWER AND BRAKES WERE REQUIRED TO TURN RIGHT.  UPON DISASSY OF AIRMOTOR CO	NTROL VALVE ASSY, FOUND SHUTTLE PISTON SHAFT BROKEN IN THE THREADED PORTION OF THE SHAFT.  THE BROKEN PIECES EXHIBITED A	 FRESH APPEARANCE AT THE BREAK.  NOTED THAT ONE END (END WHICH FAILED) OF THE THREADED SHAFT HAD A SELF-LOCKING NUT INST	ALLED WHICH WAS 'PINNED' TO PREVENT ROTATION.  NO MENTION OF THIS CAN BE FOUND IN THE OVERHAUL MANUAL DURING INSTALLATIO	N.  US ARMY REGISTRATION:  8501607.	2	H	7	2 	4T				A817
1998052200601	19980522	00601	EU  	1998	5	22	98ZZZX1895       	1	19980409	G	2432	RG380E60L	BATTERY         	CONCORDEBATT		SAAB  	SF340 	SF340A      	7850100	EU  										DC SYSTEM	LEAKING         	D	P			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	05	747P	605  			275328	340A029				BATTERY CORRODED AND LEAKING ACID DOWN FRONT HOLES IN OUTSIDE ALUMINUM BOX.  REMOVED TOP OF BATTERY, ABSORBENT PADS WET 	WITH ACID.					2	L	7	2 	4T			RT	A52EU
1998052200602	19980522	00602	CE  	1998	5	22	98ZZZX1896       	1	19980316	G	3213	23421007	STRUT           			LEAR  	35    	35LEAR      	5170600	CE  										NLG	MALFUNCTION     	B			FEHR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	13	238RC	11644				35061				DEFLATED NOSE STRUT CAUSED NOSE GEAR NOT TO CENTER DURING GEAR RETRACTION.  EXTENDED LANDING GEAR AND NOSE WOULD NOT CEN	TER.  LANDED AIRCRAFT WITHOUT STEERING.  AIRPORT CONDITIONS VERY ROUGH DUE TO ICE ON RUNWAY.  POSSIBLE SCHRADER VALVE LE	AK, SERVICED AND STRUT WAS OK.				2	L	7	2 	4F				A10CE
1998052200603	19980522	00603	SO  	1998	5	22	98ZZZX1897       	1	19980427	G	5210	73192	ACTUATOR        			EMB   	120   	EMB120RT    		SO  										PASSENGER DOOR	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	238AS				681A	120053				DURING RE-INSTALLATION OF THE PASSENGER/CREW ENTRANCE DOOR PREVIOUSLY REMOVED FOR OTHER MAINTENANCE ON ATLANTIC SOUTHEAS	T EMB120 AIRCRAFT, SN 53, THE FORWARD DOOR ACTUATOR ROD WAS FOUND SHEARED.  INVESTIGATION REVEALED A CRACK ABOUT ONE-HAL	F WAY THROUGH THE THREADED AREA OF THE ACTUATOR.  THE CRACK COULD HAVE BEEN CAUSED BY OVER TORQUEING OF THE ROD END JAM 	NUT.  RECOMMEND INSPECTION OF THE ACTUATOR JAM NUT AREA DURING SCHEDULED 'C' CHECK INSPECTIONS.			2	L	7	2 	4T			RT	A31SO
1998052200604	19980522	00604	SO  	1998	5	22	98ZZZX1898       	1	19980420	G	5730	343282L	SKIN            			LKHEED	282   	C130A       	5262502	SO  										WS 33	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	130HP				3093	56538				INSPECTION FOUND 2 EACH 1 INCH CRACKS, CHORDWISE BOTTOM WING SURFACE OUTER WS 33, PANEL RISERS AT KING PIN RUN-OUT RIVET	 HOLE.					2	H	7	4 	4T				A31NM
1998052200606	19980522	00606	SO  	1998	5	22	98ZZZX1900       	1	19980507	G	7830	MS272403	SWITCH          			GULSTM	G1159 	GIV         	3980115	SO  										TR UNLOCK	DAMAGED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	800BG					1034				GULFSTREAM ISSUED CUSTOMER BULLETIN 92 WHICH ADJUSTED THE THRUST REVERSER UNLOCK SWITCHES.  NO DEFECTS WERE NOTED ON S/N	 1034.  LATER, GAC RE-ISSUED CB 92 AMI WHICH CANCELLED CB 92.  NEXT, CB 92A WAS ISSUED WHICH DID NOT FUNCTION  ON S/N 10	34.  IT DESTROYED THE SWITCHES DUE TO IMPROPER ADJUSTMENT INSTRUCTIONS.				2	L	7	2 	4F			RT	A12EA
1998052200607	19980522	00607	NE  	1998	5	22	98ZZZX1901       	3	19980331	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		7664 	3039 		2238NR			HJ293		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FO	UR CRACKS.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998052200608	19980522	00608	CE  	1998	5	22	98ZZZX1902       	1	19980417	G	2435	03600918	BEARING         	LEARSIEGLER 	23085001    	BEECH 	B300  	B300        	1159232	CE  										START/GEN	FAILED          	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	991LL	786  			96010	FL142				THIS STARTER/GENERATOR WAS REMOVED FROM AIRCRAFT FOR BRUSH CHANGE. THE BEARINGS WERE FOUND VERY ROUGH, EXTREMELY CLOSE T	O TOTAL FAILURE.  THEY WOULD NOT HAVE MADE 1,000 HOUR TBO!  THIS UNIT HAS THE LATEST SPRING LOADED BEARINGS, AND THE FIN	NED COMMUTATOR END FRAME FOR COOLING.  TIME IS 786.1 HOURS SINCE NEW.				2	L	7	2 	4T			RT	A24CE
1998052200609	19980522	00609	NE  	1998	5	22	98ZZZX1903       	3	19980421	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			4591 		2464NR			HJ183A		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TH	REE CRACKS.  TOTAL TIME ON PROPELLER ASSEMBLY IS 9,249.9 HOURS.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998052200610	19980522	00610	NE  	1998	5	22	98ZZZX1904       	3	19980415	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		12033	3553 		3694NR			HJ692		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TW	O CRACKS.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998052200611	19980522	00611	NE  	1998	5	22	98ZZZX1905       	3	19980414	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4117 			3094NR			HJ580		PROPELLER INSPECTION FOUND FORWARD EARS OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  F	OUR CRACKS.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998052200612	19980522	00612	NE  	1998	5	22	98ZZZX1906       	3	19980331	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3091 			3379NR			HJ712		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FOUR CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998052200613	19980522	00613	NE  	1998	5	22	98ZZZX1907       	3	19980422	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3965 			1865NR			HJ903		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  ON	E CRACK.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998052200614	19980522	00614	NE  	1998	5	22	98ZZZX1908       	3	19980310	G	6110	CP2000	BEARING         			AYRES 	S2    	S2RNORMAL   	7630202	SO  						HAMSTD	12D	12D40       	NE  	PROPELLER	FAILED          	B			T4PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	4913X					2104R		8099		PROPELLER BEARING ROLLERS FLAT IN 116 HOURS.  CAUSE UNKNOWN.  STC SP 78365W.						1	L	7	1 	3R			NC	A3SW    		5	C	P257
1998052200615	19980522	00615	NE  	1998	5	22	98ZZZX1909       	3	19980422	G	6110	CP2000	BEARING         			AYRES 	S2    	S2RNORMAL   	7630202	SO  						HAMSTD	12D	12D40       	NE  	PROPELLER	FAILED          	B			T4PR	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SW	15	4913X					2104R		8099		PROPELLER BEARING ROLLERS FLAT IN 81 HOURS.  CAUSE UNKNOWN.  AFTER 20-HOUR SERVICE, PROPELLER STARTED VIBRATING.  PROPEL	LER WAS REMOVED FROM AIRCRAFT AFTER 81 HOURS.  STC SP 78365W.					1	L	7	1 	3R			NC	A3SW    		5	C	P257
1998052200616	19980522	00616	CE  	1998	5	22	98ZZZX1910       	1	19980512	G	5740		BOLT            			BEECH 	77    	77          	1153007	CE  										WING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	3818D					WA221				DURING THE 7,000 HOUR WING CARRY-THROUGH STRUCTURE INSPECTION AND WING BOLT REPLACEMENT, FOUND BOLT HEAD, WASHER, AND SP	ACER LYING IN BOTTOM OF SPAR.  NOTED CORROSION BETWEEN PARTED SURFACES OF BOLT AND HEAD -  SUSPECT CAUSE OF BOLT FAILURE	.  NOTE:  AIRCRAFT EXCEEDED 7,000-HOUR INSPECTION.  RECOMMEND AT LEAST PERIODICALLY REMOVING WING TIP CAPS AND LOOKING D	OWN SPAR FOR DEFECTS.  ACTT:  7,785.7 HOURS.			1	L	7	1 	3O				A30CE
1998052200617	19980522	00617	CE  	1998	5	22	98ZZZX1911       	1	19980429	G	2820	080010633	LINE            			CESSNA	310   	310D        	2074212	CE  										VAPOR RETURN	CHAFED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6839T	5800 				39139				VAPOR RETURN LINE WAS CHAFED THROUGH BY RUBBING ON THE EDGE OF THE FUEL TANK.  A GROMMET IS SUPPOSED TO PREVENT THE CHAF	ING, BUT ONLY HID THE DAMAGE.  CLOSE INSPECTION OF BOTH THE VAPOR RETURN AND THE FUEL FEED LINES FOR THIS TYPE OF DAMAGE	 SHOULD BE DONE AT ANNUAL, BUT IS NOT MENTIONED IN SERVICE DATA.				1	L	7	2 	3O				3A10
1998052200620	19980522	00620		1998	5	22	98ZZZX1914       	4	19980312	G	3454	6222080011	RECEIVER        	COLLINS     	VIR351      	BEECH 	58    	58          	1152740	CE  										NR 1 NAV	FAILED          	E				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	99	216HA	10186			24138	TH733				NAVIGATION RECEIVER CONVERTER FAILED CAUSING UNIT TO EMIT A BURNED ODOR IN THE AIRCRAFT COCKPIT AND UNIT DID SMOKE AT FA	ILURE.  CREW PULLED THE CIRCUIT BREAKER AND RETURNED.  NO PASSENGERS ON BOARD.					1	L	7	2 	3O				3A16
1998052200621	19980522	00621	CE  	1998	5	22	98ZZZX1915       	1	19980423	G	3233	169380060	ACTUATOR        			BEECH 	23    	B24R        	1151253	CE  										MLG	FAILED          	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	24672	2271 				MC154				SHORTLY AFTER ACFT GEAR RETRACTION DURING NORMAL TAKEOFF, PILOT DETECTED THE GEAR UNSAFE LIGHT CAME ON AND CLIMB RATE HA	D SLOWED.  PILOT EXTENDED GEAR AND MADE A SAFE LANDING WITH GEAR DOWN AND LOCKED.  DURING INSPECTION OF THE GEAR SYSTEM,	 THE GEAR WOULD NOT RETRACT AND PUMP CONTINUED TO RUN.  AFTER TROUBLESHOOTING, FOUND LT GEAR RETRACT ACTUATOR PISTON HAD	 BROKEN OFF SHAFT, NOTED BOTH ROD END BEARINGS FREE AND ONE RESTRICTED IN MOVEMENT.  REMOVED RT ACTUATOR AND INSPECTED, 	NO DAMAGE NOTED.  REPLACED DEFECTIVE ACTUATOR WITH NEW P/N 169-380060-1.  FAILED PART RETURNED TO BEECHCRAFT FOR ANALYSI	S.	1	L	7	1 	3O				A1CE
1998052200622	19980522	00622	GL  	1998	5	22	98ZZZX1916       	2	19980417	G	7414		DRIVE COUPLER   			AMTR  	SONERI	SONERAI2    		GL  	AMTRVW	VOLKS 	VW2200VOLKS 		GL  					MAGNETO	FAILED          	H				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	03	247RJ	180  				999				ALUMINUM MAGNETO DRIVE COUPLER FRACTURED CAUSING ENGINE STOPPAGE IN-FLIGHT.  PART USED IN EXPERIMENTAL AIRCRAFT FOUND TO	 HAVE AN APPROX 200 HOUR USE.  RECOMMEND REMOVING ALL IN SERVICE AND REPLACE WITH THOSE MADE FROM PHENOLIC OR MICARTA (N	OT SURE WHICH MATERIAL NOW BEING USED BY GREAT PLAINS AIRCRAFT, NEBRASKA).  DID FIND OUT THE PART MUST NOT BE MADE FROM 	ROUND STOCK (DUE TO GRAIN), BUT CUT AND SHAPED FROM FLAT STOCK.			1	M	7	1 	3O	3	O		EXPA1M71	EXP3O
1998052200623	19980522	00623	CE  	1998	5	22	98ZZZX1917       	1	19980424	G	5710	072218243	WING            			CESSNA	182   	182P        	2075816	CE  										WS 100	TWISTED         	B	L	A	A5OR	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SO	09	25HP	8681 				18263642				CUSTOMER REPORTED ACFT HAS A LT WING HEAVY CONDITION IN-FLIGHT.  ATTEMPTS TO CORRECT THE CONDITION BY ADJUSTING THE LT W	ING ECCENTRIC IAW CESSNA 182 SM DID NOT CORRECT THE CONDITION.  THE LT WING FLAP HAD TO BE LOWERED ABOUT .3750 INCH TO G	ET THE AIRCRAFT TO FLY STRAIGHT.  THIS RESULTED IN A SUBSTANTIAL LOSS OF AIR SPEED DUE TO THE OUT OF RIG CONDITION.  CHE	CKED THE WING TEST IAW CESSNA SM FIGURE 18-2 AND FOUND THE LT WING TO HAVE A 3-DEGREE TWIST BETWEEN WS 39 AND WS 100 AND	 A NEGATIVE TWIST BETWEEN STA 100 AND STA 207.  THE CESSNA SM PARA 18-8 CLEARLY STATES THAT WING SHOULD BE PARALLEL BETW	EEN STA 39 AND STA 100.  NO TWIST BETWEEN THE ROOT AND STA 100.  ALL TWIST OCCURS BETWEEN STA 100 AND STA 207.	1	H	7	1 	3O			NT	TA13
1998052200624	19980522	00624	CE  	1998	5	22	98ZZZX1918       	1	19980420	G	3010	1010EVABU	TUBING          			BEECH 	58    	58P         	1152744	CE  										RT WING HEAT	COLLAPSED       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	344RE	2178 				TJ233				AT ANNUAL INSPECTION, THE BLUE PNEUMATIC LINE FOR RT WING DE-ICE BOOTS WAS FOUND COLLAPSED IN THE AREA JUST BELOW THE RT	 CABIN HEAT VENT LOCATED AFT OF THE CO-PILOT'S SEAT.  THE VENT DUCTING APPEARED TO HAVE BECOME DISCONNECTED AND HAD HEAT	ED THE TUBING ENOUGH TO CAUSE IT TO COLLAPSE.  THE WING DE-ICE SYSTEM WAS STILL OPERATIONAL, BUT THE LINE WAS 90 PERCENT	 COLLAPSED.  SUGGEST RELOCATION OF LINE SO A MINIMUM CLEARANCE FROM DUCTING IS OBTAINED.			1	L	7	2 	3O				A23CE
1998052200625	19980522	00625	GL  	1998	5	22	98ZZZX1919       	3	19980505	G	6112	4E22002	BOOT            			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C406    	GL  	PROP AI	FAILED          	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	05	36665					E1696		911319		BOOT RETAINING STRAP BURST CAUSING BOOT TO COME IN CONTACT WITH PROPELLER SPINNER, SHORTING THE BOOT OUT CAUSING SPARKS.						1	L	7	1 	3O				3A15    		5	C	P21EA
1998052200626	19980522	00626	SO  	1998	5	22	98ZZZX1920       	2	19980402	G	8530		VALVE           			CESSNA	150   	150J        	2071820	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4 CYL INTAKE	FAILED          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	11	390DM					15070334	20590370A			AIRCRAFT WAS ON A TRAINING FLIGHT WHEN POWER WAS LOST, WITH 1500 RPM BEING MAXIMUM AVAILABLE.  A SAFE LANDING WAS MADE O	N A COUNTY STONE ROAD.  INVESTIGATION REVEALED THE INTAKE VALVE STEM HAD BROKEN AT THE BOTTOM OF VALVE KEEPER RECESS.  K	EEPER AND TOP OF STEM WERE STILL IN PLACE ON TOP OF SPRING UNDER ROCKER ARM.  VALVE DAMAGED NR 4 CYLINDER AND PISTON.  V	ALVE HEAD BROKE OFF, WENT THROUGH INTAKE AND DAMAGED NR 1 CYLINDER.  CYLINDER HAD 400 HOURS SINCE LIMITED MAINTENANCE RE	LEASE WITH EXHAUST GUIDE BEING REPLACED.		1	H	7	1 	3O	3	O		3A19    	E252
1998052200627	19980522	00627	CE  	1998	5	22	98ZZZX1921       	1	19980326	G	3230	50270025	SUPPORT         			CESSNA	310   	310R        	2074245	CE  										LT MLG TORQ TUBE	FAILED          	H				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	11	3386G	7620 				310R0819				PILOT REPORTED A LOUD BANG WHEN GEAR UP POSITION WAS SELECTED.  GEAR WAS EXTENDED AT DESTINATION AND SAFE LANDING WAS MA	DE.  INVESTIGATION REVEALED REAR TORQUE TUBE SUPPORT WAS BROKEN IN TWO AT BEARING SUPPORT, LMG.  LEFT GEAR WOULD NOT RET	RACT, SPRING ON OVER CENTER LINKAGE WAS ALL THAT WAS LOCKING GEAR DOWN.  AIRCRAFT HAD LANDED IN THE AFTERNOON IN SLUSHY 	CONDITIONS ABOVE FREEZING.  WHEN AIRCRAFT DEPARTED AT APPROX 9:00 PM, TEMPERATURE HAD DROPPED TO APPROX 10 DEGREES FAHRE	NHEIT.		1	L	7	2 	3O				3A10
1998052200628	19980522	00628	CE  	1998	5	22	98ZZZX1922       	1	19980430	G	7120	643044	BRACKET         			CESSNA	303   	T303        	2073820	CE  										LT ENG UP INBD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	511AR	4904 				T30300192				AT A 50-HOUR INSPECTION, FOUND LEFT ENGINE UPPER INBOARD MOUNT BRACKET P/N 643044 CRACKED AND SEPARATED .25 INCH.  UPON 	FURTHER INVESTIGATION, DISCOVERED LOWER INBOARD MOUNT P/N 643042 CRACKED IN TWO.  IT APPEARS THE LOWER MOUNT BROKE FIRST	 CAUSING THE UPPER MOUNT TO FAIL.  SUSPECT CAUSE APPEARS TO BE METAL FATIGUE CAUSED BY ENGINE VIBRATION.				1	L	7	2 	3O				A34CE
1998052200629	19980522	00629	CE  	1998	5	22	98ZZZX1923       	1	19980430	G	7120	643042	BRACKET         			CESSNA	303   	T303        	2073820	CE  										LT ENG LOW INBD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	511AR	4904 				T30300192				AT A 50-HOUR INSPECTION, FOUND LEFT ENGINE UPPER INBOARD MOUNT BRACKET P/N 643044 CRACKED AND SEPARATED .25 INCH.  UPON 	FURTHER INVESTIGATION, DISCOVERED LOWER INBOARD MOUNT P/N 643042 CRACKED IN TWO.  IT APPEARS THE LOWER MOUNT BROKE FIRST	 CAUSING THE UPPER MOUNT TO FAIL.  SUSPECT CAUSE APPEARS TO BE METAL FATIGUE CAUSED BY ENGINE VIBRATION.				1	L	7	2 	3O				A34CE
1998052200630	19980522	00630	CE  	1998	5	22	98ZZZX1924       	1	19980420	G	5101		CLAMP           			CESSNA	172   	172M        	2072418	CE  										ENGINE MOUNT	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	61876	4207 				17264861				THE RUBBER CUSHION CLAMP THAT SUPPORTS THE WIRE BUNDLE TO THE ALTERNATOR WAS CHAFED BY THE STEEL BRAIDING ON THE WIRE WE	ARING THROUGH CAUSING AN ELECTRICAL SHORT MELTING TIE INSULATION.  UPON FURTHER INVESTIGATION, THE OTHER TWO CLAMPS ON S	AME WIRE WERE CHAFED.				1	H	7	1 	3O			NT	3A12
1998052200631	19980522	00631	CE  	1998	5	22	98ZZZX1925       	1	19980430	G	2701	05131828	YOKE            			CESSNA	172   	172A        	2072404	CE  										COCKPIT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	6539B	4180 				47730				DURING ANNUAL INSPECTION, FOUND RIGHT CONTROL YOKE CRACKED, BUT TAPED OVER.  REPLACED YOKE WITH SERVICEABLE UNIT.						1	H	7	1 	3O				3A12
1998052200632	19980522	00632	CE  	1998	5	22	98ZZZX1926       	1	19980422	G	2752	169524071101	ACTUATOR        			BEECH 	76    	76          	1153005	CE  										FLAP	FAILED          	B	S	A	EIYR	O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			WP	07	6717Y	3900 				ME331				DURING FLAP EXTENSION, PILOT HEARD LOUD 'POP' FROM UNDER REAR SEAT AREA, AND FLAPS SNAPPED UP TO FULLY RETRACTED POSITIO	N.  INSPECTION REVEALED THAT FLAP ACTUATOR TUBE ASSY (ITEM 33 ON ATTACHED) HAD UN-THREADED FROM BALL NUT ON JACK SCREW. 	 UNIT RE-ASSEMBLED, LUBED AND INSPECTED, OPS CHECKS GOOD.  RECOMMEND MODIFICATION TO TUBE ASSY BY INSTALLATION OF ALLEN 	TYPE SET SCREW.			1	L	7	2 	3O				A29CE
1998052200633	19980522	00633	CE  	1998	5	22	98ZZZX1927       	1	19980401	G	7810	9910299	EXHAUST HEADER  			CESSNA	340   	340A        	2076405	CE  										LT ENGINE	FAILED          	D		A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	99	8673K	2016 				340A0612				PILOT BROUGHT ACFT TO MAINTENANCE BECAUSE THE LT ENGINE WOULD NOT DEVELOP FULL POWER.  DURING RUN-UP AT TURBO COMING-ON 	SPEED, ENG WOULD BOG DOWN.  AFTER SEVERAL TEST RUNS AT VARIOUS MANIFOLD PRESSURES AND PROP RPM'S, PROBLEM PERSISTED, OCC	ASIONALLY ENG WOULD DEVELOP FULL POWER.  UPON DISASSY OF EXHAUST SYSTEM, DISCOVERED BAFFLE PLATE IN THE EXHAUST HEADER, 	P/N 9910299-9, HAD BROKEN LOOSE AND LODGED IN THE INLET TO THE TURBO.  THIS PROBLEM SHOWED UP INTERMITTENTLY BECAUSE, UP	ON SHUTDOWN, BROKEN PIECES WOULD FALL BACK DOWN INTO THE HEADER TO BE SUCKED BACK UP AGAIN ON RESTART.  THIS BAFFLE PLAT	E CAN ONLY BE INSPECTED BY PARTIALLY DISASSY OF EXHAUST SYS AND BE GIVEN SPECIAL ATTENTION WHEN EXHAUST SYS IS APART.	1	L	7	2 	3O				3A25
1998052200634	19980522	00634	CE  	1998	5	22	98ZZZX1928       	1	19980505	G	2820	57001133	LINE            			CESSNA	441   	441         	2076020	CE  										LT WING FUEL	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	894FL	4958 				4410314				INSPECTED AREAS AND FOUND MAIN FUEL LINE FROM THE BOOST PUMP 'TEE' TO THE FUEL CROSSFEED SHUTOFF VALVE CHAFED BEYOND LIM	ITS.  REF:  ARTICLE FOUND IN FAA AC 43-16.					1	L	7	2 	3T			RT	A28CE
1998052200635	19980522	00635		1998	5	22	98ZZZX1929       	4	19980424	G	3418	071330481	WARNING HORN    			CESSNA	150   	152         	2071835	CE  										STALL SYSTEM	FAILED          	D		A		O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			SO	15	93088					15285398				AFTER A TRAINING FLIGHT, IT WAS REPORTED THE STALL WARNING HORN SOUNDED IN LEVEL FLIGHT.  ON LANDING APPROACH, TONE CHAN	GED TO HIGHER PITCH (NORMAL STALL WARNING HORN).  WHEN MECHANIC BLEW INTO WING STALL WARNING OPENING, HORN WOULD SOUND. 	 IT ALSO SOUNDED WHEN SUCTION WAS APPLIED.  NEW HORN INSTALLED.  IT FAILED THE SAME WAY DURING THE FIRST FLIGHT AFTER IN	STALLATION.			1	H	7	1 	3O			NT	3A19
1998052200636	19980522	00636	CE  	1998	5	22	98ZZZX1930       	1	19980401	G	3411	PH1100RWL	PITOT MAST      			CESSNA	750   	750         	2076810	CE  										NR 1 LT	OBSTRUCTED      	C				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			GL	23	5112	748  				7500010				AT EIGHTY KNOTS, THE NR 1 ADC (AIR DATA COMPUTER) FAILED AND THE FLIGHT CREW ABORTED TAKEOFF.  THE AIRCRAFT RETURNED TO 	THE RAMP AND MAINTENANCE CONFIRMED THE NR 1 PITOT TUBE WAS OBSTRUCTED.  REPLACED THE PITOT TUBE MAST.					2	L	7	2 	4J			RT	T00007WI
1998052200637	19980522	00637	SW  	1998	5	22	98ZZZX1931       	1	19980417	G	2435	230791021	ARMATURE        	LEARSIEGLER 	23065013    	GULSTM	690TP 	690         	0141720	SW  										STARTER GEN	MALFUNCTIONED   	B			IC2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15										A 23079-1020 ARMATURE WAS INSTALLED IN A 23065-013 S/G.  THIS CAUSED CONTINUOUS PROBLEMS IN PARALLELING THE LOAD.  ON TE	AR-DOWN FOR OVERHAUL, FOUND EXCESSIVE DEPTH CUTS IN IMPROPERLY MACHINED METAL REMOVAL (FOR BALANCING) ON THE BALANCING B	ANDS.  THE WORK PERFORMED WITH AN END MILL AND THE CUTS WERE EXCESSIVELY DEEP (.045 INCH/.031 INCH) WEAKENING THE SS BAL	ANCE BAND.  UNIT REJECTED AS UNSAFE.			1	H	7	2 	3T			 	2A4
1998052900059	19980529	00059	GL  	1998	5	29	98ZZZX1935       	2	19980501	G	7322	23051985	FUEL CONTROL    			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8776		2052 		85470185	S776				DURING VISUAL INSPECTION OF FUEL CONTROL DURING ENGINE BUILD-UP, FOUND FUEL CONTROL DRIVE SHAFT BEARING MAKING NOISE WHE	N ROTATED BY HAND, AND HAD SLIGHT RADIAL PLAY AND ROUGH FEEL WHEN SIDE LOAD WAS APPLIED AND ROTATED.  SENT IN FOR REPAIR	.				1	G	7	2 	3U	3	U		H3EU    	E4CE
1998052900060	19980529	00060	GL  	1998	5	29	98ZZZX1936       	2	19980501	G	7323	23057269	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21460		1369 		85520222	4075				ROTOR SPEED NR DROOPING TO 95 PERCENT AND WOULD NOT RECOVER.  GOVERNOR WAS REPLACED WITH SERVICEABLE UNIT AND DROOP DID 	NOT RECUR.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998052900061	19980529	00061	NE  	1998	5	29	98ZZZX1937       	1	19980424	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										T/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	164AG	11409	457  		A13700553X	760290				DURING 500-HOUR INSPECTION, FOUND PIVOT BEARING RETAINER DEBONDED - PADDLE 'B'.						1	G	7	2 	3U				H1NE
1998052900062	19980529	00062	SW  	1998	5	29	98ZZZX1938       	1	19980429	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40LP	708  			RH1642	45233				REPLACED DRIVE LINK FOR EXCESSIVE PLAY AT TWO PLACES.  SEE BELL L-3 FIG 6221.  UPON TEARDOWN, FOUND BEARINGS AND SPACERS	 WORN BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998052900063	19980529	00063	SW  	1998	5	29	98ZZZX1939       	1	19980429	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40LP	51   			M19	45233				REPLACED DRIVE LINK FOR EXCESSIVE PLAY AT TWO PLACES.  SEE BELL L-3 FIG 6221.  UPON TEARDOWN, FOUND BEARINGS AND SPACERS	 WORN BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998052900064	19980529	00064	SW  	1998	5	29	98ZZZX1940       	1	19980429	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2621	897  			RH0056	45400				REPLACED DRIVE LINK FOR EXCESSIVE PLAY AT TWO PLACES.  SEE BELL L-3 FIG 6221.  UPON TEARDOWN, FOUND BEARINGS AND SPACERS	 WORN BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998052900065	19980529	00065	SW  	1998	5	29	98ZZZX1941       	1	19980429	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2654	627  			M20	45482				REPLACED DRIVE LINK FOR EXCESSIVE PLAY AT TWO PLACES.  SEE BELL L-3 FIG 6221.  UPON TEARDOWN, FOUND BEARINGS AND SPACERS	 WORN BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998052900066	19980529	00066	SW  	1998	5	29	98ZZZX1942       	1	19980429	G	6230	206010336005	DRIVE LINK      			BELL  	206   	206L1       	1182107	SW  										SWASHPLATE	WORN            	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007F	734  			5392	45186				REPLACED DRIVE LINK FOR EXCESSIVE PLAY AT TWO PLACES.  SEE BELL L-3 FIG 6221.  UPON TEARDOWN, FOUND BEARINGS AND SPACERS	 WORN BEYOND LIMITS.  TOTAL TIME OF PARTS LESS THAN 1,000 HOURS/1 YEAR SINCE REPLACEMENT.					1	G	7	1 	3U				H2SW
1998011500420	19980115	00420	SO  	1998	1	15	98ZZZX195        	1	19980102	G	3222	3200	CORK            	SCOTT       		PIPER 	PA18  	PA18150     	7101828	SO  										TAILWHEEL	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	91246	691  			17969	188209012				TAIL WHEEL FORK WAS CRACKED AT CENTER TOP AREA OF THE FORK ASSY. THE CRACK STARTED AT THE HOLE FOR A PIN TO HOLD THE LOW	ER THRUST WASHER AND WENT DOWN AROUND THE FORK ASSY.  THIS MAY BE A METAL AGING PROBLEM.  THE CRACK IS ABOUT 2 INCHES LO	NG AND STRAIGHT DOWN AROUND THE PART.				1	H	7	1 	3O				1A2
1998052900236	19980529	00236		1998	5	29	98ZZZX1977       	4	19980420	G	3453	066040310111	LORAN           			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	171MU	3351 			13367	7138				LORAN LEFT LARGE CONTROL KNOB BINDS AFTER LONG USE AND SMALL LEFT KNOB FALLS OUT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998052900237	19980529	00237		1998	5	29	98ZZZX1978       	4	19980402	G	2312	064105430	TRANSCEIVER     		KY196A      	BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT DISPLAY	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	171MU	3315 			22947	7138				DISPLAY UNREADABLE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998052900238	19980529	00238	EA  	1998	5	29	98ZZZX1979       	2	19980505	G	7414	M3975	COIL            	SLICK       	4371        	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MAGNETO	OPEN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	6814H	1100 			052394	17265594	4254527A			DURING A ROUTINE 500-HOUR INSPECTION ON THE MAGNETOS, FOUND THE COIL SECONDARY RESISTANCE OUT OF LIMITS:  THE CIRCUIT WA	S OPEN.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998052900239	19980529	00239	CE  	1998	5	29	98ZZZX1980       	1	19980504	G	3230	16981002730	SIDE BRACE      			BEECH 	23    	A24R        	1151252	CE  										RT MLG	CRACKED         	B			GB7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	66TX	3473 				MC42				DURING AN ANNUAL INSPECTION, A CRACK WAS DISCOVERED ON THE MLG UPPER SIDE BRACE WELD ASSEMBLY NEAR THE AFT ATTACH POINT.						1	L	7	1 	3O				A1CE
1998052900383	19980529	00383	GL  	1998	5	29	98ZZZX1981       	2	19980512	G	7310	47086	FILTER          		6890917     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUEL NOZZLE	CONTAMINATED    	B			HEFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	90215					1698				DISCOVERED AT CLEAN AND FLOW CHECK.  ITEM 1700-2000 TBO.  CONTAMINATION OF FUEL NOZZLE FILTER.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998052900387	19980529	00387	CE  	1998	5	29	98ZZZX1982       	1	19980507	G	2810		SCUPPER         			CESSNA	336   	336         	2075602	CE  										LT AUX TANK	CRACKED         	G	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	505JK					3360080				ORIGINAL SCUPPER DRAIN ON LEFT AUXILIARY TANK HAD A CRACK INSIDE THE TANK SO IT ALLOWED WATER TO GO INSIDE THE TANK.						1	H	7	2 	3O				A2CE
1998052900388	19980529	00388	EA  	1998	5	29	98ZZZX1983       	1	19980512	G	2740	9960013	SWITCH          		601R901011  	CNDAIR	CL600 	CL6002B16   	1900305	EA  										PITCH DISCONNECT	FAILED          	B			QRRR	O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			EA	13	270RA	341  			0484	5337				DURING TRANSITION FROM CLIMB TO CRUISE FLIGHT, BOTH CHANNELS OF THE HORIZONTAL STABILIZER TRIM CONTROL SYSTEM FAILED.  C	REW WAS UNABLE TO RE-ENGAGE THE TRIM SYSTEM.  AFTER TRIM DISCONNECT WAS CYCLED ON PILOT'S YOKE, NORMAL TRIM OPERATION WA	S RE-ESTABLISHED.  MAINTENANCE CONFIRMED INTERMITTENT TRIM DISCONNECT SWITCH ON PILOT'S CONTROL YOKE.  SWITCH WAS REPLAC	ED.			2	L	7	2 	4F			RT	A21EA
1998052900390	19980529	00390		1998	5	29	98ZZZX1985       	4	19980507	G	6113	VP30351	SPINNER         			DIAMON	DA20A1	DA20A1      	05626UX	GL  										PROPELLER	CRACKED         	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	543ND	121  				10116				FOUND SPINNER CRACKED DURING INSPECTION.  THIS IS THE 9TH SPINNER IN A FLEET OF APPROXIMATELY 9 AIRCRAFT TO CRACK.  ALL 	CRACKS, UP TO 4 PER SPINNER, OCCUR FROM SCREW HOLES.  HOFFMAN SERVICE LETTER E5 ADDRESSES FORMER PROBLEMS.  SUBMITTER ST	ATED TECHNICIANS SUSPECT PUSHING ON SPINNER IS PART OF CRACKING PROBLEM.				1	L	7	1 	3O			NT	TA4CH
1998052900391	19980529	00391	SO  	1998	5	29	98ZZZX1986       	2	19980304	G	8530	631521	VALVE SPRING    		653452D     	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					NR 1 CYLINDER	FAILED          	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			WP	09	748CA	859  				421C0905	604132			PILOT REPORTED VIBRATION ON RT SIDE OF AIRCRAFT DURING TAKEOFF ROLL AND CLIMB OUT.  COULD NOT CORRECT WITH ENGINE CONTRO	LS (RPM, M.A.P., FUEL OR MAGS).  RETURNED TO AIRPORT MAINT FACILITY AND REPORTED OUT OF BALANCE PROP.  UPON MAINT GROUND	 RUN, ENG RAN ROUGH, VIBRATION AT IDLE RPM AND BACKFIRING OUT THE EXHAUST.  DIFFERENTIAL COMPRESSION CHECK REVEALED NR 1	 CYL AT ZERO COMPRESSION.  UPON FURTHER INSP, NOTED 3 PIECES WITH SUBSEQUENT DAMAGE TO THE GUIDE AND VALVE.  DAMAGE TO T	HE GUIDE WAS SO SEVERE, THE EXHAUST VALVE WAS STUCK IN THE OPEN POSITION CAUSING THE DEAD CYLINDER.		1	L	7	2 	3O	3	O		A7CE    	E7CE
1998052900392	19980529	00392	SO  	1998	5	29	98ZZZX1987       	1	19980423	G	5751		AILERON         			PIPER 	PA38  	PA38112     	7103812	SO  										FLIGHT CONTROL	OUT OF BALANCE  	D	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	2582C					3879A0242				AIRCRAFT WAS STRIPPED AND RE-PAINTED.  CONTROL SURFACE BALANCE WAS CHECKED.  AILERONS FOUND OUT OF LIMITS AS WELL AS ANO	THER FACTORY PAINTED AILERON.  NOTE:  AILERON BALANCE LIMITS - 0.0 TO 8.5 INCH/POUND.  TRAILING EDGE HEAVY (UNDERBALANCE	).				1	L	7	1 	3O				A18SO
1998011500424	19980115	00424	CE  	1998	1	15	98ZZZX199        	1	19980102	G	5312	501302014	BULKHEAD        			CESSNA	414   	414         	2075908	CE  										NOSE WELL	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				NOSE WHEEL WELL SUBSTRUCTURE INSPECTION FOUND BULKHEAD, PN 501302014, HAD CRACKED BUTT END.						1	L	7	2 	3O			RT	A7CE
1998052900397	19980529	00397	SO  	1998	5	29	98ZZZX1992       	1	19980514	G	5520		ELEVATOR        			PIPER 	PA31  	PA31350     	7103110	SO  										BALANCE DATA	REQ PLACARD     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	9GV					318252013				WHILE C/W PIPER SB 998A BY REPLACING ELEVATORS, IT WAS NOTED THAT PA 31-350'S WITH STC SA 1151S0 ARE BALANCED TO PA 31-3	25 SPEC PER SS MANUAL TABLE IV-I.  PIPER WILL NOT ADD THIS INFO TO SB.  SUBMITTER SUGGESTED AN AD THAT REQUIRES THIS INF	O ON A PLACARD AT THE BALANCE WEIGHTS.				1	L	7	2 	3O				A20SO
1998052900398	19980529	00398	SO  	1998	5	29	98ZZZX1993       	1	19980426	G	7160	1677500	CONTROL CABLE   			PIPER 	PA18  	PA18        	7101802	SO  										CARBURETOR HEAT	FAILED          	G		A		A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	14	225NY					182266				CARBURETOR HEAT CABLE COULD HAVE POSSIBLY CONTRIBUTED TO ACCIDENT.  DURING INVESTIGATION, CABLE WAS FOUND DETACHED; APPA	RENTLY IT HAD BROKEN PRIOR TO OR AS A RESULT OF THE ACCIDENT.					1	H	7	1 	3O			 	1A2
1998052900400	19980529	00400	SO  	1998	5	29	98ZZZX1995       	1	19980507	G	7810	40J22616	PIPE            			PIPER 	PA46  	PA46350P    		SO  										EXH CROSSOVER	CHAFED          	B		A	SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5EG	491  				4636051				AIRCRAFT BROUGHT IN FOR ANNUAL INSPECTION.  PILOT SQUAWKED DECREASE IN ENGINE PERFORMANCE.  AN EXHAUST STAIN WAS FOUND O	N FIREWALL.  FURTHER INSPECTION REVEALED THE EXHAUST CROSSOVER PIPE WAS CHAFED THROUGH.  THE TWO CLAMPS SECURING THE HEA	T SHIELD WERE FOUND BROKEN ALLOWING THE STANDOFF/CLAMPING FLANGES TO VIOLATE THROUGH EXHAUST PIPE.  STAINLESS STEEL WORM	 DRIVE CLAMPS CALLED OUT IN IPC ARE NOT WELL SUITED FOR THIS APPLICATION.  PRODUCT CHANGE OR RE-DESIGN MAY BE REQUIRED T	O RESOLVE PROBLEM.		1	L	7	1 	3O			RT	A25SO
1998052900403	19980529	00403	CE  	1998	5	29	98ZZZX1998       	1	19980417	G	2823	0513120200	VALVE           			CESSNA	172   	172F        	2072414	CE  										FUEL SELECT	FAILED          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	06	8213U					17252113				AIRCRAFT BROUGHT IN BECAUSE FUEL VALVE WOULD NOT DRAW FROM PROPER TANK.  VALVE HAD BEEN WORKED ON 2 TIMES BEFORE BY OTHE	R SHOPS.  OPTED TO REPLACE VALVE WITH NEW PART.  A NEW VALVE OBTAINED FROM CESSNA.  INSTALLED NEW VALVE AND IT WOULD NOT	 SHUT THE FUEL OFF.  A SECOND VALVE WAS SHIPPED WITH THE SAME RESULT.  CESSNA TECH SUPPORT WAS CALLED.  CESSNA TESTED TH	EIR STOCK AND 4 OF THE 5 VALVES TESTED FAILED OUT OF THE BOX.  THE ONE VALVE THAT TESTED GOOD WAS SHIPPED AND INSTALLED.	  THAT  VALVE FAILED AFTER MANY TANK SWITCH CYCLES.  CESSNA WENT TO VENDOR AND HAD A VALVE BUILT, TESTED, AND SHIPPED. S	UBMITTER INSTALLED VALVE AND IT WORKED.  TIME ON 3 BAD VALVES:  ZERO.	1	H	7	1 	3O			NT	3A12
1998052900404	19980529	00404	CE  	1998	5	29	98ZZZX1999       	1	19980515	G	3252	14421121	DAMPENER        			CESSNA	172   	172RG       	2072438	CE  										NLG	CRACKED         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	05	80138					172RG0507				SHIMMY DAMPENER WELDED AFTER DAMAGE.  AFTER 6 MONTHS USE, CRACK DEVELOPED WHILE IN SERVICE.  RESULTING LEAK OF FLUID CAU	SED SEVERE SHIMMY ON ATTEMPTED TAKEOFFS.  UNIT REPLACED WITH NEW ITEM FROM CESSNA.					1	H	7	1 	3O				3A17
1998011500425	19980115	00425	CE  	1998	1	15	98ZZZX200        	1	19980102	G	5312		RIVETS          			CESSNA	414   	414         	2075908	CE  										NOSE WELL	SHEARED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				NOSE WHEELWELL SUBSTRUCTURE INSPECTION FOUND BULKHEAD RIVETS SHEARED WHERE T-ANGLES, P/N 5213028-6, AND P/N 5013022-5, A	RE RIVETED TO GUSSETS, P/N 521328-4, AND P/N 5013022-801.					1	L	7	2 	3O			RT	A7CE
1998052900405	19980529	00405	CE  	1998	5	29	98ZZZX2000       	1	19980504	G	5551	NAS6795	NUT             			BEECH 	35    	S35         	1151532	CE  										STAB ATTACH	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	8693Q	5762 				D7703				AT ANNUAL INSPECTION WHILE INSPECTING THE AFT EMPENNAGE AREA, FOUND 6 OF THE 16 STABILATOR SPAR ATTACHMENT NUTS CRACKED.	  UPON REMOVING THE NUTS FOR REPLACEMENT, ONE OF CRACKED NUTS BROKE INTO SEVERAL PIECES.  THERE ARE 8 NUTS ATTACHING EAC	H STABILATOR SPAR TO THE AIRCRAFT.  THE ATTACHMENT BOLTS ARE A CLOSE TOLERANCE SLIP FIT, SO ONCE THE NUTS ARE REMOVED, T	HE BOLTS ARE FREE TO SLIDE OUT WITHOUT MUCH RESISTANCE.			1	L	7	1 	3O				3A15
1998052900406	19980529	00406	CE  	1998	5	29	98ZZZX2001       	1	19980512	G	7713	9691000419	HOSE            			BEECH 	60    	A60         	1153604	CE  										MANIFOLD PRESS	LEAK            	H		A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			WP	03	1808W	2360 				P215				PILOT COMPLAINED HE WAS UNABLE TO OBTAIN RATED MANIFOLD PRESSURE DURING CLIMB.  AFTER CHECKING INTAKE AND EXHAUST SYSTEM	S FOR LEAKS AND CHECKING CONTROLLER WITH NO IMPROVEMENT, THE MANIFOLD PRESSURE HOSES WERE PRESSURE CHECKED AND FOUND TO 	BE LEAKING.  WHEN THE FIRESLEEVE WAS PULLED BACK, THE STEEL BRAIDED HOSE FELL APART.				1	L	7	2 	3O				A12CE
1998052900407	19980529	00407	WP  	1998	5	29	98ZZZX2002       	2	19980515	G	7321	21011445	EEC             			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	XAAVE				843640	022	P76193			AFTER BENCH ADJUSTMENT OF EEC, EEC WAS INSTALLED IN ACFT.  DURING START OF ENGINE, EEC TRIPPED TO MANUAL MODE AND UNABLE	 TO RESET.  AFTER EXTENSIVE T/S, DETERMINED EEC WAS UNSERVICEABLE.  A REVIEW OF TEAR DOWN/REPAIR REPORT REVEALED EEC REM	OVED FROM SERVICE FOR THE SAME FAILURE.  FAA FORM 8130-3 STATED INSP ONLY.  EEC RETURNED TO ALLIED SIGNAL FOR WARRANTY C	ONSIDERATION.  THIS WAS SECOND EEC THAT FAILED WHILE CORRECTING A SQUAWK DURING THE SAME MAINT VISIT BY CUSTOMER.  THE F	IRST FAILED EEC WAS REPORTED ON A SEPARATE M OR D REPORT.		2	L	7	3 	4F	4	F		A46EU   	E6WE
1998052900408	19980529	00408	WP  	1998	5	29	98ZZZX2003       	2	19980515	G	7200		ENGINE          			AMD   	FALC10	FALCON10    	2730101	EU  	GARRTT	TFE731	TFE7312     	01518	WP  					NR 2	FAILED          	B		A	YL1R	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			SW	11	42EH	7926 	220  			28	P73180C			THE CREW INDICATED THEY WERE AT CRUISE ALTITUDE WHEN A VIBRATION WAS FELT AND AIRCRAFT YAWED.  NR 2 ENGINE READINGS WERE	 BAD AND THE ENGINE WAS SHUT DOWN.  THE CREW DIVERTED TO LITTLE ROCK, ARK AND LANDED AIRCRAFT SAFELY.  THE ACFT WAS BROU	GHT TO DASSAULT FALCON JET CORP FOR INSPECTION.  ENGINE APPEARS TO HAVE HAD AN INTERNAL FAILURE.  ENGINE WAS REMOVED AND	 SENT TO ALLIANCE ENGINE INC.  SUSPECT TURBINE BLADE FAILURE.			2	L	7	2 	4F	4	F		A33EU   	E6WE
1998052900410	19980529	00410	CE  	1998	5	29	98ZZZX2005       	1	19980512	G	5320	010A210787	BRACKET         			MTSBSI	MU2   	MU2B40      		CE  										BS 9085	CRACKED         	B		A	FJTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	44VR	7110 				432SA				BRACKET CRACKED IN RADIUS.  BRACKET IS UNDER STRESS FROM ELEVATOR DOWN SPRINGS AND VIBRATION IN TAIL AREA.  SUBMITTER SU	GGESTED INCREASE MATERIAL THICKNESS.					1	H	7	2 	3T				A10SW
1998052900411	19980529	00411	CE  	1998	5	29	98ZZZX2006       	1	19980429	G	3230	508100324	TORQUE KNEE     			BEECH 	90    	B90         	1152912	CE  										MLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	7BF	7696 				LJ350				DURING BEECH SB 32-3134, FOUND A MLG TORQUE KNEE WITH A CRACK.						1	L	7	2 	3T				3A20
1998052900412	19980529	00412	CE  	1998	5	29	98ZZZX2007       	1	19980423	G	3260	810520	SWITCH          	ELDEC       		RKWELL	NA265 	NA26565     	7630107	CE  										DOWNLOCK PROX	FAILED          	B			KI2R	O				OTHER                   				N			FALSE WARNING             			TX	TAXI/GRND HDL  	1			CE	01	82CR	150  			1230	46549				AFTER LANDING ON TAXI BACK TO RAMP, LIGHT GEAR INDICATED UNSAFE AND GEAR DOORS SEQUENCED TO OPEN.  AIRCRAFT STOPPED AND 	SHUT DOWN.  VISUAL INSPECTION VERIFIED GEAR WAS DOWN AND LOCKED.  UPON POWER-UP, GEAR DOORS SEQUENCED CLOSED, RIGHT GEAR	 INDICATED SAFE AGAIN.  WITHIN 5 MINUTES, RIGHT GEAR INDICATED UNSAFE AGAIN, DOORS SEQUENCED OPEN.  POWERED DOWN AND BAC	K ON AND GEAR INDICATED SAFE AGAIN, DOORS SEQUENCED CLOSED.  ALSO, NOTICED THE FAIL SEQUENCE COULD BE INITIATED BY ACTUA	TING STROBE LIGHTS, CROSSFEED OR LANDING LIGHTS.  REPLACED PROXIMITY SWITCH.		2	L	7	2 	4J				A2WE
1998052900413	19980529	00413	EA  	1998	5	29	98ZZZX2008       	2	19980519	G	7250	3001538	LOCK            		3011438     	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					CT VANE RING	MISINSTALLED    	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	96AU					B162	PCE50443			REMOVED RIGHT ENGINE POWER SECTION FOR ACCESS TO PERFORM SCHEDULED HOT SECTION INSPECTION.  UPON DISASSEMBLY, DISCOVERED	 TAB WASHERS (16 EACH) WERE NOT BENT TO THE SAFETY POSITION.  THESE WASHERS SAFETY THE BOLTS THAT RETAIN THE CT VANE RIN	G AND NR 2 BEARING COVER.  ENGINE LOG BOOK DID NOT REVEAL ANY MAINTENANCE IN THIS PART OF THE ENGINE SINCE OVERHAUL BY T	HE MANUFACTURER.  SUSPECT CAUSE:  MISSED AT QUALITY CONTROL INSPECTION AT OVERHAUL FACILITY.			1	L	7	2 	3T	4	T	 	A14CE   	E4EA
1998060500001	19980605	00001	SW  	1998	6	5	98ZZZX2009       	1	19980402	G	7810	407063001101	STACK           			BELL  	407   	407         		SW  										ENGINE EXH	CRACKED         	B			ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	1116H	603  				53046				FOUND EXHAUST STACK CRACKED NEXT TO WELD.  REPLACED STACK.						1	G	7	1 	3U			O	H2SW
1998011500426	19980115	00426	CE  	1998	1	15	98ZZZX201        	1	19980102	G	5320	50130443	STIFFENER       			CESSNA	414   	414         	2075908	CE  										NOSE WELL	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				NOSE WHEELWELL SUBSTRUCTURE INSPECTION FOUND STIFFENERS, P/N 5013044-3, P/N 5013044-11, WITH LOOSE AND WORKING RIVETS.						1	L	7	2 	3O			RT	A7CE
1998060500002	19980605	00002	EU  	1998	6	5	98ZZZX2010       	1	19980406	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B1     	8680811	EU  										T/R	DEFECTIVE       	B			ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	215LA	53   				2143				AT INSPECTION, FOUND VOID IN T/R BLADE AREA 'B' NEXT TO LANDING EDGE.  REPLACED PART.						1	G	7	1 	3U				H9EU
1998060500003	19980605	00003	SW  	1998	6	5	98ZZZX2011       	1	19980406	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R DRIVE	CORRODED        	B			ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	96335	623  				53075				INSPECTED HELICOPTER PER AD 97-22-15.  FOUND ONE T/R DRIVE DISC BEYOND DAMAGE LIMITS (CORROSION).  REPLACED PART.						1	G	7	1 	3U			O	H2SW
1998060500004	19980605	00004	SW  	1998	6	5	98ZZZX2012       	1	19980402	G	7810	407063001101	STACK           			BELL  	407   	407         		SW  										ENGINE EXH	CRACKED         	B			ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	96335	623  				53075				FOUND EXHAUST STACK CRACKED NEXT TO WELD.  REPLACED STACK.						1	G	7	1 	3U			O	H2SW
1998060500006	19980605	00006	GL  	1998	6	5	98ZZZX2014       	2	19980324	G	7240	23030911	COMBUSTION CASE 			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					FUEL NOZZLE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	58236	821  				53069	CAE847085			HIGHER THAN NORMAL MGT INDICATION BY PILOT WAS REPORTED.  INSPECTED AND PERFORMED TEST OF MEASURED GAS TEMPERATURE SYSTE	M.  NO ANOMALLY OBSERVED.  UPON FURTHER INSPECTION FOUND SEAM WELDS AROUND FUEL NOZZLE BOSS CRACKED ALLOWING COOLING AIR	 TO ESCAPE.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998060500008	19980605	00008	EU  	1998	6	5	98ZZZX2016       	1	19980512	G	6520	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R	CRACKED         	B			FBLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	31AS	492  								BEARING CRACKS ARE BEYOND LIMITS.  REPLACED WITH NEW BEARING SET.						1	G	7	1 	3U				H9EU
1998060500009	19980605	00009	EU  	1998	6	5	98ZZZX2017       	1	19980512	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R	CRACKED         	B			FBLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	31AS	492  				2689				BEARINGS ARE CRACKED BEYOND LIMITS.  REPLACED WITH NEW SET.						1	G	7	1 	3U				H9EU
1998060500010	19980605	00010	GL  	1998	6	5	98ZZZX2018       	3	19980518	G	6114	7895552	SUPPORT         		7384288     	DHAV  	DHC7  	DHC7102     	2802708	EA  						HAMSTD	24PF	24PF305     	GL  	PROP EXT DOME	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	4860J	26847	3890 		400	19				PROPELLER EXTENSION DOME RECEIVED FOR MAJOR INSPECTION.  DURING MAGNAGLOW INSPECTION, A CRACK WAS FOUND AT THE NARROWEST	 PART OF THE SUPPORT CAGE ON THE EXTERNAL SURFACE NEAR THE PIVOT AREA.  PIVOTS CHECK GOOD.  NO ABNORMAL WEAR NOTED.					2	H	7	4 	4T				A20EA   		6	C	P1NE
1998060500011	19980605	00011	EU  	1998	6	5	98ZZZX2019       	1	19980414	G	2910	NAS161212	PACKING         			AIRBUS	320   	A320214     		EU  										YELLOW HYD	DETERIORATED    	A			AJLF	A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SO	23	626AJ	2905 				626				AIRCRAFT DIVERTED TO MIAMI DUE TO LOSS OF YELLOW SYSTEM HYDRAULIC FLUID.  INVESTIGATION REVEALED THE LEAK WAS AT A UNION	 TO THE POWER TRANSFER UNIT QUICK DISCONNECT.  THE PACKING HAD DETERIORATED AND WAS SUBSEQUENTLY REPLACED WITH NO FURTHE	R LEAKS.  THE AIRCRAFT WAS THEN RELEASED FOR SERVICE.  REF:  NR 20-09-98.  ACFT TC:  2,188.				2	L	7	2 	4F			RT	A28NM
1998011500427	19980115	00427	CE  	1998	1	15	98ZZZX202        	1	19980102	G	5320	501304411	STIFFENER       			CESSNA	414   	414         	2075908	CE  										NOSE WELL	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				NOSE WHEELWELL SUBSTRUCTURE INSPECTION FOUND STIFFENERS, P/N 5013044-3, P/N 5013044-11, WITH LOOSE AND WORKING RIVETS.						1	L	7	2 	3O			RT	A7CE
1998060500012	19980605	00012	EU  	1998	6	5	98ZZZX2020       	1	19980401	G	5280	T700A5280034001	BRACKET         			SOCATA	TBM   	TBM700      	8682000	EU  										RT MLG DOOR	LOOSE           	B		A	RL8R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	700PW	3629 				29				DURING ROUTINE 100-HOUR INSPECTION PER SOCATA MM, FOUND RT MLG DOOR FORWARD BRACKET PIVOT ATTACH BRACKET LOCATED ON WING	 RIB TO HAVE A LOOSE BEARING, AXIAL DIRECTION.  PART WAS REMOVED AND VISUALLY INSPECTED.  A CRACK WAS FOUND AT THE BOTTO	M OF THE BRACKET UNDER THE BEARING.  THIS IS SECOND OCCURRENCE ON THIS TYPE AIRCRAFT.  THE OTHER ACFT HAD 854.9 HOURS TT	, 563 CYCLES.  THE BEARING DEPARTED THE BRACKET ALLOWING THE DOOR TO PIVOT DOWN AND AFT, SUPPORTED BY THE AFT BRACKET AN	D MLG DOOR ROD.  SUBSEQUENT FAILURE OF A THEN OVERSTRESSED AFT DOOR BRACKET WOULD THEN ALLOW THE DOOR TO JAM AGAINST THE	 BOTTOM OF WING AND ROTATE AROUND THE GEAR ATTACH ROD.  TOTAL CYCLES:  2,434.	1	L	7	1 	3T			RT	A60EU
1998060500014	19980605	00014	NE  	1998	6	5	98ZZZX2022       	2	19980513	G	7230	50B927	BEARING         			BOEING	777   	777222      	1385219	NM  	PWA   	PW4077	PW4077      		NE  					NR 1 MAIN	FAILED          	B			WA2D	E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NE	03	767UA	8537 			0006	26918	P777021			ENGINE REMOVED ON 5-6-98 DUE IN-FLIGHT SHUT DOWN FOLLOWING OIL FILTER BYPASS LIGHT AND LOW OIL PRESSURE LIGHT.  DISASSEM	BLY INSPECTION REVEALED FAILED NR 1 MAIN BEARING WITH HEAVY SPALLING AND 360 DEGREE CAGE SEPARATION.  THE BEARING HAS BE	EN TURNED OVER TO PRATT AND WHITNEY ENGINEERING FOR INVESTIGATION.				2	L	7	2 	4F	4	F	RT	T0001SE 	E46NE
1998060500015	19980605	00015	CE  	1998	6	5	98ZZZX2023       	1	19980515	G	2140		FUSE HOLDER     			BEECH 	90    	C90A        	1152911	CE  										HEAT SYSTEM	MISLOCATED      	B		A	VIB4	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	800PG	3255 				LJ1286				DURING A PHASE INSPECTION, NOTICED UNPROTECTED TERMINALS ON THE NORMAL HEAT FUSE HOLDER (SF119) AND MAX HEAT FUSE HOLDER	 (SF118) WERE LOCATED EXTREMELY CLOSE TO THE STRUCTURE OF ACFT.  THIS CONDITION COULD CAUSE ARCING BETWEEN TERMINALS AND	 THE STRUCTURE WITH WEIGHT ON THE FLOORBOARD.  THE NORMAL HEAT FUSE HOLDER IS LOCATED DIRECTLY UNDER THE PILOT'S SEAT IN	 INSTALLATION ZONE 131 AND THE MAX HEAT FUSE HOLDER IS LOCATED DIRECTLY UNDER THE COPILOT'S SEAT IN ZONE 132.  LOOKING F	WD IN THE ZONES THEY ARE MOUNTED ON THE AFT SIDE OF THE BLKHD AT FS 116.00.  SUBMITTER RECOMMENDED THESE AREAS BE INSPEC	TED AND ADEQUATE CLEARANCE PROVIDED FOR THE TERMINALS IF REQUIRED.	1	L	7	2 	3T			RT	3A20
1998060500016	19980605	00016	NE  	1998	6	5	98ZZZX2024       	2	19980508	G	7320	8010003	FMU             	HAMSTD      		AIRBUS	310   	A310324     	3930206	EU  	PWA   	4152  	PW4152      		NE  					ENGINE	FAILED          	A			AJLF	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	838AB	12471			F24081	676	676			ON ENGINE START AFTER PUSH-BACK, ALL PARAMETERS DECREASED RAPIDLY AFTER STARTER CUT-OUT.  TROUBLESHOOTING RESULTED IN TH	E REPLACEMENT OF THE FUEL METERING UNIT (FMU).  ALL PARAMETERS WERE SUBSEQUENTLY FOUND NORMAL AFTER AN OPERATIONAL CHECK	 WAS PERFORMED.  THE AIRCRAFT WAS THEN RELEASED FOR SERVICE.  REF:  NR 10-12-98.  TOTAL CYCLES:  4,552.				2	L	7	2 	4F			RT	A35EU   	E24NE
1998060500017	19980605	00017	EU  	1998	6	5	98ZZZX2025       	1	19980427	G	5300		DOME            			AIRBUS	310   	A310324     	3930206	EU  										NOSE	BIRD STRIKE     	A			AJLF	K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			SO	23	840AB	11930				682				ON TOUCH-DOWN INTO MONTEGO BAY, A BIRD STRIKE OCCURRED.  INSPECTIONS WERE CARRIED OUT IAW MM 05-51-14 WHICH REVEALED NO 	DAMAGE TO THE AIRCRAFT.  THE BIRD STRIKE WAS CONFINED TO THE UPPER PORTION OF THE NOSE DOME.  THE AIRCRAFT WAS THEN RELE	ASED FOR SERVICE.  REF:  NR 10-11-98.  TOTAL CYCLES:  4,777.				2	L	7	2 	4F			RT	A35EU
1998060500018	19980605	00018	WP  	1998	6	5	98ZZZX2026       	1	19980513	G	2921	4365082	DIAPHRAGM       		43442795002 	DOUG  	DC8   	DC8F55      	3021928	WP  										ACCUM TANK	TORN            	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	801CK	2482 			B718	45816				AUXILIARY HYDRAULIC POWER SURGE DAMPER ACCUMULATOR TANK HAD NEW DIAPHRAGM INSTALLED AT REPAIR.  DIAPHRAGM FAILED (TORN) 	AFTER 3 MONTHS TIME IN SERVICE.  DIAPHRAGM MANUFACTURED BY KAPCO.  THIS IS THE 5TH IDENTIFIED FAILURE BY THIS REPAIR STA	TION.				2	L	7	4 	4F				4A25
1998060500019	19980605	00019	EU  	1998	6	5	98ZZZX2027       	1	19980518	G	2435	230650153	GENERATOR       			AMD   	FALC10	FALCON10    	2730101	EU  										NR 1 ENGINE	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	96VR				2832	199				AN OVERHAULED STARTER/GENERATOR WAS INSTALLED ON THE NR 1 ENGINE OF A FALCON10.  DURING ENGINE START, THE GENERATOR SWIT	CH IN THE COCKPIT TRIPPED TO 'OFF'.  START WAS VERY SLOW.  PUT GENERATOR SWITCH 'ON' AND GENERATOR WOULD NOT WORK.  TROU	BLESHOOTING SHOWED THAT THE GENERATOR 'A' TERMINAL WAS SHORTED TO GENERATOR CASE.  LOOSENING TERMINAL BLOCK ATTACH BOLTS	 ELIMINATED SHORT.  SUSPECT BOLT LENGTH PROBLEM.  THIS SHORT RUINED THE GENERATOR CONTROL UNIT (GCU).  BOTH ITEMS WERE R	EPLACED.		2	L	7	2 	4F				A33EU
1998060500020	19980605	00020	EA  	1998	6	5	98ZZZX2028       	2	19980503	G	8530	AL14077	PISTON PIN      								LYC   	O360  	IO360A3B6   	41514	EA  					NR 4 CYLINDER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99							L2536451A			WHILE C/W DIFFERENTIAL COMPRESSION CHECK FOUND BLOW-BY ON THE NR 4 CYLINDER PRESSURIZING THE CRANKCASE, AIR COMING OUT O	F THE OIL FILLER TUBE.  UPON NR 4 CYLINDER REMOVAL, FOUND ONE PISTON PIN PLUG WORN AWAY.  CYLINDER WAS WORN WHERE THE PI	STON PIN WAS MAKING CONTACT WITH THE CYLINDER WALL.  REMOVED OIL FILTER AND FOUND METAL CONTAMINATION.  REMOVED FINGER S	CREEN AND FOUND ALUMINUM SLIVERS AND SCRAPINGS.								3	O			1E10
1998060500021	19980605	00021	NE  	1998	6	5	98ZZZX2029       	2	19980430	G	7230	717623	HUB             								PWA   	JT8   	JT8*        	52044	NE  					ENGINE HPC	MISDRILLED      	B			RA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					9S4137					HIGH COMPRESSOR REAR HUB WAS RECEIVED WITH SB 4070 HOLES NOT PROPERLY LOCATED.  THE HUB BORE SHOULD HAVE BEEN SCALLOPED,	 BUT THE HOLES WERE LOCATED ON THE BALANCE FLANGE AND THE DISK WAS DRILLED COMPLETELY THROUGH.  THE OVERHAUL AGENCY WAS 	FENIX AVIATION CORP., MIAMI, FLORIDA 33142.									4	F			E2EA
1998011500428	19980115	00428	CE  	1998	1	15	98ZZZX203        	1	19980102	G	5320	52130453	DOUBLER         			CESSNA	414   	414         	2075908	CE  										NOSE WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				NOSE WHEELWELL SUBSTRUCTURE INSPECTION FOUND DOUBLERS, P/N 5213045-3 LT, AND P/N 5213045-2 RT, CRACKED AT UPPER AFT CORN	ER RADIUS RELIEF CUT-OUTS.					1	L	7	2 	3O			RT	A7CE
1998060500023	19980605	00023	GL  	1998	6	5	98ZZZX2030       	2	19980512	G	7310	47086	FILTER          		6890917     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	90215				AG12346	1698				FOUND SOME LIGHT CONTAMINATION (5 PERCENT SCREEN COVERAGE).  CONTAMINATION APPEARS FIBEROUS IN NATURE.  RECOMMEND MORE F	REQUENT INSPECTIONS.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998060500024	19980605	00024	EA  	1998	6	5	98ZZZX2031       	2	19980511	G	8530	75838	VALVE GUIDE     			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 3-4 EXHAUST	DEFECTIVE       	B		A	OG5R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			GL	21	557DC	108  				S1630	L2466851A			DURING PRE-TAKEOFF RUNUP, ENGINE STARTED VIBRATING AT MID-RPM RANGE AND WOULD NOT ACCELERATE.  FOUND NR 3 AND NR 4 EXHAU	ST VALVES STICKING.  REAMED GUIDES TO PROPER DIMENSION.  ENGINE HAS 107.6 HOURS SINCE FACTORY OVERHAUL.  THIS OPERATOR H	AS HAD NUMEROUS LOW TIME ENGINES WITH THIS PROBLEM.  AIRCRAFT HAVE DASH 10 FUEL INJECTORS AND RUN ON 15W50 OIL AND ALSO 	RECEIVE PROPER COOL DOWN.			1	G	7	1 	3O	3	O		4H12    	1E10
1998061600001	19980616	00001	SO  	1998	6	16	98ZZZX2032       	2	19980420	G	8550	629218	DRIVEN GEAR     			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					OIL PUMP	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	745CA		46   			421C1043	277042R			PILOT REPORTED TACH INOPERATIVE AND LOSS OF OIL PRESSURE.  INSPECTION REVEALED THE OIL PUMP DRIVE GEAR ASSY SHAFT HAD SH	EARED AT POINT OF ENGAGEMENT TO THE CAMSHAFT GEAR AND SUBSEQUENT TACH INDICATION AND OIL PRESSURE LOSS OCCURRED.  FURTHE	R INSPECTION OF THE OIL PUMP ASSY REVEALED SEVERE DRIVE GEAR SHAFT AND BUSHING WEAR WITH SUBSEQUENT HOUSING SIDE WALL WE	AR.  THE BUSHINGS AND SHAFT WEAR BECAME SO SEVERE, THE OIL PUMP DRIVEN GEAR WOULD NOT PROFILE TOGETHER WITH THE DRIVE GE	AR CAUSING BOTH GEARS TO LOCK UP AND SUBSEQUENT SHAFT FAILURE.		1	L	7	2 	3O	3	O		A7CE    	E7CE
1998060500025	19980605	00025	SO  	1998	6	5	98ZZZX2033       	2	19980220	G	8550	629218	DRIVEN GEAR     			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					OIL PUMP	SEIZED          	D				O				OTHER                   				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			WP	09	745CA		156  			421C1043	610040			PILOT REPORTED YAW IN AIRCRAFT AND APPARENT LOSS OF POWER ON LT ENGINE (LOW RPM AND MAP).  PILOT EXERCISED EMERGENCY PRO	CEDURES TO RESTORE POWER, BUT WAS UNSUCCESSFUL AND THE ENG WAS SHUT DOWN IN-FLIGHT.  PROP WAS ALREADY IN FEATHER POSITIO	N WHICH WOULD INDICATE LOSS OF OIL PRESSURE.  INSPECTION REVEALED THE OIL PUMP DRIVE GEAR ASSY SHAFT HAD SHEARED AT POIN	T OF ENGAGEMENT TO THE CAMSHAFT GEAR RESULTING IN LOSS OF TACH INDICATION AND OIL PRESS.  FURTHER INSP OF OIL PUMP ASSY 	REVEALED SEVERE DRIVEN GEAR SHAFT AND BUSHING WEAR WITH HOUSING SIDE WALL WEAR.  BUSHINGS AND SHAFT WEAR BECAME SO SEVER	E THE OIL PUMP DRIVEN GEAR WOULD NOT PROFILE WITH THE DRIVE GEAR CAUSING BOTH GEARS TO LOCK UP AND SUBSEQUENT SHAFT FAIL	1	L	7	2 	3O	3	O		A7CE    	E7CE
1998060500026	19980605	00026		1998	6	5	98ZZZX2034       	1	19980511	G	2520	SL0231202	CYLINDER        	PORTER      	SL43008     															SEAT RECLINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07										A CRACK EXTENDS FROM EDGE OF HOLE FOR SPLINED FIBERNUT TO THE END OF THE HYDROLOK, APPROXIMATELY .25 INCH.  THE CIRCUMST	ANCES UNDER WHICH THE CRACK OCCURRED SEEM TO BE NORMAL OPERATION  POSSIBLY CAUSED BY FATIGUE.
1998060500027	19980605	00027	SO  	1998	6	5	98ZZZX2035       	1	19980518	G	7160	B03305	ELEMENT         	BRACKETT    	BA3310      	PIPER 	PA31  	PA31P       	7103120	SO  										ENG INDUC FILTER	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	110SK	22   				31P7630006				FILTER ELEMENT CAME OUT OF HOUSING THROUGH INDUCTION SYSTEM DUE TO IMPROPER INSTALLATION OF SCREEN.						1	L	7	2 	3O				A8EA
1998060500028	19980605	00028	CE  	1998	6	5	98ZZZX2036       	1	19980406	G	8010	08504691	RELAY           			CESSNA	310   	310R        	2074245	CE  										LT ENG STARTER	STUCK           	D				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			EA	25	181A	12518				310R0014				TEN MINUTES AFTER TAKEOFF, PILOT NOTICED ELECTRICAL POWER SURGES AND WHILE TRYING TO ISOLATE PROBLEM, LOST ALL ELECTRICA	L POWER.  INSPECTION FOUND RIGHT START RELAY HAD STUCK AND DESTROYED RIGHT STARTER AND CAUSED BATTERY MASTER RELAY TO FA	IL.  INSTALLING STARTER ENGAGED LIGHTS TO START RELAYS.  THIS WILL ADVISE PILOT OF STUCK RELAY BEFORE TAKEOFF.				1	L	7	2 	3O				3A10
1998060500029	19980605	00029	CE  	1998	6	5	98ZZZX2037       	1	19980513	G	7110	125260429	COWLING         			CESSNA	210   	T210L       	2073449	CE  										NOSE	MISMANUFACTURED 	B	P		R3RR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	2317G					21061485				THIS NEW COWL WAS PURCHASED FROM CESSNA AND IT HAS TWO PROBLEMS.  1.  THE TOP LEADING EDGE IS TOO THICK IN PLACES (FILLE	R OR ADHESIVE) AND WILL NOT CONTOUR WITH EXISTING NOSE COWL.  2.  ON THE AFT EDGE, THERE IS NOT ENOUGH MATERIAL,  AN APP	ROXIMATE .25 INCH GAP.				1	H	7	1 	3O			 	3A21
1998060500030	19980605	00030	SO  	1998	6	5	98ZZZX2038       	1	19980303	G	7810	1243700	MUFFLER         			PIPER 	PA18  	PA18105     	7101809	SO  										ENG EXHAUST	FAILED          	B			BIGR	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			NM	03	316T					182430				PILOT COMPLAINED THAT ENGINE WOULD NOT DEVELOP RATED RPM AND SEEMED TO BE RICH ON OCCASSION.  POWER LOSS SIGNIFICANT.  P	ROBLEM TRACED TO MUFFLER TAILPIPE BLOCKAGE FROM INTERNAL PIECE OF METAL THAT WOULD INTERMITTENTLY SLIDE ACROSS TAILPIPE 	AND COMPLETELY BLOCK EXHAUST FROM EXITING MUFFLER ASSEMBLY.  MUFFLER IN GOOD CONDITION IN ALL OTHER RESPECTS.  FLAME TUB	E INTACT.  LOOSE PIECE OF METAL INSIDE MUFFLER IS PERFECT LENGTH AND WIDTH TO COMPLETELY BLOCK EXHAUST.  METAL HAD TO FA	LL OFF FROM INSIDE OF MUFFLER SUBASSEMBLY.		1	H	7	1 	3O				1A2
1998060500031	19980605	00031	CE  	1998	6	5	98ZZZX2039       	1	19980516	G	3240		BRAKE LINE      			BEECH 	36    	A36         	1151604	CE  										PARK BRAKE	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	41NH					E3139				DURING INSTALLATION OF RADIOS IN A NEW LATE MODEL 1997 A-36, NOTICED THE RIGHT RUDDER CABLE WAS CHAFING THROUGH ONE OF T	HE BRAKE HYDRAULIC LINES ON THE PARKING BRAKE ASSY.  THE PARKING BRAKE UNIT IS LOCATED BELOW THE FLOORBOARDS ON THE PILO	T'S SIDE.  IT WAS NECESSARY TO ADJUST THE RADIUS OF THE LINE WHERE IT ENTERED THE PARKING BRAKE ASSY ABOUT 1 INCH TO THE	 LEFT.  SUBMITTER SUGGESTED THAT BEECH HAVE THE PARKING BRAKE ASSY ABOUT 1 INCH TO THE LEFT.  TOTAL TIME ON AIRCRAFT 26 	HOURS.		1	L	7	1 	3O				3A15
1998011500429	19980115	00429	CE  	1998	1	15	98ZZZX204        	1	19980102	G	5320	52130452	DOUBLER         			CESSNA	414   	414         	2075908	CE  										NOSE WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				NOSE WHEELWELL SUBSTRUCTURE INSPECTION FOUND DOUBLERS, P/N 5213045-3 LT, AND P/N 5213045-2 RT, CRACKED AT UPPER AFT CORN	ER RADIUS RELIEF CUT-OUTS.					1	L	7	2 	3O			RT	A7CE
1998060500032	19980605	00032	SO  	1998	6	5	98ZZZX2040       	1	19980512	G	3233	484706	O-RING          			PIPER 	PA34  	PA34220T    	7103420	SO  										LT MLG ACTUATAOR	DAMAGED         	B	S	A	VJ3R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			WP	07	4177R	224  				3449046				LANDING GEAR FAILED TO RETRACT FULLY IN-FLIGHT.  ISOLATED ACTUATORS AND FOUND LT MAIN GEAR ACTUATOR BYPASSING (AUDIBLE) 	FLUID/PRESSURE.  DISASSEMBLED ACTUATOR, FOUND DAMAGED AND APPARENTLY INCORRECT (UNDERSIDE) O-RING INSTALLED ON ACTUATOR 	PISTON.  SUSPECT INCORRECT O-RING INSTALLED AT MANUFACTURER (CLEVELAND) DURING ASSEMBLY.  SUBMITTER RECOMMENDED ACTUATOR	 AND AIRCRAFT MANUFACTURERS INSPECT ALL FACTORY STOCK AND SPARES FOR PROPER O-RING INSTALLATION.			1	L	7	2 	3O			 	A7SO
1998060500033	19980605	00033	SO  	1998	6	5	98ZZZX2041       	1	19980429	G	2622	RTA600	EXTINGUISHER    			PIPER 	PA46  	PA46350P    		SO  										PORTABLE UNIT	FAILED          	B			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	429CA	239  			R16456	463092				DURING AN ANNUAL INSPECTION, THE CABIN PORTABLE FIRE EXTINGUISHER DISTRIBUTED UNDER PIPER P/N:  459-887, FAILED WEIGHT C	HECK.  BOTTLE DOES NOT HAVE A PRESSURE GAUGE.  SEVERAL OTHER BOTTLES HAVE BEEN FOUND IN THIS CONDITION.  SUSPECT TOP/NOZ	ZLE ASSY LOOSENS AND PRESSURE BLEEDS DOWN.  SUBMITTER RECOMMENDED A ROUTINE INSPECTION OF BOTTLE AND ADDITION OF AN ALIG	NMENT LINE FROM BOTTLE TO NOZZLE WITH TORQUE SEAL.  (DUE TO THE HIGH COST OF HALON, THESE SMALLER AND CHEAPER BOTTLES AR	E BEING INSTALLED).		1	L	7	1 	3O			RT	A25SO
1998060500034	19980605	00034	EA  	1998	6	5	98ZZZX2042       	2	19980506	G	7414	73000	COUPLING        		S6LN204     	PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4A5    	41532	EA  					MAG DRIVE	FAILED          	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4365T	3200 			A25449	327200019	C1482440			RT MAGNETO REMOVED TO CHANGE BREAKER POINTS.  ON REMOVAL, NOTED THAT ONE MAGNETO DRIVE CUSHION WAS MISSING.  A SMALL PIE	CE OF THE COUPLING WAS FOUND,  IT WAS HARD/BRITTLE.  THE DRIVE COUPLING WAS FOUND CRACKED.  SUSPECT BECAUSE ONE-HALF OF 	THE CUSHION WAS MISSING (2 CUSHIONS REQUIRED, ONE ON EACH SIDE OF DRIVE COUPLING LUGS).  ENGINE OIL DRAINED, SCREENS CHE	CKED, SUM FLUSHED.  NO OTHER PIECES FOUND.			1	L	7	1 	3O	3	O		A3SO    	E295
1998060500035	19980605	00035	SO  	1998	6	5	98ZZZX2043       	1	19980508	G	2842		SENSOR          			PIPER 	PA28  	PA28161     	7102803	SO  										FUEL QUANTITY	LEAK            	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	44886					287816038				WHILE PERFORMING ANNUAL INSPECTION, PULLED WING TANKS TO C/W PIPER SB.  FOUND BOTH SENDERS LEAKING BADLY RIGHT INTO THE 	WING AND CABIN.  DEADLY COMBINATION.  SUBMITTER STATED THIS IS NOT A RARE CASE.  SO FAR, 4 OTHER PIPER 28'S HAVE HAD SAM	E PROBLEM.				1	L	7	1 	3O				2A13
1998060500036	19980605	00036	EA  	1998	6	5	98ZZZX2044       	2	19980515	G	8530	65441	SPRING SEAT     			CESSNA	172   	172K        	2072430	CE  	LYC   	O360  	O360A1A     	41514	EA  					NR 4 CYL INTAKE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	46511	273  				17257315	L1373636A			ENGINE SUCTION SCREEN REMOVED DURING ANNUAL INSP AND SEVERAL LARGE PIECES OF FERROUS METAL WERE FOUND.  RECORDS INDICATE	D THE ENG HAD NEW CYLINDERS INSTALLED DURING OVERHAUL 272.7 HOURS PREVIOUSLY.  THE PIECES OF METAL WERE FROM THE LOWER I	NTAKE VALVE SPRING SEAT P/N 65441.  ALL 4 ROCKER COVERS REMOVED AND LARGE PIECES OF A BROKEN SPRING SEAT WERE FOUND IN N	R 4 CYL ROCKER COVER.  AFTER REMOVAL OF VALVE SPRING, FOUND 2 LOWER VALVE SPRING SEATS HAD BEEN INSTALLED ON THE INTAKE 	VALVE SPRING DURING BUILD-UP OF CYL ASSY.  THE OIL SUMP REMOVED, CLEANED, FLUSHED, AND GEAR TRAIN INSPECTED.  NO DAMAGE 	FOUND.  SUMP REINSTALLED AND A NEW VALVE SPRING SEAT, BOTH SPRINGS AND VALVE KEEPERS REPLACED.  GROUND RUN WAS NORMAL.	1	H	7	1 	3O	3	O	NT	3A12    	E286
1998060500037	19980605	00037	SO  	1998	6	5	98ZZZX2045       	1	19980511	G	7120	8419741	MOUNT           			PIPER 	PA46  	PA46350P    		SO  										NLG ACT ATTACH	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	46PM	2292 				4622081				ENGINE MOUNT WAS BROKEN WHERE THE NOSE GEAER ACTUATOR ATTACHES AT THE REAR.						1	L	7	1 	3O			RT	A25SO
1998060500038	19980605	00038	CE  	1998	6	5	98ZZZX2046       	1	19980417	G	3710		FILTER          			BEECH 	58    	58          	1152740	CE  										LT GYRO PRESSURE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4621M	120  			001812	TH919				WHILE RUNNING AIRCRAFT BEFORE AN ANNUAL INSPECTION, NOTED THE LT GYRO PRESSURE WAS LOW.  THE OWNER MENTIONED THE PRESSUR	E REGULATOR NEEDED TO BE ADJUSTED.  INSPECTION OF THE PRESSURE SYSTEM FILTERS FOUND THE IN-LINE GYRO PRESSURE FILTER HAD	 A PIECE OF THE BODY OF THE FILTER MISSING AND THE NACELLE WAS COVERED WITH CARBON SOOT.  THE FILTER IS CLAMPED WITH AN 	ADEL CLAMP AND IT APPEARED THE CLAMP HAD STARTED THE CRACKS IN THE FILTER BODY AND THE PUMP PRESSURE HAD BLOWN OUT THE M	ISSING PIECE.		1	L	7	2 	3O				3A16
1998060500039	19980605	00039		1998	6	5	98ZZZX2047       	4	19980501	G	3420	KCS55A	CONNECTOR       	KING        	KA51B       	BEECH 	65    	A65         	1152803	CE  										COMPASS SYS	WRONG PART      	B			LN7R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	614BB					LC263				DURING INSTALLATION OF A KING KCS55A COMPASS SYSTEM, NOTED THE CONNECTOR PLUG FOR THE KA51B SLAVING ACCESSORY WAS INCORR	ECTLY IDENTIFIED.  THE 9-PIN PLUG SUPPLIED BY THE MFG FOR THE HARNESS IN THE AIRCRAFT WAS LABELED INCORRECTLY.					1	L	7	2 	3O			 	3A20
1998060500040	19980605	00040	EA  	1998	6	5	98ZZZX2048       	2	19980424	G	8550	73772	OIL JET         			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					PISTON COOLING	FAULTY          	B			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	621CA	509  				4636008	L9621861A			REPETITIVE OIL ANALYSIS REVEALED HIGH WEAR METAL LEVELS FROM CYLINDER AREA WEAR (PISTON, RINGS, LINER).  REMOVED AND REP	LACED CYLINDERS WITH FACTORY NEW CYLINDER KITS.  WHILE CYLINDERS WERE REMOVED, PISTON COOLING OIL JETS WERE REMOVED AND 	TESTED.  FIVE OUT OF 6 FAILED INITIAL TEST.  AFTER CLEANING ALL SIX, 4 WERE RETURNED TO SERVICE AND 2 WERE REPLACED WITH	 NEW.  THIS IS THE SECOND AIRCRAFT/ENGINE COMBINATION OCCURRENCE.  SUBMITTER SUSPECTED CLOGGED OIL JETS NOT PROPERLY COO	LING/LUBRICATING PISTONS CAUSING DISTORTION RESULTING IN WEAR.		1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1998060500041	19980605	00041	CE  	1998	6	5	98ZZZX2049       	1	19980401	G	3242	H604	LINING          	GOODYEARAERO	956043      	BEECH 	18    	E18S        	1151006	CE  										RT MLG	FAILED          	G				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			SW	15	737SW					BA402				ON TAKEOFF, BRAKE LINING SEGMENT BROKE INTO PIECES CAUSING WHEEL TO LOCK UP AND SUBSEQUENT TIRE FAILURE.						1	L	7	2 	3R				A765
1998011500430	19980115	00430	CE  	1998	1	15	98ZZZX205        	1	19980102	G	5712	082217579	RIB             			CESSNA	414   	414         	2075908	CE  										MLG WELL	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	02	69943	3709 				4140645				MLG SUPPORT STRUCTURE LT AND RT MLG WELL, INSPECTION FOUND CRACKS IN RIBS, P/N 0822175-79, AND P/N 0822175-74, CENTER RI	B WEB AT THE UPPER AFT CORNER OF CUT-OUT HOLE WHERE OPERATING PUSH/PULL ROD PASSES THROUGH, TOWARD TOP OF RIB.					1	L	7	2 	3O			RT	A7CE
1998060500042	19980605	00042	SO  	1998	6	5	98ZZZX2050       	1	19980225	G	2432	RG12	BATTERY         	CONCORDEBATT		PIPER 	J3    	J3C65       	7100510	SO  										DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	98238	10   			CBC250141	18402				BATTERY WAS BOOST CHARGED EVERY FLIGHT AND/OR 90 DAYS WHEN IN STORAGE.  BATTERY WAS USED FOR NAV LIGHTS AND HOUR METER O	NLY (NO STARTER OR GENERATOR ON AIRCRAFT).  BATTERY WAS REMOVED FROM AIRCRAFT AND CHARGED AT HOME WITH CONSTANT VOLTAGE 	CHARGER.				1	H	7	1 	3O				A691
1998060500043	19980605	00043	SW  	1998	6	5	98ZZZX2051       	1	19980508	G	5711		SPAR            			MOONEY	M20   	M20C        	5870208	SW  										STUB SPAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	9999S					680166				INSPECTION FOUND CRACKED REAR STUB SPAR.  NEEDS C/W MOONEY SB M20-217.						1	L	7	1 	3O				2A3
1998060500046	19980605	00046	CE  	1998	6	5	98ZZZX2054       	1	19980508	G	3211	24411003F	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	25	9349D	4120 				172RG1128				A FLIGHT SCHOOL AIRCRAFT WAS PRACTICING GEAR EXTENSIONS.  ON FINAL EXTENSION, THE LT MAIN GEAR WOULD NOT EXTEND.  THE GE	AR WAS CYCLED SEVERAL TIMES WITH NO SUCCESS.  A DEEP STALL FOLLOWED BY A QUICK PUSH-OVER LOCKED THE LT MAIN GEAR DOWN. A	 DOWN AND LOCKED INDICATION WAS RECEIVED IN THE COCKPIT.  A NORMAL LANDING ACCOMPLISHED.  THE LT PIVOT ASSY WAS REMOVED.	  IT WAS SHEARED AT THE DRIVE SPLINE RADIUS.  THE RT PIVOT ASSY WAS REMOVED AND FOUND CRACKED AT THE DRIVE SPLINE RADIUS	.  BOTH PIVOT ASSEMBLIES WERE REPLACED PER CESSNA SB 90-1 REV 2 AND RETURNED TO SERVICE.		1	H	7	1 	3O				3A17
1998060500047	19980605	00047	CE  	1998	6	5	98ZZZX2055       	1	19980508	G	3211	24411003F	PIVOT ASSY      			CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	25	9349D	4120 				172RG1128				A FLIGHT SCHOOL AIRCRAFT WAS PRACTICING GEAR EXTENSIONS.  ON FINAL EXTENSION, THE LT MAIN GEAR WOULD NOT EXTEND.  THE GE	AR WAS CYCLED SEVERAL TIMES WITH NO SUCCESS.  A DEEP STALL FOLLOWED BY A QUICK PUSH-OVER LOCKED THE LT MAIN GEAR DOWN. A	 DOWN AND LOCKED INDICATION WAS RECEIVED IN THE COCKPIT.  A NORMAL LANDING ACCOMPLISHED.  THE LT PIVOT ASSY WAS REMOVED.	  IT WAS SHEARED AT THE DRIVE SPLINE RADIUS.  THE RT PIVOT ASSY WAS REMOVED AND FOUND CRACKED AT THE DRIVE SPLINE RADIUS	.  BOTH PIVOT ASSEMBLIES WERE REPLACED PER CESSNA SB 90-1 REV 2 AND RETURNED TO SERVICE.		1	H	7	1 	3O				3A17
1998060500048	19980605	00048	GL  	1998	6	5	98ZZZX2056       	3	19980515	G	6111	B4426	SNAP RING       			CESSNA	172   	172RG       	2072438	CE  						MCAULY	2D34C	B2D34C220   	GL  	BLADE BASE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9531B					172RG0859		941183		PILOT NOTICED SCRATCHES ON PROPELLER DURING POST-FLIGHT INSPECTION FOLLOWING COMPLETION OF A BREAK-IN FLIGHT FOR NEWLY O	VERHAULED ENGINE AND PROPELLER.  INSPECTION FOUND SPINNER AND SPINNER BULKHEAD DAMAGED AND REQUIRED REPLACEMENT.  PROP T	T:  1,887.8 HOURS.  PROP TSO:  2.2 HOURS.				1	H	7	1 	3O				3A17    		5	C	P7EA
1998011500431	19980115	00431	CE  	1998	1	15	98ZZZX206        	1	19980102	G	5712	082217574	RIB             			CESSNA	414   	414         	2075908	CE  										MLG WELL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MLG SUPPORT STRUCTURE LT AND RT MLG WELL, INSPECTION FOUND CRACKS IN RIBS, P/N 0822175-79, AND P/N 0822175-74, CENTER RI	B WEB AT THE UPPER AFT CORNER OF CUT-OUT HOLE WHERE OPERATING PUSH/PULL ROD PASSES THROUGH, TOWARD TOP OF RIB.					1	L	7	2 	3O			RT	A7CE
1998011500432	19980115	00432	CE  	1998	1	15	98ZZZX207        	1	19980102	G	5730	08220009	SKIN            			CESSNA	414   	414         	2075908	CE  										MLG WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MLG SUPPORT STRUCTURE LT AND RT MLG WELL, INSPECTION FOUND WING SKINS, P/N 08220009, UPPER INBOARD CRACKED ABOVE RIB INS	IDE THE NACELLE BAG LOCKER.					1	L	7	2 	3O			RT	A7CE
1998011500433	19980115	00433	CE  	1998	1	15	98ZZZX208        	1	19980102	G	5743	08221807	CASTING         			CESSNA	414   	414         	2075908	CE  										MLG WELL	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MLG SUPPORT STRUCTURE LT AND RT MLG WELL, INSPECTION FOUND MLG SIDEBRACE SUPPORT CASTINGS, P/N 822180-7, AND P/N 0822180	-8, BOLTED TO RIBS, WERE LOOSE AND ONE DASH 8 CRACKED.					1	L	7	2 	3O			RT	A7CE
1998061200330	19980612	00330	SW  	1998	6	12	98ZZZX2085       	1	19980506	G	5312	206032308103S	BULKHEAD        			BELL  	206   	206L3       	1182108	SW  										TAILBOOM ATTACH	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	349AL					51388				DURING AIRFRAME MAINTENANCE, FOUND BULKHEAD ASSEMBLY (TAILBOOM RING) CRACKED IN UPPER RIGHT HAND CORNER NEAR FITTING.  R	ECOMMEND USING A MORE HEAVY DUTY PART.					1	G	7	1 	3U				H2SW
1998061200331	19980612	00331	SW  	1998	6	12	98ZZZX2086       	1	19980501	G	5532	206020113223A	SKIN            			BELL  	407   	407         		SW  										VERTICAL FIN	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2105 				53044				DEFECT WAS DISCOVERED DURING INSPECTION ASB 407-98-17.  FOUND CUTS IN SKIN ON FORWARD AND AFT SIDES OF AFT LOWER INSERT 	AT ENDS OF FORMERS FOR COWLING.  THE CAUSE IS THE SKIN WAS CUT DURING TRIMMING OF THE FORMERS DURING PRODUCTION.  COMPON	ENT P/N 206020113323A.				1	G	7	1 	3U			O	H2SW
1998061200332	19980612	00332	GL  	1998	6	12	98ZZZX2087       	2	19980430	G	7322	2537739	VALVE SLEEVE    	BENDIX      	25490923    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					FLOW BODY	SEPARATED       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5427S				331596	760168				DURING SHOP INSPECTION FOR DECELERATION OF ENGINE, FOUND FUEL CONTROL BONDING ON SLEEVE SEPARATED.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998061200333	19980612	00333	NE  	1998	6	12	98ZZZX2088       	1	19980429	G	6220	7615009100051	TRIM TAB        			SKRSKY	S76   	S76         	8143010	NE  										M/R BLADE	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	703AL	15045	400  			760266				DISCOVERED DURING 500-HOUR INSPECTION, M/R HEAD TRIM TAB DEBONDED.  SKIN CRACKED BENEATH TRIM TAB.						1	G	7	2 	3U				H1NE
1998061200334	19980612	00334	GL  	1998	6	12	98ZZZX2089       	2	19980427	G	7250	23034775	SUPPORT         		23035128    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					HOT SECTION	CRACKED         	B		A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	741SW	6520 	1978 		DW53655	760070	CAT95246S			TURBINE REMOVED FOR 2,000-HOUR OVERHAUL AND DID NOT STATE THAT ENGINE OR TURBINE WAS SMOKING OR USING OIL.  WHEN COMBUST	ION REMOVED, DISCOVERED THE FIRST STAGE NOZZLE HAD OIL STAINS ON THE VANES AND THE GP SUPPORT HAD OIL STAINS AROUND THE 	STRUT THAT WAS CRACKED.  THE STRUT WAS BADLY WORN FROM FRETTING WEAR BY THE FIRST STAGE NOZZLE SHIELD THROUGH THE WALL O	F THE STRUT CAUSING OIL TO LEAK.  THIS CRACK WAS ON THE PRESSURE SIDE OF THE SUPPORT.			1	G	7	2 	3U	3	U		H1NE    	E1GL
1998011500434	19980115	00434	CE  	1998	1	15	98ZZZX209        	1	19980102	G	5743	08221808	CASTING         			CESSNA	414   	414         	2075908	CE  										MLG WELL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	69943	3709 				4140645				MLG SUPPORT STRUCTURE LT AND RT MLG WELL, INSPECTION FOUND MLG SIDEBRACE SUPPORT CASTINGS, P/N 822180-7, AND P/N 0822180	-8, BOLTED TO RIBS, WERE LOOSE AND ONE DASH 8 CRACKED.					1	L	7	2 	3O			RT	A7CE
1998061200337	19980612	00337		1998	6	12	98ZZZX2092       	2	19980305	G	8530		ENGINE          			AMTR  		KISTR1      			LYC   		O235*       							NR 4 CYLINDER	FAILED          	G		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			GL	03	66SK					021	L858515			THIRTY MINUTES INTO LOCAL FLIGHT, ENGINE FAILED.  PILOT MADE A FORCED LANDING IN A PLOWED FARM FIELD.  NO VISIBLE DAMAGE	 INCURRED TO AIRPLANE.  ON TEARDOWN, DEEP SCORING WAS FOUND IN THE OIL PUMP GEAR HOUSING.  ALUMINUM AND PISTON RING PIEC	ES WERE FOUND IN THE SUMP.  A 2 INCH CRACK WAS FOUND IN CASE HALF.  NR 4 PISTON DISINTEGRATED FROM CYLINDER.  THREE LIFT	ERS HAD MISSING PIECES.  THE CAMSHAFT HAD IMPACT DAMAGE ON ALL LOBES.  ALL RODS HAVE IMPACT DAMAGE.  NR 4 CYLINDER IS UN	SERVICEABLE.					0
1998061200338	19980612	00338	GL  	1998	6	12	98ZZZX2093       	2	19980513	G	7210	6894171	GEARBOX         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	B			LS1R	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			EA	13	1097J	5072 	1508 		CAG31160F	900801D				TORQUE PRESSURE INCREASED WHEN THROTTLE WAS REDUCED.  SUSPECT TORQUE PISTON BLEED HOLE IS PLUGGED IN GEARBOX.  GEARBOX S	HIPPED TO OVERHAUL FACILITY FOR INSPECTION/REPAIR.  REF:  CONTROL NR 98-5-5.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998061200339	19980612	00339	GL  	1998	6	12	98ZZZX2094       	2	19980512	G	7230	6890550	COMPRESSOR      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	SEIZED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	6421 	1    		CAC34712	900801D				COMPRESSOR INSTALLED ON AIRCRAFT AT ZERO TSO.  AFTER GROUND RUNS, AIRCRAFT WAS TEST FLOWN.  UPON NEXT START ATTEMPT AFTE	R APROXIMATELY 10 MINUTES SHUTDOWN TIME, ANOTHER START WAS ATTEMPTED.  COMPRESSOR HAD SEIZED.  UPON REMOVAL AND INSPECTI	ON, IT WAS FOUND TO BE WHEEL RUB ON CASE HALF PLASTIC.				1	G	7	1 	3U	3	U		H3WE    	E4CE
1998061200340	19980612	00340	GL  	1998	6	12	98ZZZX2095       	2	19980512	G	7230	6890550	COMPRESSOR      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	VIBRATION       	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	5675 	2288 		CAC35331	900801D				EXHAUST STACKS CRACKED.  VIBRATION ANALYSIS CHECK INDICATED COMPRESSOR WAS VIBRATING EXCESSIVELY.  COMPRESSOR WAS REMOVE	D AND SENT FOR REPAIR EVALUATION.  REF:  CONTROL NR 98-5-9.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998061200341	19980612	00341	GL  	1998	6	12	98ZZZX2096       	2	19980508	G	7532	23053176	VALVE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	STICKING        	B			LS1R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	13	1097J		1075 			900801D				ENGINE NOT MAKING POWER.  BLEED VALVE STICKING.  SENT FOR REPAIR EVALUATION.  REF:  SN FF35627.  CONTROL NR 98-5-2.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998061200342	19980612	00342	GL  	1998	6	12	98ZZZX2097       	2	19980520	G	7310	47086	FILTER          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20F     	03013	GL  					FUEL NOZZLE	CONTAMINATED    	B			HEFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	21	105HH		1034 			S339				FILTER WAS CONTAMINATED WITH METAL AND OTHER DEBRIS.  FILTER WAS NOT CRUSHED, ABOUT 20 PERCENT CONTAMINATION.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998061200343	19980612	00343	SW  	1998	6	12	98ZZZX2098       	1	19980429	G	2913	66948	RETAIN CLIP     	ABEX        	75259166005 	BELL  	412   	412         	1182202	SW  										HYD PUMP DRIVE	FAILED          	E		A		A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	03	411UT	4152 			AUD14478F	33125				AIRCRAFT DISPATCHED TO ON-SCENE REQUEST.  EN ROUTE, MASTER CAUTION LIGHT ILLUMINATED INDICATING NR 2 HYDRAULIC FAILURE W	ITH CORRESPONDING GAUGE INDICATION.  PILOT DIVERTED TO NEARBY AIRPORT WHERE AN UNEVENTFUL LANDING WAS MADE.  ON THE DRIV	E SPLINE OF THE NR 2 HYDRAULIC PUMP HAD FAILED AND ALLOWED THE DRIVE SPLINE TO DISENGAGE FROM THE TRANSMISSION QUILL.				1	G	7	2 	4U				H4SW
1998061200345	19980612	00345	SW  	1998	6	12	98ZZZX2100       	1	19980513	G	2436	MS18071	REGULATOR       			BELL  	204   	UH1H        	1181407	SW  										LT DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	51AG					7120178				VOLTAGE REGULATOR WILL NOT HOLD A VOTLAGE SETTING, KEEPS FLUCTUATING.  SENT FOR REPAIR.  REF:  CONTROL NR 98-5-8.						1	G	7	1 	4U				EXPA1G71
1998061200346	19980612	00346	SW  	1998	6	12	98ZZZX2101       	1	19980512	G	7712	206375013101	TORQUEMETER     			BELL  	206   	OH58A       	1181579	SW  										ENGINE	FAILED          	B			LS1R	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			EA	13	54AG					7120721				AIRCRAFT FAILED POWER CHECK.  INVESTIGATION REVEALED TORQUEMETER READING 6 PERCENT HIGH.  TORQUEMETER WAS REPLACED.  REF	:  SN 3721.  CONTROL NR 98-5-7.					1	G	7	1 	3U				H2SW
1998061200347	19980612	00347	WP  	1998	6	12	98ZZZX2102       	1	19980513	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC	15   				290456D				EXHAUST STACK CRACKED BEYOND LIMITS.  REMOVED AND REPLACED.  INVESTIGATION IN PROGRESS.  SUBMITTER STATED THIS WAS 3RD C	RACKED EXHAUST ON THIS AIRCRAFT.					1	G	7	1 	3U				H3WE
1998061200348	19980612	00348	WP  	1998	6	12	98ZZZX2103       	1	19980512	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										RT ENGINE	CRACKED         	B		A	LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC	256  				290456D				RIGHT EXHAUST STACK CRACKED.  ENGINE WAS VIB CHECKED AND EXCESSIVE VIBRATION WAS DETECTED.  UPON FURTHER INVESTIGATION, 	DETERMINED THE UPPER ENGINE MOUNTS WERE LOOSE ON AIRFRAME.  NEW HILOCKS WERE INSTALLED ON ENGINE MOUNTS AND VIBRATION CH	ECK SHOWED VIBRATION AT ACCEPTABLE LEVELS.  AIRCRAFT RELEASED FOR FLIGHT.  REF:  CONTROL NR 98-5-3.				1	G	7	1 	3U				H3WE
1998061200349	19980612	00349	WP  	1998	6	12	98ZZZX2104       	1	19980512	G	7120		MOUNT           			HUGHES	369   	369D        	4470706	WP  										ENGINE	LOOSE           	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC	256  				290456D				RIGHT EXHAUST STACK CRACKED.  ENGINE WAS VIB CHECKED AND EXCESSIVE VIBRATION WAS DETECTED.  UPON FURTHER INVESTIGATION, 	DETERMINED THE UPPER ENGINE MOUNTS WERE LOOSE ON AIRFRAME.  NEW HILOCKS WERE INSTALLED ON ENGINE MOUNTS AND VIBRATION CH	ECK SHOWED VIBRATION AT ACCEPTABLE LEVELS.  AIRCRAFT RELEASED FOR FLIGHT.  REF:  CONTROL NR 98-5-3.				1	G	7	1 	3U				H3WE
1998061200350	19980612	00350	WP  	1998	6	12	98ZZZX2105       	1	19980513	G	7810	369A8230503	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										LT ENGINE	CRACKED         	B		A	LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				LEFT EXHAUST STACK CRACKED.  ENGINE WAS VIB CHECKED AND FOUND TO BE VIBRATING EXCESSIVELY.  UPON FURTHER INSPECTION, UPP	ER ENGINE MOUNTS APPEARED TO BE LOOSE.  NEW HILOCKS WERE INSTALLED ON UPPER ENGINE M0UNTS OF AIRFRAME.  ANOTHER VIBRATIO	N TEST WAS PERFORMED AND VIBRATION DROPPED TO AN ACCEPTABLE LEVEL.  STACK WAS REPLACED AND AIRCRAFT RELEASED FOR SERVICE	.  REF:  CONTROL NR 98-5-6.			1	G	7	1 	3U				H3WE
1998061200351	19980612	00351	WP  	1998	6	12	98ZZZX2106       	1	19980513	G	7120		MOUNT           			HUGHES	369   	369D        	4470706	WP  										ENGINE	LOOSE           	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				LEFT EXHAUST STACK CRACKED.  ENGINE WAS VIB CHECKED AND FOUND TO BE VIBRATING EXCESSIVELY.  UPON FURTHER INSPECTION, UPP	ER ENGINE MOUNTS APPEARED TO BE LOOSE.  NEW HILOCKS WERE INSTALLED ON UPPER ENGINE M0UNTS OF AIRFRAME.  ANOTHER VIBRATIO	N TEST WAS PERFORMED AND VIBRATION DROPPED TO AN ACCEPTABLE LEVEL.  STACK WAS REPLACED AND AIRCRAFT RELEASED FOR SERVICE	.  REF:  CONTROL NR 98-5-6.			1	G	7	1 	3U				H3WE
1998061200352	19980612	00352	SW  	1998	6	12	98ZZZX2107       	1	19980522	G	6720	500N72301	PUSH ROD        			HUGHES	500N  	500N        	3027374	SW  										THRUSTER	DAMAGED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	521FB					LN001				DURING INSPECTION PRIOR TO INSTALLATION, GREASE SEALS ON ROD END WERE FOUND TO HAVE DENTS AND DEFORMED FROM FACTORY BUIL	D-UP.					1	G	7	1 	3U			NC	H3WE
1998061200353	19980612	00353	SW  	1998	6	12	98ZZZX2108       	1	19980522	G	6710	369A7306505	TORQUE TUBE     			HUGHES	500N  	500N        	3027374	SW  										COLLECTIVE	MISDRILLED      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	521FB					LN001				COLLECTIVE TORQUE TUBE HAS BOLT HOLES NOT DRILLED TO PROPER SIZE FOR GEARBOX MOUNT BOLTS TO BE PASSED THROUGH.  TWO EACH	 PARTS FROM FACTORY BOTH UNDERSIZED HOLES.					1	G	7	1 	3U			NC	H3WE
1998061200354	19980612	00354	SW  	1998	6	12	98ZZZX2109       	1	19980522	G	6710	369A7306505	TORQUE TUBE     			HUGHES	500N  	500N        	3027374	SW  										COLLECTIVE	MISDRILLED      	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	524FB					LN004				COLLECTIVE TORQUE TUBE HAS BOLT HOLES NOT DRILLED TO PROPER SIZE FOR GEARBOX MOUNT BOLTS TO BE PASSED THROUGH.  TWO EACH	 PARTS FROM FACTORY BOTH UNDERSIZED HOLES.					1	G	7	1 	3U			NC	H3WE
1998061200356	19980612	00356	EA  	1998	6	12	98ZZZX2111       	2	19980504	G	8520	75190	CAMSHAFT        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					GOVERNOR DRIVE	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			EA	23	40592	638  				277405337	L817448			IN CRUISE FLIGHT, PILOT LOST PROP CONTROL, FEATHERED, AND LANDED.  FOUND CAMSHAFT BROKEN AT GOVERNOR DRIVE END.  RECORDS	 SHOW THIS WAS A NEW PART.  INSTALLED AT OVERHAUL ON 3/89.					1	L	7	2 	3O	3	O		1A10    	1E4
1998061200357	19980612	00357	CE  	1998	6	12	98ZZZX2112       	1	19980515	G	5532	3364000087	SKIN            			BEECH 	33    	F33A        	1151425	CE  										LT VERT STAB	CRACKED         	B	S	A	BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	37050					CE926				SKIN OF LEFT VERTICAL STABILIZER CRACKED.  REMOVED SKIN AND FOUND RIB P/N 33640000-11 WITH UNSHOT RIVETS AT ATTACH POINT	 TO REAR SPAR OF VERTICAL STABILIZER.  IT APPEARS THAT THIS WAS THE FIRST TIME THIS SKIN WAS REMOVED SINCE DATE OF MANUF	ACTURE.  RIVETS CAN BE INSPECTED THROUGH LIGHTNING HOLE IN REAR SPAR TO SEE IF SHOT.				1	L	7	1 	3O				3A15
1998061200358	19980612	00358		1998	6	12	98ZZZX2113       	4	19980304	G	6122	104171	DRIVE GEAR      	HARTZL      	F624L2      	PIPER 	PA31  	PA31350     	7103110	SO  										PROP GOVERNOR	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	3590N		615  		B8540T	318052148				PILOT VALVE AND DRIVE GEAR INSIDE GOVERNOR BECAME BOUND-UP CAUSING LOSS OF CONTROL OF THE UNIT.  CAUSE OF PILOT VALVE AN	D GEAR FAILURE HAS NOT BEEN IDENTIFIED.					1	L	7	2 	3O				A20SO
1998061200359	19980612	00359	SO  	1998	6	12	98ZZZX2114       	1	19980522	G	2510	510232826	BRACKET         			GULSTM	AA5   	AA5B        	3960105	SO  										PILOT SEAT BACK	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	28618	3800 				AA5B0707				SUBJECT BRACKETS ATTACH PILOT'S SEAT BACK TO SEAT PAN.  THESE BRACKETS ARE ALUMINUM AND WHEN BACK SEAT PASSENGER PULLS P	ILOT'S SEAT AFT (TO ASSIST GETTING OUT), THESE BRACKETS FLEX AND WILL FAIL.  ALL BRACKETS ON THIS AIRCRAFT HAVE CRACKED 	OR TOTALLY FAILED.  IF THESE BRACKETS FAIL, THE PILOT'S SEAT BACK WILL FALL INTO THE BACK SEAT AND UNDER CERTAIN FLIGHT 	CONTDITIONS COULD RESULT IN LOSS OF CONTROL.  SUBMITTER STATED FIX WAS TO INSTALL STEEL BRACKETS.			1	L	7	1 	3O				A16EA
1998061200360	19980612	00360	CE  	1998	6	12	98ZZZX2115       	1	19980513	G	5730	9598000190	SKIN            			BEECH 	95    	95          	1153402	CE  										RT NACELLE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	21JC	6500 				TD224				DURING ANNUAL PREPARATIONS, FOUND BEHIND BOTH ENGINES THAT LOWER AFT NACELLES WERE CHAFING THROUGH WING SKIN JUST AFT OF	 FRONT SPAR FLANGE AND LEFT UNTREATED WOULD CHAFE INTO SPAR FLANGE.  AIRCRAFT HAS 6,500 HOURS TTAF.  NO LORD MOUNT DAMAG	E, BUT SHOULD HAVE BEEN DESIGNED WITH AN ANTI-CHAFING STRIP.				1	L	7	2 	3O				3A16
1998061200361	19980612	00361	CE  	1998	6	12	98ZZZX2116       	1	19980513	G	5730	9598000189	SKIN            			BEECH 	95    	95          	1153402	CE  										WING LT NACELLE	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	21JC	6500 				TD224				DURING ANNUAL PREPARATIONS, FOUND BEHIND BOTH ENGINES THAT LOWER AFT NACELLES WERE CHAFING THROUGH WING SKIN JUST AFT OF	 FRONT SPAR FLANGE AND LEFT UNTREATED WOULD CHAFE INTO SPAR FLANGE.  AIRCRAFT HAS 6,500 HOURS TTAF.  NO LORD MOUNT DAMAG	E, BUT SHOULD HAVE BEEN DESIGNED WITH AN ANTI-CHAFING STRIP.				1	L	7	2 	3O				3A16
1998061200362	19980612	00362	SO  	1998	6	12	98ZZZX2117       	2	19980422	G	8530	SA640518	PISTON          			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  					NR 5	FAILED          	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			NM	05	180BH	198  				18052132	1313345R4			ABOUT 15 SECONDS AFTER TAKEOFF, ENGINE BEGAN TO RUN ROUGH AND LOSE POWER.  PILOT COULD NOT MAINTAIN ALTITUDE, AND MADE A	N UNEVENTFUL LANDING.  INSPECTED ENGINE, FOUND NR 5 PISTON BROKEN AND NO LONGER IN THE CYLINDER; ALSO, A 2 INCH CRACK FR	OM BASE OF NR 5 PISTON LEADING UP TO BACK BONE OF CASE.				1	H	7	1 	3O	3	O		5A6     	E273
1998061200364	19980612	00364	CE  	1998	6	12	98ZZZX2119       	1	19980526	G	5751	5124000200	SKIN            			CESSNA	421   	421C        	2076016	CE  										LT/RT AIL	DEBONDED        	B		A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	104TP	4463 				421C0635				DURING CESSNA PROGRESSIVE CARE INSPECTION, NR 3, NR 4, FOUND STIFFENERS IN BOTH AILERONS.  DEBONDED AND AILERON SKIN LOO	SE.  NO REPAIR POSSIBLE BECAUSE OF NO ACCESS DUE TO SKIN BEING BONDED TO RIBS.  EXHANGE OVERHAULED AILERONS WERE INSTALL	ED DUE TO THE FACT THERE WERE NO APPROVED REPAIRS TO THESE BONDED STRUCTURES.  ALSO, NEW AILERONS WERE HARD TO OBTAIN FA	CTORY STATIC BALANCE WHEN PAINTED.			1	L	7	2 	3O				A7CE
1998061200365	19980612	00365	EA  	1998	6	12	98ZZZX2120       	2	19980525	G	8530	05K21114	CYLINDER        								LYC   	O235  	O235L2C     	41505	EA  					NR 1-2	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		700  					L1999515			DURING 100-HOUR INSPECTION, FOUND METAL PARTICLES IN OIL FILTER.  FOUND TO BE PISTON PIN WRIST PLUG MATERIAL.  CYLINDERS	 SENT TO MANUFACTURER FOR EVALUATION.  REQUIRED OVERHAUL OR REPLACEMENT OF CYLINDERS AFFECTED.  APPEARED TO BE CYLINDERS	 1 AND 2 (COOLEST RUNNING CYLINDERS).  AVERAGE AGE OF CYLINDER, 800 HOURS, FACTORY REBUILT ENGINES.  SUBMITTER STATED TH	ESE AIRCRAFT ARE INVOLVED IN A TRAINING 141 SCHOOL.  LEFT UNCORRECTED, POSSIBLE SEVERE ENGINE DAMAGE, FAILURE.								3	O			E223
1998061200366	19980612	00366	CE  	1998	6	12	98ZZZX2121       	1	19980526	G	5210	RH50	RESISTOR        		396020      	CESSNA	210   	T210N       	2073456	CE  										DOOR SEAL SYSTEM	BURNED          	G				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SW	17	4616C					21063576				THE PILOT NOITCED SMOKE IN THE COCKPIT APROXIMATELY 6 MINUTES AFTER TAKEOFF.  ELECTRICAL POWER WAS TURNED OFF AND THE PI	LOT RETURNED TO THE AIRPORT WITHOUT FURTHER INCIDENT.  THE PILOT AND ONE PASSENGER WERE NOT INJURIED EXCEPT FOR A SMALL 	SOLDER BURN ON THE PILOT'S UPPER FOOT.  INVESTIGATION DETERMINED THAT A PASSENGER SEAT BELT DAMAGED THE INFLATABLE PNEUM	ATIC DOOR SEAL.  EXCESSIVE SEAL LEAKAGE CAUSED THE ELECTRIC PNEUMATIC PUMP TO EXCEED ITS DUTY CYCLE OVERHEATING THE PUMP	 VOLTAGE DROPPING RESISTORS.		1	H	7	1 	3O				3A21
1998061200367	19980612	00367	CE  	1998	6	12	98ZZZX2122       	1	19980513	G	5610		CANOPY          			BEECH 	45    	A45         	1152006	CE  										AIRCRAFT	DEPARTED        	G				O				OTHER                   				D			INFLIGHT SEPARATION       			AP	APPROACH       	1			GL	19	500DR	320  				G31				THE AIRCRAFT DEPARTED ON A MAINTENANCE TEST FLIGHT FOR RADIO WORK THAT HAD BEEN COMPLETED SEVERAL DAYS PRIOR.  WHILE ON 	APPROACH TO LANDING AT APPROXIMATELY 3,000 FEET MSL, THE CANOPY DEPARTED THE AIRCRAFT.  SUSPECT LATCHING HOOKS WERE NOT 	ENGAGED PROPERLY.  RECOMMEND CLOSER PRE-FLIGHT INSPECTION OF THIS AREA.				1	L	7	1 	3O				5A3
1998061200368	19980612	00368	SW  	1998	6	12	98ZZZX2123       	1	19980514	G	3246	54530251	HUB             		31337       	SWRNGN	SA226 	SA226T      	8780122	SW  										RT MLG	FAILED          	B		A	PC4R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	13	70FC	9346 			2	T226				DURING LANDING, RIGHT INBOARD MAIN DEPARTED AIRCRAFT, OUTBOARD TIRE THEN FAILED.  INVESTIGATION REVEALED ONE EACH STUD O	N HUB MISSING ONE EACH.  STUD BROKEN PREVIOUSLY.  REMAINING 6 STUDS ALL FRACTURED PRIOR TO FAILING.  THERE WAS NO EVIDEN	CE OF EXCESSIVE BRAKING (NO SCUFF/FLAT ON TIRE).  AGE OF STUDS, POSSIBLE OVER-TORQUING OF BOLTS ARE FACTORS.  ACFT ALSO 	OPERATED IN AUSTRALIA, HAS HIGH FLOTATION GEAR FOR UN-IMPROVED STRIPS - MAY BE FACTOR.  HUB DOES NOT HAVE TO COME OFF DU	RING TIRE CHANGE.  RECOMMEND VISUALLY AND NDI INSPECTION ON TIME OR CYCLE.		2	L	7	2 	4T			RT	A5SW
1998061200369	19980612	00369	CE  	1998	6	12	98ZZZX2124       	1	19980519	G	3231	50450018	BELLCRANK       			CESSNA	340   	340A        	2076405	CE  										GEAR DOOR	FAILED          	B		A	DJFR	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			EA	23	6826Y					340A1216				ARM ON CRANK ASSEMBLY SPUN ON SHAFT ALLOWING LANDING GEAR AND DOOR TO COME OUT OF SYNC.  LANDING GEAR DOOR CLOSED PRIOR 	TO GEAR GOING UP.  GEAR BOUND ON CLOSED DOOR CAUSING NUMEROUS PARTS OF MECHANICAL LINKAGE TO BE DAMAGED.  AIRCRAFT LANDE	D WITHOUT INCIDENT.  SUGGEST CLOSER INSPECTION OF THIS PART DURING SCHEDULED INSPECTION.				1	L	7	2 	3O				3A25
1998061200370	19980612	00370	EA  	1998	6	12	98ZZZX2125       	2	19980527	G	8530	LW15014	ROCKER ARM      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 4 CYL EXHAUST	FAILED          	H				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AL	01	733KE		145  			17268346	L495876			AIRCRAFT EN ROUTE TO FAIRBANKS, AK.  AT CRUISE, ENGINE RAN ROUGH, LOST ALTITUDE, MADE EMERGENCY LANDING ON ROAD.  TEAR D	OWN OF NR 4 ROCKER BOX SHOWED EXHAUST VALVE, ROCKER ARM BROKEN.  TSO:  145 HOURS.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998061200371	19980612	00371	EA  	1998	6	12	98ZZZX2126       	2	19980507	G	7414	10382807	CAPACITOR       			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					MAGNETO	DEFECTIVE       	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	17	733LW	1099 				17268384	L104776			MAGNETO POINTS AND COILS REPLACED ON 500-HOUR INSPECTION.  AIRCRAFT MADE FORCED LANDING APPROXIMATELY 3 HOURS LATER.  FO	UND CAM FOLLOWERS MELTED ON ONE SET AND RESET OTHER SET AND FLEW ACFT BACK TO BASE (APPROX ONE-HALF HOUR).  NEW POINTS S	HOWED SIGNS OF HEAT AFTER THIS SHORT FLIGHT.  BENDIX SB 587 REFERS TO THIS PROBLEM BEING CAUSED BY BAD CAPACITORS.  REPL	ACED BOTH SETS OF POINTS AND BOTH CAPACITORS.			1	H	7	1 	3O	3	O	NT	3A12    	E274
1998061200372	19980612	00372	SO  	1998	6	12	98ZZZX2127       	1	19980526	G	3211	9564308	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  										MLG LT AFT	BROKEN          	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8101K					448095005				WHILE BLEEDING LEFT BRAKE, TECHNICIAN NOTICED LT REAR MAIN LANDING GEAR TRUNNION BLOCK BROKEN IN HALF.  NO HARD LANDINGS	 REPORTED BY CREW.  INSTALLED NEW BLOCK AND C/W NDT OF AREA AND OTHER TRUNNION BLOCKS.  AN ALERT TECHNICIAN MAY HAVE SAV	ED GEAR COLLAPSING ON LANDING OR SOME OTHER MALFUNCTION.				1	L	7	2 	3O				A19S0
1998061200373	19980612	00373	GL  	1998	6	12	98ZZZX2128       	3	19980527	G	6110		BLADE           			CESSNA	210   	T210N       	2073456	CE  						MCAULY	D3A34	D3A34C402   	GL  	PROPELLER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	84BP					21064896		840673		AFTER RUN-UP, MECHANIC MOVED PROP BY HAND AND ONE BLADE ROTATED 90 DEGREES, THE OTHER 2 BLADES STAYED IN CORRECT POSITIO	N.					1	H	7	1 	3O				3A21    		5	C	P47GL
1998061200374	19980612	00374	CE  	1998	6	12	98ZZZX2129       	1	19980526	G	2434	1100747	ALTERNATOR      			BEECH 	95    	95B55       	1152729	CE  										RT ENGINE	FAILED          	B			R2JR	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			EA	21	886N					TC877				AIRCRAFT LOST ALL ELECTRICAL POWER IN-FLIGHT.  EMERGENCY LANDING MADE.  MAINTENANCE FOUND BOTH FIELD FUSES BLOWN.  INSPE	CTION OF ACFT REVEALED FOLLOWING:  RT ALTERNATOR WAS MISSING COOLING FAN.  ONE REGULATOR ONLY 26.5 VOLT OUTPUT.  RT ALTE	RNATOR OUTPUT TERMINAL BURNED AND FRAYED.  BOTH ALTERNATORS MOUNTED INCORRECTLY.  PLUG SHELL MISSING ON LT ALTERNATOR AN	D IMPROPER CONNECTOR PIN CAUSING ROTOR TO SHORT.  PROPER MAINTENANCE COULD HAVE PREVENTED THIS INCIDENT.  NO MAINTENANCE	 RECORDS MADE AVAILABLE.		1	L	7	2 	3O			RT	3A16
1998061200375	19980612	00375	EA  	1998	6	12	98ZZZX2130       	2	19980415	G	8520	SL78027	BOLT            			PIPER 	PA22  	PA22160     	7102214	SO  	LYC   	O320  	O320B2A     	41508	EA  					CONNECT ROD	FAILED          	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	8701D					225882	L1268339A			THIS ONE OUT OF EIGHT NEW CONNECTING ROD BOLTS STRETCHED AND DECREASED IN DIAMETER WHEN BEING TORQUED TO OEM SPECIFICATI	ON DURING ENGINE OVERHAUL.  ALL EIGHT BOLTS ARE 'NOT' BEING PUT INTO SERVICE.  BOLT WOULD NOT TORQUE TO OEM SPECIFICATIO	NS.				1	H	7	1 	3O	3	O		1A6     	E274
1998061200376	19980612	00376	SO  	1998	6	12	98ZZZX2131       	1	19980513	G	3230		VALVE           			PIPER 	PA34  	PA34220T    	7103420	SO  										GEAR FREE FALL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	9295N	189  				3449034				DURING ANNUAL INSPECTION AND GEAR RETRACTION CHECK, THE LANDING GEAR MOTOR WOULD RUN INTERMITTENTLY.  TROUBLESHOOTING FO	UND THE EMRGENCY GEAR FREE FALL VALVE WAS LEAKING INTERNALLY.  THE VALVE WAS REPLACED WITH A NEW ONE, GEAR OPS CHECK FOU	ND SATISFACTORY.				1	L	7	2 	3O				A7SO
1998061200378	19980612	00378	SO  	1998	6	12	98ZZZX2133       	1	19980513	G	3211		BOLT            			PIPER 	PA34  	PA34220T    	7103420	SO  										RT MLG	LOOSE           	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	9295N	189  				3449034				DURING AN ANNUAL INSPECTION, THE RIGHT LANDING GEAR WAS FOUND LOOSE.  INSPECTION FOUND THE FORWARD PIVOT BOLT FOR THE TR	UNNION WAS NOT PROPERLY TORQUED AT PRODUCTION OF THE AIRCRAFT.  THE LANDING GEAR WAS REMOVED, INSPECTED FOR CRACKS, AND 	RE-INSTALLED IAW SENECA V SM.  OPS CHECK FOUND SATISFACTORY.				1	L	7	2 	3O			 	A7SO
1998061200379	19980612	00379	SO  	1998	6	12	98ZZZX2134       	1	19980513	G	3230		BUSHING         			PIPER 	PA34  	PA34220T    	7103420	SO  										NLG DOWNLOCK	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19	9295N	189  				3449034				WHILE PERFORMING AN ANNUAL INSPECTION, THE NOSE GEAR DOWNLOCK BRACKET PIVOT BUSHING WAS NOT PROPERLY ALIGNED IN THE NOSE	 GEAR DOWNLOCK BRACKET.  THE ASSEMBLY WAS REMOVED AND INSPECTED FOR PREMATURE WEAR AND RE-INSTALLED PROPERLY WITH NEW BO	LTS.				1	L	7	2 	3O			 	A7SO
1998061200380	19980612	00380	NM  	1998	6	12	98ZZZX2135       	1	19980512	G	2710	6130031085506	CONTROL CABLE   			CHRIS 	HUSKY 	A1          	221020X	NM  										RT-LT AILERON	CHAFED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9598C	392  				1101				DURING A 100-HOUR INSPECTION, FOUND A SLIGHTLY FLAT SPOT ON THE RT AILERON CABLE ADJACENT TO THE MOST INBOARD FAIRLEAD O	N THE WING STRUT.  FURTHER INVESTIGATION AND WIPING CABLE CLEAN WITH A RAG REVEALED A BROKEN STRAND AND SEVERAL MORE SOO	N TO BREAK.  CLOSE INVESTIGATION OF THE LT AILERON CABLE IN THE SAME AREA REVEALED THE SAME PROBLEM, A BROKEN STRAND AND	 SEVERAL MORE SOON TO WEAR THROUGH.			1	H	7	1 	3O			NC	A22NM
1998061200381	19980612	00381	NM  	1998	6	12	98ZZZX2136       	1	19980523	G	5510	35004501	BRACE           			CHRIS 	HUSKY 	A1          	221020X	NM  										LT STABILIZER	FAILED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	9623Z	325  				1188				DURING AN ANNUAL INSPECTION, A RATTLING SOUND WAS DISCOVERED IN THE LEFT HORIZONTAL STABILIZER.  FURTHER INVESTIGATION R	EVEALED THE TRACK WELD SECURING THE DIAGONAL BRACE TO THE BUTT RIB HAD BROKEN LOOSE DUE TO AN INADEQUATE WELD.  THE DIAG	ONAL BRACE IS NOT A STRUCTURAL MEMBER, BUT IS THERE TO PROVIDE SUPPORT TO PREVENT THE BUTT RIB FROM DEFORMING DURING THE	 FABRIC COVERING PROCESS.  HOWEVER, IF LEFT UNREPAIRED, FURTHER VIBRATION COULD DAMAGE THE BUTT RIB AND/OR THE FACRIC CO	VERING.		1	H	7	1 	3O			NC	A22NM
1998061200651	19980612	00651	EA  	1998	6	12	98ZZZX2138       	2	19980513	G	8530	ST204	PISTON RING     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CYLINDER	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	49043	30   				15281117	L1461115			THIS ENGINE HAD 3 CYLINDERS OVERHAULED WITH RINGS IN THE FIELD.  THE FOURTH WAS REPLACED WITH A COMPLETE CHROME CYLINDER	 ASSY.  AFTER 30 HOURS OF FLIGHT, THE OIL CONSUMPTION AND BLOW-BY BECAME EXCESSIVE.  A COMPRESSION TEST SHOWED 20/80 OR 	THE 3 OVERHAULED AND 68/80 ON THE CHROME CYLINDER.  THE RINGS IN THE CHROME CYLINDER APPEARED OK WHILE THE OTHERS SHOWED	 SEVERE WEAR.			1	H	7	1 	3O	3	O	NT	3A19    	E223
1998061200653	19980612	00653	CE  	1998	6	12	98ZZZX2140       	1	19980501	G	7921	AN340A	BOLT            			CESSNA	172   	172RG       	2072438	CE  										OIL COOLER	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	6435V					172RG0696				FOUR EACH OF THESE BOLTS HOLD THE OIL COOLER TO RT BAFFLE.  TWO OF THESE BOLTS FAILED LEAVING ONLY THE TWO INBD BOLTS SE	CURING THE OIL COOLER.  FAILURE WAS DISCOVERED AT OIL CHANGE.  THIS IS THE P/N CESSNA CALLS FOR IN THE IPM (ILLUSTATED P	ARTS MANUAL).  BOTH BOLT SHANKS WERE FOUND IN THE LOWER COWL ALONG WITH THE NUTS.  BOLTS FAILED AT THE FRILLED HOLE IN S	HANK LEAVING TIP OF BOLT IN NUT.  TOTAL TIME 6,500 PLUS HOURS.			1	H	7	1 	3O				3A17
1998061200654	19980612	00654	CE  	1998	6	12	98ZZZX2141       	1	19980527	G	3230	08421022	BELLCRANK       			CESSNA	310   	310P        	2074238	CE  										NLG IDLER	FAILED          	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5092P					310P0057				NLG IDLER BELLCRANK BOLT HOLES FAILED (PULLED OUT).						1	L	7	2 	3O				3A10
1998061200655	19980612	00655	CE  	1998	6	12	98ZZZX2142       	1	19980527	G	3230	08421211	IDLER ARM       			CESSNA	310   	310P        	2074238	CE  										NLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5092P					310P0057				NLG IDLER ARM FAILED.						1	L	7	2 	3O				3A10
1998061200656	19980612	00656	CE  	1998	6	12	98ZZZX2143       	1	19980515	G	5711	071160514	SPAR            			CESSNA	182   	182S        	2072701	CE  										CARRY THRU	CRACKED         	B		A	CB5Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	697SM	133  				18280008				DURING ANNUAL INSPECTION, A CRACK OF APPROXIMATELY .50 INCH WAS FOUND ON THE FORWARD VERTICAL FACE OF THE TOP HAT SECTIO	N FORMING THE SPAR ASSY 1 INCH INBOARD OF THE OUTER EDGE AND ADJACENT BUT NOT RUNNING TO THE LT MAIN PLANE REAR ATTACH B	OLT.  CAUSE UNKNOWN AT THIS TIME, BUT WITH INSTRUCTIONS FROM CESSNA AIRCRAFT COMPANY TO REPLACE AND RETURN ITEM FOR FURT	HER INVESTIGATION.			1	H	7	1 	3O			NT	3A13
1998061200657	19980612	00657	SO  	1998	6	12	98ZZZX2144       	2	19980518	G	7322	CF46F12	VENTURI         	FACET       	MA3SPA      	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	DEFECTIVE       	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	704AC					15078450				ONE-PIECE VENTURI INSTALLED TO C/W AD 93-18-03 CAUSED DISRUPTION OF FUEL FLOW AND ENGINE WOULD NOT DEVELOP FULL POWER. S	INGLE PIECE VENTURI MANUFACTURED BY CONSOLIDATED.  P/N CF46-F12 WAS INSTALLED IN MARVEL SCHLEBLER MA3-SPA CARBURETOR TO 	C/W AD TO REPLACE 2-PIECE VENTURI.  AFTER INSTALLATION, ENGINE WOULD NOT DEVELOP FULL POWER RPM AND RAN ROUGH.				1	H	7	1 	3O	3	O		3A19    	E252
1998061200658	19980612	00658	SO  	1998	6	12	98ZZZX2145       	1	19980522	G	5541		RIB             			PIPER 	PA28  	PA28140     	7102802	SO  										RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8071N	3379 				2825321				REMOVED RUDDER BELLCRANK TO STRIP AND REPAINT AND ONCE REMOVED NOTED DISSIMILAR METAL CORROSION ON THE END RIB OF RUDDER	 AND VISIBLE HOLES FROM CORROSION.  END RIB WAS NOT PRIMED AND ATTACHED TO THE METAL BELLCRANK.  DISSIMILAR METAL CORROS	ION FORMED.  RECOMMEND AD FOR BELLCRANK REMOVAL AND INSPECT.				1	L	7	1 	3O				2A13
1998061200659	19980612	00659	SO  	1998	6	12	98ZZZX2146       	1	19980522	G	5347	6255704	SEAT TRACK      			PIPER 	PA28  	PA28140     	7102802	SO  										CABIN	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8071N	3379 				2825321				REMOVED CARPET WITH RELATED REPAIR AND NOTED THREE OF THE FOUR SEAT TRACKS CORRODED AND RIVETS DISSOLVED IN EFFECTED ARE	AS.  BAD ALLOYS IN METALERGY.  RECOMMEND AD TO INSPECT FOR BLISTERS IN SEAT TRACK RAILS.					1	L	7	1 	3O				2A13
1998061200660	19980612	00660	SO  	1998	6	12	98ZZZX2147       	1	19980522	G	5711	6560110	SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  										WING	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	8071N	3379 				2825321				APPROXIMATELY 6 INCHES FROM THE ATTACH POINT ON THE REAR FOOT OF THE I-BEAM SPAR, A 3 INCH CORROSION CRACK WAS NOTED.  C	AUSE BAD ALLOYS WHEN METALERGY WAS MADE.  RECOMMEND AD WITH CONFIRMATION OF COMPLIANCE FROM IA.					1	L	7	1 	3O				2A13
1998061200661	19980612	00661	SO  	1998	6	12	98ZZZX2148       	1	19980512	G	3233	484706	O-RING          			PIPER 	PA34  	PA34220T    	7103420	SO  										MLG ACTUATOR	WRONG PART      	B	L		VJ3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	9299E	183  				3449043				TWO PREVIOUS O-RING FAILURES AND ONE O-RING INSPECTION REVEALING O-RING DAMAGE ON ANOTHER AIRCRAFT PROMPTED INSPECTION O	F ALL ACTUATORS ON THIS AIRCRAFT (FAILURE RESULTS IN INCOMPLETE GEAR RETRACTION).  UPON DISASSEMBLY, FOUND INCORRECT O-R	INGS INSTALLED ON ALL 3 ACTUATOR PISTONS.  O-RINGS WERE DAMAGED (ROLLED AND SCUFFED), BUT HAD NOT YET FAILED.				1	L	7	2 	3O			 	A7SO
1998061200662	19980612	00662	NM  	1998	6	12	98ZZZX2149       	1	19980512	G	2710	6130031085508	CONTROL CABLE   			CHRIS 	HUSKY 	A1          	221020X	NM  										RT AILERON	WORN            	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	9598C	392  				1101				DURING A 100-HOUR INSPECTION, FOUND A SLIGHTLY FLAT SPOT ON THE RT AILERON CABLE ADJACENT TO THE MOST INBOARD FAIRLEAD O	N THE WING STRUT.  FURTHER INVESTIGATION AND WIPING CABLE CLEAN WITH A RAG REVEALED A BROKEN STRAND AND SEVERAL MORE SOO	N TO BREAK.  CLOSE INVESTIGATION OF THE LT AILERON CABLE IN THE SAME AREA REVEALED THE SAME PROBLEM.  A BROKEN STRAND AN	D SEVERAL MORE SOON TO WEAR THROUGH.			1	H	7	1 	3O			NC	A22NM
1998061200663	19980612	00663	EU  	1998	6	12	98ZZZX2150       	1	19980520	G	2130	22201N031000	SELECTOR        			AMD   	FALC50	FALCON50MYST	2730106	EU  										CABIN PRESS	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	500AF		1666 		445	170				DASSAULT FALCON JET RENTED THIS UNIT FOR SERVICE ON FALCON 50, S/N 170.  AFTER INSTALLATION AND ON FIRST FLIGHT, FLIGHT 	CREW REPORTED CABIN FLUCTUATION IN LEVEL FLIGHT.					2	L	7	3 	4F				A46EU
1998061200664	19980612	00664	GL  	1998	6	12	98ZZZX2151       	3	19980519	G	6114	D4497C501	HUB             			CESSNA	404   	404         	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	NR 2 SOCKET	CRACKED         	B		A	ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	QTVAM	1600 	1357 			4040851		807032		DURING PRE-FLIGHT, A NR 2 BLADE FOUND LOSE IN HUB SPINNER REMOVED, HUB FOUND CRACKED NR 2 BLADE SOCKET THROUGH TO CYLIND	ER.  AFTER PROPELLER DIS-ASSEMBLY, NO DAMAGE NOTED TO BLADE.  THE BLADE COULD HAVE DEPARTED THE PROPELLER WHEN FULL POWE	R WAS APPLIED.				1	L	7	2 	3O			RT	A25CE   		5	C	P45GL
1998061200665	19980612	00665		1998	6	12	98ZZZX2152       	1	19980515	G	3340		STROBE          	WHELEN      																ANTI-COLLISION	FAILED          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09			17   		003201					STROBE LASTED LESS THAN 17 HOURS AFTER REPAIR BY THE FACTORY.
1998061200666	19980612	00666	CE  	1998	6	12	98ZZZX2153       	1	19980501	G	2510	51194214	STRIKER         			CESSNA	421   	421C        	2076016	CE  										SEAT REST STOP	MISMANUFACTURED 	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09										REPLACED A NEW SEAT REST STOP AND THE THREADS HAD BEEN DOUBLE CUT.  8130-3 FORM BLOCK 3:  D25758.  BLOCK 5:  D8041968.						1	L	7	2 	3O			 	A7CE
1998061200668	19980612	00668	SO  	1998	6	12	98ZZZX2155       	1	19980506	G	2910	566177	HOSE            			PIPER 	PA46  	PA46350P    		SO  										HYDRAULIC SYS	FAILED          	B			SO5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	03	5EG	492  				4636051				HOSE PART NUMBERS ARE INCORRECT IN THE PARTS MANUAL.  FOUND THIS OCCURRENCE ON ONE OTHER (429CA, S/N 4636092) PA46350P. 	 HOSES IN THE AFT HYDRAULIC SYSTEM FOUND LEAKING THROUGH BRAIDING AND AT FITTINGS ENOUGH TO HAVE FLUID AT AND UP TO SEVE	RAL BULKHEADS FORWARD OF LEAK AREA.  SUBMITTER STATED A MORE FLEXIBLE HOSE (SMALLER OD) OR AN ANGLE FITTING ON HOSE WOUL	D REMEDY THE PROBLEM.			1	L	7	1 	3O			RT	A25SO
1998061200669	19980612	00669	SO  	1998	6	12	98ZZZX2156       	1	19980506	G	2910	566178	HOSE            			PIPER 	PA46  	PA46350P    		SO  										HYDRAULIC SYS	FAILED          	B			SO5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	03	5EG	492  				4636051				HOSE PART NUMBERS ARE INCORRECT IN THE PARTS MANUAL.  FOUND THIS OCCURRENCE ON ONE OTHER (429CA, S/N 4636092) PA46350P. 	 HOSES IN THE AFT HYDRAULIC SYSTEM FOUND LEAKING THROUGH BRAIDING AND AT FITTINGS ENOUGH TO HAVE FLUID AT AND UP TO SEVE	RAL BULKHEADS FORWARD OF LEAK AREA.  SUBMITTER STATED A MORE FLEXIBLE HOSE (SMALLER OD) OR AN ANGLE FITTING ON HOSE WOUL	D REMEDY THE PROBLEM.			1	L	7	1 	3O			RT	A25SO
1998061900001	19980619	00001	SW  	1998	6	19	98ZZZX2157       	1	19980501	G	5210	5511231120	BRACKET         		551123063   	GULSTM	560   	560         	0141402	SW  										CABIN DOOR	BROKEN          	B		A	BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	500UB	2903 				5600052				AFTER A FLIGHT, THE PILOT COULD NOT OPEN THE CABIN DOOR AND HAD TO CLIMB OUT THE EMERGENCY WINDOW.  THE DOOR COULD NOT B	E OPENED FROM THE OUTSIDE EITHER.  DISASSEMBLED THE DOOR, AS WELL, AND FOUND THE AFT LATCH PIN BELLCRANK BRACKET BROKEN 	WHICH CAUSED THE AFT DOOR LATCH PINS TO REMAIN EXTENDED.  THE BRACKET HAD BEEN STRESSED BY LINKAGE ARM HITTING IT WHEN O	PENED.			1	H	7	2 	3O				6A1
1998061900003	19980619	00003	CE  	1998	6	19	98ZZZX2159       	1	19980518	G	7920		HOSE            			BEECH 	95    	D95A        	1153408	CE  										OIL COOLER	FAILED          	H		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	64TA					TD568				OIL LINES RUNNING FROM FRONT MOUNTED OIL COOLER CONTACTED EXHAUST PIPES.  OIL LINES WERE MOUNTED TO COWLING, WHEN UPPER 	COWL HALF WAS CLOSED AND LATCHED THE COWLING WAS PULLED INWARD CAUSING THE OIL LINES TO CONTACT EXHAUST, BURNING THROUGH	 AND CAUSING COMPLETE OIL LOSS.				1	L	7	2 	3O				3A16
1998061900004	19980619	00004	EA  	1998	6	19	98ZZZX2160       	2	19980416	G	8530	60009	VALVE KEEPER    		LW11633     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 4 CYLINDER	WORN            	B			LJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	757RM		407  		A5383	15279944	L1917815			VALVE KEEPERS WORN, BUT STILL INSTALLED.  LET VALVE ASSY MOVE DOWN IN KEEPER ASSY.  VALVE WOULD NOT COMPLETELY CLOSE.  N	O DAMAGE TO CYLINDER OR PISTON.					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998061900005	19980619	00005	SO  	1998	6	19	98ZZZX2161       	1	19980501	G	3250	400004	BOLT            			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG STEERING	FAILED          	H		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	99	20TP					347870306				NOSE GEAR COLLAPSED ON LANDING.  COULD NOT GET A NOSE GEAR SAFE LIGHT AFTER PERFORMING EXTENSIVE EMERGENCY GEAR LOWERING	 PROCEDURES.  EXTENSIVE DAMAGE TO GEAR DOORS, NOSE, PROPS, AND TO ENGINES REQUIRING TEAR DOWN AND OVERHAUL.  CAUSE WAS T	HE BOLT HEAD SEPARATION P/N 400-004 (AN4-7A) ON ONE BOLT WHICH ALLOWED THE NOSE GEAR STEERING CHANNEL TO PIVOT OUT OF PO	SITION PREVENTING THE NOSE GEAR TO EXTEND COMPLETELY.			1	L	7	2 	3O				A7SO
1998061900006	19980619	00006	SO  	1998	6	19	98ZZZX2162       	1	19980515	G	3233	484706	O-RING          		9686002     	PIPER 	PA34  	PA34220T    	7103420	SO  										GEAR ACTUATOR	WRONG PART      	B	L		VJ3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	4123C	142  				3449042				TWO PREVIOUS O-RING FAILURES AND FOUR O-RING INSPECTIONS REVEALING O-RING DAMAGE ON ANOTHER AIRCRAFT PROMPTED INSPECTION	 OF ALL ACTUATORS ON THIS AIRCRAFT (FAILURE RESULTS IN INCOMPLETE GEAR RETRACTION).  UPON DISASSEMBLY, FOUND INCORRECT O	-RINGS INSTALLED ON ALL 3 ACTUATOR PISTONS.  O-RINGS WERE DAMAGED (ROLLED AND SCUFFED), BUT HAD NOT YET FAILED.				1	L	7	2 	3O			 	A7SO
1998061900007	19980619	00007	SO  	1998	6	19	98ZZZX2163       	1	19980512	G	3233	484706	O-RING          		9686002     	PIPER 	PA34  	PA34220T    	7103420	SO  										NLG ACTUATOR	WRONG PART      	B		A	VJ3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	4177R	228  				3449046				TWO PREVIOUS O-RING FAILURES PROMPTED INSPECTION OF THIS ACTUATOR (SAME P/N AS RIGHT AND LEFT GEAR ACTUATORS).  UPON DIS	ASSEMBLY, FOUND INCORRECT O-RING INSTALLED ON ACTUATOR PISTON.  O-RING WAS DAMAGED, BUT HAD NOT YET FAILED.					1	L	7	2 	3O			 	A7SO
1998061900008	19980619	00008	NE  	1998	6	19	98ZZZX2164       	2	19980518	G	8530	MYHN52	CYLINDER        			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  					NR 4	CRACKED         	B			IL1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	48695	24   				1628	21888			INSPECTION FOUND NR 4 CYLINDER CRACKED IN ROCKER BOSS AREA.						1	Q	7	1 	3R	3	R		1A16    	5E2
1998061900009	19980619	00009	SO  	1998	6	19	98ZZZX2165       	1	19980401	G	3213	3564405	GEAR ASSY       			PIPER 	PA28  	PA28161     	7102803	SO  										RT MLG	FAILED          	D	L	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	103SA	15625				288416012				RIGHT MAIN GEAR BROKE AT SCISSORS UPPER ATTACH POINT.  PILOT PERFORMING CROSSWIND TOUCH AND GO LANDINGS.						1	L	7	1 	3O				2A13
1998061900010	19980619	00010	SO  	1998	6	19	98ZZZX2166       	2	19980328	G	8520	35972	ROD BOLT        			BEECH 	55    	95A55       	1152704	CE  	CONT  	O470  	IO470L      	17026	SO  					NR 1	FAILED          	D	L			K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	05	1040T					TC318	1923459LR			ROD BOLT WAS MAGNAFLUXED AND CLEANED 75.8 HOURS PRIOR TO FAILURE.  TT UNKNOWN, SUSPECT UNDETECTED METAL FATIGUE.  BOLT B	ROKE UNDER FULL POWER AND HIGH RPM.  SUGGEST CHANGING OUT ROD BOLTS WITH NEW BOLTS AT EACH MAJOR OVERHAUL.					1	L	7	2 	3O	3	O		3A16    	3E1
1998061900011	19980619	00011	SO  	1998	6	19	98ZZZX2167       	1	19980430	G	2913	2680210	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  										RT ENG HYD	FAILED          	D				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			NE	01	131PJ	800  				317912030				PILOT REPORT - GEAR SLOW TO RETRACT.  FOUND HYDRAULIC PUMP INOPERATIVE RT ENGINE.  HYDRAULIC PUMP DRIVE GEAR SEPARATED I	NTO TWO PARTS.  GEAR KEYWAY AND SECTION OF GEAR FOUND IN OUTLET SECTION OF PUMP HEAD.  THERE WAS NO SIGN OF SEIZURE TO C	AUSE THIS FAILURE.				1	L	7	2 	3O				A20SO
1998061900013	19980619	00013	SO  	1998	6	19	98ZZZX2169       	1	19980405	G	2913	105476	POWER PACK      	PRESTOLITE  		PIPER 	PA28  	PA28RT201   	7102818	SO  										GEAR RETRACT	MALFUNCTIONED   	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	03	2853N	1552 			AH6066	28R7918176				PILOT REPORTED THAT GEAR FAILED TO RETRACT AFTER TAKEOFF.  AIRCRAFT RETURNED TO AIRPORT AND WAS INSPECTED.  FOUND HYDRAU	LIC FLUID TO BE CONGEALED AND CONTAMINATED IN PUMP RESERVOIR.  SENT PUMP OUT FOR OVERHAUL.  FLUSHED ENTIRE HYDRAULIC SYS	TEM TO REMOVE CONTAMINATED FLUID.  RE-INSTALLED OVERHAULED PUMP AND RE-SERVICED SYSTEM WITH NEW MIL5606 FLUID.  PERFORME	D GEAR OPERATIONAL AND LEAK CHECK, FOUND OK.  SUBMITTER RECOMMENDED FLUSHING HYDRAULIC SYSTEM AND REPLACING FLUID AT 5 Y	EAR/1,000 HOUR INTERVALS TO COINCIDE WITH 5 YEAR/1,000 HOUR FLEXIBLE FLUID LINE CHANGE.		1	L	7	1 	3O				2A13
1998061900015	19980619	00015	SO  	1998	6	19	98ZZZX2171       	1	19980526	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										RT ENG HYDRAULIC	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	3581C	226  			1633	318052091				PILOT REPORTED THAT THE LANDING GEAR SLOW TO CYCLE.  MAINTENANCE PERFORMED PRESSURE CHECK OF THE ENGINE DRIVEN HYDRAULIC	 PUMPS.  FOUND RIGHT ENGINE DRIVEN HYDRAULIC PUMP VERY WEAK.  INSPECTED RT HYDRAULIC FILTER AND FOUND EXCESSIVE AMOUNTS 	OF METAL.  REMOVED RT ENGINE HYDRAULIC PUMP AND DISASSEMBLED FOR INSPECTION.  FOUND THE BEARING THAT SUPPORTS THE IDLER 	GEAR EXCESSIVELY WORN WHICH ALLOWED THE IDLER GEAR TO TILT AND GALL INTO THE PUMPS CAVITY.			1	L	7	2 	3O				A20SO
1998061900017	19980619	00017	CE  	1998	6	19	98ZZZX2173       	1	19980522	G	7160	165201325	AIR DOOR        			CESSNA	182   	182P        	2075816	CE  										COWL INDUCTION	DETACHED        	H	S	A		O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	768GC					18262276				PILOT REPORTED ENG POWER LOSS AT CRUISE SETTING.  DURING GROUND RUN AT FULL POWER, LOSS OF POWER NOTED AND THROTTLE COUL	D NOT BE RETARDED (THROTTLE LOCKED).  ENG WAS SHUT DOWN BY FUEL CUTOFF AND IGNITION.  REMOVED COWLING AND FOUND ALTERNAT	E AIR DOOR CESSNA P/N 1652013-25 IN THE INDUCTION DUCT FROM AIR BOX TO FUEL INJ ASSY.  THIS CAUSED A RESTRICTION OF AIR 	FLOW TO ENG AND ALT AIR DOOR TO BECOME LODGED IN THE THROTTLE VALVE DURING FULL POWER SETTING DUE TO AIR VELOSITY ENTERI	NG ENG INTAKE.  ALT AIR DOOR IS INCORP IN THE AIR BOX AND LOCATED IN PLACE BY A PIN AND LOADED SPRINGS.  ACFT MODIFIED U	NDER STC SA3825SW FOR INSTALL OF IO-470F CONT ENG WHICH INCLUDED MODIFICATION OF INDUCTION SYS TO INCLUDE AN ALT AIR DOO	1	H	7	1 	3O			NT	TA13
1998061900018	19980619	00018	CE  	1998	6	19	98ZZZX2174       	1	19980424	G	7820	W188011	MUFFLER         			CESSNA	188   	A188B       	2073005	CE  										ENGINE EXH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	9438G	7    			7071	18801485T				NEW MUFFLER ASSY CRACKED ADJACENT TO WELD COMPLETELY AROUND TAILPIPE ALLOWING IT TO SEPARATE FROM MUFFLER.						1	L	7	1 	3O				A9CE
1998061900902	19980619	00902	SO  	1998	6	19	98ZZZX2175       	1	19980427	G	2821		GASCOLATOR      			PIPER 	J3    	PA11        	7101102	SO  										FUEL FILTER	WORN            	H	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27										POSSIBLE LOSS OF FUEL GASCOLATOR DUE TO BREAKAGE OF BAIL.  THIS HAS BEEN FOUND ON A NUMBER OF OLDER PIPERS DUE TO THE FA	CT THAT THE BAIL UPPER ENDS WEAR INTO THE BRACKET THAT HOLDS THE ENTIRE ASSEMBLY TO FIREWALL.					1	H	7	1 	3O				A691
1998061900903	19980619	00903	CE  	1998	6	19	98ZZZX2176       	1	19980527	G	5312	12124092	BULKHEAD        			CESSNA	210   	210B        	2073410	CE  										BS 230.187	CRACKED         	B	S		PCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	9722X					21058022				ROUTINE ANNUAL INSPECTION REVEALED CRACKED BULKHEAD ADJACENT TO RT RUDDER STOP ATTACH POINT.  SUSPECT WIND DAMAGE TO BE 	CAUSE.					1	H	7	1 	3O				3A21
1998061900904	19980619	00904	NE  	1998	6	19	98ZZZX2177       	3	19980501	G	6111	610112	BLADE           			AIRTRC	AT300 	AT301       	0390103	SW  						HAMSTD	12D	12D40       	NE  	PROPELLER	FAILED          	G				A				UNSCHED LANDING         				D	E		INFLIGHT SEPARATION       	VIBRATION/BUFFET          		AG	AGRICULTURE    	1			NM	07	8869S		42   			3010220		P4125		BLADE FAILED DURING SPRAY TURN (AG OPERATOR), 11.75 INCHES CAME OFF ONE BLADE.  NO VISUAL EVIDENCE OF INPACT DAMAGE.  SU	BMITTER STATED APPEARS TO BE A RESULT OF FATIGUE.  AIRCRAFT LANDED IN FIELD WITHOUT DAMAGE OTHER THAN THAT CAUSED BY SEV	ERE VIBRATION.				1	L	7	1 	3R				A9SW    		5	C	P257
1998061900905	19980619	00905		1998	6	19	98ZZZX2178       	4	19980316	G	2562	AK450	ELT             			CESSNA	421   	421C        	2076016	CE  										CABIN	FAILED          	B			EKIR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	07	421RX					421C0264				ELT UNIT 1-1/2 YEARS OLD.  GOT TEST LIGHT, BUT NO OUTPUT SIGNAL.						1	L	7	2 	3O				A7CE
1998061900906	19980619	00906		1998	6	19	98ZZZX2179       	4	19980316	G	2562	AK450	ELT             			CESSNA	414   	414         	2075908	CE  										CABIN	FAILED          	B			EKIR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			WP	07	8235Q				4505073	4140165				ELT UNIT 1-1/2 YEARS OLD.  GOT TEST LIGHT, BUT NO OUTPUT SIGNAL.						1	L	7	2 	3O			RT	A7CE
1998061900907	19980619	00907	CE  	1998	6	19	98ZZZX2180       	1	19980521	G	2571	07120591	SUPPORT         			CESSNA	182   	182R        	2072731	CE  										BATTERY	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	9921H	3154 				18268114				BOTH BATTERY SUPPORT BRACKETS WERE FOUND BROKEN DURING AN ANNUAL INSPECTION.  THESE SUPPORT BRACKETS ARE ONLY INSTALLED 	WITH THE MANIFOLD BATTERY INSTALLATION.  ITEM 12 OF PART'S LIST.					1	L	7	1 	3O			NT	3A13
1998061900908	19980619	00908		1998	6	19	98ZZZX2181       	2	19980527	G	8550	CH4810	OIL FILTER      	CHAMPION    																ENGINE OIL	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07					F104141					INSIDE PARTS OF CHAMPION OIL FILTER P/N CH48110 AND S/N F10H141 LOOSE, RATTLES WHEN SHAKEN.
1998061900909	19980619	00909	SO  	1998	6	19	98ZZZX2182       	1	19980527	G	5712	7850008	RIB             			PIPER 	PA28  	PA28R200    	7102811	SO  										WING	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	5210T	2793 				28R7235195				FOUND RIVETS, ON ATTACHMENT ANGLE, CONNECTING RIB TO AFT FALSE SPAR, OUTBOARD OF MAIN GEAR ATTACHMENTS TO SPARS, MISSING	/LOOSE DUE TO HARD LANDINGS AND/OR TIME IN SERVICE.  SUBMITTER RECOMMENDED THIS AREA BE INSPECTED CLOSELY DURING ANNUAL 	AND AFTER HARD LANDINGS ESPECIALLY IF AIRCRAFT USED FOR TRAINING.				1	L	7	1 	3O				2A13
1998061900910	19980619	00910	EA  	1998	6	19	98ZZZX2183       	2	19980526	G	8520		CONNECT ROD     			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					CYLINDERS 3,4	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	51302					17264234	L1580327A			ENGINE EXPERIENCED HIGH OIL TEMPERATURE 60 HOURS AFTER INSTALLING FACTORY OVERHAULED ENGINE.  THERE WAS NOISE WHEN TURNI	NG THE PROPELLER AFTER ENGINE SHUT DOWN.  FACTORY SERVICE REP PULLED NR 3 AND NR 4 CYLINDERS AND FOUND THAT NR 3 AND NR 	4 CONNECTING RODS HAD EXCESSIVE SIDE CLEARANCE.  ROD WAS RUBBING AGAINST CRANKSHAFT JOURNAL.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998061900911	19980619	00911	SO  	1998	6	19	98ZZZX2184       	1	19980529	G	7810	2109208	STACK           			PIPER 	PA24  	PA24        	7102402	SO  										EXHAUST SYSTEM	BROKEN          	D		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SW	99	45MB	4426 				241445				JUST AFTER TAKEOFF, PILOT REPORTED SMOKE IN THE COCKPIT.  HE DELCARED AN EMERGENCY LANDING.  AFTER TOUCH-DOWN AND REDUCI	NG POWER, SMOKE CLEARED.  AFTER SHUT DOWN, REMOVED COWLING AND FOUND EXHAUST PIPE OFF OF MUFFLER.  FOUND EXHAUST PIPE BR	OKEN AFT OF NR 3 RISER AT WELD FOR CARBURETOR HEAT SHROUD END.  SUSPECT CAUSE IS THE UNSUPPORTED MUFFLER AND PIPE ASSY P	UTS STRESS ON EXHAUST SYSTEM.  RECOMMEND THOROUGH INSPECTION OF THE ENTIRE EXHAUST SYSTEM EVERY ANNUAL INSPECTION.			1	L	7	1 	3O				1A15
1998061900914	19980619	00914	SW  	1998	6	19	98ZZZX2187       	1	19980526	G	5610	010A31874002	WINDOW          			MTSBSI	MU2   	MU2B        	5780404	SW  										RT COCKPIT	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	36G	5381 				035				WHILE PERFORMING 100-HOUR INSPECTION PER CUSTOMER'S PROGRAM, CRACK NOTED AT RT COCKPIT SIDE WINDOW.  DEEP INSPECTION OF 	ALL WINDOWS COMPLETED PER MM AND SB 224B.  ALL FOUND CRAZED DEEPER THAN LIMITS ALLOW.  AIRCRAFT WINDOWS HAD JUST BEEN RE	FURBISHED AND SIGNED OFF AS AIRWORTHY BY AN UNCERTIFIED SHOP.  WINDOWS REPLACED WITH NEW TO RETURN AIRCRAFT TO SERVICE. 	 SUBMITTER SUGGESTED USE OF PROPER TOOLS AND TECHNIQUES WHEN REFURBISHING OR INSPECTING THESE WINDOWS.			1	H	7	2 	3T				A2PC
1998061900915	19980619	00915	SW  	1998	6	19	98ZZZX2188       	1	19980526	G	5310		DRAIN           			SWRNGN	SA227 	SA227AC     	8780603	SW  										BELLY	PLUGGED         	B		A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	376PH					AC573				WHILE ASSISTING OPERATOR WITH MAINTENANCE, FOUND 40-50 GALLONS OF WATER IN AIRCRAFT BELLY BELOW FLOORBOARDS.  SAS SERVO 	UNIT COMPLETELY SUBMERGED.  FUSELAGE DRAINS CLOGGED.  CLEANED DRAINS.  REMOVED WATER AND DIRT.  REPLACED SERVO.  AIRCRAF	T USED TO HAVE FREIGHT.				2	L	7	2 	4T			RT	A8SW
1998061900916	19980619	00916	SO  	1998	6	19	98ZZZX2189       	1	19980501	G	2710		INPUT LEVER     	PARKERHANFIN		GULSTM	G1159 	G1159       	3953505	SO  										AIL ACTUATOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	122DU				65	6				AILERON ACTUATOR INPUT LEVER FOUND CRACKED AT ATTACH BOLT HOLE.  LEVER FOUND CRACKED AT ATTACHMENT BOLT HOLE.						2	L	7	2 	4F			RT	A12EA
1998061900917	19980619	00917	NE  	1998	6	19	98ZZZX2190       	2	19980428	G	7314	02532330002	FUEL PUMP       	SUNDSTRANDEM		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					DRIVE SHAFT	FAILED          	H				O				OTHER                   				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			WP	05	430MC		995  			BB904	PCE93097			DURING CRUISE FLIGHT, THE RT ENGINE FLAMED OUT AND WOULD NOT RESTART IN-FLIGHT.  AFTER A SAFE LANDING, THE ENGINE STARTE	D NORMALLY.  HOWEVER, WHEN POWERED UP TO 100 PERCENT, THE ENGINE WOULD IMMEDIATELY FLAME OUT.  INSPECTION REVEALED THE H	IGH PRESSURE, ENGINE-DRIVEN FUEL PUMP WAS AT FAULT.  THE SPLINED DRIVE SHAFT FROM THE ACCESSORY SECTION TO THE FUEL PUMP	 WAS FOUND STRIPPED.  THERE WAS, HOWEVER, ENOUGH SHEARED METAL LEFT IN THE DRIVE COUPLING TO ALLOW THE DRIVE SHAFT TO EN	GAGE INTERMITTENTLY.  CLOSE INSPECTION OF THE STRIPPED SHAFT DID NOT REVEAL ANY REASON FOR FAILURE, EXCEPT FOR METAL FAT	IGUE.  THE PUMP AND DRIVE SHAFT WERE REPLACED AND THE ENGINE FUNCTIONED NORMALLY.	1	L	7	2 	4T	4	T		A24CE   	E4EA
1998061900918	19980619	00918	SO  	1998	6	19	98ZZZX2191       	1	19980520	G	2761	2391110	ACTUATOR        	DECOTO      		LKHEED	1329  	132925      	5263125	SO  										SPEED BRAKE	LEAKING         	D		A		O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	07	38BG	6556 				5208				DURING FLIGHT, SPEED BRAKE WAS SELECTED DOWN AND LOSS OF HYDRAULIC PRESSURE WAS NOTED.  CREW EXECUTED NO HYDRAULIC PRESS	URE CHECK LIST FOR SYSTEM NR 1 AS OUTLINED IN THE FLIGHT MANUAL.  AFTER LANDING, SPEED BRAKE WAS OPENED AND FLUID WAS FO	UND LEAKING FROM THE RT SPEED BRAKE ACTUATOR.  MAINTENANCE CREW NOTED THE BUSHING SLEEVE HAD MOVED OUTSIDE OF THE END CA	P AROUND THE PISTON.  ACTUATOR WAS REMOVED AND REPLACED WITH AN OVERHAULED UNIT.			2	L	7	4 	4F				2A1SO
1998061900921	19980619	00921	CE  	1998	6	19	98ZZZX2194       	1	19980527	G	5210	54155851	DAMPER SHAFT    			LEAR  	55    	55LEAR      	5170702	CE  										AFT CABIN DOOR	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	777MC					081				DAMPER SHAFT FAILURE CAUSES DOOR TO BE SUSCEPTIBLE TO PREMATURE CLOSING.  THIS IS DONE BECAUSE WHEN PART BENDS AND TWIST	S, THE EFFECTIVITY OF DAMPER IS DIMINISHED.  ORIGINAL PARTS LASTED 12 YEARS.  CURRENT PART IS MADE OF SOFTER STEEL OR LA	CKS PROPER HEAT TREATING.  ORIGNAL PARTS FAILED BY CRACKING.  VISUAL AND HARDNESS TEST INDICATED THEY WERE HEAT TREATED.				2	L	7	2 	4F				A10CE
1998061900922	19980619	00922	NE  	1998	6	19	98ZZZX2195       	3	19980521	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		3875 	923  				HJ298			FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  SIX CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998061900923	19980619	00923	NE  	1998	6	19	98ZZZX2196       	3	19980522	G	6111	57D04951	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4037 			3240NR			HJ651		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  THREE CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998061900924	19980619	00924	CE  	1998	6	19	98ZZZX2197       	1	19980515	G	2150	541968013	AIR BOX         			LEAR  	55    	55LEAR      	5170702	CE  										HEAT EXCHANGE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	1127M	6160 				120				FOUND BROKEN OUT PIECES OF AIR BOX IN TAIL COMPARTMENT.  SUSPECT CRACKED WELD SEAM AND VIBRATION,  CAUSE - FAILURE.  INS	TALLED NEW REINFORCED AIR BOX P/N 5419680-16.					2	L	7	2 	4F				A10CE
1998061900925	19980619	00925	EA  	1998	6	19	98ZZZX2198       	2	19980501	G	8530		VALVE           								LYC   	O360  	IO360A1A    	41514	EA  					NR 3 CYL EXHAUST	FAILED          	D				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			SO	16										HEAD OF VALVE SEPARATED IN-FLIGHT.  ENGINE HAD APPROXIMATELY 2,000 HOURS.											3	O			1E10
1998061900928	19980619	00928	WP  	1998	6	19	98ZZZX2199       	1	19980430	G	5751	ARC105929	BALANCE WEIGHT  			DOUG  	DC10  	DC1010      	3022110	WP  										AILERON	BURNED          	B		A	CMDY	K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			SW	07	834LA					46946				DURING THE UNPACKING PROCEDURE OF THE AILERON BALANCE WEIGHT WHICH IS MADE OF DEPLETED URANIUM MATERIAL, IN ORDER TO BE 	INSTALLED IN THE AIRCRAFT DURING C-CHECK, IT STARTED TO BURN.  THIS PART WAS PROVIDED BY THE AIRCRAFT OPERATOR IN OVERHA	ULED CONDITION.				2	L	7	3 	4F				A22WE
1998062600084	19980626	00084	WP  	1998	6	26	98ZZZX2205       	1	19980603	G	2926	4365082	DIAPHRAGM       		43442795002 	DOUG  	DC8   	DC8*        		WP  										AUX HYD POWER	DETERIORATED    	B			DM4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19					RASA60862					AUXILIARY HYDRAULIC POWER SURGE DAMPER ACCUMULATOR TANK HAD NEW DIAPHRAGM INSTALLED IN NOVEMBER, 1997.  UNIT INSTALLED I	N ACFT FOR 15 DAYS AND REMOVED FOR LEAKAGE.  FOUND DIAPHRAGM DETERIORATED AND TORN ON LIP.  SUBMITTER STATED THIS IS THE	 6TH FAILURE OF THIS TYPE PART MANUFACTURED BY KAPCO.				2	L	7	4 	4J			F	4A25
1998062600085	19980626	00085	CE  	1998	6	26	98ZZZX2206       	1	19980501	G	2750	50000061	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										RT FLAP RETRACT	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23KW	4251 				421C0106				CESSNA TWIN ENGINE AIRCRAFT HAVE EXPERIENCED A HISTORY OF FLAP CABLE FRAYING, ELECTED TO ROUTINELY REPLACE ALL FLAP CABL	ES ON A 421C HAVING 4,251 HOURS TT.  TWO CABLES WERE FOUND IN UNAIRWORTY CONDITION.  THE CABLE FRAYING WAS NOT VISIBLE U	PON INSPECTION PRIOR TO CABLE REMOVAL.				1	L	7	2 	3O			 	A7CE
1998062600086	19980626	00086	CE  	1998	6	26	98ZZZX2207       	1	19980501	G	2750	50000062	CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										LT FLAP RETRACT	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	23KW	4251 				421C0106				CESSNA TWIN ENGINE AIRCRAFT HAVE EXPERIENCED A HISTORY OF FLAP CABLE FRAYING, ELECTED TO ROUTINELY REPLACE ALL FLAP CABL	ES ON A 421C HAVING 4,251 HOURS TT.  TWO CABLES WERE FOUND IN UNAIRWORTY CONDITION.  THE CABLE FRAYING WAS NOT VISIBLE U	PON INSPECTION PRIOR TO CABLE REMOVAL.				1	L	7	2 	3O			 	A7CE
1998062600087	19980626	00087	EA  	1998	6	26	98ZZZX2208       	2	19980604	G	8530		BOSS            		ECLW12967CN 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					EXHAUST	CRACKED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	41162					318452002				PURCHASED 12 (COMPLETE) OVERHAULED CYLINDERS FOR TIO-540J2BD.  FOURTH OF TWELVE REPAIRED UNDER WORK ORDER NR 64856, S/N 	03, FOUND CRACKS ON EXHAUST STUD BOSS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
1998062600088	19980626	00088	EA  	1998	6	26	98ZZZX2209       	2	19980604	G	8530		BOSS            		ECLW12967CN 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					EXHAUST	CRACKED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	41162					318452002				RECEIVED (4) WARRANTY REPLACEMENT (COMPLETE) OVERHAULED CYLINDERS.  TWO OF FOUR, REPAIRED UNDER WORK ORDER NUMBER, 64156	, S/N 29 AND S/N 34, WERE FOUND TO HAVE A CRACKED EXHAUST SEAT BOSS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
1998062600089	19980626	00089	EA  	1998	6	26	98ZZZX2210       	2	19980604	G	8530		BOSS            		ECLW12967CN 	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					EXHAUST	CRACKED         	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	11	41162					318452002				RECEIVED (4) WARRANTY REPLACEMENT (COMPLETE) OVERHAULED CYLINDERS.  TWO OF FOUR, REPAIRED UNDER WORK ORDER NUMBER, 64156	, S/N 29 AND S/N 34, WERE FOUND TO HAVE A CRACKED EXHAUST SEAT BOSS.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
1998062600091	19980626	00091	GL  	1998	6	26	98ZZZX2211       	2	19980520	G	7230	6890502	WHEEL BLADE     			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMP STG 3	FAILED          	B			KUVR	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SO	19	262BH	9193 	2463 		C38375	3563	CAE833583			THE PILOT REPORTED COMPRESSOR STALLS DURING LIFT OFF OF THE HELICOPTER.  AFTER INSPECTION OF THE COMPRESSOR, THE NR 3 WH	EEL WAS FOUND MISSING A BLADE.  THE BLADE BROKE OFF DAMAGING SEVERAL WHEELS BEFORE EXITING OUT.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998062600092	19980626	00092		1998	6	26	98ZZZX2212       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22697					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600093	19980626	00093		1998	6	26	98ZZZX2213       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22944					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600094	19980626	00094		1998	6	26	98ZZZX2214       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22965					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600095	19980626	00095		1998	6	26	98ZZZX2215       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22967					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600096	19980626	00096		1998	6	26	98ZZZX2216       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22968					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600097	19980626	00097		1998	6	26	98ZZZX2217       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22969					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600098	19980626	00098		1998	6	26	98ZZZX2218       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        		NM  										RESCUE BEACON	MISMANUFACTURED 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22971					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600099	19980626	00099		1998	6	26	98ZZZX2219       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22974					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600100	19980626	00100		1998	6	26	98ZZZX2220       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22977					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600101	19980626	00101		1998	6	26	98ZZZX2221       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        		NM  										RESCUE BEACON	MISMANUFACTURED 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22978					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600102	19980626	00102		1998	6	26	98ZZZX2222       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22980					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600103	19980626	00103		1998	6	26	98ZZZX2223       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22981					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600104	19980626	00104		1998	6	26	98ZZZX2224       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22983					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600105	19980626	00105		1998	6	26	98ZZZX2225       	4	19980501	G	2562	B79229	BATTERY         		BE369       	BOEING	747   	747*        	       	NM  										RESCUE BEACON	MISMANUFACTURED 	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01					22984					DEFECTIVE SEARCH AND RESCUE BATTERIES NR B79229 FITTED TO SEARCH AND RESCUE BEACONS P/N BE369.  TWO SEARCH AND RESCUE BE	ACONS FAILED B.I.T.E CHECKS.  AS A RESULT, THE SUSPECT BEACONS WERE RETURNED TO B.A.A.E. FOR INVESTIGATION/REPAIR DURING	 ROUTINE INVESTIGATION.  A TECHNICIAN NOTICES THE BATTERY CONNECTOR HOLE WAS ENLARGED; THUS, CAUSING AN INTERMITTENT FAU	LT.  THE TOTAL BATTERY STOCK WAS INSPECTED (22OFF) AND 140FF WERE FOUND TO DISPLAY THIS DEFECT.			2	L	7	4 	4F			RT	A20WE
1998062600106	19980626	00106	CE  	1998	6	26	98ZZZX2226       	1	19980518	G	5610	10138402521	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  										PILOT'S	FAILED          	B		A	VY2R	O				OTHER                   				A			FLAME/FIRE                			CR	CRUISE         	1			EA	23	19GR	1779 				FL96				PILOT'S WINDSHIELD CRACKED SEVERELY INTO HUNDREDS OF PIECES IN CRUISE FLIGHT.  THIS WAS THE INNER PANE, AND PIECES WERE 	FALLING ON THE GLARE SHIELD.  LANDED OK.  REPLACED WINDSHIELD.  SUSPECT OVERHEAT CONDITION.					2	L	7	2 	4T			RT	A24CE
1998062600107	19980626	00107	EU  	1998	6	26	98ZZZX2227       	1	19980522	G	2913	350A35013004	DRIVE ASSY      			SNIAS 	350   	AS350B      	8680801	EU  										HYDRAULIC PUMP	MALFUNCTIONED   	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NE	01	821SP	2849 				2106				PILOT REPORTED LOSS OF HYDRAULIC PRESSURE.  FOUND HYDRAULIC PUMP DRIVE GEAR TEETH STRIPPED.						1	G	7	1 	3U				H9EU
1998062600109	19980626	00109	CE  	1998	6	26	98ZZZX2228       	1	19980528	G	2710	35524302	LINK            			BEECH 	36    	A36         	1151604	CE  										AILERON CONTROL	CHAFED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	01	6182X	1494 				E1971				AILERON AND RUDDER FORWARD BUNGEE SPRING INSTALLED IN SUCH A WAY THAT MADE THE AILERON CONTROL CABLE LINK P/N 35-524302 	CHAFE UP AND DOWN THE AILERON CONTROL CABLE.  BY REVERSING THE ATTACHMENT OF THE SPRING AT THE LINK END, THE LINK IS HEL	D AWAY FROM THE AILERON CABLE TO STOP THE CHAFING.  THE CHAFING APPEARED TO BE A FACTORY MADE CONDITION.				1	L	7	1 	3O			 	3A15
1998062600110	19980626	00110	SO  	1998	6	26	98ZZZX2229       	1	19980318	G	3210		SIDE BRACE      			PIPER 	PA28  	PA28R200    	7102811	SO  										RT MLG	BINDING         	B	L	A	DPOR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	07	1354T					28R7235268				DURING TEST FLIGHT, PILOT UNABLE TO GET GEAR DOWNLOCK.  FREE FALL INOPERABLE.  ON LANDING, RT MLG FOLDED.  INSPECTION FO	UND SIDE BRACE STUDS OVERTIGHTENED, THEREFORE, BINDING GEAR.					1	L	7	1 	3O				2A13
1998062600111	19980626	00111	CE  	1998	6	26	98ZZZX2230       	1	19980602	G	7820	CEM0002	MUFFLER         	WALLCOLMNY  		CESSNA	182   	182L        	2072726	CE  										ENGINE EXHAUST	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	33DM	195  			6727	18259170				THE MUFFLER WAS OBTAINED FROM THE MANUFACTURER IN JUNE, 1996.  IT WAS INSTALLED ON THE AIRCRAFT JUNE 5, 1996.  MAY 30, 1	998, AT ANNUAL INSPECTION, THIS MUFFLER WAS FOUND TO HAVE ONE OF THE INTERNAL CONES MORE THAN 50 PERCENT BURNED OUT.  TH	E CALENDAR TIME WAS JUST A FEW DAYS UNDER 2 YEARS, BUT TOTAL HOURS WERE ONLY 194.6.  THIS MUFFLER WAS SENT TO THE MANUFA	CTURER FOR EVALUATION.			1	H	7	1 	3O			NT	3A13
1998062600112	19980626	00112	SO  	1998	6	26	98ZZZX2231       	2	19980605	G	8540	632617	GEAR            			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360A      	17025	SO  					DRIVE PAD	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	37BJ		850  			33701503				VACUUM PUMP FAILED.  NEW PUMP WOULD NOT WORK.  FOUND GEAR TEETH (ALL) MISSING FROM DRIVE GEAR.						1	H	7	2 	3O	3	O		A6CE    	E1CE
1998062600113	19980626	00113	SO  	1998	6	26	98ZZZX2232       	1	19980512	G	3233	484706	O-RING          			PIPER 	PA34  	PA34220T    	7103420	SO  										NLG ACTUATOR	DAMAGED         	B	L		VJ3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	4177R	228  				3449046				TWO PREVIOUS O-RING FAILURES PROMPTED INSPECTION OF THIS ACTUATOR (SAME PART NUMBER AS RIGHT AND LEFT GEAR ACTUATORS). U	PON DISASSEMBLY FOUND INCORRECT O-RING INSTALLED ON ACTUATOR PISTON.  O-RING WAS DAMAGED, BUT HAD NOT YET FAILED.					1	L	7	2 	3O			 	A7SO
1998062600114	19980626	00114	SO  	1998	6	26	98ZZZX2233       	1	19980512	G	3233	484706	O-RING          			PIPER 	PA34  	PA34220T    	7103420	SO  										LT MLG ACTUATOR	DAMAGED         	B	L		VJ3R	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			WP	07	4177R	224  				3449046				LANDING GEAR FAILED TO RETRACT FULLY IN-FLIGHT.  ISOLATED ACTUATORS AND FOUND LEFT MAIN GEAR ACTUATOR BYPASSING (AUDIBLE	) FLUD/PRESSURE.  DISASSEMBLED ACTUATOR.  FOUND DAMAGED AND APPARENTLY INCORRECT (UNDERSIZE) O-RING.  INSTALLED ON ACTUA	TOR PISTON.  SUSPECT INCORRECT O-RING INSTALLED AT MANUFACTURER (CLEVELAND) DURING ASSEMBLY.  RECOMMEND ACTUATOR AND AIR	CRAFT MANUFACTURERS INSPECT ALL FACTORY STOCK AND SPARES FOR PROPER O-RING INSTALLATION.			1	L	7	2 	3O				A7SO
1998062600115	19980626	00115	SO  	1998	6	26	98ZZZX2234       	1	19980520	G	3213	702057508	FORK            			GULSTM	AA1   	AA1         	0630610	SO  										STOP COLLAR	FAILED          	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	01	6212L	1920 				AA10412				NOSE WHEEL BROKE OFF DURING NORMAL LANDING.  FAILURE OCCURRED AT THE BRAZED JOINT OF THE NOSE FORK STOP COLLAR.  NO EVID	ENCE OF CORRISION OR FATIGUE NOTED.  SUGGEST INSPECTION OF THIS AREA WITH 10X MAGNIFIER AT REGULAR INTERVALS.					1	L	7	1 	3O				A11EA
1998062600116	19980626	00116	CE  	1998	6	26	98ZZZX2235       	1	19980324	G	5330	3541045239	SKIN            			BEECH 	35    	S35         	1151532	CE  										FUSELAGE	WRONG PART      	D	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	64CG				7674	D7674				BEECHCRAFT SHOP MANUAL P/N 35-590096B REVISED 3-22-96, PAGES 2-6, FIG 2-5, INDEX 12.  GAUGE .032 INCH CALLS FOR A 2024-0	 SKIN-FUSELAGE WHICH INDICATES A DEAD SOFT SKIN.  AFTER A CONVERSATION WITH RAYTHEON BEECH TECH REP, HE REVIEWED THE PRI	NTS AND INDICATED THIS SKIN TO BE A 2024-T3 SKIN.  THIS COULD CAUSE SOMEONE IN THE FIELD TO INSTALL AN INCORRECT TEMPERE	D SKIN ON A FUSELAGE.  RECOMMEND THE MANUFACTURER FURNISH SUPPORTING DATA FROM PRINTS WHEN INFORMATION IS NEEDED TO PERF	ORM REPAIRS.		1	L	7	1 	3O				3A15
1998062600117	19980626	00117	EA  	1998	6	26	98ZZZX2236       	2	19980513	G	8520		CRANKSHAFT      			CESSNA	185   	A185F       	2072821	CE  	LYC   	O540  	TIO540J2BD  	41532	EA  					CYL 2-3 AREA	FAILED          	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	15	7140H		1059 			18503351	L833061A			ENGINE RPM SURGED AND FLUCTUATED.  ENGINE LOST POWER.  AIRCRAFT FLIPPED OVER DURING EMERGENCY LANDING.  MAJOR DAMAGE, NO	 INJURIES.  NO PROPELLER STRIKE.  PRE TEAR-DOWN EXAM INDICATES THE ENGINE CRANKCHAFT IS BROKEN BETWEEN NR 2 AND NR 3 CYL	INDERS.				1	H	7	1 	3O	3	O		3A24    	E14EA
1998062600118	19980626	00118	SO  	1998	6	26	98ZZZX2237       	1	19980512	G	3233	484706	O-RING          			PIPER 	PA34  	PA34220T    	7103420	SO  										GEAR ACTUATOR	WRONG PART      	B	L		VJ3R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	9299E	183  				3449043				TWO PREVIOUS O-RING FAILURES AND ONE O-RING INSPECTION REVEALING O-RING DAMAGE ON ANOTHER AIRCRAFT PROMPTED INSPECTION O	F ALL ACTUATORS ON THIS AIRCRAFT.  (FAILURE RESULTS IN INCOMPLETE GEAR RETRACTION).  UPON DISASSEMBLY, FOUND INCORRECT O	-RINGS INSTALLED ON ALL 3 ACTUATOR PISTONS.  O-RINGS WERE DAMAGED (ROLLED AND SCUFFED), BUT HAD NOT YET FAILED.				1	L	7	2 	3O			 	A7SO
1998062600121	19980626	00121	SO  	1998	6	26	98ZZZX2238       	1	19980519	G	3610	18368032	HEAT EXCHANGER  			GULSTM	G1159 	G1159       	3953505	SO  										LT AFT PYLON	RUPTURED        	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	187PH		295  		56513	218				THE PART IN QUESTION IS A BLEED AIR HEAT EXCHANGER P/N 183680-3-2 USED ON A G-II AIRCRAFT.  THE ORIGNAL PART WAS REPLACE	D DUE TO A RUPTURE OF THE LOW PRESSURE PASSAGE AFTER 18 YEARS AND 6,000 HOURS OF OPERATION.  THE EXCHANGE UNIT IN QUESIT	ON IS NOW RUPTURED WITH A TOTAL TIME OF 295 HOURS AND ONE YEAR AND 55 DAYS IN SERVICE.  THE AIRCRAFT BLEED AIR SYSTEM IS	 IN NOMINAL OPERATING ORDER AND HAS IN NO WAY OVERSTRESSED THE UNIT.  SUBMITTER SUGGESTED THE FAILURE WAS DUE TO POOR WO	RKMANSHIP.		2	L	7	2 	4F			RT	A12EA
1998062600122	19980626	00122	CE  	1998	6	26	98ZZZX2239       	1	19980427	G	3246	40172	WHEEL           			BEECH 	200   	200BEECH    	1152920	CE  										WHEEL HALF	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	5230 			24872	BB832				WHEEL HALF IS CRACKED AT THE INBOARD TANGENT OF THE BEAD RADIUS.  THE CRACK IS APROXIMTELY 1.25 INCHES LONG AND IS NOT V	ISIBLE TO THE NAKED EYE.					1	L	7	2 	4T				A24CE
1998062600123	19980626	00123	CE  	1998	6	26	98ZZZX2240       	1	19980518	G	2612	24409315	ELEMENT         			LEAR  	60    	60LEAR      	5170707	CE  										RT ENGINE FIRE	FAILED          	B		A	IMJR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	25	219FX	3606 				007				THE RIGHT ENGINE FIRE WARNING WOULD NOT TEST.  TROUBLESHOT TO OPEN HOT SECTION LOOP.  DURING DISASSEMBLY FOR REPLACEMENT	, DISCOVERED THE LOOP WAS MIS-POSITIONED IN THE RETAINING CLAMP CAUSING THE ELEMENT TO BREAK.  THIS FACILITY ALSO HAS RE	PLACED THE SAME UNIT ON ANOTHER LEARJET 60 DUE TO THE CLAMP OPENING AND CHAFING THE SAME LOOP.  SUBMITTER RECOMMENDED TH	IS AREA BE INSPECTED AT EACH ACCESS AND CAUTION BE USED ON INSTALLATION.			2	L	7	2 	4F			RT	A10CE
1998062600289	19980626	00289	GL  	1998	6	26	98ZZZX2241       	2	19980527	G	7250	369H7301503	ROD             			HUGHES	500N  	500N        	3027374	SW  	ALLSN 	250C  	250C20R2    		GL  					GAS PRODUCER	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524FB	6037 				LN004				INSPECTION FOUND GAS PRODUCER INTERCONNECT TUBE WITH CRACKS, 2 EACH, 180 DEGREES APART AT SHORT END.						1	G	7	1 	3U	3	U	NC	H3WE    	E4CE
1998062600291	19980626	00291	NE  	1998	6	26	98ZZZX2242       	2	19980521	G	7250	798808	AIRSEAL         								PWA   	JT8   	JT8*        	52044	NE  					LP TURBINE	CRACKED         	B			M9QR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										WHILE RE-EVALUATING THE DATA FOR TI-JT8D-117 ON WELDING OF THE KNIFE EDGE AIRSEALS ON 2ND, 3RD, AND 4TH STAGE ROTATING A	IRSEALS, CRACKING WAS DETECTED IN THE PEDESTAL RADIUS.  THE PART WAS DAMAGED AS THE RESULT OF THE LASER WELDING PROCESS.	  REF:  THE INVESTIGATION IS CONTINUING.  OPERATOR CONTROL NR M9QR564N AND 98ZZZX2243.  (X)									4	F			E2EA
1998062600292	19980626	00292	NE  	1998	6	26	98ZZZX2243       	2	19980521	G	7250	759059	AIRSEAL         								PWA   	JT8   	JT8*        	52044	NE  					LP TURBINE	CRACKED         	B			M9QR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										WHILE RE-EVALUATING THE DATA FOR TI-JT8D-117 ON WELDING OF THE KNIFE EDGE AIRSEALS ON 2ND, 3RD, AND 4TH STAGE ROTATING A	IRSEALS, CRACKING WAS DETECTED IN THE PEDESTAL RADIUS.  THE PART WAS DAMAGED AS THE RESULT OF THE LASER WELDING PROCESS.	  THE INVESTIGATION IS CONTINUING.  REF:  OPERATOR CONTROL NR M9QR564N AND 98ZZZX2242.									4	F			E2EA
1998062600293	19980626	00293	NM  	1998	6	26	98ZZZX2244       	1	19980511	G	3246		WHEEL           			BOEING	747   	747273C     	1384896	NM  										MLG NR 9	DEFLATED        	B			GK4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	470EV					20653				WHILE PARKED AT GATE, NR 9 WHEEL LOST PRESSURE SUDDENLY.  SUSPECT CAUSE - FUSIBLE PLUG FAILED AND BRAKE OVERHEATED.						2	L	7	4 	4F				A20WE
1998062600295	19980626	00295	EU  	1998	6	26	98ZZZX2246       	1	19980429	G	3411	S257FN3137A	DRAIN           			BRAERO	DH125 	HS125700A   	4230170	EU  										PITOT STATIC	DETERIORATED    	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	700BW	5219 				NA0288				FOUND PITOT LEAK ON COPILOT SIDE AND STATIC SYSTEM OPEN.  TROUBLESHOOTING FOUND PITOT AND STATIC DRAINS WERE SOURCE OF L	EAKS DUE TO DETERIORATION OF DRAIN CORES.					2	L	7	2 	4F				A3EU
1998062600296	19980626	00296	NM  	1998	6	26	98ZZZX2247       	1	19980508	G	2915	V25W712077501	VALVE           			ISRAEL	1125  	1125        		NM  										HYD RESERVOIR	FAILED          	B			QRRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	705MA	1201 				011				VALVE WAS STUCK IN OPEN POSITION.  THIS WOULD NOT ALLOW A HEAD PRESSURE ONTO THE RESERVOIR.  THE RESULT WAS A CAVITATING	 PUMP.  REPLACED VALVE AND DID A TEST FLIGHT.  ALL SYSTEMS WORKED NORMALLY.  PRESSURE HELD IN RESERVOIR OVERNIGHT.					2	L	7	2 	4F			RT	A16NM
1998062600297	19980626	00297	EU  	1998	6	26	98ZZZX2248       	1	19980521	G	2910	F10A755401	LINE            			AMD   	FALC10	FALCON10    	2730101	EU  										YAW SERVO	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	23	77SF	6639 				141				AFTER A NORMAL FLIGHT, HYDRAULIC FLUID WAS NOTICED RUNNING DOWN THE VERTICAL STABILIZER EMANATING FROM THE AFT ELEVATOR 	AREA.  INVESTIGATION REVEALED THAT ONE OF THE FLEX HYDRAULIC HOSES FOR THE RUDDER/YAW SERVO WAS MAKING CONTACT WITH AND 	RUBBED THROUGH THE RIGID HYDRAULIC LINE (FOR THE SERVO) CAUSING THE LEAK.  NO DAMAGE WAS EVIDENT TO THE FLEX HOSE.  REPL	ACED THE LINE WITH A NEW ASSEMBLY.  THIS AREA IS NOT READILY ACCESSIBLE AND THE DAMAGE WAS DIFFICULT TO LOCATE EVEN WITH	 A MIRROR.  CLOSE INSPECTION OF THIS AREA SHOULD BE ACCOMPLISHED ANYTIME ACCESS IS GAINED TO THE RUDDER SERVO, AT WHICH 	TIME THE HOSE/LINE CLEARANCE SHOULD BE CHECKED THROUGH FULL RANGE OF RUDDER TRAVEL.	2	L	7	2 	4F				A33EU
1998062600298	19980626	00298	NM  	1998	6	26	98ZZZX2249       	1	19980511	G	3240		BRAKE           			BOEING	747   	747132      	1384882	NM  										NR 11-15 WHEEL	DAMAGED         	B			GK4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	857FT					20246				WHILE PARKED ON GATE, NR 9, NR 11, AND NR 15, MAIN WHEELS COLLAPSED DUE TO BRAKE OVERHEAT.  ON WHEEL CHANGE, NR 11 AND N	R 15 BRAKE UNITS WERE FOUND DAMAGED AND WERE REPLACED.					2	L	7	4 	4F				A20WE
1998062600299	19980626	00299	WP  	1998	6	26	98ZZZX2250       	1	19980513	G	3250	59561015501	BYPASS VALVE    			DOUG  	DC9   	DC932       	3022066	WP  										NLG AFT STEERING	MALFUNCTIONED   	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	620NW	17527	1    		31078	47533				AFTER LANDING, UNABLE TO GET MORE THAN APPROXIMATELY 17 DEGREES OF RIGHT NOSE WHEEL STEERING WITH CONTROL WHEEL.  REMOVE	D AND REPLACED BYPASS VALVE.  OPS CHECK GOOD.					2	L	7	2 	4F				A6WE
1998062600300	19980626	00300	WP  	1998	6	26	98ZZZX2251       	1	19980513	G	3250	59561015501	BYPASS VALVE    			DOUG  	DC9   	DC932       	3022066	WP  										NLG FWD STEERING	MALFUNCTIONED   	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	620NW	49385	1    		00644	47533				AFTER LANDING, UNABLE TO GET MORE THAN APPROXIMATELY 17 DEGREES OF RIGHT NOSE WHEEL STEERING WITH CONTROL WHEEL.  REMOVE	D AND REPLACED BYPASS VALVE.  OPS CHECK GOOD.					2	L	7	2 	4F			 	A6WE
1998062600301	19980626	00301	CE  	1998	6	26	98ZZZX2252       	1	19980518	G	5610	5044001442	RETAINER        			BEECH 	200   	200BEECH    	1152920	CE  										WINDOW	MISDRILLED      	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09										THIS WINDOW RETAINER WAS PRE-DRILLED WITH PILOT HOLES.  THE HOLES ON THE RETAINER DID NOT MATCH UP WITH THE EXITING HOLE	S ON THE AIR FRAME.  THERE IS NO WAY TO PROPERLY DRILL THE NEW FRAME AND STILL HAVE CLEAN ROUND HOLES WITH PROPER EDGE D	ISTANCE.				1	L	7	2 	4T			 	A24CE
1998062600302	19980626	00302	SO  	1998	6	26	98ZZZX2253       	1	19980317	G	3231	1159SCH23133	CONTROL VALVE   			GULSTM	G1159 	GIV         	3980115	SO  										LT MLG DOOR	MISOVERHAULED   	H		A		O				OTHER                   				W	K		INADEQUATE Q C            	FLUID LOSS                		NR	NOT REPORTED   	1			EA	25	462QS				1208	1262				PILOT REPORTED WHEN GEAR EXTENDED, ALL 3 GEARS WENT DOWN AND LOCKED THEN LOST ALL COMBINED HYDRAULIC SYSTEM FLUID.  MAIN	TENANCE FOUND LMG DOOR CONTROL VALVE MISSING LEVER AND INTERNAL PARTS, ONLY HOUSING LEFT AND WHEEL WELL.  VALVE HOUSING 	SENT BACK TO MANUFACTURER FOR ANALYSIS.  INSTALLED NEW VALVE OF SAME P/N.  SERVICED COMBINED RESERVOIR AND PERFORMED LAN	DING GEAR NORMAL AND EMERGENCY FUNCTIONAL TESTS, NO DEFECTS NOTED.  NEW VALVE LEAK CHECK GOOD.  ALL WORK PERFORMED IAW G	IV MM.  COMBINED FLUID LOSS DUE TO VALVE FAILURE.		2	L	7	2 	4F			RT	A12EA
1998062600866	19980626	00866	NE  	1998	6	26	98ZZZX2255       	2	19980424	G	7230	407402C	BLADE           		670402      	SKRSKY	S64   	S64F        		NE  	PWA   	JFTD12	JFTD12A5A   	52047	NE  					2ND STAGE	FRACTURED       	B			JYDR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			EX	EXTERNAL LOAD  	1			NM	09	159AC	349  			H64871	64084	677817			ON 4-24-98, AIRCRAFT WAS ON A FIRE FIGHTING MISSION.  DURING CLIMB-OUT, A LOUD 'BANG' SOUND OCCURRED, FOLLOWED BY A LEFT	 YAW.  THE LOAD OF WATER WAS JETTISONED AND PILOTS PUSHED MAXIMUM BEEP ON BOTH ENGINES.  THE NR 1 ENG WAS CARRYING THE L	OAD.  THE NR 2 ENG READ 70 PERCENT N1, 485 DEGREES CELSIUS T5, 6-700 POUND FUEL FLOW, AND ZERO TORQUE.  ENG WAS NOT PROD	UCING ANY POWER SO IT WAS AN IN-FLIGHT FAILURE.  ACFT LANDED IN FIRST AVAILABLE CLEAR AREA AND SHUT DOWN.  WHEN MOTORING	 NR 2 ENG, A VIBRATION WAS FELT IN THE AIRFRAME.  THE ENG WAS RETURNED TO ERICKSON AIR-CRANE WHERE ONE 2ND STAGE BLADE W	AS FOUND FRACTURED JUST ABOVE THE ROOT PLATFORM.  IT WAS SENT TO PWA,  FOR FAILURE INVESTIGATION AND REPORT ON CAUSE.	2	G	7	2 	4U	4	U		H6EA    	E15EA
1998071500006	19980715	00006	NE  	1998	7	15	98ZZZX2259       	2	19980605	G	7323	D210507	GOVERNOR        	WOODWARD    		CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9762B	5992 			2173315U	208B0109				DURING ENGINE CHANGE, OVERSPEED GOVERNOR WAS TRANSFERRED FROM ENGINE DUE OVERHAUL TO LOANER ENGINE.  AFTER INSTALL ON LO	ANER ENGINE, PR0P SHAFT WOULD NOT ROTATE.  UPON REMOVAL OF OVERSPEED GOVERNOR, SMALL BALL BEARING CAME OUT OF GOVERNOR O	IL PORT.  FLUSHED RGB AND FOUND FIVE BALL BEARINGS, FOUND TWO MORE INSIDE GOVERNOR AFTER DISASSEMBLY OF GOVERNOR.  FOUND	 BEARING CAGE AND OUTER RACE DAMAGED.  ALL SEVEN BEARINGS WERE FOUND.  REPLACED OVERSPEED GOVERNOR WITH OVERHAULED UNIT.			1	H	7	1 	3T	3	T		A37CE   	E4EA
1998070300493	19980703	00493	GL  	1998	7	3	98ZZZX2260       	2	19980522	G	7261	6876689	OIL PUMP        								ALLSN 	250B  	250B17      	03012	GL  					ENGINE	WORN            	B		A	YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17		11   					CAE881525			ENGINE WAS RECEIVED TO REPAIR FOR LOW OIL PRESSURE AND METAL IN OIL.  UPON DISASSEMBLY, FOUND THE IDLER GEAR IN THE PRES	SURE SIDE OF THE PUMP HAD WORN AWAY APPROXIMATELY .3750 INCH OF THE PRESSURE PUMP BODY AND THE IDLER GEAR SHAFT CAUSING 	STEADILY DECREASING OIL PRESSURE AND METAL IN OIL.									3	T			E10CE
1998070300494	19980703	00494	CE  	1998	7	3	98ZZZX2261       	1	19980604	G	7714	800110011	BEARING         		EM8001      	BEECH 	1900  	1900        	1154160	CE  										TACHOMETER/GEN	FAILED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01		56   			19254					TACHOMETER/GENERATOR WAS OVERHAULED 55.9 HOURS AGO.  UNIT STOPPED WORKING.  ON REMOVAL, FOUND DRIVE SHAFT SNAPPED IN TWO	. ON DI SASSEMBLY, FOUND BOTH BEARINGS HAD FAILED.  THESE BEARINGS HAVE NO IDENTIFYING MARKINGS ON THEM, ONLY ON THE SHI	PPING TUBES IS THERE ANY INFORMATION.  SUBMITTER STATED HAD AN IDENTICAL FAILURE ON ANOTHER AIRCRAFT THE SAME DAY.				2	L	7	2 	4T			RT	A24CE
1998070300495	19980703	00495	NE  	1998	7	3	98ZZZX2262       	2	19980513	G	7250	798157001	RING            								PWA   	JT8   	JT8D217A    	52053	NE  					N1 TURBINE	FAILED          	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05							708416			ENGINE REMOVED FROM SERVICE FOR 'LPT DAMAGE'.  THE SECOND STAGE VANE INNER SUPPORT LOCATING PIN BROKE LOOSE AND CAUSED I	MPACT DAMAGE TO THE T2 AND T3 BLADES, AND COMPLETE FAILURE OF ALL T4 BLADES.										4	F			E9NE
1998070300496	19980703	00496	NE  	1998	7	3	98ZZZX2263       	3	19980528	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8704 	4085 		2126NR			HJ240		INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FOUR CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998070300497	19980703	00497	CE  	1998	7	3	98ZZZX2264       	1	19980604	G	5740	BCN0018	BOLT            			BEECH 	200   	200BEECH    	1152920	CE  										WING LT AFT	CRACKED         	B		A	BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	200BE	2475 				BB832				DYE CHECK FOUND A CRACK INDICATION AT THE BOLT HEAD RADIUS.  BOLT WAS INCLUDED IN KIT P/N 101-4026-3S, S/N 7673.						1	L	7	2 	4T				A24CE
1998070300498	19980703	00498	WP  	1998	7	3	98ZZZX2265       	1	19980609	G	3230	391446411	LINK            			DOUG  	DC9   	DC941       	302207N	WP  										NLG UPLOCK	MALFUNCTIONED   	B				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			SO	09	760NW					47288				UPON INITIAL ROLLOUT, (NLG) UPLOCK CHECK FAILED CAUSING (NLG) UNSAFE LIGHT TO ILLUMINATE.  AIRCRAFT RETURNED TO BASE.  G	ROUND FUNCTIONAL TEST ACCOMPLISHED.  ALL SYSTEMS OPERATED NORMALLY.  ON SECOND FLIGHT ATTEMPT, NLG LIGHT ILLUMINATED AGA	IN.  GROUND CREW REMOVED .00025 INCH SHIM FROM UPLOCK ASSY OVER CENTER LINK IAW MM 32-21-03.  ALL SYSTEMS FUNCTIONAL CHE	CK NORMAL.  AIRCRAFT DEPARTED WITH NO FURTHER PROBLEMS.  THE ORIGINAL UPLOCK DIMENSIONS WERE WITHIN MANUFACTURER AND OPE	RATORS LIMITS.  NO FOLLOW-UP ACTION.		2	L	7	2 	4F				A6WE
1998070300499	19980703	00499	EU  	1998	7	3	98ZZZX2266       	1	19980510	G	2810		TANK            			BRAERO	DH125 	HS125700A   	4230170	EU  										DORSAL	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	23	943CE					NA0300				WHILE BENCH SERVICING ON AVIONICS STANDBY BATTERY (NR 4), (CA 125 SINTERED PLATE N1 CAD BATTERY MFG P/N 27518-001), MARA	THON POWER TECHNOLOGIES, WACO, TX).  TECHNICIAN FOUND APPROXIMATELY 1-1/2 OUNCES OF JET A FUEL INSIDE THE BATTERY CASE. 	 NEXT, THE CURRENT BATTERY INSTALLED IN HS.125-700A N943CE WAS CHECKED AND FOUND TO HAVE A SIGNIFICANT QUANTITY OF FUEL.	  THE DORSAL TANK WAS FOUND LEAKING AND THE FEED AND VENT PLUMBING SEAL WAS FOUND LEAKING INTO THE AFT EQUIPMENT BAY.  F	AILURE OF THE FEED AND VENT PLUMBING SEAL AND A BATTERY COVER THAT IS MADE WITH ONLY TWO SIDES ALLOWED FUEL TO ENTER THI	S EXPLOSIVE IGNITION SOURCE.	2	L	7	2 	4F				A3EU
1998070300500	19980703	00500	EU  	1998	7	3	98ZZZX2267       	1	19980510	G	2432	27518001	BATTERY         	MARATHON    		BRAERO	DH125 	HS125700A   	4230170	EU  										STANDBY POWER	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	943CE					NA0300				WHILE BENCH SERVICING ON AVIONICS STANDBY BATTERY (NR 4), (CA 125 SINTERED PLATE N1 CAD BATTERY MFG P/N 27518-001), MARA	THON POWER TECHNOLOGIES, WACO, TX).  TECHNICIAN FOUND APPROXIMATELY 1-1/2 OUNCES OF JET A FUEL INSIDE THE BATTERY CASE. 	 NEXT, THE CURRENT BATTERY INSTALLED IN HS.125-700A N943CE WAS CHECKED AND FOUND TO HAVE A SIGNIFICANT QUANTITY OF FUEL.	  THE DORSAL TANK WAS FOUND LEAKING AND THE FEED AND VENT PLUMBING SEAL WAS FOUND LEAKING INTO THE AFT EQUIPMENT BAY.  F	AILURE OF THE FEED AND VENT PLUMBING SEAL AND A BATTERY COVER THAT IS MADE WITH ONLY TWO SIDES ALLOWED FUEL TO ENTER THI	S EXPLOSIVE IGNITION SOURCE.	2	L	7	2 	4F				A3EU
1998070300501	19980703	00501	WP  	1998	7	3	98ZZZX2268       	1	19980505	G	5730	9919402505	TRAP PANEL      			DOUG  	DC9   	DC914       	3022034	WP  										LT WING	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	8913E	75144				45830				WHEN CHANGING LT MAIN  LANDING GEAR FIXED STRUT, FOUND MOUNTING FLANGE (SPOT FACE AREA) CORRODED ON TRAPEZODIAL PANEL. R	EMOVED CORROSION AND FOUND TO BE BELOW MINIMAL LIMITS.  REMOVED AND REPLACED LT TRAPEZODIAL PANEL.					2	L	7	2 	4F				A6WE
1998070300502	19980703	00502	GL  	1998	7	3	98ZZZX2269       	1	19980524	G	7810		EXHAUST MANIFOLD			AMTR  	WAG   	WAGARO      	05655YX	GL  										ENGINE	FAILED          	H	P			A				UNSCHED LANDING         				R	B		PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			NM	07										LEFT EXHAUST MANIFOLD BROKE LEAVING POWER LOSS AND SMOKE IN COCKPIT.  PILOT ASSUMED ENGINE FIRE.  PILOT TURNED OFF ELECT	RICAL, THEN FUEL WHILE MAKING GRADUAL TURN TO NORTH.  PILOT SELECTED AN UNCUT WHEAT FIELD TO LAND WITH NO POWER.  THREE-	POINT STALL LANDING MADE.  GREEN WHEAT GRASS FOULED LANDING GEAR AND PLANE GENTLY OVERTURNED IN TALL WHEAT GRASS.  RECOM	MEND REPLACEMENT OF EXHAUST WITH STAINLESS STEEL CUSTOM PART WHICH CAME WITH ENGINE.  NO SERIAL NUMBERS FOUND OR MANUFAC	TURER ON THIS EXHAUST OR OTHER UNDAMAGED ONE.		1	H	7	1 	3O			NC	EXPA1H71
1998070300503	19980703	00503	GL  	1998	7	3	98ZZZX2270       	3	19980529	G	6114	D4239C22	HUB             													MCAULY	2A34C	2A34C*      	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			382  		738202			735202		PROPELLER RECEIVED FOR OVERHAUL.  DURING HUB INSPECTION, HUB DISCOVERED CRACKED NR 2 BLADE SOCKET, 2 THREADS IN, 6 O'CLO	CK POSITION, TWO INCHES LONG.  CRACK DID NOT GO THROUGH TO OUTSIDE OF HUB.  CRACK DISCOVERED USING 10X POWER MICROSCOPE.															5	C	P3EA
1998070300504	19980703	00504	EU  	1998	7	3	98ZZZX2271       	2	19980525	G	8520		CONNECTING ROD  			DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					NR 2	SEIZED          	D				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CR	CRUISE         	1			NM	07	10UV	2325 	1288 			10037	4076240			ENGINE SEIZED IN-FLIGHT.  FOUND THAT THE NR 2 ROD SEIZED AND BROKE AT THE CRANK JOURNAL AND THE PISTON BROKE AT THE PIN 	HOLE, ALSO, PISTON SEIZED IN CYLINDER.  FOUND TWO PIECES OF PUSHROD O-RINGS IN OIL SCAVENGE LINE FITTING AT BOTTOM OF CA	SE.  DURING MAINTENANCE, O-RINGS WERE NOT REMOVED FROM LIFTER BORE WHEN NEW ONES WERE INSTALLED FORCING OLD O-RINGS INTO	 ENGINE CASE.			1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
1998070300505	19980703	00505	NE  	1998	7	3	98ZZZX2272       	3	19980611	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		15288	4554 		2313NR			HJ1A		INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FIVE CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998070300506	19980703	00506	EA  	1998	7	3	98ZZZX2273       	2	19980602	G	8520		CAMSHAFT LOBE   								LYC   	O720  	IO720B1A    	41546	EA  					NR 2 CYL EXH	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99			1111 				L81854			DURING 100-HOUR INSPECTION AND INSPECTION FOR REPORTED SLIGHT APPARENT POWER LOSS, FOUND NR 2 CYLINDER EXHAUST VALVE LIF	TER BODY AND CAMSHAFT LOBE FAILED PREMATURELY.  CAMSHAFT AND LIFTERS HAD BEEN RECONDITIONED AND REGROUND AT MAJOR OVERHA	UL INSTEAD OF NEW.  NO REPORTED OPERATING DIFFICULTIES.  BALANCE OF ENGINE CLEAN INTERNALLY.  ENGINE ALWAYS ON SHELL 20W	50 AD OIL.								3	O			1E15
1998070300507	19980703	00507	CE  	1998	7	3	98ZZZX2274       	1	19980519	G	2842	533311	FLOAT           			CESSNA	172   	172R        	2072401	CE  										FUEL QUANTITY	MISINSTALLED    	B			DYCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07	375ES	260  			0458	17250057				TROUBLESHOT ERRATIC RIGHT FUEL QUANTITY GAUGE TO DEFECTIVE FLOAT IN RIGHT TANK.  UPON REMOVAL OF FLOAT, FOUND PART NUMBE	R OF LEFT FLOAT.  INSPECTED LEFT FLOAT AND FOUND PART NUMBER OF RIGHT FLOAT.  FUEL FLOATS HAD BEEN INSTALLED IN REVERSE 	POSITIONS FROM FACTORY.  AIRCRAFT TOTAL TIME, 260.2 HOURS.				1	H	7	1 	3O			NT	3A12
1998070300508	19980703	00508	EA  	1998	7	3	98ZZZX2275       	2	19980420	G	8520	LW10646	CONNECT ROD     			BEECH 	60    	B60         	1153605	CE  	LYC   	O541  	TIO541E1C4  	41536	EA  					NR 3 CYLINDER	FAILED          	E				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			SO	13	66HW	2951 	734  			P559	L111959			NR 3 CYLINDER ROD BROKE IN CRUISE FLIGHT.						1	L	7	2 	3O	3	O		A12CE   	E10EA
1998070300509	19980703	00509	SO  	1998	7	3	98ZZZX2276       	1	19980206	G	2750	8290503	BELLCRANK       			PIPER 	PA46  	PA46350P    		SO  										RT FLAP	CRACK           	B		A	ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	1818W	701  				4622151				WHILE PERFORMING ANNUAL INSPECTION, THE FLAP BELLCRANK IN THE RT WING WAS FOUND CRACKED IN HALF CAUSING A 'SPLIT FLAP' C	ONDITION WHEN THE FLAPS WERE LOWERED.  GONE UNCORRECTED, LOSS OF AIRCRAFT CONTROL COULD RESULT.  RECOMMEND CLOSE ATTENTI	ON BE PAID TO THIS AREA BY MAINTENANCE AND OPERATORS.				1	L	7	1 	3O			RT	A25SO
1998070300510	19980703	00510	CE  	1998	7	3	98ZZZX2277       	1	19980408	G	2430	S159660L	CIRCUIT BREAKER 			CESSNA	210   	210M        	2073450	CE  										ALTERNATOR OUT	FAILED          	H	L			O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NE	05	1943M	2150 				21061968				WHILE EN ROUTE, LOST COMPLETE ELECTRICAL POWER IN TOTAL IFR CONDITIONS WITH ZERO VISIBILITY.  PWM MAINTENANCE COULD NOT 	DUPLICATE THE PROBLEM.  AIRCRAFT DEPARTED AND THE SAME CONDITION OCCURRED AGAIN.  THE CIRCUIT BREAKER WAS REPLACED AND T	HE CONDITION WAS NEVER DUPLICATED AGAIN.  FOUND ALTERNATOR OUTPUT CIRCUIT BREAKER KEPT TRIPPING AT A LOAD WELL BELOW ITS	 RATED VALUE.  UNSURE HOW THIS COULD BE PERIODICALLY CHECKED IN THE FIELD.			1	H	7	1 	3O				3A21
1998070300511	19980703	00511	SO  	1998	7	3	98ZZZX2278       	1	19980506	G	5712	7847506	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WS 49-50	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	21500					447995055				GEAR RETRACT BRACKET ASSEMBLIES 95643-08 AND 95643-09 LOCATED AT SAME STATION.  GEAR CYCLING STRESSING RIBS AND RIBS ARE	 FAILING.  CONCERNED ABOUT MAIN SPAR CRACKING AT SAME LOCATION.					1	L	7	2 	3O				A19S0
1998070300512	19980703	00512	SO  	1998	7	3	98ZZZX2279       	1	19980506	G	5712	7847507	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WS 49-50	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	21500					447995055				GEAR RETRACT BRACKET ASSEMBLIES 95643-08 AND 95643-09 LOCATED AT SAME STATION.  GEAR CYCLING STRESSING RIBS AND RIBS ARE	 FAILING.  CONCERNED ABOUT MAIN SPAR CRACKING AT SAME LOCATION.					1	L	7	2 	3O				A19S0
1998070300513	19980703	00513	SO  	1998	7	3	98ZZZX2280       	1	19980506	G	5712	9502800	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WS 49-50	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	21500					447995055				GEAR RETRACT BRACKET ASSEMBLIES 95643-08 AND 95643-09 LOCATED AT SAME STATION.  GEAR CYCLING STRESSING RIBS AND RIBS ARE	 FAILING.  CONCERNED ABOUT MAIN SPAR CRACKING AT SAME LOCATION.					1	L	7	2 	3O				A19S0
1998070300514	19980703	00514	SO  	1998	7	3	98ZZZX2281       	1	19980506	G	5712	9502801	RIB             			PIPER 	PA44  	PA44180     	7104402	SO  										WS 49-50	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	21500					447995055				GEAR RETRACT BRACKET ASSEMBLIES 95643-08 AND 95643-09 LOCATED AT SAME STATION.  GEAR CYCLING STRESSING RIBS AND RIBS ARE	 FAILING.  CONCERNED ABOUT MAIN SPAR CRACKING AT SAME LOCATION.					1	L	7	2 	3O				A19S0
1998070300515	19980703	00515	CE  	1998	7	3	98ZZZX2282       	1	19980513	G	5510	07321014	REINFORCEMENT   			CESSNA	185   	A185F       	2072821	CE  										LT/RT STAB HINGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	27532					18503688				AT ANNUAL INSPECTION, FOUND LEFT AND RIGHT STABILIZER HINGE REINFORCEMENTS CRACKED.  LEFT FITTING CRACKED FROM AFT EDGE 	TO BOLT HOLE AT INBOARD LOWER TAB.  RIGHT FITTING HAD SIMILAR CRACKS IN BOTH LOWER TABS.  NOT SO OBVIOUS WAS A CRACK ALO	NG 90 PERCENT OF THE LOWER FLANGE BEND RADIUS ON THE RIGHT FITTING.  SUGGEST CAREFUL INSPECTION OF THIS AREA DURING ROUT	INE INSPECTIONS ESPECIALLY HIGHER TIME AIRCRAFT.  PART TIS:  5,272 HOURS.			1	H	7	1 	3O				3A24
1998070300516	19980703	00516	CE  	1998	7	3	98ZZZX2283       	1	19980604	G	2823	05131205	SELECTOR        			CESSNA	170   	170B        	2072306	CE  										FUEL SYSTEM	LEAKING         	B			BXSR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	09	2993D					26936				DURING THE ANNUAL INSPECTION, FOUND THE FUEL SELECTOR LEAKING.  THE FUEL WAS LEAVING BEHIND A RED DYE.  THIS AIRCRAFT IS	 APPROVED FOR AUTOFUEL PER AN STC.					1	H	7	1 	3O				A799
1998070300517	19980703	00517	GL  	1998	7	3	98ZZZX2284       	1	19980524	G	3220	39008000	SHOCK CORD      			AMTR  	KITFOX	KITFOX      	05613LZ	GL  										NLG	FAILED          	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	11	38JK					751				THE KIT FOX ON LANDING SUDDENLY LOST DIRECTIONAL CONTROL.  AFTER AIRCRAFT CAME TO REST WITHOUT INJURY TO THE OCCUPANTS, 	BUT WITH SUBSTANTIAL DAMAGE TO AIRCRAFT, IT WAS DISCOVERED THE RIGHT SHOCK CORD (BUNGEE) HAD SEPARATED.  THIS PART HAD 1	25 HOURS ON IT.  ON CONTACTING SKY STAR, THE MANUFACTURER, FOUND THEY RECOMMEND REPLACEMENT OF THE PART EVERY ANNUAL.  N	OTE:  THIS RECOMMENDATION IS NOT INCLUDED IN THE ANNUAL CHECKLIST FROM SKY STAR.			1	H	7	1 	3I			NC	EXPA1H71
1998070300518	19980703	00518	SO  	1998	7	3	98ZZZX2285       	1	19980602	G	7332	8739102	GAUGE           			PIPER 	PA28  	PA28161     	7102803	SO  										FUEL PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	38952	5154 				287716297				GAUGE NORMAL AT START OF FLIGHT.  WENT TO ZERO PRESSURE FOR ABOUT 2 HOURS AND RETURNED TO NORMAL.  REMOVED GAUGE, FOUND 	SMALL HOLE IIN BELLOWS.  REPLACED GAUGE, TEST NORMAL.					1	L	7	1 	3O				2A13
1998070300519	19980703	00519	CE  	1998	7	3	98ZZZX2286       	1	19980507	G	6120	565580031	CONTROL CABLE   			CESSNA	182   	182S        	2072701	CE  										PROP CONTROL	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	403ES	108  				18250050				WHEN REMOVING PROPELLER CONTROL CABLE (OWNER/OPERATOR NOTED THAT CONTROL MOVED DURING OPERATION BECAUSE OF NO FRICTION D	EVICE).  FOUND CABLE ROUTED AGAINST AILERON INTERCONNECT CABLE ASSY JUST AFT OF FIREWALL.  INSTALLED NEW CABLE AND ADJUS	TED ROUTING SO AS NOT TO INTERFERE WITH CONTROL CABLE (AILERON).				1	H	7	1 	3O			NT	3A13
1998070300520	19980703	00520	CE  	1998	7	3	98ZZZX2287       	1	19980605	G	2510	MC19424	SEAT LOCK       			CESSNA	172   	172R        	2072401	CE  										LT SEAT	FAILED          	B			N3XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	404ER	583  				17280282				DURING A PHASE INSPECTION, THE MECHANIC FOUND THE LEFT SEAT LOCK CONTROL ASSY BROKEN. THIS IS THE THIRD CABLE BROKEN IN 	A FLEET OF FIFTEEN.					1	H	7	1 	3O			NT	3A12
1998070300521	19980703	00521	EA  	1998	7	3	98ZZZX2288       	2	19980605	G	7414	M333	IMPULSE COUPLING	SLICK       		PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					MAG PAWL PIN	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	40698					327440056				APPROXIMATE TIME ON COMPONENT 450 HOURS. NOTED ONE PAWL WORN MORE THAN THE OTHER, .130 INCH AS COMPARED TO .100 INCH.  N	OTE, .150 INCH MAXIMUM ALLOWED BY SLICK.  ALSO, NOTED THAT ONE PAWL PIN SEEMED SOFTER THAN THE OTHER BY USING  FILE AS D	ESCRIBED IN SLICK SB SB 1-80A.  SUBMITTER THOUGHT THIS MAY BE OF FURTHER INTEREST.				1	L	7	1 	3O	3	O		A3SO    	1E4
1998070300522	19980703	00522		1998	7	3	98ZZZX2289       	4	19980602	G	6113	D5540	BULKHEAD        			BEECH 	36    	A36         	1151604	CE  										PROP SPINNER	CRACKED         	B			UKJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	8209A	736  				E2781				WHILE PERFORMING OTHER MAINTENANCE, NOTICED CRACKS ON AFT SPINNER BULKHEAD.  REMOVED UNIT AND FOUND 3 CRACKS TOTALING AB	OUT 33 PERCENT AROUND AND NEAR THE BULKHEAD TO PROP MOUNTING BOLTS.  INSTALLED NEW UNIT, P/N D7170.  THIS AIRCRAFT IS A 	1993 MODEL A36 WITH 736 HOURS TT AND HAS ABOUT 40 HOURS SINCE INSPECTION.				1	L	7	1 	3O				3A15
1998012200144	19980122	00144	CE  	1998	1	22	98ZZZX229        	1	19980101	G	3230	0842102	IDLER BELLCRANK 			CESSNA	310   	310         	2074202	CE  										NLG RETRACT	FAILED          	G	L	A		O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	5332A	4130 				35532				PILOT AND 1 PASSENGER DEPARTED ON A LOCAL VFR FLIGHT.  UPON RETRACTING LANDING GEAR, PILOT HEAR A LOUD THUMP AND  AT THE	 SAME TIME, FELT A THUD UNDER HIS FEET.  THE LANDING GEAR UP INDICATION NEVER ILLUMINATED.  PILOT CHECKED TIP-TANK MIRRO	RS AND CONFIRMED THE NOSE GEAR WAS ONLY PARTIALLY RETRACTED.  ALL EFFORTS ON PILOT'S PART TO EXTEND NOSE GEAR UNSUCCESSF	UL.  INVESTIGATION REVEALED THE IDLER BELLCRANK, PN 0842102, HAD FAILED.  IDLER BELLCRANK IS PART OF LANDING GEAR RETRAC	TION SYSTEM THAT CONTROLS NOSE GEAR.  SPECIFIC LOCATION OF THIS PART IS JUST BELOW FLOORBOARD FWD OF PILOT'S SEAT.  BELL	CRANK CONNECTS GEAR DRIVE TUBE FROM GEARBOX TO REST OF NOSE GEAR RETRACTION SYSTEM.	1	L	7	2 	3O			RT	3A10
1998070300523	19980703	00523	CE  	1998	7	3	98ZZZX2290       	1	19980604	G	2810	715371	TANK            			BBAVIA	8     	8KCAB       	2110612	CE  										LT TANK	LEAK            	B			OG5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	21	67ND					66792				LEFT FUEL TANK WAS LEAKING OUT OF FILLER NECK AREA.  FOUND TANK BAFFLE BROKEN LOOSE IN TANK WHICH CAUSED CRACK AND LEAK 	AT FILLER NECK.  TANK REPAIRED/REPLACED.  SUBMITTER STATED THIS IS SECOND OCCURRENCE FOR THIS OPERATOR OF 2 8KCAB AIRCRA	FT.				1	H	7	1 	3O				A21CE
1998070300524	19980703	00524	NM  	1998	7	3	98ZZZX2291       	1	19980602	G	2711	35274001	HORN LINK       			CHRIS 	HUSKY 	A1          	221020X	NM  										ELEVATOR TRIM	BENT            	B		A	AWKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	8XJ	90   				1388				THE P/N 50025 (AN3-5) BOLT AND THE P/N 53875 (AN1115-21) CLEVIS ATTACHED TO THE ELEVATOR TRIM HORN LINK P/N 3-5274-001 C	HAFED ON THE TAIL STRUCTURE TUBING.  THE LINK SHOULD HAVE A JOGGLE BUILT IN TO DEFLECT THE TRIM CABLE INBOARD FOR CLEARA	NCE.				1	H	7	1 	3O			NC	A22NM
1998070300525	19980703	00525		1998	7	3	98ZZZX2292       	4	19980528	G	2562	4523050	ELT TRAY        		ELT1104     	CESSNA	441   	441         	2076020	CE  										ELT MOUNT	CRACKED         	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	88GW	700  			57208	4410187				DURING COURSE OF ROUTINE ELT BATTERY CHANGE NOTED 1 EACH MOUNTING SCREW HAD PULLED OUT OF MOUNTING TRAY AND A SECOND HOL	E CRACKED.  NOTE:  TRAY MOUNTED INVERTED WITH TRAY AND MOUNTING SCREWS SUPPORTING WEIGHT OF ELT.					1	L	7	2 	3T			RT	A28CE
1998070300526	19980703	00526	CE  	1998	7	3	98ZZZX2293       	1	19980507	G	6120	565580031	CONTROL CABLE   			CESSNA	182   	182S        	2072701	CE  										PROP CONTROL	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	403ES	108  				18250050				WHEN REMOVING PROPELLER CONTROL CABLE (OWNER/OPERATOR NOTED THAT CONTROL MOVED DURING OPERATION BECAUSE OF NO FRICTION D	EVICE).  FOUND CABLE ROUTED AGAINST AILERON INTERCONNECT CABLE ASSY JUST AFT OF FIREWALL.  INSTALLED NEW CABLE AND ADJUS	TED ROUTING SO AS NOT TO INTERFERE WITH CONTROL CABLE (AILERON).				1	H	7	1 	3O			NT	3A13
1998070300921	19980703	00921	NM  	1998	7	3	98ZZZX2294       	1	19980513	G	5320		SUPPORT         			BOEING	727   	7272K5      		NM  										BS 1030-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND FS 1030.0 TO FS 1116.0 FLOOR SUPPORTS CORRODED AT LBL 6.0.						2	L	7	3 	4F			RT	A3WE
1998070300922	19980703	00922	NM  	1998	7	3	98ZZZX2295       	1	19980513	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1050.0	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND FS 1050.0 FRAME CORRODED BETWEEN STR 29RT TO STR 27RT.						2	L	7	3 	4F			RT	A3WE
1998070300923	19980703	00923	NM  	1998	7	3	98ZZZX2296       	1	19980513	G	5320		SUPPORT         			BOEING	727   	7272K5      		NM  										BS 1030-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND FLOOR SUPPORTS AT FS 1030.0 THROUGH FS 1166.0 CORRODED AT RBL 8.0.						2	L	7	3 	4F			RT	A3WE
1998070300924	19980703	00924	NM  	1998	7	3	98ZZZX2297       	1	19980514	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 970-990	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S29R BETWEEN STA 970 - STA 990.						2	L	7	3 	4F			RT	A3WE
1998070300925	19980703	00925	NM  	1998	7	3	98ZZZX2298       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 970	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 970 BETWEEN S29R AND S28R.						2	L	7	3 	4F			RT	A3WE
1998070300926	19980703	00926	NM  	1998	7	3	98ZZZX2299       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 985	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 985 BETWEEN S29R AND S28R.						2	L	7	3 	4F			RT	A3WE
1998070300927	19980703	00927	NM  	1998	7	3	98ZZZX2300       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 950E	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 950F BETWEEN S27R AND S28R.						2	L	7	3 	4F			RT	A3WE
1998070300928	19980703	00928	NM  	1998	7	3	98ZZZX2301       	1	19980512	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 950E-950F	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S29R AND SKIN BETWEEN STA 950E AND STA 950F.						2	L	7	3 	4F			RT	A3WE
1998070300929	19980703	00929	NM  	1998	7	3	98ZZZX2302       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1010	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS ONTED ON FRAME 1010 AT S27L.						2	L	7	3 	4F			RT	A3WE
1998070300930	19980703	00930	NM  	1998	7	3	98ZZZX2303       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 1030 BETWEEN S74R AND S28R						2	L	7	3 	4F			RT	A3WE
1998070300931	19980703	00931	NM  	1998	7	3	98ZZZX2304       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 1050 BETWEEN S28L AND S27L.						2	L	7	3 	4F			RT	A3WE
1998070300932	19980703	00932	NM  	1998	7	3	98ZZZX2305       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 1130 BETWEEN S26L AND S26R.						2	L	7	3 	4F			RT	A3WE
1998070300933	19980703	00933	NM  	1998	7	3	98ZZZX2306       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1090	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 1090 BETWEEN S27L AND S27R.						2	L	7	3 	4F			RT	A3WE
1998070300934	19980703	00934	NM  	1998	7	3	98ZZZX2307       	1	19980512	G	5730		SKIN            			BOEING	727   	7272K5      		NM  										LT WING	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON LT WING UPPER SURFACE AT NR 4 SPOILER ATTACH POINT.						2	L	7	3 	4F			RT	A3WE
1998070300935	19980703	00935	NM  	1998	7	3	98ZZZX2308       	1	19980512	G	5330		SKIN            			BOEING	727   	7272K5      		NM  										STA 470	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON SKIN AT LOWER H.F. ANTENNA MOUNT, STA 470.						2	L	7	3 	4F			RT	A3WE
1998070300936	19980703	00936	NM  	1998	7	3	98ZZZX2309       	1	19980514	G	5347		SEAT TRACK      			BOEING	727   	7272K5      		NM  										BS 844 RBL 45.5	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON CABIN SEAT TRACK, STA 344 AT RBL 45.5.						2	L	7	3 	4F			RT	A3WE
1998070300937	19980703	00937	NM  	1998	7	3	98ZZZX2310       	1	19980514	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 674 S28L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S28L AT STA 674.						2	L	7	3 	4F			RT	A3WE
1998070300938	19980703	00938	NM  	1998	7	3	98ZZZX2311       	1	19980514	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 687 S27L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S27L AT STA 687.						2	L	7	3 	4F			RT	A3WE
1998070300939	19980703	00939	NM  	1998	7	3	98ZZZX2312       	1	19980512	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 686 S28L	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S28L AT STA 686.						2	L	7	3 	4F			RT	A3WE
1998070300940	19980703	00940	NM  	1998	7	3	98ZZZX2313       	1	19980512	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 685 S28R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S28R AT STA 685.						2	L	7	3 	4F			RT	A3WE
1998070300941	19980703	00941	NM  	1998	7	3	98ZZZX2314       	1	19980512	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 685/S27R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S27R AT STA 685.						2	L	7	3 	4F			RT	A3WE
1998070300942	19980703	00942	NM  	1998	7	3	98ZZZX2315       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 700	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 700 BETWEEN S28L AND S28R.						2	L	7	3 	4F			RT	A3WE
1998070300943	19980703	00943	NM  	1998	7	3	98ZZZX2316       	1	19980512	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 720	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 720 BETWEEN S28R AND S28L.						2	L	7	3 	4F			RT	A3WE
1998070300944	19980703	00944	NM  	1998	7	3	98ZZZX2317       	1	19980512	G	5347		SEAT TRACK      			BOEING	727   	7272K5      		NM  										STA 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON CABIN SEAT TRACK STA 1110 AT RBL 45.5.						2	L	7	3 	4F			RT	A3WE
1998070300945	19980703	00945	NM  	1998	7	3	98ZZZX2318       	1	19980514	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON FRAME 480 BETWEEN S23L AND S26L.						2	L	7	3 	4F			RT	A3WE
1998070300946	19980703	00946	NM  	1998	7	3	98ZZZX2319       	1	19980512	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 1130 S28R	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON STRINGER 28R AT STA 1130.						2	L	7	3 	4F			RT	A3WE
1998070300947	19980703	00947	NM  	1998	7	3	98ZZZX2320       	1	19980512	G	5320		SILL SUPPORT    			BOEING	727   	7272K5      		NM  										BS 1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON THE R-2 DOOR SILL AT STA 1070, WL 232.5.						2	L	7	3 	4F			RT	A3WE
1998070300948	19980703	00948	NM  	1998	7	3	98ZZZX2321       	1	19980512	G	5347	BAC1520792	SEAT TRACK      			BOEING	727   	7272K5      		NM  										PASSENGER CABIN	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND SEAT TRACK CORRODED.						2	L	7	3 	4F			RT	A3WE
1998070300949	19980703	00949	NM  	1998	7	3	98ZZZX2322       	1	19980512	G	5320		SILL            			BOEING	727   	7272K5      		NM  										PASSENGER CABIN	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND L-2 DOOR SILL CORRODED.						2	L	7	3 	4F			RT	A3WE
1998070300950	19980703	00950	NM  	1998	7	3	98ZZZX2323       	1	19980512	G	5320		SUPPORT         			BOEING	727   	7272K5      		NM  										PASSENGER CABIN	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND FOUND L-2 DOOR SILL SUPPORT CORRODED.						2	L	7	3 	4F			RT	A3WE
1998070300951	19980703	00951	NM  	1998	7	3	98ZZZX2324       	1	19980512	G	5320		INTERCOSTAL     			BOEING	727   	7272K5      		NM  										BS 1050-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND INTERCOSTAL AND BRACKET CORRODED STA 1050 - STA 1070, STR 27 - STR 28L.						2	L	7	3 	4F			RT	A3WE
1998070300952	19980703	00952	NM  	1998	7	3	98ZZZX2325       	1	19980512	G	5320		INTERCOSTAL     			BOEING	727   	7272K5      		NM  										BS 1050-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND INTERCOSTAL CORRODED STA 1050 - STA 1074, STR 29L - STR 30.						2	L	7	3 	4F			RT	A3WE
1998070300953	19980703	00953	NM  	1998	7	3	98ZZZX2326       	1	19980512	G	5320		BRACKET         			BOEING	727   	7272K5      		NM  										BS 720E	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND ADF ANTENNA MOUNT BRACKET CORRODED, STA 720E.						2	L	7	3 	4F			RT	A3WE
1998070300954	19980703	00954	NM  	1998	7	3	98ZZZX2327       	1	19980513	G	5330		SKIN            			BOEING	727   	7272K5      		NM  										BS 680.0-712.0	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND BELLY SKIN CORRODED FROM FS 680.0 TO FS 712.0 AT AND UNDER LEVELING COMPOUND APPLICATIO	N AREAS.					2	L	7	3 	4F			RT	A3WE
1998070300955	19980703	00955	NM  	1998	7	3	98ZZZX2328       	1	19980513	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 950A	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND FS 950.0 FRAME CORRODED FROM S26L TO S26R.						2	L	7	3 	4F			RT	A3WE
1998070300956	19980703	00956	NM  	1998	7	3	98ZZZX2329       	1	19980513	G	5311		FRAME           			BOEING	727   	7272K5      		NM  										BS 1148.0	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, FOUND FS 1148.0 FRAME CORRODED BETWEEN S26L TO S26R.						2	L	7	3 	4F			RT	A3WE
1998070300957	19980703	00957	NM  	1998	7	3	98ZZZX2330       	1	19980514	G	5313		STRINGER        			BOEING	727   	7272K5      		NM  										BS 950F-970	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON S29R BETWEEN STA 950F AND STA 970.						2	L	7	3 	4F			RT	A3WE
1998070300958	19980703	00958	NM  	1998	7	3	98ZZZX2331       	1	19980512	G	5320		ANGLE           			BOEING	727   	7272K5      		NM  										BS 950E	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON ANGLE AT STA 950E, S28R.						2	L	7	3 	4F			RT	A3WE
1998070300959	19980703	00959	NM  	1998	7	3	98ZZZX2332       	1	19980512	G	5311		CHORD           			BOEING	727   	7272K5      		NM  										BS 1176.9	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	369FA					21851				DURING C-CHECK INSPECTION, LEVEL 2 CORROSION WAS NOTED ON THE UPPER RIGHT SIDE OF CHORD AT STA 1176.9.						2	L	7	3 	4F			RT	A3WE
1998070300960	19980703	00960	WP  	1998	7	3	98ZZZX2333       	1	19980530	G	2435	23032027	STARTER         			HUGHES	369   	369D        	4470706	WP  										STARTER/GEN	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC		323  		15280	290456D				BRUSHES SPARKING AND FAN COVER VIBRATING LOOSE.  REMOVED FROM AIRCRAFT AND SENT FOR REPAIR EVALUATION.  CONTROL NR 98-5-	12.					1	G	7	1 	3U				H3WE
1998070300961	19980703	00961	SW  	1998	7	3	98ZZZX2334       	1	19980601	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	206   	206B        	1181511	SW  										STROBE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K		714  			2040				STROBE BOX WILL NOT POWER UP.  REPLACED AND SENT FOR REPAIR.  CONTROL NR 98-6-1.						1	G	7	1 	3U				H2SW
1998070300962	19980703	00962	SW  	1998	7	3	98ZZZX2335       	1	19980603	G	6410	HAC473	BLADE           			BELL  	47    	47G5        	1181032	SW  										T/R	DEFECTIVE       	H		A		K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SO	17	1201W	1    			A0011	7819				COLONY SERVICES, FAR PART 137 OPERATOR REPORTED AFTER INSTALLATION OF NEW TAIL ROTOR BLADES, SEVERE VIBRATION OCCURRED D	URING FLIGHT.  BLADE S/N A0011 HAD AN UNUSUAL SWELLING AT THE BLADE TIP, END OF THE EROSION GUARD.  THREE-QUARTERS OF TH	E BLADE HAD BLADE SEPARATION.  WHEN THE BLADE WAS REMOVED THE WHOLE BLADE WAS SWOLLEN.  THE BLADES HAD LESS THAN 1 HOUR 	TOTAL TIME WHEN THEY WERE REMOVED.			1	G	7	1 	3O				2H3
1998070300963	19980703	00963	SW  	1998	7	3	98ZZZX2336       	1	19980603	G	6410	HAC473	BLADE           			BELL  	47    	47G5        	1181032	SW  										T/R	DEFECTIVE       	H		A		K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SO	17	1201W	1    			B0011	7819				COLONY SERVICES, FAR PART 137 OPERATOR REPORTED AFTER INSTALLATION OF NEW TAIL ROTOR BLADES, SEVERE VIBRATION OCCURRED D	URING FLIGHT.  BLADE S/N A0011 HAD AN UNUSUAL SWELLING AT THE BLADE TIP, END OF THE EROSION GUARD.  THREE-QUARTERS OF TH	E BLADE HAD BLADE SEPARATION.  WHEN THE BLADE WAS REMOVED THE WHOLE BLADE WAS SWOLLEN.  THE BLADES HAD LESS THAN 1 HOUR 	TOTAL TIME WHEN THEY WERE REMOVED.			1	G	7	1 	3O				2H3
1998071400143	19980714	00143	GL  	1998	7	14	98ZZZX2338       	2	19980330	G	7250	6898735	TURBINE SUPORT  			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	B			EOPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	492HL	6074 			CAT35860	S803	CAE836307			FOUND CIRCUMFERENTIAL CRACKS IN THE POWER TURBINE SUPPORT RADIUS AREA.  REPLACED TURBINE.						1	G	7	2 	3U	3	U	NC	H3EU    	E4CE
1998071700056	19980717	00056	EU  	1998	7	17	98ZZZX2344       	1	19980601	G	6320	341A35014001	COUPLING        			SNIAS 	SA341 	SA341G      	8680610	EU  										MGB PINION	CRACKED         	D		A		O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SO	14	112VT					1035				DURING INSPECTION TO LOCATE IN-FLIGHT MEDIUM FREQUENCY VIBRATION, FOUND MGB INPUT PINION FLANGE FLEX COUPLING CRACKED AT	 AFT LAMINATE.  DURING INSPECTION OF THIS PART, FOUND 2 OUT OF 3 BOLTS THAT ATTACH FLEX COUPLING TO FLANGE HAD LOST TORQ	UE AND WERE STILL SAFTIED WITH COTTER PIN.  BOTH BOLTS COULD ROTATE FREELY.  THE THIRD BOLT WAS STILL TORQUED AND SAFTIE	D.  THIS PART DEFECT IS NOT CAUSE FOR A MEDIUM FREQUENCY VIBRATION IN THE AIRFRAME DUE TO THE ROTATIONAL SPEED.  AIRCRAF	T DOES NOT FLY VERY OFTEN AND THE FLEX COUPLING FACE CANNOT BE SEEN DURING ROUTINE DAILY INSPECTIONS.		1	G	7	1 	3U				H6EU
1998071700057	19980717	00057	EU  	1998	7	17	98ZZZX2345       	1	19980601	G	6320	341A35014821	BOLT            			SNIAS 	SA341 	SA341G      	8680610	EU  										MGB	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	112VT					1035				DURING INSPECTION TO LOCATE IN-FLIGHT MEDIUM FREQUENCY VIBRATION, FOUND MGB INPUT PINION FLANGE FLEX COUPLING CRACKED AT	 AFT LAMINATE.  DURING INSPECTION OF THIS PART, FOUND 2 OUT OF 3 BOLTS THAT ATTACH FLEX COUPLING TO FLANGE HAD LOST TORQ	UE AND WERE STILL SAFTIED WITH COTTER PIN.  BOTH BOLTS COULD ROTATE FREELY.  THE THIRD BOLT WAS STILL TORQUED AND SAFTIE	D.  THIS PART DEFECT IS NOT CAUSE FOR A MEDIUM FREQUENCY VIBRATION IN THE AIRFRAME DUE TO THE ROTATIONAL SPEED.  AIRCRAF	T DOES NOT FLY VERY OFTEN AND THE FLEX COUPLING FACE CANNOT BE SEEN DURING ROUTINE DAILY INSPECTIONS.		1	G	7	1 	3U				H6EU
1998071700058	19980717	00058	GL  	1998	7	17	98ZZZX2346       	1	19980601	G	2436	F0C4002A	REGULATOR       			ENSTRM	F28   	280         	3300502	GL  										DC SYSTEM	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	754MH	50   			15056	1024				UNIT REQUIRED BY AD 97-20-04 FAILED AFTER 50 HOURS.  EIGHTY PERCENT OF THE UNITS FAIL TEST.  SUBMITTER STATED THEY SHOUL	D BE RETIRED FORM SERVICE AS UNRELIABLE.  USED ON MOST OLD PIPERS, ENSTROM, AND MANY OTHER AIRCAFT.  AT LEAST ONE ACCIDE	NT WAS CAUSED BY THIS PART FAILURE.				1	G	7	1 	3O				H1CE
1998071700059	19980717	00059	NE  	1998	7	17	98ZZZX2347       	1	19980601	G	3150		DISPLAY SYSTEM  			SKRSKY	S76   	S76C        	8143008	NE  										COCKPIT IIDS	FALSE WARNING   	D		A		O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			NE	03	176CG					760485				IN-FLIGHT OVER NEW YORK CITY, THE NR 1 ENGINE-OUT WARNING LIGHT AND TONE CAME ON MOMENTARILY.  AT THE SAME TIME, THE MAS	TER CAUTION LIGHT INDICATION CAME ON MOMENTARILY.  THE CREW SELECTED RECALL FROM ENGINE IIDS DISPLAY UNIT AND FOUND THE 	A/C GENERATOR FAIL LIGHT CAUSED THE MASTER CAUTION INDICATION.  THE A/C GENERATOR INTERLOCK RELAY WILL DROP THE GENERATO	R OFF-LINE WHENEVER THERE IS AN ENGINE FAILURE.  OUR HELICOPTER IS EQUIPPPED WITH THE IIDS (INTERGRATED INSTRUMENT DISPL	AY SYSTEM).  SIKORSKY HAS INFORMED US THAT OTHER OPERATORS OF IIDS EQUIPPED HELICOPTERS HAVE EXPERIENCED THIS MOMENTARY 	PROBLEM.  IN ALL INSTANCES, IT CLEARS ITSELF AFTER A FEW SECONDS.	1	G	7	2 	3U			NC	H1NE
1998071700060	19980717	00060	EU  	1998	7	17	98ZZZX2348       	1	19980609	G	3320	PW5100D10	BULB            			AMD   	FALC50	FALCON900   	2700160	EU  										CABIN LIGHT	BURNED          	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	343MG					95				WHILE REPLACING FAILED FLUORESCENT BULB FOR CABIN LIGHTING, FOUND PLASTIC BULB ENDS (CONNECTORS) BURNED AND MELTED.  FOU	ND ALL OTHER BULBS IN SIMILAR CONDITION AND REPLACED ALL.  RECOMMEND INSPECTING ALL PRECISION WINDING BULBS, NEW BULBS H	AVE CERAMIC ENDS (CONNECTORS).				2	L	7	3 	4F			RT	A46EU
1998071700061	19980717	00061	NE  	1998	7	17	98ZZZX2349       	2	19980516	G	7310	0301007710	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					LT INJECTOR	CRACKED         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	03	96LG					2817	9362			NOTICED FUEL ON ENGINE DECK.  FUEL WAS RUNNING DOWN FROM TOP OVER ENGINE DURING START.  FOUND LEFT FUEL INJECTOR LINE CR	ACKED AT TOP FLARE.  SUBMITTER STATED THIS IS THE THIRD ONE OF THESE THEY HAVE HEARD ABOUT IN THE SAME AREA AND SUGGESTE	D MANUFACTURE FLARE PROCEDURE ON TOOL DEFECT.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1998071700064	19980717	00064	NM  	1998	7	17	98ZZZX2350       	1	19980522	G	2430	43772	INSULATOR       			SEMCO 	CLNGER	CHALLENGER  	8070802	NM  										POWER SUPPLY	SHORTED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09					173R					POWER SUPPLY S/N'S 057R, 116R, 139R, 173R, 259R, AND 328R FOUND Q5 DAMAGED BY SHORT-CIRCUIT (S/N 173R).  INSPECTION REVE	ALED MICA INSULATOR MIS-POSITIONED UNDER Q5 PERMITTING COLLECTOR TO SHORT TO CHASSIS (GROUND).  INSPECTION OF ADJACENT C	OMPONENTS (CR19 AND Q6) REVEALED SAME CONDITION ALTHOUGH NO SHORT-CIRCUITS, YET.  INSP OF REMAINING 5 UNITS REVEALED SAM	E CONDITION, ALTHOUGH NO SHORT-CIRCUITS, YET.  IT IS UNKNOWN WHETHER THESE COMPONENTS (Q5, Q6, CR19) OR RESPECTIVE INSUL	ATORS ARE ORIGINAL (FACTORY) OR ARE IN-SERVICE REPLACEMENTS.  SUBMITTER RECOMMENDED MORE CARE BE GIVEN TO PROPER PLACEME	NT OF MICA INSULATORS UNDER COMPONENTS.	1	B	0	0 					A13SO
1998071700065	19980717	00065	CE  	1998	7	17	98ZZZX2351       	1	19980609	G	2810	339210161	TEE CHORD       			BEECH 	33    	F33A        	1151425	CE  										TANK VENT TUBE	MISREPAIRED     	B	S		SL5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	1550N					CE1323				OWNER COMPLAINED OF LT FUEL TANK SIPHONING FUEL EXCESSIVELY FROM VENT SYSTEM.  FOUND WELDED TUBE TEE ASSEMBLY HAD NOT BE	EN DRILLED AFTER WELDING.  VENT AIR COULD NOT REACH ANTI-SIPHON CHECK VALVE.  AFTER DRILLING HOLE INTO TUBE, VENT SYSTEM	 OPS CHECKED GOOD.				1	L	7	1 	3O			 	3A15
1998071700066	19980717	00066	CE  	1998	7	17	98ZZZX2352       	1	19980603	G	3211	07436062	FITTING         			CESSNA	182   	182P        	2075816	CE  										NLG BS 0.0	CRACKED         	B			PCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	182ER	4888 				18263637				NOSE LANDING GEAR FITTING FOUND CRACKED AT LOWER ATTACH LEFT AND RIGHT 'BOSS' DURING A ROUTINE INSPECTION OF AIRCRAFT. C	AUSE UNKNOWN, BUT SUSPECT HARD LANDING AND SUBSEQUENT FATIGUE.  INSPECTED 5 OTHER AIRCRAFT OF SAME MODEL AND TIS.  NO OT	HER CRACKS DETECTED.				1	H	7	1 	3O			NT	TA13
1998071700067	19980717	00067	SO  	1998	7	17	98ZZZX2353       	1	19980611	G	5720	620612	DOUBLER         			PIPER 	PA28  	PA28RT201   	7102818	SO  										RT WING WALK	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2142X	3886 				28R7918089				RIGHT FORWARD WING WALK HAS BROKEN/CORRODED DOUBLER PLATE.  THIS SECTION CRACKED FULL LENGTH ON BOTH INNER AND OUTER OF 	DOUBLER PLATE.  SUBMITTER STATED THIS WAS THE SECOND ARROW THAT WAS FOUND IN THIS CONDITION.					1	L	7	1 	3O				2A13
1998071700068	19980717	00068		1998	7	17	98ZZZX2354       	1	19980616	G	2510	SL43008	CYLINDER        	PORTER      																SEAT ADJUSTER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05										SEAT BACK ADJUSTER CYLINDER INSPECTION FOUND A CRACK THAT EXTENDS FROM EDGE OF HOLE FOR SPLINED FIBER NUT TO THE END OF 	THE HYDROLOK.  SUSPECT CAUSE - NORMAL OPERATION AND METAL FATIGUE.
1998071700069	19980717	00069	SO  	1998	7	17	98ZZZX2355       	1	19980601	G	2434	481110	ALTERNATOR      	CHRYSLER    		PIPER 	PA28  	PA28181     	7102807	SO  										DC SYSTEM	FAILED          	D				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SW	99	2331M					287890247				AIRCRAFT EXPERIENCED AN ELECRICAL SYSTEM FAILURE.  TROUBLESHOT SYSTEM, FOUND ALTERNATOR DEFECTIVE.  REPLACED ALTERNATOR,	 CHARGED BATTERY.  SYSTEM OPERATES NORMALLY.					1	L	7	1 	3O				2A13
1998071700070	19980717	00070	CE  	1998	7	17	98ZZZX2356       	1	19980613	G	2821	07560106	PLUNGER         			CESSNA	210   	T210L       	2073449	CE  										FUEL STRAINER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	732GR					21061506				FUEL STRAINER PLUNGER NIPPLE WEARING.						1	H	7	1 	3O				3A21
1998071700071	19980717	00071		1998	7	17	98ZZZX2357       	4	19980608	G	6113	1250419K200	SPINNER         			CESSNA	206   	U206G       	2073356	CE  										BLADE CUTOUT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	756HK	4980 				U20604102				DURING A 100-HOUR INSPECTION, THE PROP SPINNER WAS FOUND CRACKED IN THREE PLACES.  THE CRACKS WERE IN THE CENTER OF EACH	 BLADE CUT-OUT.  NO OTHER DAMAGE WAS FOUND.  THE PROBLEM MAY HAVE BEEN CAUSED FROM PUSHING ON THE SPINNER DURING GROUND 	HANDLING.				1	H	7	1 	3O				A4CE
1998071700072	19980717	00072	SO  	1998	7	17	98ZZZX2358       	1	19980617	G	7160	86245834	HEAT BOX        			PIPER 	PA44  	PA44180     	7104402	SO  										CARBURETOR	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9290P	195  				4496019				DURING ROUTINE 100-HOUR INSPECTION, FOUND RT ENGINE CARBURETOR HEAT AIRBOX BROKEN AT THE CARBURETOR HEAT INLET TUBE.  PR	EVIOUS 100-HOUR INSPECTION FOUND LT ENGINE AIRBOX IN SAME CONDITION.  AIRCRAFT TOTAL TIME 195.0 HRS.  TOTAL TIME ON PREV	IOUS AIRBOX, 99.6 HRS.  SUSPECT CAUSE IS POSSIBLE POOR WELDING.				1	L	7	2 	3O				A19S0
1998071700073	19980717	00073	CE  	1998	7	17	98ZZZX2359       	1	19980619	G	2821	07560106	PLUNGER         			CESSNA	210   	T210M       	2073451	CE  										FUEL STRAINER	WORN            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	15	6977B					21062862				FUEL STRAINER DRAIN PLUNGER NIPPLE LEAKING FASTER THAN BEFORE.  SUBMITTER SUGGESTED CHANGING FUEL OR RUBBER ON PLUNGER.						1	H	7	1 	3O				3A21
1998012200153	19980122	00153	CE  	1998	1	22	98ZZZX238        	1	19980108	G	5620	010A31870	WINDOW          			MTSBSI	MU2   	MU2B60      	5780460	CE  										LT FWD CABIN	CRACKED         	D				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	25	6KE	5305 				766SA				WHILE CRUSING AT 24,000 FEET, A LOUD POP WAS HEARD AND PRESSURIZATION DROPPED TO 2 PSI.  A DESCENT WAS MADE TO A LOWER A	LTITUDE AND AN UNEVENTFUL LANDING WAS MADE.  UPON INVESTIGATION, THE LEFT FORWARD CABIN WINDOW WAS FOUND CRACKED ACROSS 	THE BOTTOM.  THE AREA OF THE CRACK ALSO HAD SOME CRAZING.  THE WINDOW WAS REPLACED WITH A NEW WINDOW AND ALSO ALL OF THE	 SAME PART NUMBERED WINDWS ON THE LEFT SIDE DUE TO WINDOWS BEING ORIGINAL WITH 5,305.0 FLIGHT HOURS.  THE AIRCRAFT IS A 	1981 MODEL.  SB 087/56-001 REFERENCES ALLOWABLE CRAZING IN THE WINDOWS.		1	H	7	2 	3T			RT	A10SW
1998012200154	19980122	00154	CE  	1998	1	22	98ZZZX239        	1	19980107	G	7830	49531193	ROD END         		495110175   	LEAR  	35    	35A         	5170602	CE  										LT T/R	SEPARATED       	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	23	785JM	1829 			197	655				AIRCRAFT CAME IN WITH REPORT STATING LEFT T/R FAILS TO STOW AFTER DEPLOY CYCLE.  REMOVED ACCESS PANELS TO TROUBLESHOOT. 	 FOUND LOWER REVERSER DOOR LINK SEPARATED FROM ROD END.  AFTER A VISUAL INSPECTION OF LINK AND ROD END, ROD END ENGAGEME	NT INTO LINK WAS APPROXIMATELY 2-1/2 THREADS.  CHECKED UPPER LINK TO ROD END AND FOUND THE SAME THREAD ENGAGEMENT.				2	L	7	2 	4F				A10CE
1998072400647	19980724	00647	NE  	1998	7	24	98ZZZX2426       	2	19980603	G	8530	615324	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 2 ENG NR 7	WEAR            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		307  		GV37098	542809	P33738			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION	 ON A CYLINDER.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUID	ES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION 	USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400648	19980724	00648	NE  	1998	7	24	98ZZZX2427       	2	19980603	G	8530	615323	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 2-8	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		307  		CV36754	542809	P33738			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  IN ADDITION, PISTON ASSY IS A FAA PMA P/N WHICH WHEN THIS	 ENGINE WAS OVERHAULED IN 1972, HAS ALREADY BEEN CHANGED, BUT THE ENGINE RECORDS DO NOT REFLECT THIS.  THE R2800-99/52/1	01/103W O/H AND PART MANUALS SHOW SPECIFIC AND NON-SUBSTITUTABLE P&W P/N'S FOR THE PISTON ASSY.  IN THIS ENG POS, THIS C	YL ASSY SHOWS IN EXCESS OF 1,000 HRS OF OPER USAGE.	2	L	7	2 	4R	4	R		6A6     	5E8
1998072400649	19980724	00649	NE  	1998	7	24	98ZZZX2428       	2	19980603	G	8530	615324	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 2 ENG NR 5	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		307  		A181P0DV	542809	P33738			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION	 ON A CYLINDER.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE GUID	ES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION 	USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400650	19980724	00650	NE  	1998	7	24	98ZZZX2429       	2	19980603	G	8530	615326	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 2 ENG NR 9	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		307  		37615	542809	P33738			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  IN ADDITION, PISTON ASSY IS A FAA PMA P/N WHICH WHENTHIS ENGINE WAS OVERHAULED IN 1972, HAS BEEN CHANGED ALREA	DY, BUT THE ENG RECORDS DO NOT REFLECT THIS.  THE R2800-52/99/101/103W O/H AND PARTS MANUALS SHOW SPECIFIC AND NON-SUBST	ITUTABLE P&W P/N'S FOR THE PISTON INSTALLED IN THIS POSITION.  THIS CYL ASSY SHOWS IN EXCESS OF 1,000 HRS OPER USAGE.		2	L	7	2 	4R	4	R		6A6     	5E8
1998072400651	19980724	00651	NE  	1998	7	24	98ZZZX2430       	2	19980603	G	8530	615324	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 2 ENG NR 15	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		307  		5066	542809	P33738			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400652	19980724	00652	NE  	1998	7	24	98ZZZX2431       	2	19980603	G	8530	615325	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 2 ENG NR 11	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		307  		RR1151	542809	P33738			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 307.0 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  PISTON ASSY IS AN FAA PMA P/N, WHICH, WHEN THIS ENG WAS O	VERHAULED IN 1972, REVEALED CYL ASSY HAD BEEN CHANGED ALREADY, BUT ENG RECORDS DID NOT REFLECT THIS.  R2800-99/52/101/10	3W O/H AND PARTS MANUALS SHOW SPECIFIC AND NON-SUBSTITUTABLE P&W P/N'S FOR THE PISTON IN THIS POSITION.  THIS CYLINDER A	SSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERATION USAGE.	2	L	7	2 	4R	4	R		6A6     	5E8
1998072400653	19980724	00653	NE  	1998	7	24	98ZZZX2432       	2	19980603	G	8530	615323	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 1 ENG NR 8	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		167  		1141	542809	NK510656			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400654	19980724	00654	NE  	1998	7	24	98ZZZX2433       	2	19980603	G	8530	615324	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 1 ENG NR 7	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		167  		M132844	542809	NK510656			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400655	19980724	00655	NE  	1998	7	24	98ZZZX2434       	2	19980603	G	8530	615324	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 1 ENG NR 5	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		167  		A738WYAS	542809	NK510656			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400656	19980724	00656	NE  	1998	7	24	98ZZZX2435       	2	19980603	G	8530	615324	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 1 ENG NR 3	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		167  		309880	542809	NK510656			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400657	19980724	00657	NE  	1998	7	24	98ZZZX2436       	2	19980603	G	8530	615326	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 1 ENG NR 9	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		167  		A258	542809	NK510656			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400658	19980724	00658	NE  	1998	7	24	98ZZZX2437       	2	19980603	G	8530	615325	CYLINDER        			CVAC  	440   	C131D       	2422750	WP  	PWA   	R2800 	R2800103W   	52026	NE  					NR 1 ENG NR 11	WORN            	C			W2LM	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	131CW		167  		628913	542809	NK510656			CYLINDER ASSY HAD EXTREME CLEARANCES BETWEEN VALVES AND VALVE GUIDES WHICH IS NOT INDICATIVE OF 167.1 HOURS OF OPERATION	 ON A CYLINDER ASSY.  UTILIZING USAF SPECS, I.E., SODIUM FILLED DOME TYPE EXHAUST VALVES AND CLOSE TOLERANCE STEEL VALVE	 GUIDES.  ALSO, EXCESSIVE PISTON TO CYLINDER BARREL SCUFFING.  THIS CYLINDER ASSY SHOWS EVIDENCE OF 1,000 HOURS OF OPERA	TION USAGE.			2	L	7	2 	4R	4	R		6A6     	5E8
1998072400659	19980724	00659	CE  	1998	7	24	98ZZZX2438       	1	19980610	G	5720	MS21042L5	NUT             		12270078    	CESSNA	206   	U206F       	2073333	CE  										RT WING STRUT	CRACKED         	B		A	HAXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	2392U	2827 				U20602365				DURING AN ANNUAL INSPECTION TWO OF THE MS21042L5 NUTS WERE FOUND CRACKED ALL THE WAY THROUGH TO THE BOLT ON THE RIGHT WI	NG STRUT UPPER ATTACH FITTING.  SUBMITTER STATED THE CAUSE IS UNKNOWN.					1	H	7	1 	3O				A4CE
1998072400660	19980724	00660	EA  	1998	7	24	98ZZZX2439       	2	19980505	G	8520	LW12697	CRANKSHAFT      			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FAILED          	H	S		HE8S	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CE	09	24435	6462 	2149 			3879A1121	L2120215			AIRCRAFT DESTROYED AS A RESULT OF FORCED LANDING INDUCED BY A SEPARATION OF THE ENGINE CRANKSHAFT.  SUBSEQUENT INVESTIGA	TION DISCLOSED A FATIGUE FAILURE ADJACENT TO THE CENTER MAIN BEARING JOURNAL.  THIS ENGINE HAD EXPERIENCED 2 PREVIOUS PR	OPELLER STRIKES WHICH DID NOT REQUIRE CRANKSHAFT INSPECTION UNDER LYC AD 91-14-22.  SUBMITTER SUGGESTED REVISING LYCOMIN	G AD 91-14-22 TO REQUIRE CRANKSHAFT INSPECTION IAW LYC SL L163C, FOLLOWING ANY PROPELLER STRIKE RESULTING IN PROP REWORK	 OR REPLACEMENT.		1	L	7	1 	3O	3	O		A18SO   	E223
1998072400661	19980724	00661	CE  	1998	7	24	98ZZZX2440       	1	19980421	G	2701	MS276454	BEARING         			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					YOKE	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	264ER	9520 				17270716	L3184636A			FOUND BEARING HOUSING AT BASE OF YOKE LOOSE.  HOUSING IS PRESSED IN.  A WELD MAY PREVENT THIS.						1	H	7	1 	3O	3	O	NT	3A12    	E286
1998072400662	19980724	00662	CE  	1998	7	24	98ZZZX2441       	1	19980423	G	2701		HOUSING         			CESSNA	172   	172N        	2072434	CE  										YOKE BEARING	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	38ER	5087 				17270698				FOUND CONTROL YOKE WELD ASSEMBLY BEARING HOUSING AT BASE FOR ELEVATOR ROD CONNECT IS LOOSE.  WELD INSTEAD OF PRESS FIT M	AY SOLVE PROBLEM.					1	H	7	1 	3O			NT	3A12
1998072400663	19980724	00663	SW  	1998	7	24	98ZZZX2442       	1	19980615	G	7120		MOUNT BOLT      			BBAVIA	7     	7GCAA       	21101N8	SW  										LT/RT EXHAUST	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	5115T					137				INSPECTION FOUND LEFT AND RIGHT EXHAUST PIPES RUBBING ENGINE LOWER MOUNT BOLTS AT FIREWALL.  SUBMITTER STATED CHECKED SE	VERAL AIRCRAFT OF SAME MAKE/MODEL AND ALL HAD SAME PROBLEM.					1	H	7	1 	3O				A759
1998072400664	19980724	00664	SW  	1998	7	24	98ZZZX2443       	1	19980529	G	2720	7150	INTERCONNECT    			MOONEY	M20   	M20C        	5870208	SW  										RUDDER HORN	FAILED          	B		A	PCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	6699U	2643 				2426				OWNER REPORTED VIOLENT NOSEWHEEL SHIMMY ON LANDING ROLL-OUT.  INSPECTION REVEALED RUDDER HORN INTERCONNECT, PN 7150, BRO	KE AT WELD.  RESULTANT DAMAGE TO UPPER GEAR STRUCTURE, P/N 5074, WAS NOTED.  INSPECTION OF SUBJECT WELD REVEALED THE EVI	DENCE OF A PRE-EXISTING CRACK.  SUGGEST RECURRING NDT INSPECTION OF OLD STYLE HORNS FOR CRACKS.				1	L	7	1 	3O				2A3
1998072400665	19980724	00665	EA  	1998	7	24	98ZZZX2444       	2	19980605	G	8520		CRANKCASE       			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ALT MT AREA	CRACKED         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	05	8085A					288016065	L1752739A			WHILE INVESTIGATING OIL LEAK, FOUND ENGINE CASE CRACKED RT FORWARD AFT BOSS WHERE ALTERNATOR BRACKET ATTACHES.  ENGINE I	S LYCOMING FACTORY OVERHAUL, INSTALLED 8-30-97, 340 HRS SMOH.					1	L	7	1 	3O	3	O		2A13    	E274
1998072400666	19980724	00666	SO  	1998	7	24	98ZZZX2445       	1	19980522	G	3340	2060371	CONNECTOR       			PIPER 	PA42  	PA42        	7104202	SO  										COCKPIT	SMOKED          	B			JGVR	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	09	811DA	5012 				428001029				ELECTRICAL PLUG CODE E357 MALE P/N 206037-1, FEMALE, P/N 206036-3.  WHILE IN CRUISE FLIGHT, SMOKE WITH AN 'ELECTRICAL SM	ELL' BEGAN COMING OUT OF OVERHEAD SWITCH PANEL.  PILOT INITIATED A SHUTDOWN OF ELEC SYS.  SMOKE LASTED ABOUT 10 SECONDS,	 3 EXTERIOR LIGHTING CB'S (STROBES, NAV LIGHTS, AND RECOGNITION LIGHTS) WERE TRIPPED.  PILOT GRADUALLY RESTORED POWER TO	 THE ELEC SYS AND SMOKE NEVER REAPPEARED.  THE 3 TRIPPED CB'S WERE NOT RESET IN FLIGHT.  INVEST BY MECH IN SIDNEY REVEAL	ED WHEN ANY OF THE 3 BREAKERS WERE RESET E367 (AN OVERHEAD DISCONNECT PLUG) GOT HOT AND STARTED TO SMOKE.  NO REPAIR COU	LD BE MADE IN SIDNEY.  THE 3 EXT LIGHTING SYS WERE 'MEL'D' PER DUNCAN MEL AND TRIP WAS CONTINUED WITHOUT INCIDENT.	1	L	7	2 	4T				A23SO
1998072400667	19980724	00667	GL  	1998	7	24	98ZZZX2446       	1	19980605	G	5597		WIRE            			BLANCA	1419  	14192       	1220404	GL  										TAIL	FAILED          	D	S	A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			WP	23	9849B					4101				DURING LEVEL FLIGHT, A PITCH UP MOTION OCCURRED.  UPON LANDING, THE LT FORWARD UPPER STREAMLINE TAIL WIRE HAD HAD AN APP	ARENT TENSION FAILURE AT MID-SPAN.  ALL 8 TAIL WIRES WERE REPLACED ABOUT 2 YRS AND 100 HRS TIS AGO.  THESE WIRES WERE PU	RCHASED FROM THE BELLANCA CLUB AS OBTAINED FROM MFG.  VISUAL INSPECTION (10X) OF THE FRACTURE SHOWS AN AREA OF METAL PRO	PERTY DISCONTINUITY (POSSIBLY AN INCLUSION).			1	L	7	1 	3O			 	1A3
1998072400668	19980724	00668	CE  	1998	7	24	98ZZZX2447       	1	19980608	G	3233	1280209	PIN             		12805149    	CESSNA	182   	R182        	2072734	CE  										NLG DOWNLOCK	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	182BG	89   			243	R18200256				DURING RIGGING CHECK OF NOSE GEAR, DISCOVERED ONE NOSE GEAR ACTUATOR DOWNLOCK PIN BROKEN IN TWO.  PIN BROKE AT GROOVE MA	CHINED IN PIN FOR ADDITION OF ROLL PIN.  REPLACED PIN.  SUBMITTER STATED THESE PINS HAVE A HISTORY OF WORKING LOOSE IN T	HEIR HOUSINGS.  CESSNA HAS RECENTLY ADDED THE GROOVE AND ROLL PIN TO RETAIN THE PIN.  THIS FEATURE WAS ADDED TO THIS ACT	UATOR AT THE LAST OVERHAUL ONLY 89 HOURS AGO.			1	H	7	1 	3O			RT	3A13
1998072400669	19980724	00669	SO  	1998	7	24	98ZZZX2448       	1	19980611	G	5553	3569702	CASTING RIVETS  			PIPER 	PA28  	PA28RT201   	7102818	SO  										V FIN SUPPORT	LOOSE           	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2142X	3886 				28R7918089				LOOSE HI-SHEAR RIVETS, PN 522-995, ON VERTICAL FIN CASTING SUPPORT ASSEMBLY, P/N 35697-02, AND FITTING ASSY, PN 78927-02	.  THSE RIVETS COULD BE TURNED BY HAND.  RECOMMEND CHANGING TO HI-LOC BOLTS.					1	L	7	1 	3O				2A13
1998072400670	19980724	00670	CE  	1998	7	24	98ZZZX2449       	1	19980601	G	2731		CHAIN           			CESSNA	182   	182G        	2072716	CE  										CENTER CONSOLE	FAILED          	D	S			K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			WP	07		4700 								THE ELEVATOR TRIM BECAME INOPERATIVE WHEN INSPECTED. THE LAST PIVOT PIN OF THE CHAIN WAS FOUND SEPARATED FROM THE SIDE L	INK.  THIS IS DIFFICULT TO INSPECT BECAUSE IT IS LOCATED INSIDE THE CENTER CONSOLE.					1	H	7	1 	3O			NT	3A13
1998072400671	19980724	00671	CE  	1998	7	24	98ZZZX2450       	1	19980526	G	3233	AN38034	COTTER PIN      		45810070    	BEECH 	45    	A45         	1152006	CE  										MLG ACTUATOR	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	3111C					528275				LANDING GEAR FAILED TO COME DOWN, TRIPPED CIRCUIT BREAKER, WOULD NOT CRANK DOWN MANUALLY.  DURING TEAR-DOWN INSPECTION, 	FOUND COTTER PIN (AN380-3-4) BROKEN ON WORM GEAR (45-810143) CAUSING NUT, AN 310-7,					1	L	7	1 	3O				5A3
1998072400673	19980724	00673	SO  	1998	7	24	98ZZZX2452       	2	19980615	G	8520	653058A1	CAMSHAFT        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					PROP GOV DRIVE	FAILED          	B			PIYR	E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	21	2622A	157  				414A0310				OPERATOR EXPERIENCED AN IN-FLIGHT FEATHERING OF THE LEFT ENGINE AND IMMEDIA TELY SHUT DOWN.  UPON INVESTIGATION, IT WAS 	REVEALED THE CAMSHAFT HAD BROKEN AT THE PROPELLER GOVERNOR DRIVE END.  CAUSE UNKNOWN, UNIT SENT TO FACTORY FOR INSPECTIO	N.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1998072400674	19980724	00674	CE  	1998	7	24	98ZZZX2453       	1	19980529	G	5712	53981	RIB             			BBAVIA	8     	8KCAB       	2110612	CE  										LT WING ROOT	DEFECTIVE       	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2656Z					36018				RIVETS PULLED AT BUTT RIB LT AND RT WING ON TOP SKIN.  RIVETS PULLED THROUGH RIB NOT SKIN.  AMERICAN CHAMPION CHANGED RI	B THICKNESS AND FASTENER TYPE AND SPACING 1.5 YEARS AGO.  UNKNOWN NUMBER OF WINGS OUT THERE WITH THIS PROBLEM.  NEED SL 	OR AD.				1	H	7	1 	3O				A21CE
1998072400675	19980724	00675	CE  	1998	7	24	98ZZZX2454       	1	19980529	G	5712	53982	RIB             			BBAVIA	8     	8KCAB       	2110612	CE  										RT WING ROOT	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2656Z					36018				RIVETS PULLED AT BUTT RIB LT AND RT WING ON TOP SKIN.  RIVETS PULLED THROUGH RIB NOT SKIN.  AMERICAN CHAMPION CHANGED RI	B THICKNESS AND FASTENER TYPE AND SPACING 1.5 YEARS AGO.  UNKNOWN NUMBER OF WINGS OUT THERE WITH THIS PROBLEM.  NEED SL 	OR AD.				1	H	7	1 	3O				A21CE
1998072400676	19980724	00676	SO  	1998	7	24	98ZZZX2455       	1	19980716	G	2150	73965010	BELT            			PIPER 	PA32  	PA32R301    	7103218	SO  										AIR COND DRIVE	FAILED          	B			BCBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	324G	221  				3246003				REF:  AIR CONDITIONING INSTALLATION DRIVE BELT SERVICE HISTORY:  BROKEN AND REPLACED AT 135.7 TT 4/4/96.  BROKEN AND REP	LACED AT 213.4 TT 7/16/96.  BROKEN AND REPLACED AT 283.0 TT 7/25/97.  BROKEN AND REPLACED AT 504.1 TT 6-16-98.  SUBMITTE	R STATED BELTS WERE REPLACED IAW SM 21-50-00 REV 7-1-97, WHICH IS CURRENT AND S/L 903A.  EVEN WHEN ALIGNED WITH GREAT CA	RE, THIS IS VERY TYPICAL OF SERVICE LIFE.			1	L	7	1 	3O				A3SO
1998072400677	19980724	00677	EU  	1998	7	24	98ZZZX2456       	2	19980615	G	8520		CONNECT ROD     			DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	FAILED          	D				L				ABORTED APPROACH        				R	B	Y	PARTIAL RPM/PWR LOSS      	SMOKE/FUMES/ODORS/SPARKS  	ENGINE STOPPAGE           	AP	APPROACH       	1			EA	05	50ML	900  				10007				PILOT ATTEMPTED GO-AROUND.  HEARD A BANG AND LOST SIGNIFICANT POWER.  WAS ABLE TO MAKE APPROACH TO A CROSS-RUNWAY. CABIN	 FILLED WITH SMOKE ON FINAL AND ENGINE FINALLY SEIZED.  LANDED OK, BUT FIRE IN ENGINE COMPARTMENT CONTINUED TO BURN.  FI	RE WAS PUT OUT.  CONNECTING ROD BROKE LOOSE AT CRACKSHAFT AND MADE HOLE IN CASE.  OIL SPRAYED ON EXHAUST CAUSING FIRE. S	IGNIFICANT DAMAGE FROM FIRE TO COMPOSITE BELLY AND ENGINE.			1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
1998072400678	19980724	00678	CE  	1998	7	24	98ZZZX2457       	1	19980601	G	5310		STRUCTURE       			BEECH 	60    	B60         	1153605	CE  										CABIN	CORRODED        	B			OACR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	51AL					P247				WHILE DOING PAINT AND INTERIOR, SEVERE CORROSION WAS NOTICED UNDER THE EXISTING INSULATION.  SUBMITTER STATED THE CORROS	ION WAS CAUSED BY THE INSULATION HOLDING WATER FROM SEAL CONDENSATION.  ALSO, FOUND WINDOWS WITH BAD SEAL POSSIBLY FROM 	SITTING ON THE RAMP IN THE SUN.  THIS PROBLEM WOULD NOT HAVE BEEN NOTICED UNTIL SUCH WORK WAS PERFORMED OR SIDE WALLS, C	EILING AND INSULATION WERE REMOVED FOR AN ANNUAL INSPECTION.  SUBMITTER SUGGESTED A POSSIBLE SOLUTION, USE BAGGED INSULA	TION AND INSPECT BI-ANNUALLY.		1	L	7	2 	3O				A12CE
1998072400679	19980724	00679	SO  	1998	7	24	98ZZZX2458       	1	19980528	G	3310	B002694	DIMMER          	LAMAR       		PIPER 	PA31  	PA31310     	7103103	SO  										PANEL LIGHTS	BURNED          	B		A	VY2R	E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	23	65TT	423  				317612078				IN-FLIGHT, PILOT SELECTED PANEL LIGHTS ON, SMOKE BLEW OUT OF THE INSTRUMENT PANEL INSTANTLY.  PILOT SHUT OFF ALL POWER. 	 SAFE LANDING WAS MADE.  FOUND PANEL LIGHT DIMMER ASSY BURNT AND SHOWS SIGNS OF HIGH HEAT.  INSPECTED ALL ASSOCIATED WIR	ING, NO DEFECTS NOTED.  INSTALLED NEW DIMMER ASSY.  OPS NORMAL.  PILOT REPORTS THIS IS THE SECOND TIME IN 4 YEARS THAT T	HIS SAME PROBLEM OCCURRED.  POSSIBLE DEFECTIVE DIMMER UNIT.			1	L	7	1 	3O			RT	A20SO
1998072400680	19980724	00680	SW  	1998	7	24	98ZZZX2459       	1	19980526	G	7160	649643	INDUCTION TUBE  			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360MB   	17025	CE  					CYL NR 3 FLANGE	CRACKED         	B			EA6R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	747MR	254  				251212	317222			NOTICED FUEL STAINS AROUND CYLINDER NR 3.  REMOVED AND INSPECTED, INDUCTION TUBE WAS CRACKED AROUND FLANGE.						1	L	7	1 	3O	3	O		2A3     	E9CE
1998072400681	19980724	00681	EA  	1998	7	24	98ZZZX2460       	2	19980624	G	7414	1068256011	MAGNETO         	BENDIX      		PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					ENGINE	FAILED          	D				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			EA	25	8106P	1    				288011007				RECEIVED BENDIX MAG AS A FACTORY OVERHAULED UNIT FROM TELELDYNE CONTINENTAL.  INSTALLED MAG, RAMP TEST GROUND RUN OK.  A	IRCRAFT FLEW FOR 45 MINUTES AND HAD COMPLETE ENGINE FAILURE DUE TO MAG FAILURE.  FOUND BOTH BREAKER POINTS NOT GROUNDING	 TO MAG CASE.  SUBMITTER RECOMMENDED TELEDYNE REVIEWS OVERHAUL PROCEDURES AND POINTS MOUNTING METHODS.				1	L	7	1 	3O	3	O		2A13    	E295
1998072400682	19980724	00682	CE  	1998	7	24	98ZZZX2461       	1	19980616	G	2434	991059111	ALTERNATOR      			CESSNA	172   	172R        	2072401	CE  										DC SYSTEM	SHORTED         	D				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	11	9572W	12   			A128671	17280544				ALTERNATOR FAILED DUE TO BATTERY AND GROUND WIRE TERMINALS BREAKING OFF AND SHORTING TO ALTERNATOR.  SUBMITTER STATED TE	RMINALS WEAK.  MATERIAL TOO THIN FOR GAUGE OF WIRE.					1	H	7	1 	3O			NT	3A12
1998072400683	19980724	00683	GL  	1998	7	24	98ZZZX2462       	1	19980618	G	5610	205600902	SPRING          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										CANOPY	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	96CF	900  				10157				NOISE WAS HEARD WHEN CANOPY WAS OPENED.  ONE OF THE CANOPY ASSIST SPRINGS BROKE AT THE BENT PORTION THAT ATTACHES TO THE	 ATTACH BRACKET.  SUBMITTER STATED THIS IS THE SECOND SPRING TO BREAK AT THE SAME LOCATION.  POSSIBLE POOR BENDING PROCE	DURE AT FACTORY.				1	L	7	1 	3O			NT	TA4CH
1998072400684	19980724	00684	CE  	1998	7	24	98ZZZX2463       	1	19980617	G	2410	07502201	BOLT            			CESSNA	182   	182S        	2072701	CE  										ALT MOUNT	MISSING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	4104D	39   				18280176				FOLLOWING FERRY FLIGHT FROM U.S. TO U.K., ALTERNATOR TENSIONING BOLT FOUND MISSING, AND MAIN MOUNTING BOLT FOUND LOOSE. 	 SUBSEQUENTLY, MAIN ATTACH BRACKET, STAY SUPPORT, AND ATTACH BOLT WERE FOUND WITH EXCESSIVE WEAR.  BELT TENSION WAS GOVE	RNED BY WEIGHT OF ALTERNATOR HANGING ON MULTI-RIB BELT.				1	H	7	1 	3O			NT	3A13
1998073000011	19980730	00011	SO  	1998	7	30	98ZZZX2464       	1	19980601	G	3230		BREAKER         			PIPER 	PA24  	PA24250     	7102404	SO  										MLG	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			NM	10										PILOT SELECTED GEAR DOWN.  GEAR REMAINED IN WHEEL WELL.  PILOT USED EMERGENCY SYSTEM TO LOWER GEAR.  LANDING FINE.  AFTE	R A LENGTHY TROUBLESHOOT, DETERMINED THE GEAR MOTOR CIRCUIT BREAKER WOULD CONDUCT CURRENT IN A NO-LOAD SITUATION.  UPON 	PLACING LANDING GEAR SELECTOR IN UP POSITION, CIRCUIT BREAKER WAS STOPPING ALMOST ALL CURRENT FLOW WITH NO BREAKER TRIPP	ING.  REPLACED 30-AMP CIRCUIT BRE AKER, GEAR CYCLES FINE.			1	L	7	1 	3O				1A15
1998072400685	19980724	00685	SO  	1998	7	24	98ZZZX2465       	2	19980625	G	8540	653236	DRIVE GEAR      			CESSNA	172   	R172E       	2072413	CE  	CONT  	O360  	IO360D      	17025	SO  					OIL PUMP	FAILED          	C	L	A		O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	09	24FC					R1720199	062942R			WHILE IN-FLIGHT, OIL PRESSURE AND TACHOMETER DROP TO ZERO, WAS ABLE TO LAND ON PRIVATE GRASS STRIP WITHOUT INCIDENT.  DE	TERMINED THE OIL PUMP DRIVE GEAR HAS FAILED CAUSING FAILURE OF OIL PUMP, TACH DRIVE AND ALTERNATOR GEAR.					1	H	7	1 	3O	3	O		3A17    	E1CE
1998072400686	19980724	00686	SO  	1998	7	24	98ZZZX2466       	1	19980625	G	3097		WIRE            			PIPER 	PA31T 	PA31T1      	7103126	SO  										COCKPIT	FAILED          	B			AQCR	H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	17	555AT					31T8104045				DURING PRE-FLIGHT GROUND CHECK,  COCKPIT FILLED WITH SMOKE AND NUMEROUS DE-ICE SYSTEM RELATED C/B'S TRIPPED.  PILOT SECU	RED SYSTEMS AND DEPARTED ACFT WITHOUT INCIDENT.  INSP OF ACFT FOUND CONNECTOR E462 IN FORWARD AVIONICS BAY HAD MELTED SH	ORTING THE 14 AWG WIRES FOR THE LIP DE-ICE TO THE ADJACENT 22 AWG PANEL.  THE 22 AWG WIRES MELTED THROUGH THEIR INSULATI	ON IN SEVERAL PLACES BETWEEN THE CONNECTOR IN THE FORWARD AVIONICS BAY AND THE OVERHEAD SWITCH PANEL.  UPON CLOSER INSP,	 PIPER SB NR 795A HAD BEEN C/W ALTHOUGH NO LOG ENTRY FOUND.   SB REQUIRES THE 14 AWG WIRE TO BE RUN THROUGH 3 PINS ON TH	E CONNECTOR.  SUBMITTER SUGGESTED THE 14 AWG WIRE BE REMOVED FROM THE CONNECTOR ALTOGETHER AND SPLICED INDEPENDENTLY.	1	L	7	2 	3T			 	A8EA
1998072400687	19980724	00687	EA  	1998	7	24	98ZZZX2467       	2	19980608	G	7314		GASKET          	ROMEC       	R69080J4A   	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					RELIEF VALVE	LEAK            	D	L	A		O				OTHER                   				B	K		SMOKE/FUMES/ODORS/SPARKS  	FLUID LOSS                		LD	LANDING        	1			EA	05	101MA				D8586	317752186	RL184768A			UPON LANDING, PILOT REPORTED SMELLING FUEL IN THE CABIN.  UPON INVESTIGATING THE SMELL, FOUND WHEN FUEL PUMPS AND EMERGE	NCY FUEL PUMP WERE TURNED ON, FUEL WAS LEAKING BADLY FROM THE GASKET AT THE RELIEF VALVE.  LYC SB 529 AND CRANE/LEAR ROM	EC SB 101SB020 COVERS THIS PROBLEM.  THIS AIRCRAFT HAD JUST COME OUT OF INSPECTION THREE HOURS BEFORE THIS HAPPENED AND 	THERE WAS NO FUEL LEAKAGE AND SCREWS WERE NOT LOOSE.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1998072400688	19980724	00688	SO  	1998	7	24	98ZZZX2468       	2	19980502	G	8530		CYLINDER        			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					NR 2	FAILED          	C				A				UNSCHED LANDING         				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			NM	11	6362E		8864 			46462	14384D9A			PILOT WAS IN NORMAL CRUISE WHEN HE HAD A SUDDEN POWER LOSS AND ENGINE VIBRATION.  AN UNEVENTFUL LANDING WAS MADE ON A RO	AD.  INVESTIGATION REVEALED THE NR 2 CYLINDER HAD SEPARATED ABOUT 2 INCHES FROM THE ENGINE CASE.  THE SEPARATION WAS THR	OUGH THE STEEL PORTION OF THE BARREL.  THE PISTON WAS DESTROYED AND THE CONNECTING ROD BENT.  UNKNOWN WHAT ADDITIONAL IN	TERNAL DAMAGE MAY BE DISCOVERED AT ENGINE DISASSEMBLY.  CAUSE OF THIS IS UNKNOWN.  THE TOTAL TIME ON THIS ENGINE IS 3,59	3 HOURS AND IT IS NOT KNOWN IF THIS IS AN ORIGINAL CYLINDER.		1	H	7	1 	3O	3	O	NT	3A12    	E253
1998072400690	19980724	00690	GL  	1998	7	24	98ZZZX2470       	1	19980527	G	5310		STRUCTURE       			AMTR  	KITFOX	KITFOX      	05613LZ	GL  										LT MLG	FAILED          	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	560GR					560				THE FUSELAGE BUCKLED IN THE AREA OF THE LEFT LANDING GEAR.  INSPECTION REVEALED THE DIAGONAL TUBE COMPLETELY BROKE JUST 	ABOVE THE WELD.  ALL INDICATIONS ARE THE WELD WAS TOO HOT WHEN THE FUSELAGE WAS WELDED AT THE FACTORY CAUSING THE BRITTL	ENESS.				1	H	7	1 	3I			NC	EXPA1H71
1998072400691	19980724	00691	GL  	1998	7	24	98ZZZX2471       	2	19980617	G	7250	23008020	TIE BOLT        		6898735     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE 2ND STG	FAILED          	H		A	CUFL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	2944W	1246 			CAT22774	748	CAE833715			DURING AN ACCIDENT INVESTIGATION ON A BELL 206B2 CONVERTED TO B3, NOTED THE ENGINE TURBINE, 2ND STAGE WHEEL FLY-AWAY DAM	AGING THE HELICOPTER FUSELAGE.  FURTHER INVESTIGATION REVEALED THE TIE-BOLT BROKE ABOUT .25 INCH FROM THE THREADED AREA.	  THE TIE-BOLT WAS REPLACED PER CEB 1212 DURING THE TURBINE HEAVY MAINTENANCE INSPECTION.  TO PREVENT RECURRENCE, SUBMIT	TER SUGGESTED THIS TIE-BOLT BE GIVEN A THOROUGH INSPECTION.  FOR SIGN OF CORROSION AND CRACKS, USE FLUORESCENT PENETRANT	 INSPECTION METHOD AT TURBINE HEAVY MAINTENANCE INSPECTION OR WHENEVER THE GAS PRODUCER TURBINE IS REMOVED FOR ANY REASO	N.	1	G	7	1 	3U	3	U		H2SW    	E4CE
1998072400693	19980724	00693	SW  	1998	7	24	98ZZZX2473       	1	19980130	G	6510	206040365001	SHAFT           			BELL  	206   	206L1       	1182107	SW  										T/R	FAILED          	H		A		O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			SW	03	3904L					45597				THE AIRCRAFT LOST DIRECTIONAL CONTROL DURING LANDING TO AN OFFSHORE PLATFORM. THE PILOT WAS ABLE TO EXECUTE A SUCCESSFUL	 AUTOROTATIONAL LANDING TO THE PLATFORM WITHOUT CAUSING DAMAGE TO THE AIRCRAFT.  INVESTIGATION OF THE INCIDENT REVEALED 	THAT THE BONDED COUPLING ON THE NR 5 TAIL ROTOR DRIVESHAFT FAILED.  ENGINEERING EVALUATION OF THE SHAFT REVEALED THAT TH	E SHAFT HAD APPARENTLY BEEN SUBJECTED TO SAND BLASTING, WHICH, IN TURN, MAY HAVE LED TO THE DISBONDING OF THE COUPLING.			1	G	7	1 	3U				H2SW
1998072400694	19980724	00694	NE  	1998	7	24	98ZZZX2474       	2	19980603	G	7310	416198001	TUBE            			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENG FUEL AFT	FAILED          	H				K				NONE                    				K	Y		FLUID LOSS                	ENGINE STOPPAGE           		IN	INSP/MAINT     	1			SW	99	967LS					7067	LE45224			DURING ENGINE COOL DOWN PERIOD, THE ENGINE SHUT DOWN ON ITS OWN.  THE MAIN FUEL LINE (AFT REAR) TO THE MANIFOLD HAD CRAC	KED JUST BEHIND THE FLARE AT THE MANIFOLD CONNECTION, HALF OF THE CIRCUMFERENCE.					1	G	7	2 	3U	3	U		H13EU   	E5NE
1998072400695	19980724	00695	NE  	1998	7	24	98ZZZX2475       	1	19980604	G	3240	50075551	BRAKE ASSY      			SKRSKY	S76   	S76C        	8143008	NE  										LT MLG WHEEL	DEFECTIVE       	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	165ML	224  				760471				WHEEL ASSEMBLY DID NOT ROTATE FREELY.  FOUND THAT RIVET FROM BRAKE ASSY BROKEN OFF AND DISLODGED BETWEEN BRAKE ASSY AND 	WHEEL ASSY.  WHEEL ASSY WAS DAMAGED BEYOND REPAIR (INNER WHEEL HALF ONLY).					1	G	7	2 	3U			NC	H1NE
1998072400696	19980724	00696	WP  	1998	7	24	98ZZZX2476       	1	19980605	G	7810	369A8230504	EXHAUST         			HUGHES	369   	369D        	4470706	WP  										RT STACK	CRACKED         	B	S		EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING AN ANNUAL INSPECTION, THE RIGHT HAND EXHAUST STACK WAS FOUND CRACKED ON THE INSIDE DIAMETER OF THE ELBOW FOR ABOU	T 5 INCHES FORWARD AND INTO THE FLANGE THAT CONTACTS THE ENGINE EXHAUST COLLECTOR.  REPLACED STACK.					1	G	7	1 	3U				H3WE
1998072400697	19980724	00697	WP  	1998	7	24	98ZZZX2477       	1	19980605	G	2810	369A8101	COVER PLATE     		369H81015   	HUGHES	369   	369D        	4470706	WP  										FUEL CELL	LOOSE           	B			EOOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AL	03	5074R	8793 				1151D				DURING AN ANNUAL INSPECTION, A FUEL LEAK FROM THE AIRCRAFT BELLY WAS NOTED.  SUBSEQUENT INSPECTION FOUND THE RIGHT HAND 	FUEL CELL COVER BOLTS (THUS THE COVER) WERE LOOSE.  INSPECTED SEAL AND RETORQUED.					1	G	7	1 	3U				H3WE
1998072400698	19980724	00698	WP  	1998	7	24	98ZZZX2478       	1	19980605	G	6220	369A13063	BEARING         		369D21200   	HUGHES	369   	369D        	4470706	WP  										M/R HUB	WORN            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		1105 		1694	1151D				DURING AN ANNUAL INSPECTION OF THE MAIN ROTOR, ALL PIVOT BEARINGS WERE FOUND WORN BEYOND LIMITS AND ONE FAR ENOUGH TO WE	AR INTO AND SCRAPPING ONE OF THE PIVOT PINS.  REPLACED AFFECTED PARTS.					1	G	7	1 	3U				H3WE
1998072400699	19980724	00699	WP  	1998	7	24	98ZZZX2479       	1	19980605	G	6220	369D21248	PIVOT PIN       		369D21200   	HUGHES	369   	369D        	4470706	WP  										M/R HUB	WORN            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		1105 		1694	1151D				DURING AN ANNUAL INSPECTION OF THE MAIN ROTOR, ALL PIVOT BEARINGS WERE FOUND WORN BEYOND LIMITS AND ONE FAR ENOUGH TO WE	AR INTO AND SCRAPPING ONE OF THE PIVOT PINS.  REPLACED AFFECTED PARTS.					1	G	7	1 	3U				H3WE
1998072400700	19980724	00700	WP  	1998	7	24	98ZZZX2480       	1	19980605	G	6322	369D25621	PULLEY GUARD    		369D25100701	HUGHES	369   	369D        	4470706	WP  										OIL COOLER FAN	WORN            	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		956  		1810	1151D				DURING AN ANNUAL INSPECTION, THE OIL COOLER BLOWER PULLEY GUARD ON THE M/R TRANSMISSION WAS FOUND TO BE SEVERELY WORN IN	 THE AREA OF THE BLOWER BELT.  NO EVIDENCE OF BELT DAMAGE.  REPLACED PULLEY GUARD.					1	G	7	1 	3U				H3WE
1998072400701	19980724	00701	WP  	1998	7	24	98ZZZX2481       	1	19980605	G	7810	369A8232	SPRING          			HUGHES	369   	369D        	4470706	WP  										EXH CLAMP	BROKEN          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING AN ANNUAL INSPECTION, THE AFT EXHAUST CLAMP RETAINING SPRING WAS FOUND BROKEN.  REPLACED SPRING.						1	G	7	1 	3U				H3WE
1998072400702	19980724	00702		1998	7	24	98ZZZX2482       	4	19980605	G	2350	A21815869805	SWITCH          			HUGHES	369   	369D        	4470706	WP  										COMM TRANSMIT	FAILED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R	8793 				1151D				PILOT COMPLAINED THE TRANSMIT SWITCH WOULD STICK PERIODICALLY.  REPLACED SWITCH.						1	G	7	1 	3U				H3WE
1998072400703	19980724	00703	GL  	1998	7	24	98ZZZX2483       	2	19980605	G	7510	2060626253	ACTUATOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE ANTI-ICE	FAILED          	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R		468  			1151D	CAE832750			DURING AN ANNUAL INSPECTION OF THE ENGINE ANTI-ICE VALVE SYSTEM, FOUND THE ACTUATOR ERRATIC (THIS AIRCRAFT HAS BEEN MODI	FIED, BY FIELD APPROVAL, FOR INSTALLATION OF THE BELL HELICOPTER 206B ENGINE ANTI-ICE ACTUATOR SYSTEM).  REPLACED ACTUAT	OR.				1	G	7	1 	3U	3	U		H3WE    	E4CE
1998072400704	19980724	00704	WP  	1998	7	24	98ZZZX2484       	1	19980605	G	6710		CYCLIC STICK    			HUGHES	369   	369D        	4470706	WP  										FLT CONTROL	LOOSE           	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING AN ANNUAL INSPECTION WHILE PERFORMING THE CYCLIC STICK SLACK INSPECTION, THE LATERAL PIVOT BOLT WAS FOUND LOOSE C	AUSING FORE AND AFT SLACK.  REPLACED BEARINGS AND RETORQUED THE BOLT.					1	G	7	1 	3U				H3WE
1998072400705	19980724	00705	WP  	1998	7	24	98ZZZX2485       	1	19980605	G	7714		CONNECTOR       			HUGHES	369   	369D        	4470706	WP  										N2 TACH GEN	DEFECTIVE       	B			EOOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5074R					1151D				DURING AN ANNUAL INSPECTION, THE N2 TACHOMETER GENERATOR PLUG WAS FOUND TO HAVE BUT ONE STRAND REMAINING ON ONE OF THE W	IRES.  REPAIRED WIRE/PLUG.					1	G	7	1 	3U				H3WE
1998072400706	19980724	00706	NM  	1998	7	24	98ZZZX2486       	1	19980602	G	5313		STRINGER        			BOEING	727   	727232      	1384082	NM  										BS 1070-1090	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	16784					20639				DURING C-CHECK, GOUGES WERE NOTED ON STR 7L BETWEEN STA 1070 AND STA 1090.						2	L	7	3 	4F				A3WE
1998072400707	19980724	00707	NM  	1998	7	24	98ZZZX2487       	1	19980602	G	5330		SKIN            			BOEING	727   	727232      	1384082	NM  										BS 380	DENTED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	16784					20639				DURING C-CHECK, AN OUT OF LIMITS DENT WAS NOTED AT STA 380 BETWEEN S19R AND S20R.						2	L	7	3 	4F				A3WE
1998072400708	19980724	00708	NM  	1998	7	24	98ZZZX2488       	1	19980602	G	5330		SKIN            			BOEING	727   	727232      	1384082	NM  										BS 1153	CRACKED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	16784					20639				DURING C-CHECK, THE RIGHT HAND FUSELAGE SKIN WAS NOTED CRACKED AT STA 1153 BETWEEN S11R AND S12R.						2	L	7	3 	4F				A3WE
1998072400709	19980724	00709	NM  	1998	7	24	98ZZZX2489       	1	19980602	G	5320		SUPPORT BEAM    			BOEING	727   	727232      	1384082	NM  										RT MLG AFT	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	16784					20639				DURING C-CHECK, THE INBOARD LOWER AFT SECTION OF RIGHT HAND MAIN LANDING GEAR SUPPORT BEAM WAS NOTED TO BE GOUGED.						2	L	7	3 	4F				A3WE
1998072400710	19980724	00710	NM  	1998	7	24	98ZZZX2490       	1	19980602	G	5280		HINGE FITTING   			BOEING	727   	727232      	1384082	NM  										LT MLG DOOR	GOUGED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5280					20639				DURING C-CHECK, THE LEFT MAIN LANDING GEAR OUTBOARD DOOR HINGE FITTING WAS NOTED GOUGED.						2	L	7	3 	4F				A3WE
1998072400711	19980724	00711	NM  	1998	7	24	98ZZZX2491       	1	19980602	G	5510		BEAM            			BOEING	727   	72727       	138400K	NM  										LT STAB STA 99	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	16784					20639				DURING C-CHECK, EXFOLIATION CORROSION ON LEFT HORIZONTAL UPPER TRAILING EDGE BEAM BETWEEN STA 99.8 AND STA 136.5.						2	L	7	3 	4F				A3WE
1998072400712	19980724	00712	NM  	1998	7	24	98ZZZX2492       	1	19980602	G	5330		SKIN            			BOEING	727   	727232      	1384082	NM  										RT AFT FUSELAGE	DAMAGED         	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	16784					20639				DURING C-CHECK, THE NR 2 ENGINE SUPPORT SKIN PANEL WAS NOTED DAMAGED.						2	L	7	3 	4F				A3WE
1998072400713	19980724	00713	SW  	1998	7	24	98ZZZX2493       	1	19980610	G	5610	36004312SS	WINDSHIELD      	PPG         		GULSTM	690TP 	695         	7630518	SW  										COPILOT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	218MS					95041				COPILOT'S WINDSHIELD DEVELOPED CRACKS ALONG THE HEATING ELEMENTS ON OUTSIDE PANE OF GLASS.  THIS WINDSHIELD WAS MANUFACT	URED 1/96 AND HAS A TOTAL TIME OF 642.2 HOURS.  WINDSHIELD MANUFACTURED BY PPG.					1	H	7	2 	3T				2A4
1998072400714	19980724	00714	NM  	1998	7	24	98ZZZX2494       	1	19980512	G	3230	ARG72331	CRANK ASSY      			DOUG  	MD11  	MD11        	3023602	NM  										LT MLG	FAILED          	B				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	489GX	16241				48458				AFTER TAKEOFF AND GEAR RETRACTION, RED UNSAFE LIGHT ON, LEFT MAIN LANDING GEAR REMAINS ILLUMINATED, LANDING GEAR RECYCLE	D.  ONCE CONDITION REMAINS, VISUALLY CHECK LANDING GEAR IS UP AND LOCKED.  CONTINUE FURTHER FLIGHT.  FCO GROUND FOUND LT	 GEAR CRANK ASSY, SENSOR SUPPORT, PN ARG 72331, BROKEN, AND SENSOR MISSING, CRACK ASSY SENSOR ASSY WITH CABLE REPLACED A	ND ADJUSTED PER MM 32-61-15 P410.  FUNCTIONAL CHECK NORMAL.			2	L	7	3 	4F			RT	A22WE
1998072400715	19980724	00715	EA  	1998	7	24	98ZZZX2495       	1	19980601	G	3213	13A04000058	AXLE            	WIPLINEINC  	13003       	DHAV  	DHC6  	DHC6300     		EA  										LT/RT MLG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	167WC	527  				343				DURING MAIN WHEEL AND TIRE CHANGE, FOUND INBD AXLE DRAG LINK ASSY CRACKED THROUGH BRAKE TORQUE PLATE BOLT HOLES ON INBD 	AXLES ON BOTH LT AND RT GEAR ASSY.  SUSPECT STRESS CORROSION.  STEEL AXLE IN ALUMINUM CASTING.  AIRCRAFT OPERATES IN SAL	T WATER AREA.				1	H	7	2 	3T				A9EA
1998072400716	19980724	00716	EA  	1998	7	24	98ZZZX2496       	1	19980601	G	3213	13A04000058	AXLE            	WIPLINEINC  	13004       	DHAV  	DHC6  	DHC6300     		EA  										LT/RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	167WC	527  				343				DURING MAIN WHEEL AND TIRE CHANGE, FOUND INBD AXLE DRAG LINK ASSY CRACKED THROUGH BRAKE TORQUE PLATE BOLT HOLES ON INBD 	AXLES ON BOTH LT AND RT GEAR ASSY.  SUSPECT STRESS CORROSION.  STEEL AXLE IN ALUMINUM CASTING.  AIRCRAFT OPERATES IN SAL	T WATER AREA.				1	H	7	2 	3T				A9EA
1998072400717	19980724	00717	WP  	1998	7	24	98ZZZX2497       	2	19980515	G	7321	21011445	EEC             			AMD   	FALC50	FALCON50MYST	2730106	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	XAAVE				117755	022	P76193			EEC WAS CONNECTED TO BENCH TEST EQUIPMENT TO ADJUST EFR SETTING.  AFTER EEC WARM-UP PERIOD PRIOR TO ADJUSTING EFR, THE T	ECHNICIAN FOUND THE EEL WAS NOT FUNCTIONING.  A REVIEW OF THE TEAR DOWN/REPAIR REPORT REVEALED THE EEC HAD BEEN REMOVED 	FROM SERVICE FOR THE SAME REASON THE TECHNICIAN FOUND WHILE ATTEMPTING TO BENCH SET THE EPR SETTING.  IT WAS FURTHER NOT	ED THAT THERE WAS NO REPAIRS ACCOMPLISHED TO THIS EEC.  THE FAA FORM 8130-3 STATED INSPECTION ONLY.			2	L	7	3 	4F	4	F		A46EU   	E6WE
1998072400718	19980724	00718	SO  	1998	7	24	98ZZZX2498       	1	19980619	G	5411	1202170	FRAME           			EMB   	120   	EMB120RT    		SO  										LT ENG MACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	212AS					120008				DURING C-CHECK INSPECTION, NR 1 FRAME ON LEFT ENGINE NACELLE WAS FOUND CRACKS IN WEB APPROXIMATELY 5 INCHES OUTBOARD OF 	MOUNT HOLES FOR LEFT AND RT SIDE OF ENGINE FORWARD TORQUE MOUNT.  RIGHT NACELLE WAS ALSO FOUND TO HAVE A CRACK IN THE SA	ME AREA ON THE OTBD SIDE OF TORQUE MOUNT.				2	L	7	2 	4T			RT	A31SO
1998080700002	19980807	00002	SW  	1998	8	7	98ZZZX2530       	1	19980530	G	5510	206023119110	SUPPORT         			BELL  	407   	407         		SW  										HORIZ STAB RT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	2365 				53054				AFTER BEING NOTIFIED THAT ONE OTHER AIRCRAFT IN FLEET HAD LOST ITS SLAT, C/W A VISUAL INSPECTION AND FOUND THE HORIZONTA	L STABILIZER SLAT SUPPORT ON THE RT SIDE CRACKED.  TWO EACH.  TWO OUTBOARD SLAT SUPPORTS CRACKED IN RADIUS ARE OF SUPPOR	T TO HORIZONTAL STABILIZER MOUNTING AREA.				1	G	7	1 	3U			O	H2SW
1998080700003	19980807	00003	GL  	1998	8	7	98ZZZX2531       	2	19980608	G	7210	6893672	PINION GEAR     		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	850  			NN76206	53203	CAE847197			UPON DISASSEMBLY AND INSPECTION OF PARTS, FOUND EXCESSIVE GALLING ON PINION GEAR AND SPALLING ON T/M GEAR.  PINION GEAR 	HAD EXCESSIVE GALLING ON GEAR TEETH.  POSSIBLY DUE TO IMPROPER MESHING OF GEARS.  SECONDARY DAMAGE.  T/M GEAR PN 689367.	  SN NN144843, TT:  849.6 HOURS.  SPALLING GEAR TEETH.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998080700004	19980807	00004	GL  	1998	8	7	98ZZZX2532       	2	19980608	G	7250	23032328	ROTATING SEAL   		23063354    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					NR 5	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	850  				53203	CAE847189			ENGINE WAS REMOVED FOR MAKING METAL.  REMOVED NR 5 BEARING AND FOUND METAL IN BEARING CAVITY.  REMOVED NR 5 BEARING FOR 	INSPECTION AND FOUND METAL SLIVERS UNDER NR 5 BEARING NUT AND CAP LOCK WASHER.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998080700005	19980807	00005	GL  	1998	8	7	98ZZZX2533       	2	19980608	G	7250	6871505	BEARING         		23063354    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					NR 5	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	1164 			MP74698	53044	CAE847170			ENGINE WAS REMOVED FOR MAKING METAL.  INSPECTED AND FOUND GALLING ON NR 5 BEARING AND METAL SLIVERS UNDER NR 5 BEARING N	UT AND CUP WASHER.  ALSO FOUND NR 5 BEARING INTERNAL OUTER RACE DETERIORATING.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998080700006	19980807	00006	GL  	1998	8	7	98ZZZX2534       	2	19980608	G	7210	689672	PINION GEAR     		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	1565 			NN75495	53107	CAE847125			UPON DISASSEMBLY OF GEARBOX AND INSPECTION OF PARTS DUE TO METAL, FOUND PINION GEAR HAD EXCESSIVE GALLING ON GEAR TEETH.	  POSSIBLY DUE TO IMPROPER MESHING OF GEARS.  SECONDARY DAMAGE:  T/M GEAR P/N 6893673 S/N NN143321.  TT:  15,65.3 HOURS.	  SPALLING ON GEAR TEETH.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998080700007	19980807	00007	SW  	1998	8	7	98ZZZX2535       	1	19980530	G	5510	206023119109	SUPPORT         			BELL  	407   	407         		SW  										HORIZ STAB LT	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	2365 				53107				AFTER BEING NOTIFIED THAT ONE OTHER AIRCRAFT IN FLEET HAD LOST ITS SLAT, C/W A VISUAL INSPECTION AND FOUND THE HORIZONTA	L STABILIZER SLAT SUPPORT AT THE MID-INBOARD SUPPORT CRACKED ON THE LT SLAT.  ONE EACH.  ONE MID-INBOARD SLAT SUPPORTS C	RACKED IN RADIUS AREA OF SUPPORT TO HORIZONTAL STABILIZER MOUNTING AREA.				1	G	7	1 	3U			O	H2SW
1998080700008	19980807	00008	GL  	1998	8	7	98ZZZX2536       	2	19980608	G	7250	6871505	BEARING         		23063354    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					FWD NR 5	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	567AL	282  			MP74957	53246	CAE847271			ENGINE REMOVED FOR MAKING METAL.  UPON INSPECTION BEARINGS FOUND BAD NR 5 BEARING.  SOURCE OF METAL WAS CAUSED BY GEARBO	X TORQUE METER AND PINION GEAR DETERIORATING.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998080700009	19980807	00009	GL  	1998	8	7	98ZZZX2537       	2	19980505	G	7322	2537739	VALVE SLEEVE    	BENDIX      	23059933    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30      	03013	GL  					FUEL CONTROL	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5427S	4475 	1987 			760168				DURING OVERHAUL OF FUEL CONTROL, FOUND BONDING MATERIAL ON VALVE SLEEVE BROKEN.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998080700010	19980807	00010		1998	8	7	98ZZZX2538       	4	19980613	G	2561	ACRL81A	RESCUE LIGHT    			SKRSKY	S76   	S76         	8143010	NE  										LIFE VEST	DEFECTIVE       	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5403C	14581				760141				UPON COMPLETION OF LIFE VEST INSPECTION (12 EACH), EVERY RESCUE LIGHT WITH A MNAUFACTURE DATE OF JUNE, 1997, HAD FAILED 	DUE TO CASE SWELLING (9 EACH) AFTER ONLY 3 MONTHS IN SERVICE.  OTHER LIGHTS WITH DIFFERENT MANUFACTURE DATES DID NOT FAI	L DURING THE SAME 3 MONTH PERIOD.				1	G	7	2 	3U				H1NE
1998080700012	19980807	00012	WP  	1998	8	7	98ZZZX2540       	1	19980605	G	2435	23032027	STARTER         			HUGHES	369   	369D        	4470706	WP  										START/GEN	FAILED          	B			LS1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	13	369AW		692  			470117D				SHOOTS SPARKS OUT OF THE TOP.  SENT FOR REPAIR EVALUATION.  REF:  CONTROL NR 98-62.						1	G	7	1 	3U				H3WE
1998080700013	19980807	00013	SW  	1998	8	7	98ZZZX2541       	1	19980609	G	6720	206011809107	HORN            			BELL  	206   	206L1       	1182107	SW  										T/R PITCH CHANGE	MISMANUFACTURED 	B		A	ZV1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2611					45417				INSTALLED OVERHAULED T/R HUB AND BLADES ON AIRCRAFT.  NOTICED AFTER RIGGING T/R HORNS, P/N 206-011-809-107, THEY WERE CO	NTACTING T/R HUB, P/N 206-011-810-139.  REMOVED AND REPLACED ASSY.  INSPECTION OF REMOVED UNITS AND OF UNITS IN STOCK SH	OWED THAT MACHINING OF HUBS AND HORNS IS NOT CONSISTANT.  SUGGEST TRAIL AND ERROR METHOD OF MATCHING UP HORNS TO HUBS OR	 CHANGE TO USING 206-011-809-109 HORNS.			1	G	7	1 	3U				H2SW
1998080700014	19980807	00014	WP  	1998	8	7	98ZZZX2542       	1	19980617	G	7900	369A8324	VALVE           			HUGHES	369   	369D        	4470706	WP  										RT CABIN PANEL	SEEPING         	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	369AW				252410	470117D				VALVE SEEPING.  REMOVED FROM AIRCRAFT AND DESTROYED.						1	G	7	1 	3U				H3WE
1998080700015	19980807	00015	SW  	1998	8	7	98ZZZX2543       	1	19980617	G	3340	010770062A49A	POWER BOX       	WHELEN      		BELL  	206   	206B        	1181511	SW  										STROBE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718				01404	1917				WOULD NOT GENERATE POWER OUTPUT.  SEND FOR REPAIR EVALUATION.						1	G	7	1 	3U				H2SW
1998080700220	19980807	00220	SW  	1998	8	7	98ZZZX2557       	1	19980602	G	5744		MOUNT           			GULSTM	500   	500S        	0141107	SW  										RT FLAP INBD	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	900RA					3070				CRACK IN AIRFRAME ACROSS AREA WHERE FLAP HINGE BRACKET BOLTS ON.  FOUND ON RT WING, OUTBOARD FLAP SEGMENT, INBOARD MOUNT	.  CRACK VISABLE WITH NAKED EYE.  CRACK 1.25 INCHES LONG, BOTH DOUBLER AND SKIN.  TOTAL TIME AIRFRAME:  APPROXIMATELY 6,	805.4 HOURS.				1	H	7	2 	3O				6A1
1998080700221	19980807	00221	EU  	1998	8	7	98ZZZX2558       	1	19980615	G	2700		FLIGHT CONTROL  			BAC   	146   	AVRO146RJ100	1500096	EU  										PITCH	OSCILLATION     	H				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SO	19	504MM					E3221				CLO/ADZ - FLT 1176 - STRONG PITCH OSCILLATION WAS FELT DURING FLIGHT.   LEVELLED AT FL 240, SPEED 260 KNOTS, ENGINE ANTI	ICE ON.  OUTER WING AND TAIL ANTI-ICE ON.  CHECK LIST WAS PERFORMED.  VISUAL INSPECTION PERFORMED ON ELEVATORS AND CONTR	OL SYSTEM.  OPERATIONAL CHECK RESULTS NORMAL.  NO VISUAL DAMAGE ON ELEVATOR AND ALL DRAIN HOLES WERE CLEAR, GUST DAMPER 	INSPECTED AND FOUND OK.  PLEASE KEEP UNDER OBSERVATION AMM REF 27-31-21 PAGE 501 AND 27-30-31 PAGE 201.			2	H	7	4 	4F			RT	A49EU
1998080700222	19980807	00222	EA  	1998	8	7	98ZZZX2559       	2	19980630	G	8520		CRANKSHAFT      			PIPER 	PA18  	PA18135     	7101820	SO  	LYC   	O360  	O360A1A     	41514	EA  					NR 4 ROD JOURNAL	FAILED          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	25	3257B		472  			183275	L473636A			AIRCRAFT SUFFERED CATASTROPHIC ENGINE SEIZURE.  MADE SUCCESSFUL GOLF COURSE LANDING.  ENGINE DISASSEMBLY RECEIVED BROKEN	 CRANKSHAFT AT THE FORWARD SIDE OF NR 4 ROD JOURNAL.					1	H	7	1 	3O	3	O		1A2     	E286
1998080700223	19980807	00223	EU  	1998	8	7	98ZZZX2560       	1	19980629	G	3234	643500100	SELECTOR SWITCH 			BAC   	146   	AVRO146RJ100	1500096	EU  										MLG	MALFUNCTIONED   	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	19	508MM				3096	E3247				FLT 596 - AIR TURN BACK.  WHEN THE LANDING GEAR LEVER IS SELECTED UP, THE LEVER STICKS AND A STRIKE OF THE GEAR.  WHEN S	ELECTED UP, STILL CONTINUED AND GOT WORSE.  LANDING GEAR SELECTOR SWITCH WAS CHANGED AND PERFORMED TEST IAW AMM 32-30-14	, PAGE 201.  AIRCRAFT WAS JACKED AND PERFORMED VISUAL INSPECTION OF MLG AND NLG WHEEL WELL PAYING ATTENTION TO DOOR HITS	, DENTS, SCRATCHES, ETC.  PERFORMED AUXILIARY BRAKES SYSTEM TEST IAW AMM 32-41-91, PAGE 501, AND WHEEL BALANCE CHECK.  L	ANDING GEAR CYCLES UP AND DOWN IAW AMM 32-10-14, PAGE 301.		2	H	7	4 	4F			RT	A49EU
1998080700224	19980807	00224	NE  	1998	8	7	98ZZZX2561       	2	19980601	G	7210		GEARBOX         			EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  					REDUCTION GRBOX	CHAFED          	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	212AS				RGB115001	120008	PCE115001			ON REDUCTION GEARBOX JUST IN FRONT OF RIGHT FORWARD ENGINE MOUNT FORWARD LOWER BOLT HOLE, THERE IS A CHAFE MARK .958 INC	H BY .480 INCH.  DEEPEST SPOT IS .098 INCH CAUSED BY MISLOCATED BONDING WIRE FROM NACELLE TO ENGINE.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998080700226	19980807	00226	NM  	1998	8	7	98ZZZX2562       	1	19980702	G	3350	P2070003001	FLASHLIGHT      			BOEING	737   	7372H5      	138448E	NM  										BATTERY	FAILED          	H				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	05	220US					20453				DURING PRE-FLIGHT CHECK, THE F/A REPORTED THAT ONE OF THE 2 FLASHLIGHTS IN THE AFT GALLEY DID NOT BLINK WITHIN THE REQUI	RED 7 SECONDS.  PLACED FLASHLIGHT ON MEL 25-12.					2	L	7	2 	4F				A16WE
1998080700227	19980807	00227	CE  	1998	8	7	98ZZZX2563       	1	19980519	G	7120		BOLT            			BEECH 	100   	B100        	1152919	CE  										ENGINE MOUNT	LOOSE           	E				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			GL	09	108EB	5605 				BE108				REPORT IN C/W WITH FAR 135.415 (5). UPON LANDING WHEN THE PROP'S WERE CYCLED INTO BETA (REVERSE) A FEW SECONDS LATER, SM	OKE ENTERED CABIN.  UPON INSPECTION OF AIRCRAFT AND ENGINES, FOUND THE PIN THAT IS INSTALLED IN THE ENGINE TRUSS TUBES T	O SEAL THE ACCESS HOLE FOR THE INSTALLATION OF ANTI-CORROSION COMPOUND WAS LOOSE.  ANTI-CORROSION COMPOUND WAS LEAKING A	ND BEING VAPORIZED (SMOKE) BY EXHAUST.  UPON BRINGING PROP TO BETA, AIR WAS DRAWN FORWARD INTO ENGINE INLET AND INTO ENV	IRONMENTAL SYSTEM AND THE SMOKE ENTERED CABIN.  REMOVED LOOSE PIN, CLEANED AREA, REINSTALLED PIN WITH STRUCTURAL ADHESIV	E SEALANT PER PROCEDURES PROVIDED BY RAYTHEON TECH SUPPORT.	1	L	7	2 	4T				A14CE
1998080700228	19980807	00228	EU  	1998	8	7	98ZZZX2564       	1	19980722	G	2910	MY20751763	LINE            			AMD   	FALCON	FALCON20    	2730103	EU  										AUXILIARY PUMP	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	250RA	2004 				481				UPON RETURN TO AIRCRAFT, HYDRAULIC FLUID WAS DRIPPING DOWN SIDE OF PLANE.  INVESTIGATION FOUND CRACKED LINE BY THE AUXIL	IARY PUMP.  REPLACED LINE AND WAS FIXED.					2	L	7	2 	4F			RT	A7EU
1998080700229	19980807	00229	NE  	1998	8	7	98ZZZX2565       	3	19980622	G	6111	6607132886	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  						ROTOL	R389	R3894123F25 	NE  	OUTER SLEEVE	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		22775	3451 		SF340132442			DRG743686		DURING INSPECTION FOR REPAIR, NOTED THAT BLADE, SN SF340-132/442, HAD A CRACK VISABLE IN OUTER SLEEVE.  PROPELLER AND BL	ADE REMOVED FROM AIRCRAFT BY CUSTOMER DUE TO REPORT OF VIBRATION IN PROPELLER BLADE.  REJECTED FROM FURTHER SERVICE AT T	HIS STATION.				2	L	7	2 	4T			RT	A52EU   		6	C	P30NE
1998080700231	19980807	00231	CE  	1998	8	7	98ZZZX2567       	1	19980323	G	5610	10138402515	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  										LEFT	CRACKED         	B			EBVR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			GL	09	552TP	2811 			9221645163	FL1				DURING CRUISE AT 24,000 MSL, WINDSHIELD CRACKED.  CRACKING PROPAGATED INTO MULTIPLE SPIDERWEB CRACKS WHICH ENCOMPASSED E	NTIRE WINDSHIELD AREA ON INSIDE PANE.  WINDSHIELD WAS INSTALLED 12-18-92.					2	L	7	2 	4T			RT	A24CE
1998080700232	19980807	00232	NM  	1998	8	7	98ZZZX2568       	1	19980722	G	2913	40183	PUMP            			ISRAEL	1125  	1125        		NM  										NR 2 ENGINE	LEAK            	B			QRRR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	705MA				AH6580A	011				UPON ENGINE SHUTDOWN, PUMP STARTED TO LEAK FLUID OUT TO THE DRAIN MAST.  PUMP CONTINUED TO LEAK.  REPLACED PUMP WITH NEW	.  RECOMMENDED A RESEAL OR OVERHAUL OF PART.					2	L	7	2 	4F			RT	A16NM
1998080700233	19980807	00233	EA  	1998	8	7	98ZZZX2569       	2	19980413	G	8520	72877	TAPPET          			BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  					NR 3 CYL INTAKE	BROKEN          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	21	901VL	8686 	7    			1003	L1967440AC			DURING DAILY CHECK, MECHANIC FOUND EXCESSIVE OIL LEAK ON LEFT ENGINE.  COWLING REMOVED AND FOUND NR 3 CYLINDER INTAKE PU	SH HOUSING BROKEN.  AFTER REMOVAL OF HOUSING, FOUND HYDRAULIC TAPPET BODY BROKEN.  ENGINE REMOVED TO INVESTIGATE.  MORE 	INFORMATION WILL BE SUBMITTED WHEN REPAIR STATION INVESTIGATES.				1	H	7	3 	3O	3	O		A29EU   	E295
1998080700236	19980807	00236	NE  	1998	8	7	98ZZZX2572       	2	19980106	G	7240	729237	COMBUSTION CASE 			BOEING	747   	747*        		NM  	PWA   	JT9   	JT9D7J      	52054	NE  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		66900	12030		BD5083	FGPJM	662446			FPI INSPECTION OF THIS CASE FOUND A 360 DEGREE CIRCUMFERENTIAL CRACK INDICATION ON THE FRONT FLANGE.  EDDY CURRENT INSPE	CTION FOUND AN INDICATION AROUND 20 PERCENT OF THE CIRCUMFERENCE.  P & W HAVE BEEN ASKED TO INVESTIGATE THIS CASE AS PRO	PAGATION OF THIS CRACK WOULD HAVE CAUSED A RUPTURE EVENT.				2	L	7	4 	4F	4	F	RT	A20WE   	E20EA
1998080700239	19980807	00239	NE  	1998	8	7	98ZZZX2573       	2	19980606	G	7210	664643	GEARBOX         			BOEING	727   	727251      	138408H	NM  	PWA   	JT8   	JT8D15      	52051	NE  					ENG OIL LINE	LEAK            	B			EB1R	E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	279US				0162	21158	P700522B			PRECAUTIONARY SHUTDOWN NR 3 ENG.  ENG LOW OIL PRESS LIGHT ILLUMINATED WHILE LANDING, OIL QTY GAUGE READS ZERO.  ENG OIL 	PRESS LOW.  COWLING OPENED AND MAJOR OIL LEAK NOTED.  VISUAL INSP DID NOT UNCOVER OIL LEAK.  ENG CLEANED AND OIL SYS RES	ERVICED.  ENG STARTED AND LEAK IDENTIFIED IMMEDIATELY.  BANJO FITTING ON THE OIL PRESS SENSE LINE FOUND LOOSE WHERE IT A	TTACHED TO GRBX AND OIL WAS SPRAYING OUT.  ENG SHUT DOWN AND INVEST REVEALED THREADS HOLDING BANJO FITTING TO GRBX WERE 	BADLY WORN.  A HELIOCOIL INSERT INSTALLED IN THREADED BOSS OF GRBX.  AFTER REPAIR OF GRBX, ENG RESERVICED WITH OIL AND L	EAK CHECK PERFORMED.  NO LEAKAGE NOTED DURING HIGH POWER ENG RUN AND ALL INDICATIONS NORMAL.  ACFT RETURNED TO SERVICE.	2	L	7	3 	4F	4	F		A3WE    	E2EA
1998080700240	19980807	00240	EA  	1998	8	7	98ZZZX2574       	2	19980615	G	7414	10349237	GEAR            			BEECH 	60    	60          	1153602	CE  	LYC   	O541  	TIO541E1A4  	41536	EA  					RT MAGNETO	FAILED          	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			NM	11						P38				PILOT REPORTED ROUGH RUNNING ENGINE.  REMOVED FUEL CONTROL, FLOW CHECKED.  FOUND BAD RIGHT MAGNETO.  TEETH STRIPPED FROM	 DISTRIBUTOR GEAR.					1	L	7	2 	3O	3	O		A12CE   	E10EA
1998080700241	19980807	00241	CE  	1998	8	7	98ZZZX2575       	1	19980427	G	3244	650T661	TIRE            			BEECH 	99    	C99         	1154006	CE  										BALANCE PATCH	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6656N	511  			62340022	U213				FIFTH TIME SAME PROBLEM, DIFFERENT ACFT, BUT SAME TIRE.  MANUFACTURER:  GOODYEAR.  FLIGHT CUSTOM II, 650-10 6PR TUBELESS	.  THIS ACFT ON 1-7-97 AT 8,010.7 TT.  PILOT REPORTS SHIMMY IN NOSE WHEEL.  UNABLE TO BALANCE TIRE.  NO VISIBLE DEFECT N	OTED.  GOOD THREAD LIFE, APPEARS ROUND.  DISMOUNT FOUND LOOSE BALANCE PATCH.  INSTALLED NEW TIRE AND BALANCED.  ON 4-27-	98 AT 8,521.7 TT, SAME WRITE-UP AND PROBLEM.  AFTER 511.4 TIME IN SERVICE.  DEBONDED BALANCE PATCH.			1	L	7	2 	3T				A14CE
1998080700242	19980807	00242	CE  	1998	8	7	98ZZZX2576       	1	19980613	G	5210	130909N32	NUT             		11440002337 	BEECH 	1900  	1900C       	1154161	CE  										HANDLE ARM	MISSING         	H				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	5632C					UC81				THREE UPPER AIRSTAIR DOOR LATCHES FAILED TO PROPERLY LATCH AND CAUSED DOOR FRAME TO FAIL WHILE IN PRESSURIZED FLIGHT.  A	IRCRAFT DE-PRESSURIZED AND THE PILOT RETURNED TO THE POINT OF DEPARTURE WITHOUT FURTHER INCIDENT.  SUSPECT FAILURE OF LA	TCHING MECHANISM PUSH ROD ATTACHMENT HARDWARE THAT PREVENTED ALL LATCH CAMS FROM FULLY ROTATING AND CAPTURING DOOR FRAME	 LUGS.			2	L	7	2 	4T			RT	A24CE
1998080700243	19980807	00243	SW  	1998	8	7	98ZZZX2577       	1	19980602	G	5542		SKIN            			GULSTM	560   	560         	0141402	SW  										RUDDER	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	269CM	1300 				5600268				A 1 INCH CRACK BETWEEN TWO RIVET HOLES ON THE LOWER FORWARD RUDDER LEADING EDGE SKIN.						1	H	7	2 	3O				6A1
1998080700244	19980807	00244	GL  	1998	8	7	98ZZZX2578       	3	19980706	G	6111	57D04951	FORK            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1365 			1802NR			HE20		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998081900003	19980819	00003	GL  	1998	8	19	98ZZZX2579       	3	19980709	G	6110	57C04721	COUNTERWEIGHT   			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	SAFETY PIN HOLE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1365 						HE21		INSPECTION FOUND CRACK COMING OUT OF SAFETY PIN HOLE GOING IN THE DIRECTION OF BLADE.  TWO WEIGHTS.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998080700245	19980807	00245	GL  	1998	8	7	98ZZZX2580       	3	19980706	G	6111	57D04951	FORK            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1365 			1848NR			HE21		PROPELLER INSPECTION FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998080700246	19980807	00246	SW  	1998	8	7	98ZZZX2581       	1	19980510	G	5610	55112854	WINDOW          			GULSTM	560   	560         	0141402	SW  										RT COCKPIT	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	772AA					5600136				DURING SCHEDULED INSPECTION, FOUND WINDOW CRACK APPROXIMATELY SIX INCHES LONG IN UPPER FORWARD CORNER CONNECTING FOUR AT	TACH HOLES.  COULD NOT DETERMINE CAUSE OF CRACK.  REPLACED WITH NEW WINDOW.  CRACKED WINDOW HAD DATE OF 5-1-91 STAMPED B	ELOW PART NUMBER.				1	H	7	2 	3O				6A1
1998080700248	19980807	00248	GL  	1998	8	7	98ZZZX2582       	2	19980701	G	7210	6895007	BEARING         		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	567AL	282  			JJ14209	53246	CAE847271			UPON DISASSEMBLY AND INSPECTION OF PARTS, FOUND T/M JOURNAL BEARING WITH EXCESSIVE GALLING ON END OF ROLLERS AND DEEP BA	NDING DOWN MIDDLE OF ROLLERS.  EXCESSIVE GALLING AND BANDING OF T/M JOURNAL BEARING GALLING ON ROLLERS WAS ONLY TO OUTER	 PART OF ROLLERS AND BANDING WAS LOCATED ONLY IN MIDDLE OF ROLLERS.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998080700249	19980807	00249	GL  	1998	8	7	98ZZZX2583       	2	19980529	G	7250	23001967	WHEEL           			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 3 SHROUD	CRACKED         	B			CK2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911ET	2252 			CAT40415	S187	CAE830500			UPON REMOVAL OF 3RD STAGE TURBINE WHEEL FOR CYCLE LIMIT, FOUND A CRACK COMPLETELY THROUGH THE WHEEL SHROUD AND A PORTION	 OF ONE BLADE.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998080700250	19980807	00250	SW  	1998	8	7	98ZZZX2584       	1	19980519	G	6230	206010454005	SLEEVE          		206010450001	BELL  	206   	206B        	1181511	SW  										SWASHPLATE	DENTED          	B		A	BKFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	55WT	3366 	2219 		6DJ690216	1683				DURING RE-SHIM PROCEDURE, FOUND DENT IN SLEEVE APPROXIMATELY 2 INCHES BELOW UNIBALL ON DATA PLATE SIDE.  DENT HAD CORRES	PONDING REFLECTION INSIDE SLEEVE.  AREA HAD RUBBING WEAR FROM CONTACT WITH SUPPORT.  SUPPORT WAS UNDAMAGED.  RECOMMEND V	ISUAL INSPECTION OF OUTER SURFACE OF ENTIRE SLEEVE AT EACH INSPECTION.				1	G	7	1 	3U				H2SW
1998080700251	19980807	00251	NE  	1998	8	7	98ZZZX2585       	1	19980616	G	6320	5835010025102	OIL PUMP        			SKRSKY	S58T  	S58ET       	8141803	NE  										ANGLE GEARBOX	JAMMED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	03	4247V		618  			581547				LOW OIL PRESSURE LIGHT ILLUMINATED IN FLIGHT.  A PRECAUTIONARY LANDING WAS MADE.  ON SITE INSPECTION DETERMINED THAT A P	IECE OF COTTER PIN HAD BROKEN OFF AND WAS CAUGHT IN THE PUMP.  THE BROKEN COTTER PIN AND OIL PUMP WERE REPLACED.  UPON R	UN-UP, SYSTEM CHECKED GOOD.				2	G	7	2 	4U				1H11
1998080700252	19980807	00252	EU  	1998	8	7	98ZZZX2586       	1	19980706	G	2612	9560129980	DETECTOR        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENGINE FIRE	FAILED          	B		A	RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4035W	989  			13275	2912	9442			DURING 500-HOUR T INSP' INSPECTION OF 3 OF THE 6 ENGINE FIRE DETECTORS WERE FOUND DEFECTED PER TURBOMECA MM CHAP 26-11-0	0 PARA 1 INSPECTION PROCEDURES.  TWO WERE OVERHEATED AND ON ONE THE OHMS WERE TOO LOW.  SUBMITTER STATED THE OPERATOR BE	LIEVES THEY SHOULD HAVE HAD LONGER COMPONENT LIFE SINCE THIS IS THE ONLY FORM OF FIRE PROTECTION FOR THE AIRCRAFT.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1998080700253	19980807	00253	EU  	1998	8	7	98ZZZX2587       	1	19980706	G	2612	9560129980	DETECTOR        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENGINE FIRE	FAILED          	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	4035W	989  			13276	2912	9442			DURING 500-HOUR T INSP' INSPECTION OF 3 OF THE 6 ENGINE FIRE DETECTORS WERE FOUND DEFECTED PER TURBOMECA MM CHAP 26-11-0	0 PARA 1 INSPECTION PROCEDURES.  TWO WERE OVERHEATED AND ON ONE THE OHMS WERE TOO LOW.  SUBMITTER STATED THE OPERATOR BE	LIEVES THEY SHOULD HAVE HAD LONGER COMPONENT LIFE SINCE THIS IS THE ONLY FORM OF FIRE PROTECTION FOR THE AIRCRAFT.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1998080700254	19980807	00254	EA  	1998	8	7	98ZZZX2588       	2	19980703	G	7210	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COMBINE GEARBOX	MAKING METAL    	B			LCF2	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	09	16973	13046	2310 		CPGB1804	30882				CHIP LIGHT ILLUMINATED, METAL FOUND ON MAGNETIC CHIP PLUG.  EXCESSIVE TORQUE SPLIT.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998080700255	19980807	00255	SW  	1998	8	7	98ZZZX2589       	1	19980703	G	6320	206040004107	TRANSMISSION    			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	MAKING METAL    	B			LCF2	K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	09	5748H				BMC00230	45490				TRANSMISSION CHIP LIGHT ILLUMINATED.  EXCESSIVE METAL FOUND ON SUMP CHIP PLUG AND IN OIL FILTER.						1	G	7	1 	3U				H2SW
1998080700256	19980807	00256	SW  	1998	8	7	98ZZZX2590       	1	19980623	G	6710	206062721011	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY				3948	2871				ACTUATOR INOPERATIVE, WILL NOT RESPOND.  REMOVED AND SENT FOR REPAIR EVALUATION.						1	G	7	1 	3U				H2SW
1998080700257	19980807	00257	GL  	1998	8	7	98ZZZX2591       	2	19980617	G	7412	106149501D	EXCITER         			BELL  	206   	OH58A       	1181579	SW  	ALLSN 	250C  	250C10D     	03011	GL  					ENGINE IGNITION	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	54AG				90300645	7120721				ENGINE IGNITION EXCITER FAILED INTERNALLY.  SENT FOR REPAIR.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998080700258	19980807	00258	GL  	1998	8	7	98ZZZX2592       	2	19980619	G	7323	23006259	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322		3291 		2AAD1155	1736				SLUGGISH TO RETURN TO POWER.  GOV REMOVED FROM AIRCRAFT AND SENT FOR REPAIR EVALUATION.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998080700259	19980807	00259	SW  	1998	8	7	98ZZZX2593       	1	19980614	G	6310	206040222005	SHAFT           			BELL  	206   	206L3       	1182108	SW  										FREEWHEEL	MISMANUFACTURED 	B			ZV1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					A005440					P/N 206-040-222-005, WAS ORDERED FOR 206L-3 FREE WHEELING UNIT PER NEW 206L SERIES IPC.  SHAFT IS TOO SHORT FOR L-3.  L-	3 F/W UNIT REQUIRES A 206-040-222-009 SHAFT.					1	G	7	1 	3U				H2SW
1998080700260	19980807	00260	NM  	1998	8	7	98ZZZX2594       	1	19980630	G	3213	NAS1330H3K216L	RIVNUT          			DOUG  	MD900 	MD900       	3027375	NM  										RT SKID TUBE	MISINSTALLED    	B		A	EGRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	903LF		795  			90000030				THE SCREWS THAT HOLD THE FORWARD AND AFT SHOES ON THE SKID TUBE WERE FOUND LOOSE (ITEM 12 ON THE PARTS BREAKDOWN).  THE 	SKID TUBE ASSY, LT AND RT, WERE REMOVED FROM THE HELICOPTER AND FOUND THE RIVNUTS (10 PER SKID) P/N NAS1330H3K216L HAD B	EEN INSTALLED, BUT WERE NEVER PULLED OR EXPANDED.  THEY WERE HELD IN PLACE BY PRO-SEAL COMPOUND.  CORRECTIVE ACTION WAS 	TO INSTALL THE RIVNUTS PROPERLY.			1	G	7	2 	3U			NC	H19NM
1998080700261	19980807	00261	NM  	1998	8	7	98ZZZX2595       	1	19980630	G	3213	NAS1330H3K216L	RIVNUT          			DOUG  	MD900 	MD900       	3027375	NM  										LT SKID TUBE	MISINSTALLED    	B	S		EGRR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17	903LF		795  			90000030				THE SCREWS THAT HOLD THE FORWARD AND AFT SHOES ON THE SKID TUBE WERE FOUND LOOSE (ITEM 12 ON THE PARTS BREAKDOWN).  THE 	SKID TUBE ASSY, LT AND RT, WERE REMOVED FROM THE HELICOPTER AND FOUND THE RIVNUTS (10 PER SKID) P/N NAS1330H3K216L HAD B	EEN INSTALLED, BUT WERE NEVER PULLED OR EXPANDED.  THEY WERE HELD IN PLACE BY PRO-SEAL COMPOUND.  CORRECTIVE ACTION WAS 	TO INSTALL THE RIVNUTS PROPERLY.			1	G	7	2 	3U			NC	H19NM
1998080700262	19980807	00262	EU  	1998	8	7	98ZZZX2596       	1	19980612	G	6410	350A12004008	BLADE           			AEROSP	AS355 	AS355F2     	8680812	EU  										TAIL ROTOR	DEFECTIVE       	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SO	15	335FP	3595 			3943	5456				PILOT REPORTED T/R GEARBOX CHIP LIGHT ILLUMINATED SHORTLY AFTER TAKEOFF.  PILOT DIVERTED TO NEAREST AIRPORT AND SECURED 	HELICOPTER.  EXAMINATION OF CHIP DETECTOR BY MAINTENANCE DETERMINED GEARBOX FAILURE.  DUE TO PREVIOUS DIFFICULTY IN BALA	NCING TAIL ROTOR, MAINTENANCE ELECTED TO INSTALL ANOTHER SERVICEABLE TAIL ROTOR GEARBOX AND A NEW TAIL ROTOR BLADE ASSY.	  GROUND RAN HELICOPTER AND BALANCED TAIL ROTOR.  AIRCRAFT RETURNED TO SERVICE.  TEAR DOWN OF THE GEARBOX INDICATED THE 	METAL WAS GENERATED BY THE LABYRINTH SEAL RUBBING THE HOUSING DUE TO AN OUT OF BALANCE TAIL ROTOR BLADE.		1	G	7	2 	3U				H11EU
1998080700263	19980807	00263	CE  	1998	8	7	98ZZZX2597       	1	19980505	G	2510	1015310172	SEAT            			BEECH 	300   	300BEECH    	1152930	CE  										COPILOT	NOT LATCHED     	B		A	VIB4	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	195AL	6921 				FA102				DURING PHASE INSP, NOTICED COPILOT'S SEAT DID NOT FULLY LATCH IN THE MOST FWD HOLES IN THE SEAT TRACK.  REVIEWED MANDATO	RY SB 2444 R2 AND FOUND KA 300 SERIES ACFT WAS NOT COVERED.  CORRECTED PROBLEM AND MADE POSITIVE LATCHING OF THE SEAT. A	D 92-27-10 AND AD 97-06-06, WERE ISSUED AGAINST THE KING AIR 90 SERIES, F90 SERIES, 99 AIRLINERS, 100 SERIES, 200 SERIES	, 2900 SERIES, ACFT.  BOTH OF WHICH REFERENCE MANDATORY SB 2444 R2.  SUBMITTER STATED THIS HAD BEEN A PROBLEM WITH MANY 	KING AIR SERIES ACFT.  FELT THE MODEL AND S/N LISTINGS IN AD 97-06-06 AND MANDATORY SB 2444 R2 SHOULD BE REVIEWED.		2	L	7	2 	4T				A24CE
1998080700165	19980807	00165	EA  	1998	8	7	98ZZZX2598       	2	19980611	G	8520	5015	STUD            			BEECH 	80    	65B80       	1152812	CE  	LYC   	O720  	IO720A1B    	41546	EA  					NR 5 CYLINDER	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	103BA	5747 				LD435	L114554A			CYLINDER HOLD DOWN STUD BROKE UNDER NUT.  SUSPECT DEFECTIVE STUD.						1	L	7	2 	3O	3	O		3A20    	1E15
1998080700166	19980807	00166	SO  	1998	8	7	98ZZZX2599       	2	19980611	G	7322		THROTTLE        	FACET       	MA45        	CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  					CARBURETOR	STICKS          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	110US		288  		N171777CMF	18260234	800439R4			THROTTLE WOULD STICK WIDE OPEN AT FULL POWER.  UPON DISASSEMBLY OF CARBURETOR, DETERMINED THAT WEAR OF THE FULL OPEN STO	PS ON THE CARBURETOR BODY AND THROTTLE STOP ARM, THE POWER ENRICHMENT LEVER OPERATES THE AIR METERING PIN WOULD TRAVEL P	AST ITS DESIGN LIMITS.  EVENTUALLY, THE ACTION BROKE THE AIR METERING PIN AND JAMMED IT BETWEEN THE LEVER AND AIR METERI	NG JET WHEN AT FULL POWER.  RECOMMEND TO CHECK FOR EXCESSIVE WEAR OF STOPS, ESPECIALLY FULL OPEN.  INSTALLED OVERHAULED 	MARVEL-SCHREBLER CARB., MA4-5, P/N 10-4893-1, FROM CONSOLIDATED FUEL SYSTEMS, INC.		1	H	7	1 	3O	3	O	NT	3A13    	E273
1998080700167	19980807	00167	SO  	1998	8	7	98ZZZX2600       	2	19980527	G	8530	639661	VALVE           		B3762A2     	LUSCOM	8     	8A          	8190104	SO  	CONT  	A65   	A651        	17003	SO  					NR 2 CYL INT	FAILED          	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AL	03	1322B					5959				AIRCRAFT IN-FLIGHT, LOST POWER, MADE FORCED LANDING ON ROAD.  DAMAGE TO WINGS AND FUSELAGE, NO INJURIES, TEAR DOWN OF EN	GINE REVEALED BROKEN NR 2 CYLINDER INTAKE VALVE.  ENGINE TSOH:  120 HOURS.					1	H	7	1 	3O	3	O		A694    	E205
1998080700168	19980807	00168	SO  	1998	8	7	98ZZZX2601       	2	19980501	G	8530	SA631475	PISTON          			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					PIN BORE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	1609X	20   				21060645				PISTON PIN BORE IN PISTON WORN.  PISTONS HAVE 20 HOURS IN SERVICE SINCE NEW.  PARTS WERE BOUGHT FROM SUPERIOR PARTS.						1	H	7	1 	3O	3	O		3A21    	E5CE
1998080700169	19980807	00169	CE  	1998	8	7	98ZZZX2602       	1	19980519	G	2701	40418750026	COLUMN          			BEECH 	18    	E18S        	1151006	CE  										LT CONTROL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	233TM	10243				BA275				CRACKED ON FRONTSIDE ABOUT 1 INCH LONG.  CRACKS CAUSED BY HIGH TT AND TWISTING LOAD.						1	L	7	2 	3R				A765
1998080700171	19980807	00171	SO  	1998	8	7	98ZZZX2604       	1	19980601	G	5711	6207006	SPAR CAP        			PIPER 	PA28  	PA28140     	7102802	SO  										WING INBOARD	CORRODED        	B		A	BX4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	8071N					2825321				LOWER AFT INBOARD SECTION ON MAIN SPAR CAP HAS SEVERE EXFOLIATION CORROSION.  CORROSION IS 1 INCH UNDER OUTBOARD END OF 	WING ATTACH DOUBLER AND EXTENDS OUTBOARD APPROXIMATELY 4 INCHES.  CRACK CREATED BY CORROSION IS ABOUT .1250 INCH THICK A	T AFT EDGE OF SPAR CAP.  THE REST OF THE WING STRUCTURE HAD VERY MILD SURFACE CORROSION.  ABOUT WHAT WOULD BE EXPECTED F	OR A 32 YEAR OLD NON-TREATED OR PROOFED WING.  TOP OF CAP IS AFFECTED AREA.			1	L	7	1 	3O				2A13
1998080700172	19980807	00172	NE  	1998	8	7	98ZZZX2605       	2	19980623	G	7230	810251	VANE            								PWA   	JT8   	JT8D217A    	52053	NE  					T2 INNER SEAL	DAMAGED         	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05							717368			ENGINE REMOVED FROM SERVICE FOR LPT FAILURE.  THE SECOND STAGE VANE DAMAGE AT INNER AIR SEAL.  SPECIFIC CAUSE OF FAILURE	 IS UNDER INVESTIGATION AT GE.										4	F			E9NE
1998080700173	19980807	00173	CE  	1998	8	7	98ZZZX2606       	1	19980522	G	3213	25410411	GEAR LEG        			CESSNA	303   	T303        	2073820	CE  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	104ER	5740 				T30300277				FOUND LOWER LEG AT KNEE JOINT CRACKED ALONG THE CASTING LINE AT THE MOUNTING SWIVEL PIN ATTACHMENT AND THE LEG WAS SEPAR	ATING AT THE CRACKED AREA.  ANOTHER LEG WAS CHECKED TO BE USED AS A REPLACEMENT, BUT ALSO WAS FOUND CRACKED.  THE CRACKS	 IN THE CASTING APPEAR TO START FROM THE INSIDE-OUT AND WILL NOT SHOW ANY DEFECTS UNTIL THE CASTING HAS BROKEN.				1	L	7	2 	3O				A34CE
1998080700174	19980807	00174	CE  	1998	8	7	98ZZZX2607       	1	19980318	G	3233	35825108	BOLT            			BEECH 	36    	36BEECH     	1151602	CE  										NLG ACTUATOR	MISSING         	E				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SW	05	1194A	4577 				E159				UPON LANDING, THE NOSE LANDING GEAR COLLAPSED.  INVESTIGATION DETERMINED THE ACTUATOR ROD BOLT WAS MISSING.  THE CAUSE C	OULD BE EITHER A FAILED BOLT OR FAILED SAFETY.  SUBMITTER STATED CLOSER INSPECTION OF THIS AREA COULD PREVENT THIS OCCUR	RENCE IN FUTURE CASES.				1	L	7	1 	3O				3A15
1998080700175	19980807	00175	CE  	1998	8	7	98ZZZX2608       	1	19980601	G	5230	16943001533	SKIN            		16943001535 	BEECH 	76    	76          	1153005	CE  										BAGGAGE DOOR	CORRODED        	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2074N	6471 				ME91				DURING SPOT INSPECTION OF AIRCRAFT UNDERGOING ANNUAL INSPECTION, NOTED BAGGAGE DOOR OUTER SKIN CORRODED ON LOWER HALF OF	 DOOR.  CORROSION FROM INSIDE OF DOOR HAS PERFORATED SKIN IN 8 PLACES.  DOOR SKIN WAS LOOSE APPROXIMATELY ONE-THIRD OF D	OOR PARAMETER:  BONDING FAILURE.  SUBMITTER RECOMMENDED INTERNAL INSPECTION OF DOOR ASSY.				1	L	7	2 	3O				A29CE
1998080700178	19980807	00178	CE  	1998	8	7	98ZZZX2611       	1	19980625	G	5511	053200198	SPAR            			CESSNA	172   	172N        	2072434	CE  										HORIZ STAB	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	2350E	6909 				17271246				AT 100-HOUR INSPECTION, A CRACK APPROXIMATELY 1.25 INCHES LONG WAS FOUND AT LOCATION DESCRIBED IN 6.C.  THE SPAR REINFOR	CEMENT, PN 0532001-97, HAD A CORRESPONDING CRACK.  POSSIBLE CAUSE MIGHT BE GROUND HANDLING PROCEDURE.  PULLING DOWN OR S	ITTING ON STABILIZER TO TURN THE AIRCRAFT.				1	H	7	1 	3O			NT	3A12
1998080700179	19980807	00179	CE  	1998	8	7	98ZZZX2612       	1	19980625	G	5511	053200197	SPAR            			CESSNA	172   	172N        	2072434	CE  										HORIZ STAB FRONT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	2350E	6909 				17271246				AT 100-HOUR INSPECTION, A CRACK APPROXIMATELY 1.25 INCHES LONG WAS FOUND AT LOCATION DESCRIBED IN 6.C.  THE SPAR REINFOR	CEMENT, PN 0532001-97, HAD A CORRESPONDING CRACK.  POSSIBLE CAUSE MIGHT BE GROUND HANDLING PROCEDURE.  PULLING DOWN OR S	ITTING ON STABILIZER TO TURN THE AIRCRAFT.				1	H	7	1 	3O			NT	3A12
1998080700184	19980807	00184	SO  	1998	8	7	98ZZZX2617       	2	19980616	G	8530	637781	VALVE           			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 5 CYL EXHAUST	FAILED          	B			G1TR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	340MD	923  				340A0058	R266560R			WHILE DOING COMRPESSION CHECK ON THE ENGINE, FOUND LOW COMPRESSION NR 5 CYLINDER.  REMOVED ROCKER BOX COVER AND FOUND TH	E EXHAUST VALVE TOP STEM WORN DOWN TO BE EVEN WITH THE ROTATOR.  THE ROCKER ARM WAS ALSO DAMAGED BY HITTING THE ROTATOR.	  VALVE MAY HAVE BEEN DEFECTIVE.				1	L	7	2 	3O	3	O		3A25    	E8CE
1998080700185	19980807	00185	CE  	1998	8	7	98ZZZX2618       	1	19980630	G	7810	1029100637	SHIELD          			BEECH 	58    	58TC        	1152746	CE  										ENGINE EXHAUST	LOOSE           	B			QC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	110CW					TK115				THE EXHAUST SHIELD HAD COME LOOSE ON BOTH LT AND RT ENGINES.  BOTH SHIELDS HAD CAUSED ENOUGH DAMAGE TO WARRANT REMOVAL O	F BOTH ENGINE MOUNTS FOR REPAIR.					1	L	7	2 	3O				A23CE
1998080700186	19980807	00186	CE  	1998	8	7	98ZZZX2619       	1	19980630	G	7120	102910026137	MOUNT           			BEECH 	58    	58TC        	1152746	CE  										LT ENGINE	DAMAGED         	B			QC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	110CW					TK115				THE EXHAUST SHIELD HAD COME LOOSE ON BOTH LT AND RT ENGINES.  BOTH SHIELDS HAD CAUSED ENOUGH DAMAGE TO WARRANT REMOVAL O	F BOTH ENGINE MOUNTS FOR REPAIR.					1	L	7	2 	3O				A23CE
1998080700187	19980807	00187	CE  	1998	8	7	98ZZZX2620       	1	19980630	G	7120	102910026137	MOUNT           			BEECH 	58    	58TC        	1152746	CE  										RT ENGINE	DAMAGED         	B			QC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	110CW					TK115				THE EXHAUST SHIELD HAD COME LOOSE ON BOTH LT AND RT ENGINES.  BOTH SHIELDS HAD CAUSED ENOUGH DAMAGE TO WARRANT REMOVAL O	F BOTH ENGINE MOUNTS FOR REPAIR.					1	L	7	2 	3O				A23CE
1998080700189	19980807	00189	CE  	1998	8	7	98ZZZX2621       	1	19980629	G	2930		LINE            			CESSNA	182   	182Q        	2072732	CE  										HYD GAUGE B NUT	FAILED          	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	11	35G					R18201785				A HYDRAULIC INDICATOR WAS INSTALLED IN THE AIRCRAFT UTILIZING AN EXISTING 'TEE' ON THE HYDRAULIC POWER PACK.  THE FLARE 	ON THE LINE GOING TO THE HYDRAULIC PRESSURE GAUGE FAILED CAUSING THE LINE TO BLOW OUT OF ITS 'B' NUT.  THE HYDRAULIC FLU	ID SUPPLY WAS SUBSEQUENTLY DISCHARGED INTO THE AIRCRAFT CABIN.  THE PILOT WAS NOT ABLE TO ACTUATE THE LANDING GEAR.  A G	EAR-UP LANDING FOLLOWED.			1	H	7	1 	3O			NT	3A13
1998080700190	19980807	00190	SO  	1998	8	7	98ZZZX2622       	2	19980701	G	8530	SA10200AL	CYLINDER        			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300D       	17022	SO  					NR 2	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3794F	222  			12214	17255289	34859D6D			NR 2 CYLINER REMOVED FOR ZERO COMPRESSION.  EXHAUST VALVE SEAT BADLY WORN AND EXHAUST GUIDE VERY LOOSE.  INTAKE VALVE AL	SO LEAKING AND SEAT IS TOO WIDE.  EXHAUST VALVE EXTREMELY LOOSE IN GUIDE.  COULD CAUSE HEAD OF VALVE TO BREAK OFF CAUSIN	G A CATASTROPHIC ENGINE FAILURE.  SUBMITTER RECOMMENDED CLOSER QUALITY CONTROL OF CYLINDER ASSY, NEW COMPLETE CYLINDER A	SSY INSTALLED.			1	H	7	1 	3O	3	O	NT	3A12    	E253
1998080700191	19980807	00191	CE  	1998	8	7	98ZZZX2623       	1	19980608	G	3230		DRAG BRACE      			BEECH 	58    	58          	1152740	CE  										NLG	FAILED          	B		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4097S	7439 				TH601				NOSE GEAR UPPER DRAG BRACE (ORIGINAL TUBING STYLE) BROKE AT THE WELD FOR THE ACTUATOR ATTACHMENT POINT.  APPEARS TO HAVE	 CRACKED AND FAILED FROM AGE STRESS AND POSSIBLE INTERIOR CORROSION.  SUBMITTER STATED BEECHCRAFT OFFERS A NEW STYLE CAS	TING DRAG BRACE ASSEMBLY FOR THIS AIRCRAFT IN THE FORM OF A KIT.				1	L	7	2 	3O				3A16
1998080700192	19980807	00192	SO  	1998	8	7	98ZZZX2624       	1	19980624	G	3211	95781304	TRUNNION        			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	CRACKED         	C	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	49SA	8800 				347350057				INSPECTION FOUND .5 INCH CRACK IN NOSE GEAR TRUNNION AT RETRACT PIVOT POINT WELDED AREA.  SUBMITTER STATED CRACKS HAVE A	LSO BEEN FOUND SAME AREA ON 3 OTHER SENECA IN AIRCRAFT WITH SIMILAR TIME ON PART.					1	L	7	2 	3O				A7SO
1998080700193	19980807	00193	SO  	1998	8	7	98ZZZX2625       	1	19980624	G	3230	AN735	BOLT            			PIPER 	PA34  	PA34200     	7103405	SO  										NLG DRAG LINK	BENT            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	49SA	15   				347350057				SUBMITTER OPERATES 8 SENECCA AIRCRAFT IN FLIGHT SCHOOL CONDITIONS AND CONTINUOUSLY FINDS AN 7-35 UPPER DRAG LINK BOLT (N	OSE GEAR) BENT WHICH DIRECTLY AFFECTS THE DOWNLOCK RIGGING CAUSING COLLAPSE.  SUBMITTER STATED THIS WHOLE DESIGN IS VERY	 LIGHT-WEIGHT AND POOR.  SUBMITTER STATED SWING AND INSPECT ALL SENECCAS EVERY 15 HOURS IN AN ATTEMPT TO SLOW THE INTENS	ITY OF THESE INCIDENTS.			1	L	7	2 	3O				A7SO
1998080700194	19980807	00194	SO  	1998	8	7	98ZZZX2626       	1	19980601	G	5412	2524900	FIREWALL        			PIPER 	PA30  	PA30        	7103002	SO  										LT AIR FILTER MT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	525PG	2633 				301737				UPON REMOVAL OF AIR FILTER ASSEMBLIES, LEFT AND RIGHT FIREWALL WAS FOUND CRACKED IN BOTH UPPER AND LOWER MOUNTING POINTS	.  SUBMITTER STATED INSUFFICIENT SUPPORT IS OBVIOUS PROBLEM.					1	L	7	2 	3O				A1EA
1998080700195	19980807	00195	SO  	1998	8	7	98ZZZX2627       	1	19980601	G	5412	2524901	FIREWALL        			PIPER 	PA30  	PA30        	7103002	SO  										RT AIR FILTER MT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	525PG	2633 				301737				UPON REMOVAL OF AIR FILTER ASSEMBLIES, LEFT AND RIGHT FIREWALL WAS FOUND CRACKED IN BOTH UPPER AND LOWER MOUNTING POINTS	.  SUBMITTER STATED INSUFFICIENT SUPPORT IS OBVIOUS PROBLEM.					1	L	7	2 	3O				A1EA
1998080700196	19980807	00196	SO  	1998	8	7	98ZZZX2628       	1	19980528	G	8120	RJ061231	BRACKET         			PIPER 	PA30  	PA30        	7103002	SO  										RT ENGINE TURBO	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	525PG	2633 				301737				UPON REMOVAL OF BRACKET FROM LOWER RIGHT ENGINE MOUNT, FOUND BRACKET CRACKED ACROSS FACE OF BRACKET AND AROUND BOLT HEAD	 CIRCUMFERENCE.  INSPECTION OF OPPOSITE ENGINE BRACKET REVEALED SAME CONDITION.  BOTH APPEAR TO HAVE SUFFICIENT METAL TO	 BOLT CONTACT.  RECOMMEND EITHER INSTALL AN 960-716 WASHER UNDER HEAD OR REDESIGN BRACKET.  IF AN 960-716 WASHER IS INST	ALLED, POSSIBLE REPLACING OF BOLT WITH NEXT LENGTH MIGHT BE REQUIRED.			1	L	7	2 	3O				A1EA
1998080700197	19980807	00197	EA  	1998	8	7	98ZZZX2629       	2	19980624	G	7414	10382585	CONTACT ASSY    	BENDIX      	D4RN3000    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE MAGNETO	DEFECTIVE       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	09	4903F	420  			E219707GR	17273100	L300476T			PILOTS REPORTED AIRCRAFT WOULD INTERMITTENTLY LOSE POWER.  PROBLEM WAS TRACED TO MAGNETO POINTS INADEQUATELY GAPPED.  ST	APLE WHICH ATTACHES FELT TO NYLON CAM RIDER ON POINTS WAS FOUND TO BE INTERFERRING WITH PROPER OPERATION OF POINTS NOT A	LLOWING THEM TO OPEN.  IT APPEARS THAT STAPLE WAS NOT CRIMPED SMALL ENOUGH TO CLEAR CONTACT ASSEMBLY FRAME.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998080700198	19980807	00198	SO  	1998	8	7	98ZZZX2630       	1	19980612	G	3010	4577001	MOTOR           			PIPER 	PA31T 	PA31T1      	7103126	SO  										LT DEICE	SHORTED         	B			G1TR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			SW	17	555AT	3562 			9098	31T8104045				PILOT/OWNER REPORTED SMOKE AND CIRCUIT BREAKERS TRIPPED IN-FLIGHT, LANDED WITHOUT INCIDENT.  INVESTIGATION FOUND LT ENGI	NE DE-ICE DEFLATOR MOTOR SHORTED AND BURNT WIRING FROM MOTOR THROUGH FUSELAGE TO THE OVERHEAD PANEL IN COCKPIT.					1	L	7	2 	3T				A8EA
1998080700199	19980807	00199	SO  	1998	8	7	98ZZZX2631       	1	19980619	G	2822	1C69	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31P       	7103120	SO  										BOOST	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6805L		273  		8A164	31P7				PUMP INSTALLED 4-6-97 WITH NEW FUEL CELL.  OVERHAULED 1-15-97, 272.8 HRS SINCE INSTALLED.  SERVICE LIFE SHORT.  DON'T KN	OW WHY PUMP IS INOPERABLE.					1	L	7	2 	3O				A8EA
1998080700200	19980807	00200	CE  	1998	8	7	98ZZZX2632       	1	19980618	G	7111	07527321	COWL FLAP       			CESSNA	182   	182S        	2072701	CE  										LT EXIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	649DH	26   				18280142				ORIGINAL CUSTOMER SQUAWK WAS LOOSE AND SMOKING FASTENERS.  AFTER DETAILED INSPECTION, FOUND COWL FLAP EXIT (LT/RT) CRACK	ED.  EACH CRACK ABOUT 1 INCH IN LENGTH.  SUSPECT CAUSE AT THIS TIME IS EXCESSIVE VIBRATION DUE TO SHAPE OF PARTS AND AMO	NT OF AIR FLOW PASSING OVER PARTS.				1	H	7	1 	3O			NT	3A13
1998080700201	19980807	00201	CE  	1998	8	7	98ZZZX2633       	1	19980618	G	7111	07527321	COWL FLAP       			CESSNA	182   	182S        	2072701	CE  										RT EXIT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	649DH	26   				18280142				ORIGINAL CUSTOMER SQUAWK WAS LOOSE AND SMOKING FASTENERS.  AFTER DETAILED INSPECTION, FOUND COWL FLAP EXIT (LT/RT) CRACK	ED.  EACH CRACK ABOUT 1 INCH IN LENGTH.  SUSPECT CAUSE AT THIS TIME IS EXCESSIVE VIBRATION DUE TO SHAPE OF PARTS AND AMO	NT OF AIR FLOW PASSING OVER PARTS.				1	H	7	1 	3O			NT	3A13
1998080700202	19980807	00202	EA  	1998	8	7	98ZZZX2634       	2	19980401	G	7322	105257	CARBURETOR      	FACET       	MA3PA       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					COTTER PIN	MISOVERHAULED   	B			EBVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	09	9KA		641  		DM0765	15284552				DURING DISASSEMBLY FOR REPAIR, NOTED THAT ALL INSTALLED COTTER PINS WERE STANDARD STEEL HARDWRE AND NOT THE STAINLESS ST	EEL COTTER PINS SPECIFIED IN THE ILLUSTRATED PARTS LIST OF THE APPROPRIATE COMPONENT MM.					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998080700203	19980807	00203	CE  	1998	8	7	98ZZZX2635       	1	19980611	G	3297		WIRE            			CESSNA	421   	421C        	2076016	CE  										THROTTLE SWITCH	CHAFED          	D				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			WP	07	936AF					421C0606				LANDING GEAR WARNING HORN SOUNDED WITH THROTTLES RETARDED OR FLAPS EXTENDED WITH THE LANDING GEAR DOWN AND LOCKED (GREEN	 GEAR INDICATOR LIGHTS ILLUMINATED).  WIRES TO THE THROTTLE POSITION SWITCHES WERE FOUND CHAFED BY THE CASTLE NUT AND CO	TTER PIN ON THE PITCH TRIM WHEEL AXLE BOLT.  WIRES WERE REPAIRED AND REPOSITIONED AWAY FROM CASTLE NUT AND COTTER PIN. O	PS CHECKED OK.  AIRCRAFT TT:  3,709.7 HOURS.			1	L	7	2 	3O			 	A7CE
1998080700204	19980807	00204	EA  	1998	8	7	98ZZZX2636       	2	19980425	G	8530	LW11633CN	CYLINDER        								LYC   	O235  	O235L2C     	41505	EA  					CYLS 1,2,4	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01		1721 					DA10579			REMOVED NR 1, NR 2, AND NR 4 CYLINDERS DUE TO LEAKAGE PAST RINGS.  RINGS TOTALLY WORN OUT.  ONE CYLINDER CRACKED.  EXCHA	NGE CYLINDER SUPPLIED.  TWO CYLINDERS BURNED TO TIO.  NEW PISTONS AND RINGS INSTALLED.  NEW INTAKE SEALS.  NEW OIL RETUR	N SLEEVES, 6L M20W50 INSTALLED.  NEW OIL FILTER.  GROUND RUN OK.									3	O			E223
1998080700205	19980807	00205	SO  	1998	8	7	98ZZZX2637       	1	19980625	G	3260	452860	CONTROL ROD     			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG DOWNLOCK	SEIZED          	D		A		O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	19	4072K					318152018				RIGHT MAIN LANDING GEAR WOULD NOT SHOW DOWN-N-LOCK DURING GEAR EXTENSION.  VISUAL INSPECTION FROM GROUND SHOWED GEAR TO 	BE DOWN.  AIRCRAFT LANDED WITHOUT INCIDENT.  INSPECTION OF GEAR SHOWED DOWNLOCK CONTROL ROD LOWER BALL END TO BE FROZEN 	NOT ALLOWING DOWNLOCK TO FREELY CONTACT DOWNLOCK SWITCH.  REPLACED ROD END.  OPS CHECKED GEAR AND CHECKED OK.  DOWNLOCK 	IS LOCATED IN EXHAUST, AND AIRCRAFT DOES NOT FLY MUCH, CORROSION AND LACK OF LUBRICATION WILL ATTRIBUTE TO EARLY FAILURE	.  AIRCRAFT TT:  4,099.2 HOURS.		1	L	7	2 	3O				A20SO
1998080700206	19980807	00206	CE  	1998	8	7	98ZZZX2638       	1	19980630	G	3710	442CW6	PUMP            	AIRBORNE    		BEECH 	80    	65B80       	1152812	CE  										LT ENG VACUUM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	46MA	294  			033627	LD413				VACUUM PUMP FAILED DURING FLIGHT TRAINING OPERATIONS.  WHEN MAXIMUM TAKEOFF POWER WAS USED.						1	L	7	2 	3O				3A20
1998080700207	19980807	00207	SO  	1998	8	7	98ZZZX2639       	1	19980701	G	2430	62279000	DIODE ASSY      			PIPER 	PA28  	PA28180     	7102808	SO  										BATTERY BOX	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4722L					284044				FOUND DIODE ASSEMBLY 62279-000 RUSTED OUT AT RESISTOR WHERE IT MOUNTS.  THIS PART IS LOCATED UNDER MASTER SOLENOID ON BA	TTERY BOX (PIPER PART).					1	L	7	1 	3O				2A13
1998080700208	19980807	00208	CE  	1998	8	7	98ZZZX2640       	1	19980626	G	3246	40148	WHEEL           			MTSBSI	MU2   	MU2B36      	5780412	CE  										RT MLG	FAILED          	B			TUPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	500PJ					668				INNER WHEEL HALF EXPERIENCED A BEARING FAILURE.   FAILURE RESULTED IN BRAKE DISC RUBBING INTO BRAKE ASSEMBLY REQUIRING B	RAKE ASSEMBLY REPLACEMENT.  INNER WHEEL HALF ALSO REQUIRED REPLACEMENT DUE TO CRACKING AROUND BEARING AREA.					1	H	7	2 	3T			RT	A10SW
1998080700209	19980807	00209	CE  	1998	8	7	98ZZZX2641       	1	19980630	G	7921	646685	OIL COOLER      			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					FORWARD SIDE	BROKEN          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	60RR	778  				421C0885	292133R			FOUND THE DIAGONAL BRACE ACROSS THE FORWARD SIDE OF THE OIL COOLER BROKEN OFF AT BOTH ENDS.						1	L	7	2 	3O	3	O		A7CE    	E7CE
1998080700210	19980807	00210	CE  	1998	8	7	98ZZZX2642       	1	19980630	G	7921	646685	OIL COOLER      			CESSNA	421   	421C        	2076016	CE  										FORWARD SIDE	BROKEN          	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	60RR	778  				421C0885				FOUND THE DIAGONAL BRACE ACROSS THE FORWARD SIDE OF THE OIL COOLER BROKEN OFF AT THE LOWER END.						1	L	7	2 	3O				A7CE
1998080700211	19980807	00211	SO  	1998	8	7	98ZZZX2643       	1	19980703	G	2430	62279000	DIODE ASSY      			PIPER 	PA28  	PA28140     	7102802	SO  										BATTERY BOX	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	6892W	2517 				2821049				FOUND DIODE ASSY 62279-000 RUSTED OUT AT RESISTOR WHERE IT MOUNTS.  THIS PART IS LOCATED UNDER MASTER SOLENOID ON BATTER	Y BOX (PIPER PART).					1	L	7	1 	3O				2A13
1998080700212	19980807	00212	CE  	1998	8	7	98ZZZX2644       	1	19980626	G	2434	DOFF10300BRX	ALTERNATOR      			CESSNA	210   	210L        	2073448	CE  										DC SYSTEM	FAILED          	B			E96R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	732AK					21061361				ALTERNATOR INOPERATIVE.  WINDINGS SHOW OPEN CIRCUIT.						1	H	7	1 	3O				3A21
1998080700213	19980807	00213	EA  	1998	8	7	98ZZZX2645       	2	19980626	G	7322	105135	CARBURETOR BOWL 			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	LOOSE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	738QP	3423 	1375 		CK818348	17270157	L777276T			DURING FLIGHT, PILOT REPORTED A RATTLING NOISE WHEN THE CARBURETOR HEAT WAS APPLIED.  AFTER LANDING, THE ENGINE COULD NO	T BE SHUT DOWN USING MIXTURE CONTROL.  DURING TROUBLESHOOTING, FOUND THAT CARBURETOR BOWL ATTACHMENT BOLTS HAD COME LOOS	E, BUT THE LOCKING TAB HAD NOT BEEN DISTURBED.  THIS, IN TURN, CAUSED A GAP OF .030 INCH BETWEEN THE BOWL AND UPPER MOUN	T ALLOWING FUEL INTO THE ENGINE.  SUBMITTER RECOMMENDED A CLOSER LOOK BE TAKEN AT THE CARBURETOR DURING ROUTINE INSPECTI	ON PAYING ATTENTION TO THE BOLTS.		1	H	7	1 	3O	3	O	NT	3A12    	E274
1998080700214	19980807	00214	CE  	1998	8	7	98ZZZX2646       	1	19980629	G	3240		HOSE            			BEECH 	80    	6580        	1152806	CE  										RT BRAKE ASSY	FAILED          	B			CS3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	74ME					LD6				BOTH CAPTAIN'S AND COPILOT'S RT BRAKE PEDAL - ACTION EITHER MUSHY OR NON-EXISTANT.  AFTER EXTENSIVE TROUBLESHOOTING '3 D	AYS' OF PURE FRUSTRATION, THE PROBLEM WAS LOCATED IN THE FLEXIBLE HOSE BETWEEN GEAR LEG AND BRAKE ASSY.  WHEN RT BRAKE W	AS APPLIED, SUFFICIENT PRESSURE WOULD PARTIALLY OPERATE CALIPERS.  THEN FLEX HOSE WOULD SWELL DROPPING THE BRAKE PRESSUR	E.  HOSE REPLACED.  OPS CHECK NORMAL.			1	L	7	2 	3O				3A20
1998080700215	19980807	00215	SO  	1998	8	7	98ZZZX2647       	2	19980707	G	8520	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O550  	IO550A      		SO  					TAPPET FACE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	98904	1110 				310R1240	280352R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E3SO
1998080700216	19980807	00216	SO  	1998	8	7	98ZZZX2648       	2	19980707	G	8520	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O550  	IO550A      		SO  					TAPPET FACE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	98904	1133 				310R1240	280461R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E3SO
1998080700217	19980807	00217	SO  	1998	8	7	98ZZZX2649       	2	19980624	G	8530	SA631815	ROCKER SHAFT    			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					NR 4 CYL EXH	FAILED          	B			R2JR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	CR	CRUISE         	1			EA	21	601PB	60   				421B0879	267193P			LEFT ENGINE ROUGHENED IN-FLIGHT, HAD TO BE SHUT DOWN.  SAFE LANDING MADE.  MAINTENANCE FOUND NR 4 CYL EXHAUST PUSH ROD P	USHED THROUGH VALVE COVER.  FOUND ROCKER SHAFT BOLTS BROKEN.  CAUSE OF FAILURE BELIEVED TO BE FROM UNDERTORQUE AND IMPRO	PER SETTING OF BOLT SAFETY LOCKS.  CYLINDERS WERE INSTALLED 60 HOURS PREVIOUSLY.  BOLTS ON OTHER CYLINDERS FOUND UNDERTO	RQUED AND SAFTIES NOT FULLY SET.  CYLINDER SENT FOR TEAR DOWN.  VALVES WERE REPLACED.  C/W RE-TORQUE AND NEW SAFETY TABS	 ON ALL CYLINDERS.  OIL FILTER INSPECTED.  OIL CHANGED.  PROPER USE OF A CALIBRATED TORQUE WRENCH AND NOT RE-USING SAFET	Y TABS MAY HAVE PREVENTED THIS INCIDENT.	1	L	7	2 	3O	3	O		A7CE    	E7CE
1998080700218	19980807	00218	GL  	1998	8	7	98ZZZX2650       	3	19980212	G	6114	D3332C68	HUB             													MCAULY	2AF36C	2AF36C68    	GL  	NR 2 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								64572		PROPELLER WAS RECEIVED FOR OVERHAUL.  DURING HUB INSPECTION, A CRACK WAS FOUND IN NR 2 BLADE SOCKET, 3 THREADS IN, 11.00	 POSITION, 1 INCH LONG.  CRACK WAS DISCOVERED USING A 10X MICROSCOPE.  CRACK DID NOT GO THROUGH TO THE OUTSIDE OF HUB.															5	C	P911
1998081400121	19980814	00121		1998	8	14	98ZZZX2651       	4	19980630	G	3120	D11125240	TACHOMETER      			DIAMON	DA20A1	DA20A1      	05626UX	GL  										HOURMETER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	96CF	1010 			1196	10157				HOUR METER ON TACHOMETER STOPPED RECORDING.  OPENED TACHOMETER AND FOUND THE MAIN DRIVE GEAR CAME LOOSE ON THE SHAFT.  T	HIS IS THE 4TH OCCURRENCE OF THIS PROBLEM ON THE EXACT MODEL TACHOMETER.  MFG NEEDS TO ATTACH DRIVE GEAR MORE PERMANENTL	Y TO THE SHAFT.  TACHOMETER RPM INDICATOR STILL CONTINUES TO OPERATE CORRECTLY.				1	L	7	1 	3O			NT	TA4CH
1998081400122	19980814	00122	SO  	1998	8	14	98ZZZX2652       	1	19980701	G	2432	G243	BATTERY         			PIPER 	PA46  	PA46350P    		SO  										HANDLE	DEFECTIVE       	B			YEBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	881DB	572  			601537341	4622067				WHILE REMOVING BATTERY FROM AIRCRAFT FOR SERVICING, ONE END OF ROPE HANDLE ON BATTERY FAILED AT ATTACH POINT.  BATTERY F	ELL AND ONE CORNER OF BATTERY WAS CRUSHED.  BATTERY HAD TO BE REPLACED.  SUSPECT CAUSE - POOR DESIGN OR DEFECTIVE MANUFA	CTURING.  TO PREVENT RECURRENCE DO NOT CARRY BATTERY BY ROPE HANDLE.				1	L	7	1 	3O			RT	A25SO
1998081900040	19980819	00040	CE  	1998	8	19	98ZZZX2653       	1	19980515	G	7602	PP56ADS4	CLAMP           			BEECH 	23    	B23         	1151240	CE  										CARBURETOR MIX	SLIPPED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	7614R					M1237				MXITURE CONTROL CABLE HOUSING SLIPPED DUE TO INCORRECT MOUNTING CLAMP CAUSING INTERMITTENT LEAN RUNNING.  INSTALLED PROP	ER CLAMP AND RIGGED SYSTEM TO PROVIDE CUSHION PER MM.					1	L	7	1 	3O			RT	A1CE
1998081900041	19980819	00041	CE  	1998	8	19	98ZZZX2654       	1	19980617	G	2720	00252400023	CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  										RUDDER	FRAYED          	B	P		HP6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	705MB	487  				E2836				AFT RUDDER CABLE WAS EVIDENTLY ROUTED THROUGH AFT PULLEY BRACKET UNDER FORWARD CABLE GUARD ON PULLEY GROOVE, BUT OVER AF	T CABLE GUARD (NAS427K11).  THE RESULTING FRICTION FRAYED CABLE ALMOST TO THE BREAKING POINT AND CRACKED AND DAMAGED CAB	LE GUARD.				1	L	7	1 	3O			 	3A15
1998081400123	19980814	00123	GL  	1998	8	14	98ZZZX2655       	1	19980623	G	2720	202720000	CONTROL CABLE   			DIAMON	DA20  	DA20A1      	2990000	GL  										RUDDER LT OTBD	FAILED          	D		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			EA	05	50ML	950  				10007				ON TAKEOFF, LT OUTBOARD RUDDER CABLE BROKE AT THE FORWARD CABLE SWAGE ATTACH POINT, FORWARD OF PILOT'S LT RUDDER PEDAL. 	 PILOT LANDED SAFELY BY PULLING ON RUDDER CABLE WITH HAND CONTROL.					1	L	7	1 	3O			NT	TA4CH
1998081400124	19980814	00124	CE  	1998	8	14	98ZZZX2656       	1	19980517	G	7160	16500441	DUCT            			CESSNA	185   	A185F       	2072821	CE  										AIR INTAKE	DETACHED        	E		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4603E					18503811				THE ENGINE LOST POWER SHORTLY AFTER TAKEOFF.  FOUND ENGINE AIR INTAKE DUCT DISCONNECTED FROM DUCT ADAPTER P/N 1652021-10	.  CLAMP WAS STILL ON THE ADAPTER.  THIS DUCT IS MADE OF SILICON IMPREGNATED CLOTH AND BECOMES VERY FLEXIBLE WITH EXTEND	ED USE AND VERY SLIPPERY WITH SOME OIL ON IT.  IF THE CLAMP WAS NOT TIGHTENED ENOUGH, THE HIGH VOLUME OF AIR PASSING THR	OUGH THE DUCT AT TAKEOFF MAY HAVE PULLED IT OFF THE ADAPTER.  SUBMITTER STATED HAVE ALSO SEEN THE DUCT MOVE BACK AND CON	TACT THE AUXILIARY FUEL PUMP COVER.  BOTH OF WHICH WILL CHOKE THE ENGINE DOWN.		1	H	7	1 	3O				3A24
1998081400125	19980814	00125	SO  	1998	8	14	98ZZZX2657       	1	19980623	G	5710		WING            			PIPER 	PA28  	PA28180     	7102808	SO  										LT TANK AREA	CORRODED        	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4345P					283105				WHILE DOING ANNUAL INSPECTION REPLACING VERY STIFF TANK HOSE IN THE WING - THE LEFT TANK ON BEING PULLED EXPOSED MOUSE N	EST.  THE NEST WAS FORWARD OF SPAR AND INBOARD OF TANK ALMOST FILLING 2 SPACES BETWEEEN RIBS.  THERE WAS CONNSIDERABLE C	ORROSION.				1	L	7	1 	3O				2A13
1998081400126	19980814	00126	SO  	1998	8	14	98ZZZX2658       	1	19980630	G	3233	AN517A	BOLT            			PIPER 	PA31T 	PA31T2      	7103127	SO  										LT MLG ACTUATOR	MISSING         	B				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			GL	17	42ND					31T8166033				DURING EXTENSION OF THE LANDING GEAR FOR LANDING, THERE WAS NO LEFT DOWN AND LOCKED INDICATION.  MANUAL HYDRAULIC EXTENS	ION WAS INEFFECTIVE.  PNEUMATIC EXTENSION SYSTEM WAS ACTIVATED WHICH LED TO A DOWN AND LOCKED INDICATION AND AN UNEVENTF	UL LANDING WAS MADE.  DURING INSPECTION OF THE LEFT MAIN LANDING GEAR, THE MAIN LANDING GEAR EXTENSION ACTUATOR BOLT WAS	 FOUND MISSING.  A DETAILED INSPECTION FOUND THE BOLT HAD APPEARED TO HAVE SHEARED.  SUBMITTER RECOMMENDED THIS BOLT BE 	INSPECTED AND/OR REPLACED DURING INSPECTIONS.		1	L	7	2 	3T			RT	A8EA
1998081400127	19980814	00127	CE  	1998	8	14	98ZZZX2659       	1	19980525	G	3230	084100077	BELLCRANK       			CESSNA	310   	310C        	2074210	CE  										LT MLG	SHEARED         	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	03	333WD	5300 				310C0002				AFTER LANDING AIRCRAFT SAFELY ON RUNWAY, LT MAIN LANDING GEAR COLLAPSED DUE TO BELLCRANK ASSY FAILURE.  EXAMINATION OF B	ELLCRANK, BOTH CONNECTION POINTS OF STRUT ASSEMBLY WERE SHEARED.  SUBMITTER SUGGESTED MORE INDEPTH INSPECTION OF BELLCRA	NK ASSY LOOKING FOR STRESS OF FATIGUE FRACTURES, POSSIBLY USING DYE PENETRANT INSPECTION.  INSPECTION INTERVAL SHOULD BE	 AFTER 3,000 HRS AND EVERY 1,500 HRS AFTER.			1	L	7	2 	3O				3A10
1998081400129	19980814	00129	CE  	1998	8	14	98ZZZX2661       	1	19980701	G	5321		FLOORBOARD      			CESSNA	310   	310R        	2074245	CE  										CABIN AFT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	101G					310R0017				REAR FLOORBOARD BECAME BOWED FROM HEAVY USE.  FLOOR IN CONTACT WITH MICROSWITCH AND ON FLAP MOTOR CAUSING INTERMITTENT O	PERATION.					1	L	7	2 	3O				3A10
1998081400130	19980814	00130	EU  	1998	8	14	98ZZZX2662       	3	19980706	G	6111	C13318A	BLADE           			ZLIN  	242   	Z242L       	9970204	EU  						MUHBR	MTV	MTV3BC      	EU  	FERRULE	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	242HH	462  			LA4817	0675		940065		PROPELLER BLADE FERRULE HAS A CRACK APPROXMATELY 1 INCH LONG.  SEVERE CORROSION UNDER COUNTERWEIGHT CLAMP.						1	L	7	1 	3O			0	A76EU   		5	C	USSR
1998081400131	19980814	00131	CE  	1998	8	14	98ZZZX2663       	1	19980611	G	3246	40135	WHEEL           	PARKERHANFIN	16101901    	CESSNA	414   	414A        	2075907	CE  										LT MLG	FAILED          	B	S		DC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	30EE	4168 				4140443				WHEEL CRACKED AT INBOARD BEAD SEAT.  APPROXIMATELY 4 INCHES PUSHED RIM AGAINST BRAKE CALIPER AND BRAKE PADS.  REPLACED E	NTIRE WHEEL AND BRAKE DISC.					1	L	7	2 	3O				A7CE
1998081400132	19980814	00132	CE  	1998	8	14	98ZZZX2664       	1	19980708	G	5511	00244002373	SPAR            			BEECH 	58    	58P         	1152744	CE  										HORIZONTAL STAB	CRACKS          	B			RF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	133Z	4400 				TJ367				UPON INSPECTION OF LEFT SUPPORT CHANNEL, THE CHANNEL HAD CRACKS IN UPPER AND LOWER RADII.  THE CRACKS WERE STOP DRILLED 	AND THE DRILL PENETRATED THE SPAR.  THE SPAR AND CHANNEL WERE REPLACED, THE CHANNEL APPARENTLY HAD A LARGE BOW IN IT AND	 CAUSED THE UPPER AND LOWER CRACKS.				1	L	7	2 	3O				A23CE
1998081400133	19980814	00133	CE  	1998	8	14	98ZZZX2665       	1	19980708	G	5510	9562001075	CHANNEL         			BEECH 	58    	58P         	1152744	CE  										H STAB LT SUP	CRACKED         	B		A	RF1R	K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	01	133Z	4400 				TJ367				UPON INPSECTION, THE HORIZONTAL STABILIZER LEFT SUPPORT AFT CHANNEL WAS FOUND CRACKED IN THE UPPER AND LOWER BEND RADII.	  THE CHANNEL HAD A LARGE BOW FROM TOP TO BOTTOM AND WAS NOT RESTING AGAINST THE SPAR.  POORLY FIT.  (FROM MFG).					1	L	7	2 	3O				A23CE
1998081400134	19980814	00134	CE  	1998	8	14	98ZZZX2666       	1	19980625	G	5280	00282001639	PIN             			BEECH 	58    	58P         	1152744	CE  										NLG DOOR	FAILED          	B			RF1R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	01	112Z					TJ371				UPON RETRACTING GEAR, NOSE GEAR DOORS STAYED OPEN.  GEAR WAS EXTENDED, SAFE LANDING WAS MADE.  INSPECTION REVEALED NOSE 	GEAR DOOR PIN ASSY BROKE PIN OFF.  POSSIBLY NOT RIGGED PROPERLY.  INSTALLED NEW PIN ASSY AND RIGGED.					1	L	7	2 	3O				A23CE
1998081400135	19980814	00135		1998	8	14	98ZZZX2667       	1	19980630	G	8120		BEARING HOUSING 	ROTOMASTER  																TURBO	DEFECTIVE       	B			RB9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										HOUSING SHOWS SIGNS OF FLAMESPRAY REPAIR.  FLAMESPRAY DAMAGE IS LOCATED ON GASKET SURFACE ON THE ALIGNMENT RING AND NEAR	 SEAL BORE AREA .  FLAMESPRAY IS SEPARATING FROM THE ORIGINAL BASE METAL.  PART IS UNREPAIRABLE AND REJECTED FROM  SERVI	CE.
1998081400136	19980814	00136		1998	8	14	98ZZZX2668       	1	19980630	G	8120		BEARING HOUSING 	ROTOMASTER  	600368      															TURBO	DEFECTIVE       	B			RB9R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15										ALUMINUM BEARING HOUSING WITH OBVIOUS SIGNS OF FLAMESPRAY REPAIR.  GASKET SURFACE AND ALIGNMENT RING ARE SEPARATING FROM	 THE BASE METAL.  SOME LARGE PIECES ARE ALREADY MISSING.  BRASS IS VISIBLE ALL OVER.  THIS PART IS UNREPAIRABLE AND WILL	 BE REJECTED FROM SERVICE.  IT IS SUBMITTER'S OPINION THAT BECAUSE THE FLAMESPRAY IS AN UNRELIABLE REPAIR ON THESE PARTS	, THE PROCESS SHOULD BE STOPPED.  NOTE:  ALUMINUM AND BRASS ARE NOT COMPATIBLE METALS.
1998081400137	19980814	00137	SW  	1998	8	14	98ZZZX2669       	1	19980701	G	3211	MS2000728	BOLT            			BBAVIA	8     	8GCBC       	1220803	SW  										RT MLG	FAILED          	H	S	A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	99	88451	1143 				13175				RIGHT LANDING GEAR ATTACH BOLT BROKE AS THE AIRCRAFT TURNED OFF THE RUNWAY AFTER A NORMAL LANDING.  NO HARD LANDING HIST	ORY.					1	H	7	1 	3O				A21CE
1998081400138	19980814	00138	SO  	1998	8	14	98ZZZX2670       	2	19980701	G	7414		MAGNETO         	SLICK       	6320        	CESSNA	340   	340CESSNA   	2076404	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE	FAILED          	B			CWBR	A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			GL	05	543D									PILOT  MADE PRECAUTIONARY LANDING WHEN LEFT ENGINE GOT ROUGH IN-FLIGHT.  ENGINE WOULD NOT RE-START ON GROUND.  FOUND LEF	T MAGNETO SEVERELY CORRODED INTERNALLY.  INVESTIGATION REVEALED RIGHT MAGNETO ON LEFT ENGINE AND BOTH MAGS ON RIGHT ENGI	NE IN SAME CONDITION, BUT HAD NOT FAILED YET.  FOUR NEW MAGS INSTALLED IN AIRCRAFT.				1	L	7	2 	3O	3	O		3A25    	E8CE
1998081400139	19980814	00139	EA  	1998	8	14	98ZZZX2671       	2	19980601	G	7414	M3081	POINT SET       	SLICK       	6350        	PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  					RT MAGNETO	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8216T	58   			95080073	328206037				UPON REPORT OF DEAD RIGHT MAGNETO, FOUND CONTACT POINT LOOSE IN POINT SET BODY.  OTHERWISE, POINT SET IN EXCELLENT CONDI	TION.					1	L	7	1 	3O	3	O		A3SO    	E14EA
1998081400140	19980814	00140	SO  	1998	8	14	98ZZZX2672       	1	19980707	G	7430	103512001	SWITCH          			PIPER 	PA28  	PA28R201    	7102816	SO  										MAG SWITCH	WORN            	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	171M	516  				28R7837051				AT ANNUAL INSPECTION, FOUND MAGNETO IGNITION SWITCH SO BADLY WORN THAT THE KEY WOULD FALL OUT.  REPLACED SWITCH.						1	L	7	1 	3O				2A13
1998081400141	19980814	00141	SO  	1998	8	14	98ZZZX2673       	1	19980707	G	5712	3572405	RIB             			PIPER 	PA28  	PA28R201    	7102816	SO  										WING WALK	CRACKED         	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	171M	5163 				28R7837051				AT ANNUAL INSPECTION, FOUND THE NOSE RIB UNDER THE WING WALK AREA CRACKED IN TWO PLACES.  REPLACED RIB.						1	L	7	1 	3O				2A13
1998081400142	19980814	00142	SO  	1998	8	14	98ZZZX2674       	1	19980707	G	2730	6353000	SHAFT           			PIPER 	PA28  	PA28R201    	7102816	SO  										PITCH TRIM	WORN            	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	171M	5163 				28R7837051				AT ANNUAL INSPECTION, FOUND PITCH TRIM HAD EXCESS FREE PLAY.  REPLACED DRUM AND SHAFT.						1	L	7	1 	3O				2A13
1998081400143	19980814	00143	SO  	1998	8	14	98ZZZX2675       	1	19980707	G	2730	6524600	DRUM            			PIPER 	PA28  	PA28R201    	7102816	SO  										PITCH TRIM	WORN            	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	171M	5163 				28R7837051				AT ANNUAL INSPECTION, FOUND PITCH TRIM HAD EXCESS FREE PLAY.  REPLACED DRUM AND SHAFT.						1	L	7	1 	3O				2A13
1998081400144	19980814	00144	SO  	1998	8	14	98ZZZX2676       	1	19980707	G	2710	62701143	CONTROL CABLE   			PIPER 	PA28  	PA28R201    	7102816	SO  										AILERON	WORN            	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	171M	5163 				28R7837051				AT ANNUAL INSPECTION, FOUND AILERON CABLE WORN BEYOND LIMITS.  REPLACED AND RE-RIGGED AILERON CABLES.						1	L	7	1 	3O			 	2A13
1998081400145	19980814	00145	EA  	1998	8	14	98ZZZX2677       	2	19980709	G	8530		CYLINDER        			PIPER 	PA20  	PA20        	7102002	SO  	LYC   	O320  	O320*       	41508	EA  					EXHAUST PORT	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	1160C	515  			113027	20962	113027			DURING THE ANUAL INSPECTION, DISCOVERED CRACKS IN THREE OF FOUR CYLINDERS. THE CRACKS WERE LOCATED IN THE EXHAUST PORT. 	 A CYLINDER COMPRESSION CHECK DID NOT REVEAL THE CRACKS.  THE CRACKS ARE ONLY DETECTED BY VISUAL INSPECTION.  SUBMITTER 	RECOMMENDED VISUAL INSPECTION OF EXHAUST PARTS AT 100 HR/ANNUAL INSPECTIONS, AND ANYTIME THE EXHAUST SYSTEM IS REMOVED.				1	H	7	1 	3O	3	O		1A4     	E274
1998081400146	19980814	00146	CE  	1998	8	14	98ZZZX2678       	1	19980713	G	5540	05310183	HINGE           			CESSNA	172   	172R        	2072401	CE  										RUDDER	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	441CA	192  				17280441				LOWER RUDDER ATTACH POINT HINGES EXCESSIVE WEAR.  IT APPEARS THE ATTACH POINT HOLE WAS DRILLED OVERSIZE IN ORDER FOR ALL	 3 ATTACH POINTS TO ALIGN UP.					1	H	7	1 	3O			NT	3A12
1998081400147	19980814	00147	CE  	1998	8	14	98ZZZX2679       	1	19980713	G	2460		SUPPORT         			CESSNA	172   	172R        	2072401	CE  										WIRE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	441CA					17280441				PEEL AND STICK ELECTRICAL WIRE SUPPORTS COMING LOOSE.  INTERFERRING WITH FLAP BELLCRANKS, CONTROL CABLES, AND RUBBING ON	 AIRCRAFT STRUCTURE.  SUBMITTER STATED ONLY EFFECTS THE 172R MODEL.					1	H	7	1 	3O			NT	3A12
1998081400148	19980814	00148	CE  	1998	8	14	98ZZZX2680       	1	19980713	G	7810	05540112	MUFFLER         			CESSNA	172   	172R        	2072401	CE  										HEATER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	441CA	192  				17280441				FOUND THE HEATER MUFFLER CRACKED AROUND THE FLANGE AREA ALONG THE WELD.  THIS MAKES SECOND ONE SEEN WITH LESS THAN 200 H	OURS TT.  CRACK WAS APPROXIMATELY 6 INCHES.  SUBMITTER STATED ONLY AFFECTS THE 172R MODELS.					1	H	7	1 	3O			NT	3A12
1998081400150	19980814	00150		1998	8	14	98ZZZX2682       	4	19980707	G	3422	FDO103011	FLUX DETECTOR   			CESSNA	414   	414A        	2075907	CE  										GYRO	SHORTED         	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	13	6604C	574  			H05595A	414A0030				GYRO CIRCUIT BREAKER TRIPPED 6 MINUTES INTO FLIGHT.  CIRCUIT BRAKER WOULD NOT RESET.  DISCOVERED THE FLUX DETECTOR P/N F	DO103011 HAD SHORTED INTERNALLY CAUSING THE GYRO CIRCUIT BREAKER TO TRIP.  FLUX DETECTOR WAS REPLACED.  AIRPLANE RETURNE	D TO SERVICE.				1	L	7	2 	3O				A7CE
1998081400154	19980814	00154	CE  	1998	8	14	98ZZZX2686       	1	19980709	G	3230	60820091	UPLOCK PIN      			BEECH 	60    	B60         	1153605	CE  										NLG	FAILED          	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	15	947GB	3190 				P365				ON LANDING, NOSE GEAR COLLAPSED.  SECTION OF LOWER DRAG BRACE FOUND ON RUNWAY.  SECTION HAD BROKEN OFF AT OVERCENTER PIN	.  UPLOCK P/N FAILED, BOTH ENDS DEPARTED AIRCRAFT AND WERE NOT FOUND.  SECTION OF UPLOCK PIN REMAINED IN NOSE GEAR UPPER	 STRUT HOUSING.  BEECH SB 2036 HAD NOT BEEN ACCOMPLISHED.				1	L	7	2 	3O				A12CE
1998081900042	19980819	00042	SO  	1998	8	19	98ZZZX2688       	2	19980708	G	8550	CH48110	OIL FILTER      	CHAMPION    		CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					ELEMENT	DEFECTIVE       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	02	4846D				F09G05	34946	069746R			OUTLET TUBE HAS BURRS ON INSIDE SURFACE FROM MACHINING OPERATION.  BURRS ARE HAIR-LIKE AND EASILY DETACHED.  FILTER INSP	ECTED PRIOR TO INSTALLATION AND NOT USED.  BURR APPEARS TO HAVE BEEN CAUSED WHEN CUTTING TOOL WAS RETRACTED. TOOKMARK CO	NTAINING BURRS IS ON A WIDE-PITCH SPIRAL OF APPROXIMATELY .25 INCH PITCH.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1998081400156	19980814	00156	CE  	1998	8	14	98ZZZX2689       	1	19980701	G	2914	2080007201	LEVER           			CESSNA	337   	T337D       	2075719	CE  										EMERGENCY PUMP	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	5311Q	1200 				3371093				DURING AN ANNUAL INSPECTION, CRACKS WERE DETECTED RADIATING FROM THE EMERGENCY GEAR PUMP LEVER FORKS.  BUSHINGS ON THE L	OWER END OF THE FORK WERE VERY WORN CAUSING EXCESSIVE PLAY.					1	H	7	2 	3O			 	A6CE
1998081400157	19980814	00157	GL  	1998	8	14	98ZZZX2690       	3	19980212	G	6114	D4206C55	HUB             													MCAULY	2AF34C	2AF34C55    	GL  	NR 1 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					791919			791919		PROPELLER RECEIVED FOR OVERHAUL.  AFTER PROPELLER DISASSEMBLY, HUB CRACKED IN NR 1 BLADE SOCKET 1 THREAD IN.  ONE INCH L	ONG AT 9:30 O'CLOCK POSITION.  CRACK DID NOT GO THROUGH THE HUB TO THE OUTSIDE OF HUB.  CRACK FOUND BY USING 10X MICROSC	OPE INSPECTION.  HUB WAS RETURNED TO CUSTOMER.														5	C	P5EA
1998081400158	19980814	00158	SO  	1998	8	14	98ZZZX2691       	1	19980701	G	2150	11M1030	BELT            			PIPER 	PA32  	PA32300     	7103212	SO  										AIR CONDITIONER	BROKE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	31569					327840133				AFTER APPROXIMATELY 1.50 HOURS, AIR CONDITIONER BELT BROKE.						1	L	7	1 	3O				A3SO
1998081400159	19980814	00159	SO  	1998	8	14	98ZZZX2692       	1	19980701	G	2150	11M1030	BELT            			PIPER 	PA32  	PA32300     	7103212	SO  										AIR CONDITIONER	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	31569					327840133				BELT BROKE AFTER 2.1 HOURS OPERATION, PULLEY ALIGNMENT WAS CHECKED AND VERIFIED BY THREE CERTIFIED AIRCRAFT MECHANICS. P	ROBLEM DID NOT EXIST UNTIL THE BELT DESIGN WAS CHANGED.					1	L	7	1 	3O				A3SO
1998081400160	19980814	00160	NM  	1998	8	14	98ZZZX2693       	1	19980715	G	3246	TW23A	WHEEL           	MAULE       	TW101       	CHILD 	S2    	S2BPITTS    	0110304	NM  										TAIL	FAILED          	D		A		K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	05	514BD	1    				5321				TAIL WHEEL RUBBER SEPARATED FROM METAL WHEEL AFTER THE FIFTH LANDING.  THIS IS THE SECOND OCCURRENCE IN A MONTH.  THE SI	DEWALL THICKNESS WAS UNDER .0312 INCH.  THIS IS WHERE THE SEPARATION STARTED.  THE TAIL WHEEL QUALITY FROM THE MANUFACTU	RER HAS BEEN POOR FOR THE LAST SIX MONTHS.  MFG HAS BEEN CONTACTED AND IS WORKING ON A SOLUTION.				1	Q	7	1 	3O				A8SO
1998081400161	19980814	00161	GL  	1998	8	14	98ZZZX2694       	1	19980701	G	5610		SPRING          			DIAMON	DA20A1	DA20A1      	05626UX	GL  										CANOPY	FAILED          	H	S			A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SW	99	856DF	1200 				10126				DURING FLIGHT, A LOUD NOISE WAS HEARD IN THE COCKPIT.  INSPECTION REVEALED THE CANOPY ASSIST SPRING (EASES OPENING OF CA	NOPY - 1 INSTALLED EACH SIDE) HAD BROKEN.  FLIGHT RETURNED TO BASE WITH NO FURTHER INCIDENT.  THIS WAS THIRD TIME ON 2 A	IRCRAFT.				1	L	7	1 	3O			NT	TA4CH
1998081400162	19980814	00162	EA  	1998	8	14	98ZZZX2695       	2	19980707	G	8500		ENGINE          			CESSNA	172   	172K        	2072430	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE EXHAUST	FIRE            	H		A		O				OTHER                   				A			FLAME/FIRE                			IN	INSP/MAINT     	1			SW	03	7224G					17258924	L2994427A			ENGINE WAS WARM.  WHEN STARTING AIRCRAFT ACCORDING TO WARM ENGINE START-UP PROCEDURE, IT CAUGHT FIRE BEFORE IT STARTED. 	 RECOMMENDATION:  LET ENGINE COOL OFF LONGER OR MODIFY STARTING PROCEDURE.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998081400163	19980814	00163	GL  	1998	8	14	98ZZZX2696       	3	19980212	G	6114	C1579C1	HUB             													MCAULY	2A36C	2A36C1      	GL  	NR 1 SOCKET	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					56862			56862		PROPELLER WAS RECEIVED FOR OVERHAUL.  DURING HUB INSPECTION, A CRACK WAS FOUND IN NR 1 BLADE SOCKET, 1 THREAD IN AT 5.30	 POSITION, 1 INCH LONG.  CRACK WAS DISCOVERED USING A 10X MICROSCOPE.  TRACK DID NOT GO THROUGH TO OUTSIDE OF HUB.															5	C	P880
1998081400164	19980814	00164	CE  	1998	8	14	98ZZZX2697       	1	19980601	G	2430	DGR3	CONTROL UNIT    	LAMAR       		CESSNA	210   	P210N       	2073454	CE  											FAILED          	D				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	01		3    			80093420					ALTERNATOR CONTROL UNIT FAILED.  INTERNALLY, FIELD OUTPUT PIN IS SHORTED TO GROUND.  INSPECTION OF REST OF ELECTRICAL SY	STEM REVEALED NO DEFECTS IN WIRING OR SWITCHES.  INSTALLATION OF ELECTRO SYSTEMS R575G RESTORED NORMAL OPERATION OF ELEC	TRICAL SYSTEM.  NOTE:  UNIT FAILED WAS SUPPLIED NEW FROM CESSNA.  IS MANUFACTURED BY LAMAR INDUSTRIES, A DIVISION OF PRE	CISION AIR MOTIVE.			1	H	7	1 	3O				3A21
1998081900043	19980819	00043	SO  	1998	8	19	98ZZZX2698       	2	19980421	G	8520	629104	SNAP RING       								CONT  	O470  	O470R       	17026	SO  					CRANKSHAFT	MISINSTALLED    	B	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11							811959R			THE ENGINE WHICH CONTAINED THESE PARTS WAS SHIPPED DIRECTLY FROM TCM AFTER REMANUFACTURE.  UPON DISASSEMBLY, FOUND THE C	RANKSHAFT COUNTERWEIGHT PIN SNAP RINGS WERE INSTALLED WITH THE SMOOTH ROUNDED SIDE TO THE OUTSIDE.  THE O-470 OVERHAUL M	ANUAL (72-50-07 PARA D) SPECIFICALLY STATES THE RETAINING RING IS TO BE INSTALLED 'WITH THE FLAT OR ROUGH SIDE OF THE RE	TAIING RING TO THE OUTSIDE'.  ALSO, ONE OF THE SNAP RINGS WAS NOT SEATED IN THE RETAINING RING GROOVE.  THIS CONDITION, 	IF NOT DETECTED, WOULD CAUSE A CATASTROPHE.							3	O			E273
1998081900044	19980819	00044	CE  	1998	8	19	98ZZZX2699       	1	19980625	G	2731		CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										ELEVATOR TRIM	MISROUTED       	B			MZER	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15	9730F	426  				17280032				WHILE PERFORMING CESSNA SB 98-27-06, FOUND ELEVATOR TRIM CABLES ROUTED WRONG.  (CABLES SWITCHED AROUND ON PULLEYS).  TRI	M TAB DOWN TRAVEL WAS ALSO INCORRECT.  FOUND 19 DEGREES, LIMIT IS 15 DEGREES, PLUS OR MINUS ONE DEGREE.  TRIM CABLE TENS	ION WAS TOO HIGH.  WAS 22 POUNDS.  LIMIT IS 15 POUNDS PLUS 5, MINUS ZERO.  ALL 4 TRIM ACTUATOR ATTACH SCREWS FOUND LOOSE	, 1 WAS ONLY IN 2 TURNS AND CROSS-THREADED IN NUTPLATE.  ELEVATOR TRAVEL FOUND OUT OF LIMITS. FOUND UP TRAVEL 30 DEGREES	, DOWN 26 DEGREES.  LIMITS ARE 28 DEGREES PLUS OR MINUS 1 DEGREE, UP 23 DEGREES PLUS OR MINUS 1 DEGREE DOWN.  FOUND BOTH	 ALERON CABLES ON SAME PULLEY IN LEFT WING ROOT.	1	H	7	1 	3O			NT	3A12
1998081400165	19980814	00165	CE  	1998	8	14	98ZZZX2700       	1	19980625	G	2821	07560397	STRAINER        			CESSNA	172   	172R        	2072401	CE  										FUEL SYSTEM	SEPARATION      	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1FACN	400  				17280417				THREADS BROKEN AND SUBSEQUENT SEPARATION OF THE BOWL AT GASCOLATOR ON THE NEW 172R DURING DISMANTLING ON THE FIRST 100 H	OUR INSPECTION.  INTERNAL INSPECTION HAS REVEALED THAT ONLY TWO THREADS WORKED FROM STANDPIPE 0756036-2 AND TOP ASSY 075	6039-6.  AIRWORTHINESS WAS RESTORED BY REPLACING THE FULL ASSY 'FUEL STRAINER ASSY' 0756039-7 SUPPLIED.  ALSO THE NEW FU	EL STRAINER FEATURES ONLY TWO THREADS WORKING.			1	H	7	1 	3O			NT	3A12
1998081400166	19980814	00166	SO  	1998	8	14	98ZZZX2701       	1	19980625	G	7810	3121202	PIPE            			PIPER 	PA23  	PA23250     	7102308	SO  										EXH CROSSOVER	FAILED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5938Y	2660 				273103				DURING POST 50 HOUR RUN-UP, NOTICED LOUDER THAN NORMAL EXHAUST NOISE IN NR 1 ENGINE.  REMOVED NOSE COWLS AND FOUND FORWA	RD EXHAUST CROSSOVER TUBE HEAT SHROUD BLOWN OPEN ABOUT 2 INCHES ROUND POINTING TOWARD ENGINE CASE.  REMOVAL OF SHROUD UN	COVERED EXHAUST SLIP JOINT OUTER SECTION (LONG SINGLE TUBE) DISTORTED AND BLOWN OUT.  HOT EXHAUST GASSES WERE VENTING DI	RECTLY TOWARD LOWER CASE AND SUMP AREA.  ESTIMATE PART FAILED NO MORE THAN 10 HOURS PRIOR TO DISCOVERY.  AIRCRAFT HAD 45	 HOURS FLIGHT TIME SINCE ANNUAL.  CONTINUED OPERATION IN THIS CONDITION WOULD HAVE RESULTED IN AN ENGINE FIRE.		1	L	7	2 	3O				1A10
1998081400167	19980814	00167	CE  	1998	8	14	98ZZZX2702       	1	19980609	G	3600	P610051	HOSE            			CESSNA	425   	425         	2076018	CE  										PNEU SYSTEM	MELTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	5CE	5100 				4250135				HOSE, P/N P610051, MELTED THROUGH AND BRITTLE.  FACTORY SUGGESTED REPLACING HOSE WITH A HIGHER TEMPERATURE HOSE.  LOUD A	IR PRESSURE LEAK IN COCKPIT AREA.  NO AIR PRESSURE INDICATION ON AIR PRESSURE GAUGE.  HOSE RUNS FROM T-FITTING UNDER RIG	HT AIR CONDITIONER EVAPORATOR TO FORWARD PRESSURE BULKHEAD.				1	L	7	2 	3T			RT	A7CE
1998081400168	19980814	00168	EA  	1998	8	14	98ZZZX2703       	1	19980709	G	3030	ST3003HA	HEATER          			CNDAIR	CL600 	CL6002B16   	1900305	EA  										STATIC PORT	FAILED          	B			JZBR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	25	449ML				6777	5022				'HEAT FAIL' LIGHT ILLUMINATED ON CONTROL PANEL; SWITCH ISOLATED TO RT STATIC POINT.  PART ORDERED NEW.  UNIT ARRIVED IN 	INOPERABLE CONDITION (OPEN HEATER COIL). SUBSEQUENT ORDER OF TWO STATIC PORTS PRODUCED 1 OUT OF 2 ALSO INOPERABLE.  INST	ALLED SERVICEABLE PART.  SYSTEM CHECKS OK.				2	L	7	2 	4F			RT	A21EA
1998081400169	19980814	00169	NE  	1998	8	14	98ZZZX2704       	2	19980701	G	8520	11768	CAM RING        			SCWZER	G164  	G164B       	3952802	EA  	PWA   	R1340 	R134051     	52016	NE  					ENGINE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8116K	8750 	195  		638917	572B	24219			ENGINE O/H FACILITY NOTIFIED OWNERS OF SPECIFIC ENGINES WITH A HIGH POSSIBILITY OF DEFECTIVE CAM ROLLERS AND AXLES THAT 	HAD BEEN INSTALLED WITH A HIGH INCIDENT OF FAILURE RATES.  UPON DISASSEMBLY OF ENGINE, IT BECAME APPARENT THAT THIS ENGI	NE, INDEED, HAD DEFECTIVE PARTS INSTALLED.  THE CAM RING HAD VISIBLE AND ADVANCED GALLING OF THE APPROACH RAMPS AND LOBE	S.  AN OVERHAULED CAM RING WITH NEW ROLLERS AND EXHAUST AXLES WERE APPLIED BY COVINGTON ACFT AND ENGINE REASSEMBLED.			1	Q	7	1 	3R	3	R		1A16    	5E2
1998081400170	19980814	00170	WP  	1998	8	14	98ZZZX2705       	1	19980618	G	3230	59248499	SIDE BRACE      			DOUG  	DC9   	DC9         	3022002	WP  										MLG	CRACKED         	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					PJE042					A CRACK WAS FOUND AT THE SHANK END APPROXIMATELY 90 DEGREES FROM THE MLG.  THE CRACK WAS 1 INCH LONG AND .015 INCH DEEP.	  FIXED SIDE BRACE ATTACHES TO THE MAIN LANDING GEAR SIDE BRACE.					2	L	7	2 	4F				A6WE
1998081400171	19980814	00171	NM  	1998	8	14	98ZZZX2706       	1	19980629	G	2150	27521	EMI FILTER      		2676        	BOEING	747   	747*        		NM  										CHILLER	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23					1361					MALFUNCTION WAS CAUSED BY THE FAILURE OF AN EMI FILTER CAPACITOR.  A NEW UPDATED FILTER WAS INTRODUCED IN MID 1996 AND S	ERVICE BULLETIN WAS ISSUED TO CHANGE OLD STYLE FILTER TO THE NEW REPLACEMENT MODEL.  THIS IS SECOND INCIDENT KNOWN OF OV	ER 4,500 UNITS IN OPERATION.				2	L	7	4 	4F			RT	A20WE
1998081400172	19980814	00172	EA  	1998	8	14	98ZZZX2707       	2	19980601	G	7200		ENGINE          			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  					LT ENGINE	FAILED          	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	99	603PA					LJ403	PCE21765			LEFT ENGINE LOST POWER IN-FLIGHT.  AIRCRAFT LANDED WITH NO INCIDENT.  NO DETERMINATION MADE, UNIT MUST BE TORN DOWN TO I	NSPECT.  SOUNDS LIKE BAD BEARINGS WHEN MOTORED BY STARTER.  ACFT LOST POWER IN-FLIGHT.  LANDED SAFELY AT SHEBOYGAN, WINC	ONSIN.  PILOT REPORTED ENGINE DECREASED IN POWER, BUT WAS SHUT DOWN AS A PRECAUTION.  ENGINE REMOVED FOR DISASSEMBLY AND	 INSPECTION.  ENGINE MOTORED ON GROUND WITH STARTER.  SOUNDED LIKE COMPRESSOR BLADES WERE DRAGGING.  METAL CONTAMINATION	 FOUND IN EXHAUST STACKS.		1	L	7	2 	3T	3	T		3A20    	E4EA
1998081400173	19980814	00173	CE  	1998	8	14	98ZZZX2708       	1	19980520	G	2710	676014118	BEAM            			CESSNA	750   	750         	2076810	CE  										AIL PCU ATTACH	LOOSE           	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	206PC	834  				7500016				DURING C/W SB 750-27-11, BOTH AILERON PCU'S  WEEPING HYD FLUID.  PCU'S REPLACED AND SB  ACCOMPLISHED.  ACFT RIGGED AND T	ESTED IAW CE750 MM.  ON NEXT FLT, COCKPIT EICAS MESSAGES INDICATED AILERON PCU RIGGING INADEQUATE.  HYD SERVICE UNIT RE-	INSTALLED, RIGGING RE-CHECKED AND FOUND IN C/W PUBLISHED MM PROCEDURES.  NOTICED BEAMS SUPPORTING PCU'S FLEXING.  THREE 	OF 11 FWD BEAM BOLTS, WHICH MOUNT INTO NUT PLATES, HAD NO TORQUE DUE TO STRIPPED NUT PLATES.  PER CESSNA, REMOVED NUT PL	ATES AND REINSTALLED BOLTS WITH NUTS.  THIS DID NOT SOLVE RIGGING DILEMMA.   USE OF PROTOTYPE DATA MONITOR UNIT ALLOWED 	FINE-TUNING OF THE RIGGING OF THE PCU'S.  ACFT TEST FLOWN AND FOUND TO OPERATE NORMAL IN ALL REGIMES OF FLIGHT.	2	L	7	2 	4J			RT	T00007WI
1998081400174	19980814	00174		1998	8	14	98ZZZX2709       	2	19980713	G	7414	M3529	IMPULSE COUPLING	SLICK       	4373        	AMTR  		RV4         			CONT  		IO360A      							LT MAGNETO	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	988BB	60   			95080145	BB1				AIRCRAFT ENGINE IS EQUIPPED WITH ELECTRONIC IGNITION ON RIGHT SIDE OF ENGINE WITH A START MODE, SO DID NOT REALIZE THE I	MPULSE ON LEFT SIDE.  SLICK MAG WAS GOING BAD UNTIL THE MAGNETO TOTALLY DID NOT WORK.  IMPULSE COUPLING SPRING LOST TENS	ION UNTIL MAG FAILURE.							0
1998081400180	19980814	00180	CE  	1998	8	14	98ZZZX2714       	1	19980507	G	3230	4430	BRUSH           		1153800025  	BEECH 	200   	200BEECH    	1152920	CE  										MLG MOTOR	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	83JN	809  			1099	BB553				ONE OF FOUR BRUSHES WAS WORN TO EXCESSIVE LIMIT.  CAUSED LANDING GEAR TO NOT OPERATE CORRECTLY.  BRUSH WORN TO EXPOSE WI	RE.					1	L	7	2 	4T				A24CE
1998081400181	19980814	00181	EA  	1998	8	14	98ZZZX2715       	2	19980709	G	8530		CYLINDER        			PIPER 	PA20  	PA20        	7102002	SO  	LYC   	O320  	O320*       	41508	EA  					ROCKER BOSS	DEFECTIVE       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	1160C				6605303H	20962	113027			TWO OF FOUR NEW COMPLETE CYLINDER ASSEMBLIES WERE DEFECTIVE.  ONE CYLINDER HAD BEAT ROCKER SHAFT BOSSES, THE OTHER HAD A	 CRACK IN THE EXHAUST PORT.					1	H	7	1 	3O	3	O		1A4     	E274
1998081400182	19980814	00182	EA  	1998	8	14	98ZZZX2716       	2	19980709	G	8530	65099REV1	CYLINDER        			PIPER 	PA20  	PA20        	7102002	SO  	LYC   	O320  	O320*       	41508	EA  					EXHAUST PORT	DEFECTIVE       	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	1160C				6622627H	20962	113027			TWO OF FOUR NEW COMPLETE CYLINDER ASSEMBLIES WERE DEFECTIVE.  ONE CYLINDER HAD BEAT ROCKER SHAFT BOSSES, THE OTHER HAD A	 CRACK IN THE EXHAUST PORT.					1	H	7	1 	3O	3	O		1A4     	E274
1998081400184	19980814	00184	SO  	1998	8	14	98ZZZX2718       	2	19980623	G	7310	63521854S1200	LINE            			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520AF   	17040	SO  					FUEL PUMP	FAILED          	D				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			NM	01	4617A					P21000809	245246R			DURING TEST FLIGHT AFTER INSTALLING FACTORY REBUILT ENG, FUEL PRESS DROPPED FROM REQUIRED 186 POUNDS PER/HR TO 80 POUNDS	 PER/HR.  A SAFE PRECAUTIONARY LANDING WAS EXECUTED.  UPON EXITING RUNWAY, ENG STOPPED RUNNING WITHOUT PULLING THE MIXTU	RE.  EXITING ACFT, FUEL FOUND RUNNING FROM LOWER COWL.  REMOVING COWL AND INSPECTING FUEL SYSTEM, DISCOVERED B-NUT ON HI	GH PRESS FUEL LINE FROM FUEL PUMP TO FUEL CONTROL WHICH IS INSTALLED BY FACTORY, LOOSE.  THIS NUT WAS MARKED WITH ANTI-T	AMPER PAINT BY THE FACTORY AND WAS INSPECTED AND FOUND TIGHT.  PREVIOUS TO FLT, FULL POWER RUN-UPS AND FUEL FLOW CHECKS 	PERFORMED IAW FACTORY GUIDE LINES FOR ENG.  POST-RUN EXAM REVEALED NO LEAKS.	1	H	7	1 	3O	3	O	 	3A21    	E8CE
1998081400185	19980814	00185	WP  	1998	8	14	98ZZZX2719       	1	19980528	G	5320	AFA70981	SPLICE          			DOUG  	DC10  	DC1030      	3023501	WP  										BS 1812.63	CRACKED         	B			SWRY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	240NW					48319				FUSELAGE STATION 1812.63.  PRODUCTION SPLICE OF LONGERON NR 46 RT.  FORWARD LONGERON SECTION AT SPLICE, P/N AFA 7098-1 H	AS 200 MM LONG CRACKS IN THE WEB-TO-CROWN RADII.  CRACKS ARE MOST LIKELY CAUSED BY STRESS CORROSION.  INSTALL SHIMS TO P	REVENT PRE-LOAD (IN PRODUCTION AND IN REPAIRS).  APPLY CORROSION PROTECTION PER SRM 51.				2	L	7	3 	4F				A22WE
1998081400186	19980814	00186	WP  	1998	8	14	98ZZZX2720       	1	19980528	G	5320	AGA70391	SPLICE          			DOUG  	DC10  	DC1030      	3023501	WP  										BS 1812.63	CRACKED         	B			SWRY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	240NW					48319				FUSELAGE STATION 1812.63.  PRODUCTION SPLICE OF LONGERON NR 46 RT.   AFT SECTION AT SPLICE, P.N AGA7039-1, HAS 200 MM LO	NG CRACKS IN THE RADIUS OF WEB-TO-CROWN.   CRACKS ARE MOST LIKELY CAUSED BY STRESS CORROSION.  INSTALL SHIMS TO PREVENT 	PRE-LOAD (IN PRODUCTION AND IN REPAIRS).  APPLY CORROSION PROTECTION PER SRM 51.				2	L	7	3 	4F				A22WE
1998081400187	19980814	00187	WP  	1998	8	14	98ZZZX2721       	1	19980528	G	5321		FLOOR           			DOUG  	DC10  	DC1030      	3023501	WP  										GALLEY	CORRODED        	B			SWRY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	33	240NW					48319				CORROSION CAUSED BY LIQUIDS FROM AFT GALLEYS AND LAVATORIES PENETRATING THROUGH GALLEY FLOOR COVERING.  APPLIED CORROSIO	N INHIBITING COMPOUND ON THE FLOOR SUPPORT-TEE.  RECOMMENDED TO RE-APPLY EACH D-CHECK.  RECOMMENDED TO PERIODICALLY INSP	ECT FLOOR COVERING AND SEAL FOR DISCREPANCIES.				2	L	7	3 	4F				A22WE
1998081400188	19980814	00188	NE  	1998	8	14	98ZZZX2722       	2	19980629	G	7230	50B050	SEAL SCAT       								PWA   	4460  	PW4460      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C4634					NR 1 BEARING SEAL SCAT IS A CHROME FACED SEAL.  ONCE THE CHROME IS REMOVED, THERE ARE CRACKS IN THE BASE METAL DETECTED 	BY FMPI.  USUALLY LIGHT MACHINING WILL REMOVE THESE INDICATIONS, BUT THIS CONDITION APPEARS TO BE GETTING WORSE ON THIS 	PART.  THE CRACKS IN THIS PART CANNOT BE REMOVED.									4	F			E24NE
1998081400191	19980814	00191		1998	8	14	98ZZZX2725       	4	19980709	G	2563		PIN             			RKWELL	NA265 	NA26540     	6402608	CE  										DRAG CHUTE	FAILED          	B			Y1RR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	467H									THE CLIP THAT RETAINS THE DRAG CHUTE RETAINING PIN VIBRATES LOOSE WHEN CHUTE WAS DEPLOYED, IT DETACHED FROM THE AIRCRAFT	.  THE YOKE AND RETAINING PIN CAUGHT ON THE EDGE OF THE SKIN CAUSING DAMAGE TO LOWER TAIL SKIN AND STRUCTURE.  THIS IS A	 ONE OF A KIND INSTALLATION DONE ON STC SA1721SW.  SUSPECT CAUSE OF INCIDENT WAS IMPROPER INSTALLATION OF C-CLIP RETAINE	R ON RETAINING PIN.  THE CHUTE WAS DEPLOYED AS A TEST OF THE SYSTEM AND DID NOT CAUSE A LANDING PROBLEM.			2	L	7	2 	4J				A2WE
1998081900045	19980819	00045	CE  	1998	8	19	98ZZZX2726       	1	19980617	G	3231	1N2430	BOLT            			LEAR  	35    	35A         	5170602	CE  										NLG WELL	MISINSTALLED    	B	L	A	JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	365N					300				NOSE GERA DOOR MECHANISM ROD ATTACH PONT BOLT P/N AN24-30 TO NOSE STRUT IS BEING INCORRECTLY INSTALLED ACCORDING TO LEAR	JET IPC CH 32-23-05, FIG 05, ITEM 21, PAGE 0, AND CAUSING GOUGING TO THE SKIN AT FRAME 5, FS 160.77.  IN REFERENCE TO TH	E ILLUSTRATION, THE POSITION OF THE BOLT HEAD SHOULD BE INSTALLED WITH THE BOLT HEAD FACING OUTBOARD TO MAINTAIN CLEARAN	CE BETWEEN THE BOLT HEAD AND FRAME SKIN.  THE GOUGING OCCURS WHEN THE BOLT HEAD IS BEING INSTALLED IN THE INBOARD POSITI	ON AND THE THREADED PORTION OF THE BOLT IS GOUGING THE FRAME SKIN.		2	L	7	2 	4F			 	A10CE
1998081400386	19980814	00386	EA  	1998	8	14	98ZZZX2776       	2	19980609	G	8530	145902	VALVE           			SKRSKY	S58   	S58E        	8141809	NE  	WRIGHT	R1820 	R182084     	67020	EA  					NR 6 CYL EXH	FAILED          	B			HTIR	R	A			AUTOROTATION            	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	17	58HF		446  			571692	BL513995			WHILE IN NORMAL FLIGHT, EXHAUST VALVE FAILED CAUSING ENGINE TO SHUT DOWN.  AIRCRAFT WAS AUTOROTATED SAFELY TO THE GROUND	 WITHOUT FURTHER DAMAGE.					2	G	7	1 	4R	4	R		1H11    	TC169
1998081400388	19980814	00388	SW  	1998	8	14	98ZZZX2779       	1	19980701	G	7722	2060751907	INDICATOR       			BELL  	206   	206B        	1181511	SW  										ENGINE TOT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX		90   		2388	2872				TOT FLUCTUATING.  REMOVED FROM AIRCRAFT.  AWAITING FUNCTIONAL CHECK.						1	G	7	1 	3U				H2SW
1998081400389	19980814	00389	SW  	1998	8	14	98ZZZX2780       	1	19980629	G	2912	2060760341	FILTER          			BELL  	206   	206B        	1181511	SW  										HYD	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX				0288	2872				FAILED TO BYPASS WHEN FILTER PLUGGED.  REMOVED AND SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998081400390	19980814	00390	SW  	1998	8	14	98ZZZX2781       	1	19980629	G	2437	2060751863	LOAD METER      			BELL  	206   	206B        	1181511	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX				2904	2872				NEEDLE WILL NOT MOVE AT ALL.  REMOVED FROM AIRCRAFT AND SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998081400391	19980814	00391	SW  	1998	8	14	98ZZZX2782       	1	19980205	G	6220	206011150105	STRAP FITTING   			BELL  	206   	206L3       	1182108	SW  										M/R	WORN            	H			A05L	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206MY	816  			A13359	51514				THE FITTING PIN HOLES EXCEEDS MAXIMUM DIMENSION ON THE UNWORN PORTION OF THE HOLE PER 206L-1 CRO BY .005 INCH TO .0053 I	NCH.  REPLACED FITTING WITH NEW FITTING.					1	G	7	1 	3U				H2SW
1998081400394	19980814	00394	WP  	1998	8	14	98ZZZX2785       	1	19980520	G	5302	269A23237	FITTING         			HUGHES	269   	269C        	4470504	WP  										TAIL BOOM ATTACH	FAILED          	A				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	41TH	179  				S1747				PILOT REPORTED THE TAIL BOOM FORWARD ATTACH FITTING FAILED DURING A SUDDEN APPLICATION OF POWER WHILE RECOVERING FROM A 	SIMULATED AUTOROTATION.  OTHER EVIDENCE SUGGESTS THE FITTING LUG MAY HAVE FAILED DUE TO TAIL ROTOR CONTACT WITH SOFT GRO	UND.				1	G	7	1 	3O				4H12
1998081400395	19980814	00395		1998	8	14	98ZZZX2786       	4	19980623	G	3422	369H92832	GYRO            			HUGHES	369   	369D        	4470706	WP  										COCKPIT DG	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC		513  		4370	290456D				DIRECTIONAL GYRO INOPERABLE.  REMOVED AND SENT FOR REPAIR.						1	G	7	1 	3U				H3WE
1998081400396	19980814	00396	WP  	1998	8	14	98ZZZX2787       	1	19980701	G	2436	369A4652	REGULATOR       			HUGHES	369   	369D        	4470706	WP  										BATTERY BOX	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC		1204 		35114	290456D				VOLTAGE REGULATOR WILL NOT ADJUST.  REMOVED FROM AIRCRAFT AND SENT FOR REPAIR.						1	G	7	1 	3U				H3WE
1998081400397	19980814	00397	GL  	1998	8	14	98ZZZX2788       	2	19980623	G	7314	3865005	PUMP            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	STRIPPED        	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	5027P	2900 			TIO4760	611002D				THREADS STRIPPED ON PUMP LOW PRESSURE VALVE.  REMOVED FROM AIRCRAFT AND SENT FOR REPAIR.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998081400398	19980814	00398		1998	8	14	98ZZZX2789       	4	19980701	G	3421	146021101	INDICATOR       			BELL  	204   	UH1H        	1181407	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	51AG				A152227	7120178				ATTITUDE INDICATOR WILL NOT CAGE.  REMOVED FROM AIRCRAFT.						1	G	7	1 	4U				EXPA1G71
1998081400399	19980814	00399	SW  	1998	8	14	98ZZZX2790       	1	19980728	G	6710	2060103423	PITCH LINK      		206010350   	BELL  	206   	206B        	1181511	SW  										PYLON	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	76PE					1818				CRACKS AT END OF TUBE WHERE ADJUSTMENT INSERT LOCATED (206-010-356-001).  AIRCRAFT TOTAL TIME 9,500 HOURS.  FOUND DURING	 100-HOUR INSPECTION..					1	G	7	1 	3U				H2SW
1998081400400	19980814	00400	NE  	1998	8	14	98ZZZX2791       	1	19980717	G	6520		GEARBOX         			SKRSKY	S76   	S76B        	8143007	NE  										TAIL ROTOR	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	01	780P	3815 	471  		A23900078	760359				DURING 150-HOUR ZONE INSPECTION, FOUND APPROXIMATELY 2 INCH CRACK IN GEARBOX HOUSING NEAR INPUT SIDE.  CRACK WAS NOT NEA	R ANY MOUNTING BOSS, STUD OR HOLE.  CRACK WAS ALMOST UNDETECTABLE BY VISUAL MEANS.  MECHANIC FOUND CRACK BY WIPING CASE 	DOWN WITH SOLVENT AND THEN NOTICED OIL ON THE CASE THE NEXT DAY.  FURTHER INVESTIGATION REVEALED THE CRACK.				1	G	7	2 	4U				H1NE
1998081400401	19980814	00401	SW  	1998	8	14	98ZZZX2792       	1	19980629	G	2436	07639CSV115212A	REGULATOR       			BELL  	204   	UH1B        	1181410	SW  										DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	847MC				BR6229A	638694				VOLTAGE REGULATOR WILL NOT HOLD VOLTAGE.  REMOVED FROM AIRCRAFT AND SENT TO REPAIR.						1	G	7	1 	4U				EXPA1G71
1998081400402	19980814	00402	GL  	1998	8	14	98ZZZX2793       	2	19980406	G	7323	2540117	DRIVE SPLICE    	BENDIX      	23057870    	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					GOVERNOR	DISCONNECTED    	D	S			K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SW	03	842LA		879  			0020E	CAE800974F			THE ENGINE RPM BECAME UNSABLE.  REMOVED GOVERNOR, FOUND RETAINING RING, RING RETAINER, AND SHIM MISSING FROM SHAFT.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998081400403	19980814	00403	SW  	1998	8	14	98ZZZX2794       	1	19980629	G	3340	0107700621A490A	POWER SUPPLY    			BELL  	206   	206B        	1181511	SW  										STROBE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322				03640	1736				STROBE POWER SUPPLY  BOX WILL NOT POWER UP.  REMOVED FROM AIRCRAFT AND SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998081400405	19980814	00405	NE  	1998	8	14	98ZZZX2796       	1	19980713	G	6320	S613523053102	GEAR            			SKRSKY	S61   	S61N        	8142104	NE  										M/R GEARBOX	FAILED          	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			NM	10	9119S		269  		B12802562					MAIN GEARBOX CHIP LIGHT CAME ON IN-FLIGHT.  AIRCRAFT WAS SHUT DOWN AND FERROUS METAL FLAKES FOUND ON CHIP PLUG.  UPON DI	SASSEMBLY OF GEARBOX, INPUT GEAR WAS FOUND CRACKED.  THE CRACK WAS AT THE BASE OF TOOTH FOR THE ENTIRE LENGTH OF TOOTH A	ND INTO BEARING AREA.  INSPECTION OF GEAR SHOWED AN INCLUSION IN THE METAL WHERE THE CRACK ORIGINATED.				2	G	7	2 	4U				1H15
1998081400406	19980814	00406	SW  	1998	8	14	98ZZZX2797       	1	19980706	G	2436	15891F	REGULATOR       			BELL  	206   	206B        	1181511	SW  										DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9007K		1218 		RK23643	2040				VOLTAGE REGULATOR WILL NOT ADJUST.  SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998081400407	19980814	00407	SO  	1998	8	14	98ZZZX2798       	1	19980724	G	3211	401310	BOLT            			PIPER 	PA28  	PA28R201T   	7102813	SO  										TRUNNION PLATE	LOOSE           	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2611M	2276 				28R7803138				DURING ANNUAL INSPECTION, A WRENCH WAS USED TO CHECK THE MLG TRUNNION FLAP BOLTS FOR TIGHTENESS.  ALL WERE FOUND LOOSE. 	 SUBMITTER HAD BEEN CHECKING ALL PA28R, PA32R, AND PA34 THAT HE SERVICED AND FOUND MOST LOOSE.  THE MAIN LANDING GEAR CA	N MOVE UP AND DOWN DURING LANDING CAUSING THE SPAR HOLES TO ELONGATE AND POSSIBLY CRACK.  SUBMITTER STATED THEY SHOULD B	E CHECKED AT LEAST MONTHLY.			1	L	7	1 	3O				2A13
1998081400408	19980814	00408	SO  	1998	8	14	98ZZZX2799       	1	19980724	G	3211	401311	BOLT            			PIPER 	PA28  	PA28R201T   	7102813	SO  										TRUNNION PLATE	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	2611M	2276 				28R7803138				DURING ANNUAL INSPECTION, A WRENCH WAS USED TO CHECK THE MLG TRUNNION FLAP BOLTS FOR TIGHTENESS.  ALL WERE FOUND LOOSE. 	 SUBMITTER HAD BEEN CHECKING ALL PA28R, PA32R, AND PA34 THAT HE SERVICED AND FOUND MOST LOOSE.  THE MAIN LANDING GEAR CA	N MOVE UP AND DOWN DURING LANDING CAUSING THE SPAR HOLES TO ELONGATE AND POSSIBLY CRACK.  SUBMITTER STATED THEY SHOULD B	E CHECKED AT LEAST MONTHLY.			1	L	7	1 	3O				2A13
1999013000003	19990130	00003		1999	1	30	98ZZZX2800       	4	19980713	G	2562	JE21978ONG	ELT             			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										ANTENNA	MISMANFACTURED  	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	197TB	424  			13321	1806				ANTENNA INSULATING SEPARATOR INSTALLED ON WRONG SIDE.  ALLOWS BUILT-IN ANTENNA TO BE CONNECTED AT ALL TIMES, STOWED OR E	XTENDED.					1	L	7	1 	3O			NT	A51EU
1998081400409	19980814	00409	CE  	1998	8	14	98ZZZX2801       	1	19980716	G	2434	ALT9422R	ALTERNATOR      	ELECTROSYS  		BEECH 	58    	58          	1152740	CE  										SHAFT	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H		215  		7092418	TH219				REMOVED ALTERNATOR AT ENGINE CHANGE.  FOUND SHAFT BEARINGS FAILED (DRIVE END), .1250 INCH MOVEMENT SIDE TO SIDE. UP AND 	DOWN.  TIME IN SERVICE 215 HOURS.  REMOVED JUST PRIOR TO FAILURE AND ENGINE DAMAGE.  (ELECTRO SYSTEMS O/H UNIT).					1	L	7	2 	3O				3A16
1998081400410	19980814	00410	CE  	1998	8	14	98ZZZX2802       	1	19980717	G	8011	6462751	STARTER         	ELECTROSYS  		BEECH 	58    	58          	1152740	CE  										ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H		80   		U149773	TH219				INSPECTION FOUND STARTER FAILED IN 45 DAYS AND 80-HOUR TIME IN SERVICE.  ELECTRO SYSTEMS O/H UNIT.						1	L	7	2 	3O				3A16
1998081400411	19980814	00411	SO  	1998	8	14	98ZZZX2803       	1	19980723	G	2434	ALU8421	ALTERNATOR      	PRESTOLITE  		PIPER 	PA31  	PA31350     	7103110	SO  										DC SYSTEM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	35892		86   		6090245					FRONT HOUSING CRACKED (ON MOLD MARKS) BEHIND COOLING FAN.  ALUMINUM CASTING CRACKED .8750 INCH AROUND THE ALTERNATOR WIT	H ONLY ONE SUPPORT LEFT SUSTAINING DRIVE PULLEY AND COOLING FAN.  CRACK FOLLOWED CASTING SEAM AROUND THE CIRCUMFERENCE.					1	L	7	2 	3O				A20SO
1998081400412	19980814	00412	SO  	1998	8	14	98ZZZX2804       	2	19980720	G	8520		BOLTS           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					CRANKCASE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	409EX	159  				4040436	218323R			TRU-BOLTS (UPPER  TWO) AND UPPER TWO CYLINDER HOLD-DOWN STUDS FOUND BROKEN ON NR 6 CYLINDER OF THE NR 1 ENGINE.  CAUSED 	EXHAUST STACK TO BREAK AT FLANGE.  EXHAUST GAS DAMAGED CROSS MEMBER OF ENGINE CRADLE, PROP GOVERNOR, COWLING AND IGNITIO	N HARNESS.				1	L	7	2 	3O	3	O		A25CE   	E7CE
1998081900054	19980819	00054	CE  	1998	8	19	98ZZZX2805       	1	19980721	G	2820	0700099130	FUEL LINE       			CESSNA	182   	182S        	2072701	CE  										UNDER FLOOR	MISINSTALLED    	B	P		RSUR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	446ES	66   				18280113				DURING A ROUTINE INSPECTION, FUEL LINE NR 0700099-130 WAS FOUND INSTALLED WITHOUT THE FERREL UNDER THE B-NUT FITTING.  T	HE LOCATION WAS UNDER THE FLOORBOARD DIRECTLY UNDER THE PILOT'S SEAT.  AMAZING THE LINE WAS NOT LEAKING, YET!					1	H	7	1 	3O			NT	3A13
1998081400414	19980814	00414	SO  	1998	8	14	98ZZZX2807       	2	19980723	G	8520		CONNECT ROD     			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520N    	17040	SO  					NR 2 CYLINDER	FAILED          	B			AZOR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	63JH		578  			414A0036	514105			THIS ENGINE WAS OVERHAULED 5-27-85.  TIME SINCE OVERHAUL 578 HOURS.  THE CONNECTING ROD FAILED AT THE CAP/BOLT AREA.  PO	SSIBLE BOLT FAILURE.  NO FURTHER INFORMATION WAS AVAILABLE.					1	L	7	2 	3O	3	O		A7CE    	E8CE
1998081400415	19980814	00415	SO  	1998	8	14	98ZZZX2808       	2	19980721	G	7323	182738	O-RING          		A210800J    	BEECH 	58    	58          	1152740	CE  	CONT  	O550  	IO550C      		SO  					GOVERNOR	FAILED          	B			EK2D	O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			SW	09	73TT	227  			11977228	TH1565	810296			DROP OF APPROXIMATELY 800 RPM ON TAKEOFF.  PHASING COIL O-RING ENTANGLED WITH FLYWEIGHT ASSEMBLY.						1	L	7	2 	3O	3	O		3A16    	E3SO
1998081400416	19980814	00416	CE  	1998	8	14	98ZZZX2809       	1	19980729	G	2571		BATTERY BOX     			CESSNA	210   	T210M       	2073451	CE  										FIREWALL	CORRODED        	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	761VZ	2113 				21062565				DURING ANNUAL INSPECTION, RIVETS IN BOTTOM OF BOX WERE FOUND CORRODED AND MISSING UNDER PLASTIC LINER ALLOWING ACID INTO	 COCKPIT.  MORE FREQUENT INSPECTION RECOMMENDED.					1	H	7	1 	3O				3A21
1998081400417	19980814	00417	EA  	1998	8	14	98ZZZX2810       	2	19980727	G	7322	AN9112D	NIPPLE          			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540L3C5    	41532	EA  					CARBURETOR INLET	FAILED          	G				O				OTHER                   				K	A		FLUID LOSS                	FLAME/FIRE                		NR	NOT REPORTED   	1			GL	21	9142C					R18200417				NIPPLE THAT CONNECTS CARBURETOR FINGER SCREEN TO SUPPLY LINE T-FITTING BROKE OFF IN FLIGHT CAUSING FUEL TO BE SPRAYED IN	TO ENGINE COMPARTMENT.  FUEL IGNITED AND BURNED A HOLE THROUGH BELLY SKIN JUST AFT OF FIREWALL.					1	H	7	1 	3O	3	O	RT	3A13    	E295
1998081400418	19980814	00418	NE  	1998	8	14	98ZZZX2811       	2	19980706	G	7200		ENGINE          			BOEING	747   	747273C     	1384896	NM  	PWA   	JT9   	JT9*        	52054	NE  					NR 2	FAILED          	B			GK4Y	A	J			UNSCHED LANDING         	DUMP FUEL               			J			WARNING INDICATION        			CL	CLIMB          	1			WP	03	470EV					20653				DURING CLIMB-OUT AT 8,000 FEET, AIRCRAFT EXPERIENCED A LOUD EXPLOSIVE NOISE PLUS HIGH EGT ON NR 2 ENGINE.  AIRCRAFT AIR 	TURN BACK AFTER DUMPING FUEL.  ON INVESTIGATION, FOUND METAL PARTICLES IN NR 2 ENGINE TAILPIPE.					2	L	7	4 	4F	4	F		A20WE   	E20EA
1998081400676	19980814	00676	NE  	1998	8	14	98ZZZX2812       	1	19980706	G	2410		ROLLERS         		643520500048	SKRSKY	S64   	S64F        		NE  										RIDING SURFACE	WORN            	B		A	JYDR	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			NM	09	159AC	4604 	1879 		A6130	64084				SUBMITTER STATED THIS MDR AFFECTS S-64E MODEL.  ACFT WAS FLYING UNDER NORMAL CONDITIONS WHEN NR 1 AND NR 2 GEN WENT OFF-	LINE AND INVERTER POWER WAS NEEDED FOR A/C TO RETURN TO LANDING.  INITIAL INSP REVEALED ALL WIRES CONNECTED AND CB'S IN 	CORRECT POSITIONS.  ALSO, NR 1 AND NR 2 GENERATOR SPLINED QUILL SHAFTS WERE SHEARED ALLOWING GEN DRIVE GEARS IN REAR ACC	Y COVER TO SPIN FREELY.  NEW SPLINED QUILL SHAFTS INSTALLED IN GENERATORS AND A/C CONTINUED IN SERVICE.  INVEST SHOWED E	XCESS WEAR EXISITED RESULTING IN SLIPPAGE AND RE-ENGAGEMENT OF TTO FREE WHEEL UNIT.  SPLINED QUILL SHAFTS IN NR 1 AND NR	 2 GENERATORS WERE BROKEN BECAUSE OF POLAR INERTIA OF GEN ROTORS WHEN TTO FREE WHEEL UNIT SLIPPED AND RE-ENGAGED.	2	G	7	2 	4U				H6EA
1998082100051	19980821	00051	NE  	1998	8	21	98ZZZX2832       	1	19980630	G	6210	61152052001	BLADE           		641520201042	SKRSKY	S64   	S64F        		NE  										MAIN ROTOR	FAILED          	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										NOTE:  THE ACRONYM 'BIM' STANDS FOR BLADE INSPECTION METHOD AND IS A TERM REGISTERED BY SIKORSKY.  THE INDICATOR SENSES 	PRESSURE WITHIN THE BLADE SPAR AND CHANGES COLOR TO DENOTE A LEAK WHICH MAY BE CAUSED BY A CRACKED SPAR INDICATING THIS 	MDR SUBJECT HAS AIRWORTHINESS IMPLICATIONS.  THESE BIM INDICTORS WERE OVERHAULED BY AIR SHUNT INSTRUMENTS INC.  RECEIVED	 AT EAC WITH SERVICEABLE TAGS AND WERE PLACED IN SERVICEABLE INVENTORY.  AFTER THREE INDICATORS WERE DISCOVERED DEFECTIV	E, THE REMAINING STOCK OF 23 WAS SENT TO THE BLADE SHOP TO BE TESTED IAW SB 64F 62-10-1, SB 64B15-4C.  A TOTAL OF 23 IND	ICATORS WERE FOUND DEFECTIVE.	2	G	7	2 	4U				H6EA
1998012200377	19980122	00377	WP  	1998	1	22	98ZZZX287        	1	19980109	G	2710	5642920503	SUPPORT ASSY    		5715841501  	DOUG  	DC8   	DC8*        		WP  										AILERON CONTROL	CRACKED         	B		A	DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										THE AILERON CONTROL REVERSION ASSEMBLY HAS A CRACK ON BOTH SIDES OF THE SUPPORT ASSEMBLIES.						2	L	7	4 	4J			F	4A25
1998012200380	19980122	00380	CE  	1998	1	22	98ZZZX290        	1	19980108	G	2510	08127358	PIVOT ARM       			CESSNA	414   	414A        	2075907	CE  										PILOT SEAT	BROKEN          	B			DWSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	650DB	3061 				414A0853				PILOT REPORTED SEAT BACK MOVEMENT.  FOUND PILOT'S SEAT INBOARD PIVOT ARM UPPER PORTION BROKEN.  ONCE PART WAS REMOVED, B	ROKEN SECTION APPEARED TO HAVE BEEN CRACKED FOR SOME TIME.  WITH UPHOLSTERY IN THIS AREA, INSPECTION IS DIFFICULT.					1	L	7	2 	3O				A7CE
1998012200383	19980122	00383	SW  	1998	1	22	98ZZZX293        	1	19980106	G	2820	1C2710	CARTRIDGE       			BELL  	206   	206B        	1181511	SW  										FUEL PUMP	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K				4AG172	2040				FUEL PUMP DOES NOT PUMP FUEL DUE TO FAILED CARTRIDGE.						1	G	7	1 	3U				H2SW
1998082800042	19980828	00042		1998	8	28	98ZZZX2939       	2	19980421	G	7322	252414512	SERVO SCREEN    	BENDIX      	RSA5AD1     	AMTR  		GLASAIRIIRG 			LYC   		IO320B1A    							FUEL SERVO	CONTAMINATED    	G				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			SO	15	274PS		86   		1853334	274	RL255155A			AIRCRAFT LOST POWER. POWER LOSS WAS DUE TO VERY FINE FIBERGLASS PARTICLES IN THE ENGINE'S FUEL SERVO FUEL SCREEN.  RECOM	MEND REMOVING SAID SCREEN AND CLEANING WITH COMPRESSED AIR AND SOLVENT EVERY 25 HOURS IN SERVICE.  INSPECT FOR ANY REMAI	NING DEBRIS, THEN REPLACE - TEST FOR FULL FUEL FLOW.							0
1998012200384	19980122	00384	SW  	1998	1	22	98ZZZX294        	1	19980106	G	7714	206075682001	INDICATOR       			BELL  	206   	206B        	1181511	SW  										N1 TACHOMETER	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K				S4210	2040				NO INDICATION ON N1 TACHOMETER GAUGE.						1	G	7	1 	3U				H2SW
1998082800043	19980828	00043	NE  	1998	8	28	98ZZZX2940       	2	19980713	G	7322	552721	BEARING         	HAMSTD      	78550034    	SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					FCU	FAILED          	H				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			CR	CRUISE         	1			WP	05					UDAJ7280					REFERENCE:  FR37729.  ENGINE SHUT DOWN IN-FLIGHT.  SUSPECT TBD - BEARING IN FLYWEIGHT ASSEMBLY OF FUEL CONTROL SEPARATED	, LOOSE BALL BEARINGS DISPERSED THROUGHOUT FUEL CONTROL.  SUBMITTER SUSPECTS FUEL CONTROL TO BE OVERHAULED.  CUSTOMER: E	XPRESS AIRLINES.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998082800044	19980828	00044	CE  	1998	8	28	98ZZZX2941       	1	19980701	G	5260		CLEVIS PIN      			BEECH 	300   	300BEECH    	1152930	CE  										AIRSTAIR DOOR	WORN            	H				K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			CE	03	300TJ	4500 				FA13				CABIN DOOR ANNUNCIATOR LIGHT ILLUMINATED ON GROUND.  INVESTIGATION REVEALED BENT AND WORN CLEVIS PIN IN FORWARD, UPPER L	ATCH HOOK MECHANISM.  SUBMITTER SUGGESTED TIME IN SERVICE POSSIBLE REASON FOR FAILURE.					2	L	7	2 	4T				A24CE
1998082800045	19980828	00045	NE  	1998	8	28	98ZZZX2942       	2	19980731	G	7230	50B050	SEAL SEAT       								PWA   	4460  	PW4460      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C3881					THIS IS ANOTHER BEARING SEAL SEAT IN THE SERIES OF THIS PART NUMBER FOUND WITH WHAT APPEARS TO BE HEAT CRACKS IN THE CHR	OME SEAL FACE WHICH APPEAR TO BE TRANSFERRING INTO THE BASE METAL.  SOME CAN BE GROUND AND REMOVED, OTHERS SUCH AS THIS,	 ARE SCRAP.									4	F			E24NE
1998082800046	19980828	00046	NE  	1998	8	28	98ZZZX2943       	2	19980526	G	7230	430151801	BEARING         								LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		30   					LE45313			ADVANCING THROTTLES FROM 'IDLE' TO 'FLY' POSITION, NR 2 BEARING FAILED.  SUSPECT CAUSE WAS MULTIPLE BLADE SHIFT P.T. ROT	OR CAUSING OUT OF BALANCE CONDITION.										3	U			E5NE
1998082800047	19980828	00047	GL  	1998	8	28	98ZZZX2944       	2	19980803	G	7322	2539641	SPRING          		DPV1        						ALLSN 	250C  	250C30      	03013	GL  					FUEL CONTROL	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23			434  		337032					FUEL CONTROL UNIT RETURNED TO A REPAIR AND OVERHAUL FACILITY FOR A REPORTED ENGINE DECELERATION.  TROUBLESHOOTING FOUND 	THE FUEL CONTROL GOVERNOR SPRING BROKEN WHICH CONFIRMED THE REPORTED ENGINE DECELERATION.										3	U			E1GL
1998082800048	19980828	00048	EA  	1998	8	28	98ZZZX2945       	1	19980702	G	7120	AQ10VSS1	BEARING         			CNDAIR	CL600 	CL6002B19   		EA  										LT/RT ENGINE	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4336 				7008				AT ENGINE REMOVAL, NOTED THE SMALL BEARINGS WERE CORRODED.  INSTALLED NEW BEARINGS.						2	L	7	2 	4F			RT	A21EA
1998082800049	19980828	00049	EA  	1998	8	28	98ZZZX2946       	1	19980702	G	7120	AW205VSS1	BEARING         		601370155   	CNDAIR	CL600 	CL6002B19   		EA  										LT/RT ENGINE	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X					7008				AT ENGINE REMOVAL, NOTED THE LARGE BEARINGS WERE CORRODED.  INSTALLED NEW BEARINGS.						2	L	7	2 	4F			RT	A21EA
1998082800050	19980828	00050	EA  	1998	8	28	98ZZZX2947       	1	19980702	G	7120	6013701413	FITTING         			CNDAIR	CL600 	CL6002B19   		EA  										RT ENGINE	CHAFED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4336 			1074	7008				DURING ENGINE REMOVAL, NOTED A FOULING CONDITION OCCURRING BETWEEN THE FITTING AND SHAFT ASSY. THE SHAFT IS SCORED .0005	 INCH TO .001 INCH IN DEPTH.  THIS IS CAUSE FOR REJECTION PER RJ MM CHAPTER 71-22-01 PAGE 403 PARA 2.A.(5).  INSTALLED A	 NEW FITTINGS.				2	L	7	2 	4F			RT	A21EA
1998082800051	19980828	00051	EA  	1998	8	28	98ZZZX2948       	1	19980702	G	7120	601370205	SHAFT           			CNDAIR	CL600 	CL6002B19   		EA  										RT ENGINE	SCORED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4336 				7008				DURING ENGINE REMOVAL, NOTED A FOULING CONDITION OCCURRING BETWEEN THE FITTING AND SHAFT ASSY.  THE SHAFT IS SCORED .000	5 INCH TO .001 INCH IN DEPTH.  THIS IS CAUSE FOR REJECTION PER RJ MM CHAPTER 71-22-01 PAGE 403 PARA 2.1.(5).  INSTALLED 	A NEW SHAFT.				2	L	7	2 	4F			RT	A21EA
1998082800052	19980828	00052	EA  	1998	8	28	98ZZZX2949       	1	19980702	G	7120	601370205	SHAFT           			CNDAIR	CL600 	CL6002B19   		EA  										LT ENGINE	SCORED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4336 				7008				DURING ENGINE REMOVAL, NOTED A FOULING CONDITION OCCURRING BETWEEN THE FITTING AND SHAFT ASSEMBLY.  THE SHAFT HAS VISIBL	E CONTACT IMPRESSIONS OF NO MEASURABLE DEPTH.  THIS IS CAUSE FOR REJECTION PER RJ MM CHAPTER 71-22-01 PAGE 403 PARA. 2.A	.(5).  INSTALLED A NEW SHAFT.				2	L	7	2 	4F			RT	A21EA
1998012200385	19980122	00385	SW  	1998	1	22	98ZZZX295        	1	19980106	G	6710	20606272111	ACTUATOR        			BELL  	206   	206B        	1181511	SW  										ENG DROOP COMP	INOPERATIVE     	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K					2040				INTERNAL MOTOR SHUT-OFF INOPERABLE.						1	G	7	1 	3U				H2SW
1998082800053	19980828	00053	EA  	1998	8	28	98ZZZX2950       	1	19980701	G	7120	6013701413	FITTING         			CNDAIR	CL600 	CL6002B19   		EA  										LT ENGINE	CHAFED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4336 				7008				DURING ENGINE REMOVAL, NOTED A FOULING (CONTACT) CONDITION OCCURRING BETWEEN THE FITTING AND SHAFT ASSEMBLY.  THE SHAFT 	HAS VISIBLE CONTACT IMPRESSIONS OF NO MEASURABLE DEPTH.  THIS IS CAUSE FOR REJECTION PER RJ MM CHAPTER 71-22-01 PAGE 403	 PARA. 2.A.(5).  INSTALLED A NEW FITTING.				2	L	7	2 	4F			RT	A21EA
1998082800054	19980828	00054	CE  	1998	8	28	98ZZZX2951       	1	19980507	G	2133	34E163	VALVE           	JANITROL    		CESSNA	500   	S550        	2076607	CE  										FLOW CONTROL	FAILED          	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	25	550KM	5603 			11850220	S5500081				AS AIRCRAFT CLIMBED THROUGH 10,000 FEET, CABIN WOULD NOT PRESSURIZE.  INSPECTION FOUND BOTH FLOW CONTROL VALVES HAD FAIL	ED INTERNALLY.  SUBMITTER STATED EXERCISE VALVES MORE FREQUENTLY DURING MAINTENANCE RUNS OR EVALUATION FLIGHTS OR ESTABL	ISH A TBO OR REPLACEMENT LIFE.  (APPEARS NOT TO BE A FLEET PROBLEM).				1	L	7	2 	4F			RT	A22CE
1998082800055	19980828	00055	CE  	1998	8	28	98ZZZX2952       	1	19980507	G	2133	34E163	VALVE           	JANITROL    		CESSNA	500   	S550        	2076607	CE  										FLOW CONTROL	FAILED          	E				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	25	550KM	5603 			11850221	S5500081				AS AIRCRAFT CLIMBED THROUGH 10,000 FEET, CABIN WOULD NOT PRESSURIZE.  INSPECTION FOUND BOTH FLOW CONTROL VALVES HAD FAIL	ED INTERNALLY.  SUBMITTER STATED EXERCISE VALVES MORE FREQUENTLY DURING MAINTENANCE RUNS OR EVALUATION FLIGHTS OR ESTABL	ISH A TBO OR REPLACEMENT LIFE.  (APPEARS NOT TO BE A FLEET PROBLEM).				1	L	7	2 	4F			RT	A22CE
1998082800056	19980828	00056	EU  	1998	8	28	98ZZZX2953       	1	19980722	G	8010	SN229	TERMINAL        			AMD   	FALC10	FALCON10    	2730101	EU  										RT ENG PYLON	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	211EC	6600 				166				RIGHT ENGINE WOULD NOT CRANK, INSPECTION FOUND THE THROUGH-HULL TERMINAL AND WIRE LUG BURNED THROUGH.  SUSPECT TERMINAL 	LOOSENED FROM TIME IN SERVICE.  NOTE:  BOLT WAS SECURED BY LOCK TAB AND WAS TIGHT.					2	L	7	2 	4F				A33EU
1998082800057	19980828	00057	CE  	1998	8	28	98ZZZX2954       	1	19980724	G	3222	AN2430	BOLT            		2342100     	LEAR  	35    	35A         	5170602	CE  										NLG STRUT	MISINSTALLED    	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	40DK					171				NOSE GEAR DOOR MECHANISM ROD ATTACH POINT BOLT P/N AN24-30 TO NOSE STRUT IS BEING INSTALLED INCORRECTLY ACCORDING TO LEA	RJET IPC CH 32-23-05, FIG 05, ITEM -21, PAGE 0, AND CAUSING GOUGING TO THE SKIN AT FRAME 5, FS 160.77.  IN REFERENCE TO 	THE ILLUSTRATION, THE POSITION OF THE BOLT HEAD SHOULD BE INSTALLED WITH THE BOLT HEAD FACING OUTBOARD TO MAINTAIN CLEAR	ANCE BETWEEN THE BOLT HEAD AND FRAME SKIN.  THE GOUGING OCCURS WHEN THE BOLT HEAD IS BEING INSTALLED IN THE INBOARD POSI	TION AND THE THREADED PORTION OF THE BOLT IS GOUGING THE FRAME SKIN.  THERE IS NO NOTE OR CAUTION IN THE LEARJET MM.		2	L	7	2 	4F			 	A10CE
1998082800058	19980828	00058	GL  	1998	8	28	98ZZZX2955       	2	19980727	G	7200		ENGINE          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					POWER SECTION	MAKING METAL    	B		A	LS1R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	13	90322	11045				1736	CAE830571			ENGINE CHIP LIGHT CAUTION LIGHT ILLUMINATED.  PILOT MADE PRECAUTIONARY LANDING AT A FIELD SITE 3 MILES SOUTH OF AIRPORT.	  CHIP DETECTORS REMOVED AND INSPECTED IAW ALLISON OPERATION AND OVERHAUL MANUAL 10WZ PAG G-1.  SMALL CHIPS AND FLAKES W	ERE NOTED (3), PLUGS, CLEANED AND REINSTALLED.  AIRCRAFT WAS RUN 30 MINUTES ON GROUND.  PLUGS RE-INSPECTED AND NO ACCUMU	LATION NOTED.  PLUGS RE-INSTALLED AND ENGINE RETURNED TO SERVICE IAW PAR G-3 (A) OF ALLISON 10WZ.  AIRCRAFT RETURNED.  E	NGINE MODULES TO BE REMOVED FOR INSPECTION.		1	G	7	1 	3U	3	U		H2SW    	E4CE
1998082800059	19980828	00059	WP  	1998	8	28	98ZZZX2956       	1	19980709	G	5400	57530112	PLANK           			DOUG  	DC8   	DC863F      	302198F	WP  										NR 4 PYLON	CRACKED         	B	S		EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	867BX	79190				46049				PYLON PLANK CRACK LOCATED AT YN226.  SUSPECT CAUSE OF THE CRACK IS VIBRATION.						2	L	7	4 	4F				4A25
1998082800060	19980828	00060	WP  	1998	8	28	98ZZZX2957       	1	19980709	G	5400	57530111	PLANK           			DOUG  	DC8   	DC863F      	302198F	WP  										NR 2 PYLON	CRACKED         	B	S		EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	867BX					46049				PYLON PLANK HAS CRACK LOCATED AT 19.5 INCHES AFT FROM YN190.  SUSPECT CAUSE OF THE CRACK WAS VIBRATION.						2	L	7	4 	4F				4A25
1998082800061	19980828	00061	WP  	1998	8	28	98ZZZX2958       	1	19980709	G	5711	5615058505	SPAR CAP        			DOUG  	DC8   	DC863F      	302198F	WP  										LT WING XRS22	CRACKED         	B	S		EE4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23	867BX	79190				46049				FOUND LT WING INBD LOWER AUXILIARY SPAR CAP CRACKED ON VERTICAL FLANGE AT XRS22.  SUSPECT CAUSE OF THE CRACK WAS VIBRATI	ON.					2	L	7	4 	4F				4A25
1998082800063	19980828	00063	NE  	1998	8	28	98ZZZX2959       	3	19980720	G	6111	6607132886	BLADE           			SAAB  	SF340 	SF340A      	7850100	EU  						ROTOL	R389	R3894123F25 	NE  	NR 4	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		22606	3539 		132938			DRG59087		CUSTOMER REPORTED REMOVING PROPELLER FROM AIRCRAFT DUE TO EXCESSIVE BLADE TIP MOVEMENT TO NR 4 BLADE.  BLADE WAS FOUND W	ITH A CRACKED OUTER SLEEVE WHEN PROPELLER WAS DISASSEMBLED.  CRACK RUNS COMPLETELY AROUND OUTSIDE DIAMETER OF OUTER SLEE	VE.  BLADE REJECTED FORM FURTHER SERIVCE AT THIS STATION.				2	L	7	2 	4T			RT	A52EU   		6	C	P30NE
1998082800065	19980828	00065	CE  	1998	8	28	98ZZZX2961       	1	19980709	G	2435	23080023	GENERATOR       	LUCAS       		LEAR  	35    	31A         	5170531	CE  										LT ENG START/GEN	FAILED          	B			FJKR	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SO	17	444HC	1429 	465  		92013	064				LEFT ENGINE STARTER/GENERATOR DRIVE END BEARING FAILED CAUSING CATASTROPHIC FAILURE OF STARTER/GENERATOR.  (IN-FLIGHT). 	 STARTER/GENERATOR DRIVE SHAFT FAILED TO SHEAR AS DESIGNED RESULTING IN SEVERE VIBRATION, ENGINE IN-FLIGHT SHUT DOWN, EN	GINE DAMAGE.  SHAFT TESTING BY LUCAS ASEROSPACE SHOWED NORMAL AS DESIGNED.				2	L	7	2 	4F			RT	A10CE
1998082800068	19980828	00068	CE  	1998	8	28	98ZZZX2964       	1	19980520	G	3234	48C48603	VALVE           			LEAR  	35    	35LEAR      	5170600	CE  										MLG SELECTOR	CRACKED         	D	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	02	89TC	7577 			0069	026				AIRCRAFT HAD HYDRAULIC LEAK THAT WAS VERY MINOR.  NUMEROUS ATTEMPTS MADE TO LOCATE THE SOURCE OF THE LEAK.  THE LEAK WAS	 TRACED TO THE LANDING GEAR SELECTOR VALVE.  UPON REMOVAL OF THE VALVE, A .75 INCH LONG CRACK WAS FOUND ON THE UPPER AFT	 SECTION OF THE VALVE ON THE RETURN SIDE.  VALVE IS LOCATED ON THE WING STRUCTURE JUST AFT OF THE MAIN GEAR WHEEL WELLS.				2	L	7	2 	4F				A10CE
1998082800069	19980828	00069	SO  	1998	8	28	98ZZZX2965       	1	19980713	G	3213	1159LM4014711	PIN             			GULSTM	G1159 	G1159A      	3970109	SO  										LT MLG	BROKEN          	B	P	A	RO3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	7096E					498				WHILE DISASSEMBLING LT MLG ASSY FOR SHOCK STRUT SERVICING,  P/N 1159LM40147-11 PIN WAS FOUND CRACKED IN TWO HALVES.  THI	S PIN IS WHAT HOLDS MLG TRAILING ARM TO THE SHOCK STRUT.  THE TRAILING ARM ASSY IS THE MAJOR COMPONENT THAT THE BRAKES, 	WHEEL, AND TIRE ASSY CONNECT TO.  FAILURE OF THIS PIN COULD HAVE A CATASTROPHIC EFFECT ON THE ACFT STRUCTURE DURING FLIG	HT AND LEAD TO AN UNCONTROLLABLE LANDING.  IT COULD NOT BE VERIFIED THE PIN WAS A P/N 1159LM40147-11, IT IS POSSIBLE IT 	COULD BE LOWER GROSS WEIGHT LANDING PIN.  MLG ASSYS ON THE ACFT ARE G-IV LANDING GEAR INSTALLED ON A G-III ACFT.  CAUSE 	OF THE FAILURE HAS NOT BEEN DETERMINED.  TT OF PART 917.7 HRS AND 555 LANDINGS SINCE NEW.	2	L	7	2 	4F				A12EA
1998082800070	19980828	00070	NE  	1998	8	28	98ZZZX2966       	3	19980717	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8721 	4135 		2393			HJ335		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBORD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  ONE CRACK.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998082800071	19980828	00071	SO  	1998	8	28	98ZZZX2967       	1	19980708	G	5410	120039858001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT/RT ENG NAC	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	273AS					120222				DURING PERFORMANCE OF C-CHECK INSPECTION TASKS ON THE NR 1 FRAME OF THE ENGINE NACELLE, CRACKS WERE VISUALLY DETECTED ON	 THE LT ENGINE'S FRAME IN THE WEB OTBD OF THE MOUNT HOLES FOR THE INBD SIDE FORWARD TORQUE MOUNT AND ON THE RT ENGINE'S 	FRAME ON THE OTBD SIDE OF THE OTBD MOUNT HOLES.  BOTH CRACKS WERE APPROX 0.5 INCH IN LENGTH AND CONFIRMED BY FLUORESCENT	 PENETRANT INSPECTION.  CAUSE IS STILL UNKNOWN.  CLOSE ATTENTION SHOULD BE PAID DURING INSPECTION OF THIS AREA.			2	L	7	2 	4T			RT	A31SO
1998082800072	19980828	00072	SO  	1998	8	28	98ZZZX2968       	1	19980717	G	5410	12003858001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT/RT ENG NAC	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	284AS					120249				DURING PERFORMANCE OF C-CHECK INSPECTION TASK ON NR 1 FRAME OF ENGINE NACELLE, CRACKS VISUALLY DETECTED AROUND THE MOUNT	 HOLES FOR THE TORQUE MOUNT.  THE LT MOUNT'S CRACKS WERE FOUND ON THE INBD AND OTBD SIDES.  THE INBD SIDE WAS CRACKED IN	 ONE LOCATION APPROX .3 INCH IN LENGTH.  THE LTBD SIDE WAS CRACKED IN ONE LOCATION AT APPROX .1 INCH IN LENGTH.  RT MOUN	T'S CRACKS WERE FOUND ON THE INBD AND OTBD SIDES.  INBD SIDE WAS CRACKED IN 1 LOCATION AND BARELY DETECTABLE.  OTBD SIDE	 CRACKED APPROX .35 INCH IN LENGTH.  ALL CRACKS CONFIRMED BY FLUORESCENT PENETRANT INSP.  CAUSE UNKNOWN.  CLOSE ATTENTIO	N MUST BE PAID DURING INSP OF THIS AREA.  THIS IS THE FOURTH FINDING.  ACFT OPERATED BY FAR PART 121 AIR CARRIER (ASOA).	2	L	7	2 	4T			RT	A31SO
1998082800073	19980828	00073	SO  	1998	8	28	98ZZZX2969       	1	19980707	G	5410	12003888001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT/RT ENGINE	CRACKED         	B	S		WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	211AS					120007				DURING PERFORMANCE OF C-CHECK INSP, TASKS ON NR 1 FRAME OF ENG NACELLE, CRACKS VISUALLY DETECTED IN AREA OF MOUNT HOLES 	FOR TORQUE MOUNT.  LT MOUNT'S CRACKS FOUND ON INBD AND OTBD SIDES.  INBD SIDE CRACKED IN 2 LOCATIONS APPROX .5 INCH APAR	T AND .25 INCH AND 5 INCHES IN LENGTH.  OTBD SIDE CRACKED IN 1 LOCATION AT APPROX .25 INCH IN LENGTH.  RT MOUNT'S CRACKS	 FOUND ON INBD AND OTBD SIDES.  INBD SIDE CRACKED IN 1 LOCATION AT APPROX .2 INCH IN LENGTH.  OTBD SIDE CRACKED IN 2 LOC	ATIONS APPROX .5 INCH APART AND APPROX .2 INCH AND .25 INCH IN LENGTH.  ALL CRACKS CONFIRMED BY FLUORESCENT PENETRANT IN	SP.  CAUSE IS UNKNOWN.  CLOSE ATTENTION MUST BE PAID DURING INSP.  ACFT OPERATED BY A FAR PART 121 AIR CARRIER (ASOA).	2	L	7	2 	4T			RT	A31SO
1998082800075	19980828	00075	NE  	1998	8	28	98ZZZX2971       	2	19980721	G	7250	840001	BLADE           								PWA   	JT8   	JT8D9A      	52048	NE  					ENGINE T1	FAILED          	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05			16170				P687794			TURBINE SUFFERED COMPLETE FAILURE OF BOTH N1 AND N2 TURBINES.  PART IS IN THE GE ENGINE SERVICES - DALLAS LAB FOR INVEST	IGATION.										4	F			E2EA
1998082800076	19980828	00076	CE  	1998	8	28	98ZZZX2972       	1	19980721	G	3246	101800145	WHEEL           			BEECH 	B300  	B300        	1159232	CE  										MLG	CRACKED         	B			ML2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	5626Y	3200 			555	FL43				WHEEL HALF FOUND CRACKED IN WEB DURING VISUAL INSPECTION CONFIRMED BY ZYGLOW INSPECTION.  WHEEL HALF THAT HAS VALVE STEM	 IN IT.					2	L	7	2 	4T			RT	A24CE
1998082800078	19980828	00078	NM  	1998	8	28	98ZZZX2973       	1	19980715	G	3310	2631	DIMMER          			DOUG  	MD11  	MD11F       	3023600	NM  										COCKPIT LIGHT	BURNED          	H				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			WP	03	105EV	17046			2200	48544				MALFUNCTION OF THIS DIMMER ASSY OF COCKPIT OVERHEAD BACKGROUND LIGHT CAUSED SMOKE IN THE COCKPIT AND AIR TURN BACK DURIN	G FLIGHT ROUTE OF TPE TO ANC ON 7-13-98.  EVA REPAIR STATION (FAA CIRS NR QOCY349J) INSPECTED AND FOUND NO HIDDEN DAMAGE	, EXCEPT THE OVERHEAD LIGHT DIMMER ASSY INOPERATIVE.  REPLACED A NEW DIMMER ASSY IAW MM 33-11-03.  AIRCRAFT RETURNED TO 	SERVICE. (X)			2	L	7	3 	4F			RT	A22WE
1998082800079	19980828	00079	CE  	1998	8	28	98ZZZX2974       	1	19980701	G	3040	66002031	VALVE           			LEAR  	35    	35A         	5170602	CE  										WINDSHIELD HEAT	STUCK           	H				H				DEACTIVATE SYST/CIRCUITS				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			EA	03	196SD	4380 				414				AT FL 430,THE WINDSHIELD OVERHEAT LIGHT CAME ON.  THE PILOT IMMEDIATELY SHUT OFF THE WINDSHIELD HEAT.  THE COPILOT THEN 	NOTICED THE RIGHT WINDSHIELD HAD MELTED.  SYSTEM WAS TROUBLESHOT AND RAM AIR VALVE FOR W/S HEAT SYSTEM WAS FOUND STICKIN	G.  OVERHEAD SHUT-OFF VALVE WAS FUNCTIONAL, BUT DID NOT REACT IN TIME TO PREVENT MELTING.				2	L	7	2 	4F				A10CE
1998082800080	19980828	00080	EU  	1998	8	28	98ZZZX2975       	2	19980722	G	7230	JR28788	RETAIN RING     		MO2300AA    						RROYCE	TAY   	TAYMK65015  		EU  					02 MOD STATOR	CRACKED         	B			AALR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07		12424			TM4431		17431			DURING ENGINE REPAIR 02 MODULE WAS REMOVED.  FOUND CRCK APPROXIMATELY 20 INCHES LONG ON OUTSIDE OF RING.  CONDITION CAUS	ED BY CORROSION IN VANE RAIL.  REF:  OPER CONTROL NR:  RC002T.										4	F
1998082800082	19980828	00082	WP  	1998	8	28	98ZZZX2977       	1	19980701	G	3213	369H6001	STRUT           			HUGHES	369   	369H        	4470718	WP  										RT FWD MLG	CRACKED         	B	S		GK4Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03		2439 								A CRACK WAS DISCOVERED ON THE RIGHT FORWARD LANDING GEAR STRUT.  THE CRACK WAS LOCATED AT THE LOWER AREA NEAR HOLES OF T	HE STRUT WHERE THE SKID ATTACHES.  THESE CRACKS WERE DISCOVERED DURING A 300-HOUR INSPECTION.					1	G	7	1 	3U				H3WE
1998082800083	19980828	00083	CE  	1998	8	28	98ZZZX2978       	1	19980709	G	2820	11200406131	LINE            			CESSNA	210   	210L        	2073448	CE  										LT WING FWD LE	LEAKING         	D	L	A		K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		IN	INSP/MAINT     	1			WP	23	2100D	3665 				21061464				DURING AN ANNUAL INSPECTION, THE LT HAND FORWARD FUEL FEED LINE FROM THE TANK TO THE FITTING AT THE WING ROOT FWD DOOR P	OST WAS FOUND LEAKING.  THE FUEL LINE WAS FOUND CORRODED THROUGH BY GALVONIC CORROSION.  THE GALVANIC ACTION WAS BETWEEN	 THE BLACK SCAT AIR-LINE TUBE STEEL WIRE COMING IN CONTACT WITH THE FUEL LINE.   THE CORROSION MAY HAVE BEEN ENHANCED BY	 MOIST AIR FROM THE LEADING EDGE AIR INLET.  THE PROBLEM COULD BE RESOLVED BY COVERING THE FUEL LINE WITH SPIRAL WRAP OR	 OTHER PROTECTIVE WRAP.  NOTE:  THE LEAK WAS APPROX 4 INCHES OUTBOARD FROM THE WING ROOT AND WAS NOTICED BY THE FUEL DYE	 STAIN.  NO ACTUAL FUEL LEAKAGE WAS NOTICED, BUT A SLIGHT FUEL ODOR WAS NOTICED.	1	H	7	1 	3O				3A21
1998090900001	19980909	00001	GL  	1998	9	9	98ZZZX2979       	3	19980721	G	6110		PROPELLER       			CESSNA	206   	P206A       	2073308	CE  						HARTZL	HCJ3Y	PHCJ3YF1    	GL  	MOUNT STUDS	LOOSE           	D	P	A		O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			SW	99	4614F	55   				P2060214		FP71A		PROPELLER IS NEW AND WAS INSTALLED ON 10-17-97 ON A CONTINENTAL IO-550-F9B ENGINE.  UNDER STC NR SA283050.  AFTER 55.4 H	OURS, PILOT EXPERIENCED A VIBRATION AT 7,000 FEET.  UPON LANDING, THE PROP WAS DISCOVERED TO BE LOOSE ON THE CRANKSHAFT 	FLANGE.  SEVERAL STRUTS ON PROP ARE OUT FURTHER THAN THE OTHERS.  ALSO, TWO STEEL LOCK NUTS ARE DIFFERENT IN COLOR AND A	PPEARANCE AND ALSO HAVE SOME OF THE LOCKING EARS BROKEN OFF.  THERE ARE ALSO TWO OTHER NUTS THAT HAVE LOST THEIR LOCKING	 ABILITY.  THEY WILL SCREW ON BY HAND.		1	H	7	1 	3O				A4CE    		5	C	P36EA
1998082800084	19980828	00084	CE  	1998	8	28	98ZZZX2980       	1	19980625	G	5210	300024	PUMP            			CESSNA	210   	P210N       	2073454	CE  										DOOR SEAL	BURNED          	G	L	A		A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			EA	23	5083W	489  			289079	P21000635				DURING IFR FLIGHT AT 5,000 FEET, PILOT EXPERIENCED SMOKE IN THE CABIN.  PILOT OPENED THE VENT AND EMERG WINDOWS AND LOWE	RED THE LANDING GEAR AND FLAPS FOR A DIVERT.  THE SMOKE BECAME HEAVY AND AN UNEVENTFUL LANDING ACCOMPLISHED ON RUNWAY 14	 AND PILOT SECURED THE ENG AND MASTER SWITCH WHILE ON RUNWAY.  INVEST FND AIR PUMP FOR INFLATABLE DOOR SEAL SOURCE OF TH	E FIRE.  PUMP HAD OVERHEATED AND MELTED, THEN IGNITED THE PLASTIC HOUSING.  FURTHER INVEST FND PUMP MOUNTED ON THE FWD S	IDE OF UPPER LEFT-HAND BULKHEAD P/N 2113041-13 AT FS 18.0.  THIS LOCATION CONTAINED THE PUMP BEWEEN THE OUTER SKIN AND U	PHOLSTERED INTERIOR SIDE PANEL IN APPROX A 4 INCH SPACE.  THE PUMP WAS FUSED FOR 10 AMPS IN A 28-VOLT ELEC  SYS.	1	H	7	1 	3O				3A21
1998082800085	19980828	00085	NM  	1998	8	28	98ZZZX2981       	1	19980618	G	3231	400089001	BELLCRANK       			PIPER 	PA60  	PA60600     	7106001	NM  										RT INBD MLG DOOR	CRACKED         	B		A	BONR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	60DC	1074 				600978061234				DURING 100-HOUR INSPECTION, RT INBOARD MLG DOOR BELLCRANK WAS FOUND CRACKED NEAR PIVOT POINT.  THIS PART HAD BEEN REPLAC	ED BECAUSE OF FAILURE 1,074.3 HOURS (4 YEARS, 4 MONTHS) TIME IN SERVICE.  LEFT BELLCRANK FAILED IN LIKE MANNER 2 MONTHS 	AGO (M OR D REPORT FILED).  SUBMITTER RECOMMENDED SB OR AD REQUIRING REPETITIVE INSPECTION.  REPLACEMENT PART IS MUCH IM	PROVED DESIGN.			1	M	7	2 	3O			RT	A17WE
1998082800087	19980828	00087	CE  	1998	8	28	98ZZZX2983       	1	19980722	G	7810	646795	INLET           			BEECH 	36    	B36TC       	1151609	CE  										TURBO	CRACKED         	B			QC4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	6930C	1390 								AD 89-24-03 CALLED FOR 100-HOUR INPSECTION OF TURBOCHARGER.  THIS AIRCRAFT HAS NEW P/N PART AND WAS CRACKED 2 INCHES AT 	THE Y-TURBO INLET.					1	L	7	1 	3O				3A15
1998082800088	19980828	00088	CE  	1998	8	28	98ZZZX2984       	1	19980714	G	3250	126064411	BUNGEE          			CESSNA	206   	U206G       	2073356	CE  										NLG STEERING	WEAK            	E				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			NM	08	7261N	5354 				U20603591				ON TWO NON-CONSECUTIVE LANDINGS WITH THE SAME PILOT, THE A/C VEERED OFF THE RUNWAY TO THE RIGHT.  PILOT EXPRESSED A LOSS	 OF DIRECTIONAL CONTROL OF THE A/C DUE TO AN UNSTEERABLE NOSE GEAR AND POSSIBLY A NOSE GEAR THAT MAY HAVE NOT BEEN FULLY	 CENTERED ON INITIAL CONTACT WITH RUNWAY.  SUBSEQUENT INSP UNCOVERED NO DEFINITE CAUSE OR PROBLEM, HOWEVER, STEERING BUN	GEE WAS REPLACED ALONG WITH A NOSE GEAR STRUT DISASSY AND INSP.  SUSPECT CAUSE WAS LIKELY A COMBINATION OF A WEAKENED BU	NGEE.  A NOSE STRUT OVERSERVICED WITH AIR, THEREBY, NOT ALLOWING STRUT TO COMPRESS SUFFICIENTLY FOR PROPER STEERING AND 	PILOT'S LOW TIME AND EXPERIENCE.	1	H	7	1 	3O				A4CE
1998082800089	19980828	00089	CE  	1998	8	28	98ZZZX2985       	1	19980710	G	3230	50410011	BELLCRANK       			CESSNA	402   	402A        	207590M	CE  										LT MLG	FAILED          	G	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	17UA					402A0017				BELLCRANK ASSEMBLY BROKE.  REASON UNKNOWN.  NO DOWN AND LOCK INDICATION IN COCKPIT.  AIRCRAFT LANDED WITH LEFT MAIN GEAR	 COLLAPSING UPON TOUCHDOWN.					1	L	7	2 	3O				A7CE
1998082800090	19980828	00090	EA  	1998	8	28	98ZZZX2986       	2	19980717	G	7414	M3333	IMPULSE COUPLING	SLICK       	6051        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					MAGNETO	LOOSE           	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8127K	391  				327940268	L2070048A			REMOVED MAGNETO FOR 400-HOUR IMPULSE INSPECTION.  FOUND BOTH PAWL PINS HAD BECOME LOOSE ON IMPULSE BODY WITH ONE PIN NEA	RLY READY TO COME OUT OF ITS MOUNT HOLE.  THIS WAS A NEW MAGNETO ASSY INSTALLED ON ENGINE AS A UNIT.					1	L	7	1 	3O	3	O		A3SO    	1E4
1998082800091	19980828	00091		1998	8	28	98ZZZX2987       	4	19980723	G	2215	065000300000	SERVO           			CESSNA	172   	172R        	2072401	CE  										AUTOPILOT	MALFUNCTIONED   	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	9710F	246  				17280017				PILOT SQUAWKED GRINDING NOISE WHEN AILERON WAS MOVED UP AND DOWN.  WHEN TROUBLESHOOTING, FOUND NOISE COMING FROM SERVO. 	 WHEN OPERATING ON THE GROUND, LIGHT WOULD COME ON AND HORN WOUULD GO OFF SAYING THAT AUTOPILOT WAS DISENGAGED, EXCEPT S	ERVO OUT AT WING WAS STILL ENGAGED.  SOLENOID FOR AUTOPILOT TO DISENGAGE AND ENGAGE STICKING.				1	H	7	1 	3O			NT	3A12
1998082800092	19980828	00092	SO  	1998	8	28	98ZZZX2988       	1	19980701	G	7120	401403	BOLT            			PIPER 	PA46  	PA46350P    		SO  										ENGINE MOUNT	LOOSE           	B	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	9160X					4622046				FOUND BOLTS WHICH HOLD ENGINE MOUNT FRAME TO FUSELAGE LOOSE.  SUBMITTER STATED TO PREVENT THIS FROM BECOMING A PROBLEM, 	THESE BOLTS AND NUTS SHOULD BE LOOKED AT EVERY INSPECTION.					1	L	7	1 	3O			RT	A25SO
1998082800093	19980828	00093	WP  	1998	8	28	98ZZZX2989       	1	19980721	G	7933	8A583000	THERMAL VALVE   			HUGHES	369   	369D        	4470706	WP  										OIL COOLER	STICKS          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW				D646	470117D				FOUND VALVE STICKING AFTER INSTALLING NEW VALVE DURING TROUBLESHOOTING PROCEDURES.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998082800094	19980828	00094		1998	8	28	98ZZZX2990       	1	19980702	G	3020	2001288003	DUCT            	BOEING      	655812310   															ANTI-ICE	MISREPAIRED     	B		A	L4PR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01										DUCT ASSEMBLY RECEIVED FOR REPAIR WITH UNDOCUMENTED BRAZE REPAIR ON A BELLOWS ASSY.  THIS PART IS INCLUDED IN THE ANTI-I	CING SYSTEM.  SUBMITTER STATED SAFETY OF FLIGHT IS A CONCERN.  REF:  US AIRWAYS, INC.  S/O 2120189-51R.
1998082800504	19980828	00504	WP  	1998	8	28	98ZZZX3004       	1	19980710	G	3234	1118940	SELECTOR        			DOUG  	DC3   	DC3C        	3021457	WP  										GEAR	JAMMED          	H				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			NM	05	115Z		2154 			33567				DURING TAKEOFF CLIMB OF FIRST FLIGHT OF THE DAY, THE LANDING GEAR WOULD NOT RETRACT.  SEVERAL ATTEMPTS WERE MADE TO SELE	CT THE GEAR HANDLE UP, HOWEVER, THE GEAR HANDLE COULD NOT PHYSICALLY BE MOVED TO THE GEAR UP POSITION.  MAINTENANCE FOUN	D THE LANDING GEAR HANDLE STEEL CATCH HAD BECOME LOOSE AND WAS NO LONGER INDEXED CORRECTLY TO MATE WITH THE LANDING GEAR	 HANDLE SELECTOR VALVE QUADRANT.			2	L	7	2 	4R				A669
1998082800505	19980828	00505	NM  	1998	8	28	98ZZZX3005       	1	19980626	G	3246		BOLT            	PARKERHANFIN	40124       	PIPER 	PA60  	PA60601     	7106010	NM  										MLG ASSY	FAILED          	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	07	947TS	3731 				610022				WHEEL ASSEMBLY FOUND WITH INCORRECT BOLTS INSTALLED.  INSTALLED NEW P/N AN5-35A BOLTS.						1	M	7	2 	3O			RT	A17WE
1998082800506	19980828	00506		1998	8	28	98ZZZX3006       	4	19980724	G	2565	150125070	RESTRAINT       	BFGOODRICH  	101660103   															EVAC SLIDE	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19					PAB397					EVACUATION SLIDE RECEIVED PACKED WITH SHEAR PIN RESTRAINTS INSTALLED.  RECEIVING INSPECTION REVEALED THE SHEAR PIN RESTR	AINTS WERE PREVIOUSLY ACTIVATED.  THE TWO HALVES OF THE SHEAR PIN RESTRAINTS WERE RE-ATTACHED WING STEEL SAFETY WIRE.  O	NCE SHEAR PIN RESTRAINTS ARE ACTIVATED AND BROKEN DURING A SLIDE DEPLOYMENT, EACH SHEAR PIN RESTRAINT MUST BE REPLACED W	ITH NEW.  SHEAR PIN RESTRAINTS ARE DESIGNED TO BREAK AT A PRESCRIBED LOAD.  FAILURE TO BREAK AT THE REQUIRED LOAD CAN CA	USE THE EVACUATION SLIDE TO DEPLOY IMPROPERLY AND POSSIBLY CAUSE THE SLIDE TO MALFUNCTION DURING AN ACTUAL EMERGENCY.
1998082800507	19980828	00507		1998	8	28	98ZZZX3007       	4	19980724	G	2565	150125170	RESTRAINT       	BFGOODRICH  	101660103   															EVAC SLIDE	MISINSTALLED    	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19					PAB397					EVACUATION SLIDE RECEIVED PACKED WITH SHEAR PIN RESTRAINTS INSTALLED.  RECEIVING INSPECTION REVEALED THE SHEAR PIN RESTR	AINTS WERE PREVIOUSLY ACTIVATED.  THE TWO HALVES OF THE SHEAR PIN RESTRAINTS WERE RE-ATTACHED WING STEEL SAFETY WIRE.  O	NCE SHEAR PIN RESTRAINTS ARE ACTIVATED AND BROKEN DURING A SLIDE DEPLOYMENT, EACH SHEAR PIN RESTRAINT MUST BE REPLACED W	ITH NEW.  SHEAR PIN RESTRAINTS ARE DESIGNED TO BREAK AT A PRESCRIBED LOAD.  FAILURE TO BREAK AT THE REQUIRED LOAD CAN CA	USE THE EVACUATION SLIDE TO DEPLOY IMPROPERLY AND POSSIBLY CAUSE THE SLIDE TO MALFUNCTION DURING AN ACTUAL EMERGENCY.
1998082800508	19980828	00508	CE  	1998	8	28	98ZZZX3008       	1	19980520	G	3246	4083	WHEEL           	PARKERHANFIN	16103000    	BEECH 	35    	V35B        	1151548	CE  										INNER HALF	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	11JB	1900 				D9234				REMOVED WHEEL FROM AIRCRAFT FOR ROUTINE SERVICE/MAINTENANCE.  WHEEL HAD HEAVY COAT OF PAINT SOME OF WHICH WAS COMING LOO	SE DUE TO AGE.  AFTER REMOVING LOOSE PAINT, WHEEL WAS CLEANED AND INSPECTED.  A 1 INCH LONG CRACK WAS FOUND THAT STARTED	 NEXT TO THE BEARING RACE AND WENT OUTWARD.  CRACK DID NOT PENETRATE THROUGH WHEEL HALF.  WHEEL HALF WAS REPLACED WITH N	EW.  SUBMITTER SUGGESTED ANY LOOSE OR CRACKED PAINT ON WHEEL HALVES BE CAUSE OF FURTHER INSPECTION.			1	L	7	1 	3O				3A15
1998082800509	19980828	00509	CE  	1998	8	28	98ZZZX3009       	1	19980722	G	3710	2H2428	MANIFOLD        			BEECH 	58    	58P         	1152744	CE  										VACUUM SYSTEM	LEAKING         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	2110A	178  				TJ129				DURING ENGINE STARTS, PNEUMATIC GAUGE SHOWED 2 BUTTONS WITH RIGHT ENGINE OFF AND ZERO PRESSURE.  BOTH BUTTONS PULLED WHE	N RIGHT ENGINE STARTED AND GAUGE INDICATED 5.25 INCHES.  TROUBLESHOOTING REVEALED CHECK VALVES IN MANIFOLD LEAKING.  VAL	VE HAD BEEEN INSTALLED NEW 11-21-95.				1	L	7	2 	3O				A23CE
1998082800510	19980828	00510	CE  	1998	8	28	98ZZZX3010       	1	19980722	G	2842	0023810003	TRANSMITTER     			BEECH 	58    	58P         	1152744	CE  										FUEL QUANTITY	LEAKING         	B			MOGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	25	2110A	2287 				TJ129				DURING ANNUAL INSPECTION, FUEL WAS NOTED LEAKING PAST RIGHT WING LEADING EDGE.  FUEL TANK UPPER TRANSMITTER, NEW UNIT IN	STALLED.					1	L	7	2 	3O				A23CE
1998082800511	19980828	00511	SO  	1998	8	28	98ZZZX3011       	1	19980730	G	2720	62867002	PEDAL PAD       		6348500     	PIPER 	PA28  	PA28181     	7102807	SO  										RUDDER	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	3053N					287990288				WHEN PAD IS INSTALLED ON RUDDER PEDAL, THERE IS INSUFFICIENT AMOUNT OF RETAINING LIP.  WHEN GLUED INTO PLACE, THE GLUE D	ETERIORATES FOAM PADDING.  END RESULT IS USING 2 PLASTIC ZIP TIES TO HOLD PAD IN PLACE.					1	L	7	1 	3O				2A13
1998082800512	19980828	00512	SO  	1998	8	28	98ZZZX3012       	2	19980701	G	8530		CYLINDER ASSY   			CESSNA	182   	182J        	2072722	CE  	CONT  	O470  	O470R       	17026	SO  					NR 1 AND 3	MISOVERHAULED   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	3090F				54356	18257190	462023			THIS ENGINE WAS OVERHAULED AND INSTALLED ON 3-25-92, NR 1 AND NR 3 CYLINDERS WERE REMOVED AT 536.7 HOURS DUE TO LOW COMP	RESSION.  CYLINDERS WERE SENT BACK FOR REPAIR BOTH INTAKE AND EXHAUST SEATS AND EXHAUST GUIDES WERE BAD,  CYLINDERS RE-I	NSTALLED AT 621.6 HOURS.  NR 1 CYLINDER WAS AGAIN REMOVED DUE TO ZERO COMPRESSION.  VALVE SEATS WERE CROOKED AND EXTREME	LY WIDE AND EXHAUST GUIDE WAS VERY LOOSE.  SUBMITTER RECOMMENDED CLOSER QUALITY CONTROL.  EXHAUST VALVE COULD HAVE CAUSE	D CATASTROPHIC FAILURE.		1	H	7	1 	3O	3	O	NT	3A13    	E273
1998082800513	19980828	00513	SO  	1998	8	28	98ZZZX3013       	1	19980718	G	2434	411810	ALTERNATOR      	PRESTOLITE  		PIPER 	PA32  	PA32RT300   	7103215	SO  										DC SYSTEM	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	31609				048020C	32R7885111				ALTERNATOR FAILED DUE TO OLD AGE.						1	L	7	1 	3O				A3SO
1998082800514	19980828	00514	SO  	1998	8	28	98ZZZX3014       	1	19980723	G	2434		RING TERMINAL   	PRESTOLITE  	P3CB        	PIPER 	PA31  	PA31350     	7103110	SO  										ALTERNATOR	CRACKED         	E				A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			J			WARNING INDICATION        			CR	CRUISE         	1			NE	03	33MV	4208 				318252035				ON AN EMPTY LEG OF A PART 135 FLIGHT, PILOT NOTICED CHARGING SYSTEM VOLTAGE IN RED WITH FULL LOAD ON CHARGING SYSTEM.  P	ILOT DECREASED LOAD TO GET VOLTAGE BACK IN GREEN, AND RETURNED TO BASE.  SUBSEQUENT INVESTIGATION REVEALED THE RING TERM	INAL ON RIGHT ALTERNATOR AT LEAD WAS CRACKED AND ABOUT TO FALL OFF.  SUSPECT CAUSE WAS REPEATED REMOVAL AND INSTALLATION	 AND VIBRATION.  RECOMMEND THAT RUBBER BOOTS BE PULLED BACK AT EACH INSPECTION TO CHECK TERMINALS.			1	L	7	2 	3O				A20SO
1998082800515	19980828	00515	CE  	1998	8	28	98ZZZX3015       	1	19980722	G	3243	C360746	BRAKE CYLINDER  			CESSNA	172   	172P        	2072436	CE  										CALIPER	CRACKED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	504MA	4868 				17275917				DURING ANNUAL INSPECTION, BOTH BRAKE CYLINDERS WERE FOUND CRACKED AT UPPER CALIPER BOLT HOLE.  BELIEVED CAUSED BY AGE (O	RIGINAL EQUIPMENT) AND POSSIBLY PAST OVERTORQUE OF BOLTS.  REPLACED BOTH ASSEMBLIES.					1	H	7	1 	3O			NT	3A12
1998082800516	19980828	00516	EA  	1998	8	28	98ZZZX3016       	2	19980720	G	8530	SL17235	VALVE           		LW11633     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 2 CYL EXHAUST	FAILED          	H			LJQS	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	69193	172  			B108	15282542	L1474615			NR 2 EXHAUST VALVES SEIZED IN VALVE GUIDE AND VALVE HEAD SEPARATED AFTER CONTACT WITH PISTON.  SEIZURE OF VALVE STEM IN 	GUIDE MOST LIKELY DUE TO CARBON ACCUMULATION.  AIRCRAFT OPERATED UNDER 14CFR PART 141.  SUBMITTER RECOMMENDATION:  C/W S	B 388B AT MORE FREQUENT INTERVALS.				1	H	7	1 	3O	3	O	NT	3A19    	E223
1998082800517	19980828	00517		1998	8	28	98ZZZX3017       	4	19980605	G	2562	006062	BATTERY PACK    	DORNEMARGLN 	DMELT81     	BEECH 	36    	A36         	1151604	CE  										ELT	EXPLODED        	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	72567	1311 			8594	E2280				ELT BATTERY DUE REPLACEMENT.  INSPECTED ELT PER FAR 91.207 (D).  NO DEFECTS NOTED.  REPLACED BATTERY WITH NEW ARTEX P/N 	00-60-62.  ASSEMBLED COVER ON ELT (BATTERY PLUG IS FOOL PROOF, CAN ONLY CONNECT ONE WAY.  COLOR CODED WIRES MATCHED).  B	ATTERY EXPLODED WITHIN 30 MINUTES, BEFORE FUNCTION CHECK WITH NEW BATTERY.  ELT WAS NOT INSTALLED IN AIRCRAFT AT TIME OF	 EXPLOSION.  NO VISIBLE BARE WIRE EXPOSED.  BATTERY MANUFACTURER WAS CONTACTED.  ELT INSTALLED NEW IN 1986.			1	L	7	1 	3O				3A15
1998082800518	19980828	00518	GL  	1998	8	28	98ZZZX3018       	1	19980701	G	3213		STRUT           			BLANCA	17    	1730A       	1220433	GL  										LT MLG	MALFUNCTIONED   	D				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			NM	03	6302X					8430988				LEFT MAIN GEAR WOULD NOT COMPLETELY RETRACT.  FOUND THE STRUT PRESSURE WAS IN EXCESS OF 120 PSI WITH CORrECT PRESSURE. O	PS CHECKED OK.					1	L	7	1 	3O				A18CE
1998082800519	19980828	00519	CE  	1998	8	28	98ZZZX3019       	1	19980723	G	2822	5100001	PUMP            	DUKES       		CESSNA	172   	172R        	2072401	CE  										FUEL BOOST	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	77AF	1142 				17280071				DURING A 100-HOUR INSPECTION, NOTED FUEL WAS LEAKING FROM PUMP DRAIN TUBE.  OPERATION OF THE PUMP RESULTED IN A STEADY F	LOW OF FUEL FROM THE DRAIN.  A CHECK OF SISTER PLAN N93AF, 17280073, PRODUCED SIMILAR DEFECT.  PUMPS ON BOTH PLANES HAVE	 BEEN REPLACED WITH NO FURTHER LEAKS.  A THIRD 172R WAS MENTIONED IN AN FBO AS TO HAVING THE SAME PROBLEM.				1	H	7	1 	3O			NT	3A12
1998082800520	19980828	00520	CE  	1998	8	28	98ZZZX3020       	1	19980723	G	2822	5100001	PUMP            			CESSNA	172   	172R        	2072401	CE  										FUEL BOOST	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	83AF					17280073				FOLLOWING THE FINDING OF A FUEL bOOST PUMP LEAK ON ANOTHER AIRCRAFT (SISTER ACFT), INSPECTION FOUND SIMILAR LEAK.  PUMP 	WAS REPLACED.					1	H	7	1 	3O			NT	3A12
1998082800521	19980828	00521	SO  	1998	8	28	98ZZZX3021       	2	19980727	G	8530	537750	BOLT            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 3 CYL ROCKER	BROKEN          	E				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	13	9RZ		458  			421C0236	L604763			LEFT ENGINE DEVELOPED OIL LEAK IN-FLIGHT.  RETURNED TO BASE WITH NO PROBLEMS.  FOUND HOLE IN NR 3 CYLINDER VALVE COVER. 	 REMOVED VALVE COVER AND FOUND BOTH ROCKER SHAFT RETAINING BOLTS BROKEN. TIME ON PARTS SINCE ASSEMBLY AFTER REPAIR, 96.6	 HOURS.				1	L	7	2 	3O	3	O		A7CE    	E7CE
1998082800522	19980828	00522	CE  	1998	8	28	98ZZZX3022       	1	19980721	G	7820		MUFFLER         			CESSNA	182   	182S        	2072701	CE  										RT FLANGE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	95242	150  				18280146				DURING OIL CHANGE, FOUND RT MUFFLER FLANGE BROKEN OUT AROUND WELDED AREA.   CANNOT DETERMINE IF MANUFACTURER OF MUFFLER 	IS AT FAULT WITH A BAD WELD.					1	H	7	1 	3O			NT	3A13
1998082800523	19980828	00523	CE  	1998	8	28	98ZZZX3023       	1	19980620	G	2730	051010545	CONTROL CABLE   			CESSNA	172   	172L        	2072432	CE  										ELEV TRIM	FRAYED          	B		A	UKJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	9891G					17259791				WHILE PERFORMING AN ANNUAL INSPECTION, FOUND AFT ELEV TRIM CABLE SEVERELY FRAYED DOWN TO THE CENTER STRAND AT THE 90 DEG	REE PULLEY IN THE TAIL SECTION.  FURTHER INSPECTION DISCLOSED THE CABLE WAS TWISTED AROUND THE OTHER CABLE INSIDE THE HO	RIZONTAL STABILIZER.  THE AILERON CONTROL SYSTEM WAS MISSING NUMEROUS SPACERS (ALL) AND MOST BUSHINGS IN THE BELLCRANKS 	IN THE LEFT AND RIGHT WINGS.  SUBMITTER STATED THIS ACFT WENT THROUGH MAJOR STRUCTURAL REPAIRS OVER 5 YRS AGO DUE TO HUR	RICANE DAMAGE.		1	H	7	1 	3O			NT	3A12
1998082800524	19980828	00524	CE  	1998	8	28	98ZZZX3024       	1	19980620	G	2730		BUSHING         			CESSNA	172   	172L        	2072432	CE  										LT/RT WING	MISSING         	B			UKJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	23	9891G					17259791				WHILE PERFORMING AN ANNUAL INSPECTION, FOUND AFT ELEV TRIM CABLE SEVERELY FRAYED DOWN TO THE CENTER STRAND AT THE 90 DEG	REE PULLEY IN THE TAIL SECTION.  FURTHER INSPECTION DISCLOSED THE CABLE WAS TWISTED AROUND THE OTHER CABLE INSIDE THE HO	RIZONTAL STABILIZER.  THE AILERON CONTROL SYSTEM WAS MISSING NUMEROUS SPACERS (ALL) AND MOST BUSHINGS IN THE BELLCRANKS 	IN THE LEFT AND RIGHT WINGS.  SUBMITTER STATED THIS ACFT WENT THROUGH MAJOR STRUCTURAL REPAIRS OVER 5 YRS AGO DUE TO HUR	RICANE DAMAGE.		1	H	7	1 	3O			NT	3A12
1998082800525	19980828	00525		1998	8	28	98ZZZX3025       	1	19980728	G	3246	9544207	WHEEL           	GOODYEARAERO																MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99					815111					INSPECTION FOUND WHEEL HALF CRACKED NEAR A MACHINED HOLE.
1998082800526	19980828	00526	SO  	1998	8	28	98ZZZX3026       	1	19980806	G	8120	LW10119	BRACKET         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					UPPER AFT MOUNT	CRACKED         	B			VY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	65TT	3058 				317612078				FOUND TURBO UPPER AFT MOUNT BRACKET CRACKED AT WELD.  THIS WAS A HARD AREA TO SEE AND SHOULD BE LOOKED AT EVERY INSPECTI	ON.					1	L	7	2 	3O	3	O		A20SO   	E19EA
1998082800527	19980828	00527	SO  	1998	8	28	98ZZZX3027       	2	19980730	G	8530	654966	CYLINDER        								CONT  	O520  	GTSIO520*   	17032	SO  					INTAKE VALVE	DEFECTIVE       	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19										THE INTAKE VALVE SEAT WAS FOUND NOT SEATED INTO THE CYLINDER HEAD PROPERLY.  IF UNDETECTED, THE SEAT AND VALVE WOULD LEA	K AFTER ONE TO TWO HOURS OF OPERATION.										3	O			E7CE
1998082800528	19980828	00528	EA  	1998	8	28	98ZZZX3028       	2	19980803	G	7414	M3635	IMPULSE COUPLING	SLICK       	6355        	PIPER 	PA28  	PA28235     	7102810	SO  	LYC   	O540  	O540B4B5    	41532	EA  					LT MAGNETO	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05		745  			96020024					REMOVED LEFT MAGNETO FOR INSPECTION.  DURING PROCESS OF INSPECTING COUPLING ASSY, NOTICED THE COILED SPRING SHOWING SIGN	S OF ABNORMAL WEAR NEAR THE CONNECTING PORTION OF SPRING TO THE POST OF HOUSING.  SPRING IS WEARING ON CENTER POST OF PA	WL ASSEMBLY.  NO ABNORMAL OILING OR CORROSION OBSERVED ON PAWL PLATE ASSY OTHER THAN JUST AROUND PIN AREA.				1	L	7	1 	3O	3	O		2A13    	E295
1998082800578	19980828	00578	CE  	1998	8	28	98ZZZX3029       	1	19980701	G	2710	365210111	CONTROL CABLE   			BEECH 	35    	K35         	1151524	CE  										AILERON	FRAYED          	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	9540R					D6103				ALL AILERON CABLES (4 EACH) WERE FOUND WORN AND FRAYED AT THE FAIRLEADS AT THE OUTBOARD END OF THE MAIN WHEEL WELLS.  RE	COMMEND AD NOTE REQUIRING CABLE REPLACEMENT AT REGULAR INTERVALS POSSIBLY 4,000 HOURS OR 20 YEARS WHICHEVER COMES FIRST.					1	L	7	1 	3O			 	3A15
1998082800579	19980828	00579	CE  	1998	8	28	98ZZZX3030       	1	19980701	G	2710	365210113	CONTROL CABLE   			BEECH 	35    	K35         	1151524	CE  										AILERON	FRAYED          	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	9540R					D6103				ALL AILERON CABLES (4 EACH) WERE FOUND WORN AND FRAYED AT THE FAIRLEADS AT THE OUTBOARD END OF THE MAIN WHEEL WELLS.  RE	COMMEND AD NOTE REQUIRING CABLE REPLACEMENT AT REGULAR INTERVALS POSSIBLY 4,000 HOURS OR 20 YEARS WHICHEVER COMES FIRST.					1	L	7	1 	3O			 	3A15
1998082800580	19980828	00580	EA  	1998	8	28	98ZZZX3031       	2	19980728	G	7414	M3333	IMPULSE COUPLING			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					LT MAGNETO	WORN            	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	39586	592  				327840168	1732L48A			REMOVED MAGNETO FOR INSPECTION.  IN THE PROCESS OF INSPECTING COUPLING PAWL PINS (WHICH REQUIRES REMOVAL OF COUPLING FRO	M MAGNETO) OBSERVED THAT COUPLING SPRING IS SHOWING ABNORMAL WEAR JUST AFT OF THE CENTER OF SPRING ATTACH POINT.  WEAR I	S A RESULT OF CONTACT BETWEEN SPRING AND COUPLING DRIVE HOUSING POST.  NO ABNORMAL OILING OR CORROSION OBSERVED ON COUPL	ING ASSEMBLY.  PAWL PINS AND PAWLS IN GOOD CONDITION WOULD PASS INSPECTION.			1	L	7	1 	3O	3	O		A3SO    	1E4
1998082800581	19980828	00581	GL  	1998	8	28	98ZZZX3032       	3	19980729	G	6114	6888502	TRANSFER TUBE   			CVAC  	440   	440         	2422902	WP  						ALLSN	A6441	A6441FN606  	GL  	NR 2 PROPELLER	PLUGGED         	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			EA	25	39		60   			480		HC672		AIRCRAFT WAS FLYING LOCAL WHEN THE PILOT NOTICED NR 2 PROP STARTING TO OVERSPEED.  PILOT USED EMERGENCY PROCEDURES TO SH	UT DOWN NR 2 ENGINE AND FEATHER NR 2 PROP.  NR 2 PROP DID NOT FEATHER.  PILOT DECLARED EMERGENCY, ACFT LANDED WITHOUT IN	CIDENT.  UPON INSPECTION OF NR 2 NACELLE, FOUND EVIDENCE OF LEAKING PROP OIL.  WHEN FEATHERING RESERVOIR REMOVED, ONE TR	ANSFER TUBE FELL OUT OF PROP HUB.  UPON CLOSER INSPECTION OF TRANSFER TUBE, FOUND IT CLOGGED WITH PLASTIC.  THIS CLOG MO	VED THE TUBE, THEN DUMPED THE PROP OIL.  REPLACED PROP HUB AND BLADES, FEATHERED RESERVOIR, AND REGULATOR.		2	L	7	2 	4R				6A6     		6	C	P898
1998082800582	19980828	00582	EA  	1998	8	28	98ZZZX3033       	2	19980730	G	7414		IMPULSE SHAFT   	SLICK       	6351        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	40698	195  			95010028	327440056	L2381948A			REMOVED MAGNETO FOR 200 HOUR CHECK.  FOUND IMPULSE ASSY LOOSE ON SHAFT.  NUT HAD WORN THREADS ON SHAFT EVEN THOUGH COTTE	R PIN WAS STILL IN PLACE.  WOODRUFF KEYS HAD BEEN CUT NEARLY IN HALF.  SUBMITTER STATED THIS IS THE SECOND MAGNETO/IMPUL	SE ASSY FOUND TO HAVE THIS CONDITION.  THE OTHER UNIT ALSO HAD LESS THAN 200 HOURS.  SUBMITTER BELIEVES BOTH NUTS HAD BE	EN TORQUED PROPERLY.			1	L	7	1 	3O	3	O		A3SO    	1E4
1998082800583	19980828	00583	CE  	1998	8	28	98ZZZX3034       	1	19980702	G	3230	582212715	ANGLE           			CESSNA	441   	441         	2076020	CE  										RT MLG UPLOCK	CRACKED         	B	S	A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	441JA	5235 				4410137				DURING A PHASE INSPECTION, FOUND A CRACK IN THE OUTBOARD END OF THE RT MAIN GEAR UPLOCK HOOK SUPPORT ANGLE WHICH ATTACHE	S TO THE FORWARD WING SPAR WEB.  CRACK ORIGINATES AT THE OUTBOARD HI-LOCK HOLE AND EXTENDS FOR A TOTAL LENGTH OF APPROXI	MTELY 1.0 INCH.  INSTALLED NEW ANGLE.				1	L	7	2 	3T			RT	A28CE
1998082800584	19980828	00584	EA  	1998	8	28	98ZZZX3035       	2	19980618	G	8550	55000065	HOSE            			GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					ENG CRANKCASE.	COLLAPSED       	G		A		A				UNSCHED LANDING         				E	R	J	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	CR	CRUISE         	1			SW	05	4542L					AA5B1320				IN CRUISE FLIGHT, ENGINE BEGAN TO RUN ROUGH.  THE PILOT NOTED LOST OIL PRESSURE.  HE CONTACTED ATC WHO DIRECTED HIM TO N	EAREST AIRPORT.  THE ENGINE KEPT DETERIORATING AND WHEN PILOT HAD THE FIELD MADE, SHUT ENGINE DOWN TO AVOID A CATASTROPH	IC FAILURE.  ACFT LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED ENGINE HAD NO OIL; IT HAD USED 7 QUARTS IN 3 HRS OF O	PERATION.  DISCOVERED INNER WALL OF BREATHER HOSE HAD COLLAPSED CAUSING CRANKCASE TO PRESSURIZE.  FLETCH AIR INC, SB 187	, ADDRESSES THIS ISSUE.  IT HAD NOT BEEN ACCOMPLISHED ON THIS ACFT.  SUBMITTER RECOMMENDED AN AD BE ISSUED REQUIRING THE	 ACCOMPLISHMENT OF SB.	1	L	7	1 	3O	3	O		A16EA   	E286
1998082800585	19980828	00585	CE  	1998	8	28	98ZZZX3036       	1	19980722	G	5511	053200197	SPAR            			CESSNA	172   	172P        	2072436	CE  										HORIZONTAL STAB	CRACKED         	B		A	MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	504MA	4869 				17275917				DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER MAIN SPAR LEFT DOUBLER WAS FOUND CRACKED ONE-HALF OUTBOARD OF LEFT BUTT 	RIB.  CRACK EXTENDED VERTICALLY INTO DOUBLER BEND RADIUS.  DOUBLER WILL BE REPLACED PER CESSNA SEB94-8 WITH IMPROVED UNI	T.				1	H	7	1 	3O			NT	3A12
1998082800597	19980828	00597	CE  	1998	8	28	98ZZZX3047       	1	19980730	G	3230	24130023	FITTING         			CESSNA	172   	172RG       	2072438	CE  										NLG ACTUATOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	5207U	5481 				122RG0283				INSPECTION FOUND NLG ACTUATOR FITTING CRACKED. THE FITTING IS A MACHINED PIECE OF ALUMINUM THAT THE NOSE GEAR ACTUATOR A	TTACHES TO THE AIRFRAME.  IT IS POSSIBLE THE CENTER PART OF THE CASTING CRACKED ON BOTH SIDES DUE TO HARD LANDING OR IMP	ROPER ACTUATOR RIGGING.				1	H	7	1 	3O				3A17
1998082800598	19980828	00598	CE  	1998	8	28	98ZZZX3048       	1	19980717	G	5210	300024	PUMP            			BEECH 	58    	58          	1152740	CE  										DOOR SEAL	FAILED          	B				H				DEACTIVATE SYST/CIRCUITS				B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			EA	25	53RD				28445	TH483				PILOT NOTICED BURNING SMELL IN COCKPIT.  TURNED OFF AVIONICS AND SMELL CONTINUED.  PILOT NOTICED DOOR SEAL LIGHT WAS ILL	UMINATED.  SHUT OFF DOOR SEAL SYSTEM AND SMELL WENT AWAY.  INSPECTION REVEALED PUMP BADLY DISTORTED AND MELTED.  DROPPIN	G RESISTOR WIRING MELTED NEAR RESISTOR.				1	L	7	2 	3O				3A16
1998082800599	19980828	00599	CE  	1998	8	28	98ZZZX3049       	1	19980804	G	3222	58420005	FORK ASSY       			CESSNA	414   	414A        	2075907	CE  										NLG	FAILED          	B		A	VY2R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	23	555DG	2345 				414A0115				WHILE TAXIING, NOSE WHEEL ASSY BROKE AWAY FROM LOWER FORK ASSY.  ENTIRE LOWER STRUT AND FORK ASSY, WHEEL, BEARINGS, AXLE	 TUBE, AND SPACERS HAD TO BE REPLACED.  AIRCRAFT WAS RE-PAINTED SINCE LAST ANNUAL INSPECTION.  SUSPECT ALL THE GREASE WA	S BLASTED FROM THE BEARINGS IN PREP FOR PAINT.  SUGGEST RE-GREASING ENTIRE GEAR AFTER ANY CLEANING OF GEAR BY PRESSURE.				1	L	7	2 	3O				A7CE
1998082800600	19980828	00600	CE  	1998	8	28	98ZZZX3050       	1	19980731	G	5753	0523537	FLAP            			CESSNA	182   	182Q        	2072732	CE  										RT WING	JAMMED          	D		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	03	735MH					18265528				PILOT REPORTED DURING DAY VFR FLIGHT, FLAPS JAMMED WHILE IN RETRACT MOTION.  INITIAL INSPECTION ON THE GROUND REVEALED T	HE RT FLAP COCKED SIDEWAYS AND CONTACTED THE AILERON.  FLAP TRACKS AND ROLLERS HAD NO LUBRICATION AND LOWER FLAP LIMIT S	WITCH WAS OUT OF ADJUSTMENT.  FLAP SUSTAINED TORSIONAL DAMAGE.  SINGLE CAUSE UNKNOWN.  FLAP, ROLLERS, AND TRACK BRACKETS	 WERE REPLACED.  SWITCH WAS ADJUSTED AND TRACKS LUBRICATED.			1	H	7	1 	3O			NT	3A13
1998082800601	19980828	00601	CE  	1998	8	28	98ZZZX3051       	1	19980727	G	5320	169400117	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	834KS	3677 				M1512				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAIING AIRCRAFT.  SUBMITER SUGGESTED CLOSE INSPECTION OF STR	UCTURE MOUNTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998082800602	19980828	00602	CE  	1998	8	28	98ZZZX3052       	1	19980727	G	5320	169400118	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	834KS	3677 				M1512				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAIING AIRCRAFT.  SUBMITER SUGGESTED CLOSE INSPECTION OF STR	UCTURE MOUNTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998082800603	19980828	00603	CE  	1998	8	28	98ZZZX3053       	1	19980727	G	5320	1694000117	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	842KS	3813 				M2367				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF  LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MO	UNTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998082800604	19980828	00604	CE  	1998	8	28	98ZZZX3054       	1	19980727	G	5320	1694000118	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	842KS	3813 				M2367				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF  LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MO	UNTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998082800605	19980828	00605	SO  	1998	8	28	98ZZZX3055       	1	19980722	G	2913	1213HBG310A	PUMP            			PIPER 	PA31  	PA31325     	7103105	SO  										RT ENG HYDRAULIC	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	4503L	864  			OC10452	318012031				PILOT CHECKED RIGHT HYDRAULIC PUMP BY PLACING LANDING GEAR HANDLE IN DOWN POSITION.  GEAR HANDLE FAILED TO RETURN TO NEU	TRAL IN A REASONABLE TIME INDICATING RT PUMP HAD FAILED.  NO FLUID LOSS WAS DISCOVERED.  CAUSE OF PUMP FAILURE IS UNKNOW	N.				1	L	7	2 	3O				A20SO
1998082800606	19980828	00606	CE  	1998	8	28	98ZZZX3056       	1	19980721	G	2121	EM6039	BLOWER MOTOR    			BEECH 	90    	C90         	1152913	CE  										VENTILATION	FAILED          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CE	07	90WP	1121 			1283	LJ1383				DURING CRUISE FLIGHT, SMOKE FILLED THE COCKPIT AND CABIN.  A SAFE LANDING WAS MADE.  THE PILOT REPORTED THE ORIGIN OF TH	E SMOKE TO BE AT HIS FEET.  THE FLOOR WAS PULLED UP AND IT WAS CLEAR THE BLOWER MOTOR HAD SEVERELY OVERHEATED.  THE BLOW	ER ASSY WAS REMOVED AND MOTOR WAS FOUND SEIZED.  THERE WAS NO EVIDENCE OF DAMAGE TO THE AIRCRAFT WIRING AND NO CIRCUIT B	REAKER TRIPPED.			1	L	7	2 	3T				3A20
1998082800607	19980828	00607	EA  	1998	8	28	98ZZZX3057       	2	19980722	G	7414	ES103825881	COIL            	ELECTROSYS  	D6RN3200    	PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					RT MAGNETO	FAILED          	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			GL	25	62992	98   			I209605GR	317712013				NOTICED A RISE IN EGT ABOUT 15 MINUTES FROM (38D).  RT ENGINE RUNNING SMOOTH.  CHECKED RT MAGNETO AFTER LANDING AND FOUN	D RT SIDE DEAD.  ON INSPECTION OF MAGNETO, FOUND A CRACK AND A BURNED AREA WHERE COIL WAS ARCING TO CASE OF MAG.  SAME P	ROBLEM HAD OCCURRED ONCE BEFORE 98 HRS AGO.  NEW COIL AND CONDENSER INSTALLED AT THAT TIME.  INSTALLED NEW MAG THIS TIME	.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1998082800608	19980828	00608	CE  	1998	8	28	98ZZZX3058       	1	19980721	G	3201		WHEEL PANT      			CESSNA	177   	177B        	2073708	CE  										MLG WHEEL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	28P	2692 				17701783				INSPECTION FOUND LEFT HAND FIBERGLASS WHEEL PANTS ATTACHING BOLT HOLE MOUNT HOLE HAS 2 INCH LONG CRACK.						1	H	7	1 	3O				A13CE
1998082800609	19980828	00609	CE  	1998	8	28	98ZZZX3059       	1	19980727	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	441RK	4882 				4410074				DURING A PHASE INSPECTION, A CRACK WAS FOUND IN THE RIGHT WING CANTED RIB TOP CAP.  CRACK STARTS AT AFT SIDE OF FORWARD 	WING SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS AND IS APPROXIMATELY ONE INCH IN LENGTH.  CRACK WAS STOP DRILLED AT B	OTH ENDS PER CESSNA INSTRUCTIONS.				1	L	7	2 	3T			RT	A28CE
1998082800611	19980828	00611	SW  	1998	8	28	98ZZZX3061       	1	19980629	G	5711	5263L	SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  										WING REAR	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	8352V		70   			494				WHILE INSPECTING THE WINGS FOR THE UPCOMING WOOD SPAR AD, FOUND SWIRL AREA WHERE THE SPAR HAD BEEN CHEWED BY MICE.  THE 	AREA HAD BEEN VARNISHED OVER AT THE LAST RECEIVER AND SIGNED OFF.  SUBMITTER RECOMMENDED THAT ACFT WITH WOOD SPARS BE CH	ECKED CLOSER FOR STORAGE PROBLEM AND BETTER INSPECTION AFTER STORAGE.  THIS DAMAGE NECESSITATED THE REPLACEMENT OF ALL 4	 SPARS.			1	H	7	1 	3O				A759
1998082800612	19980828	00612	SW  	1998	8	28	98ZZZX3062       	1	19980629	G	5711	5262L	SPAR            			BBAVIA	7     	7ECA        	21101NN	SW  										WING FORWARD	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	8352V		70   			494				WHILE INSPECTING THE WINGS FOR THE UPCOMING WOOD SPAR AD, FOUND SWIRL AREA WHERE THE SPAR HAD BEEN CHEWED BY MICE.  THE 	AREA HAD BEEN VARNISHED OVER AT THE LAST RECEIVER AND SIGNED OFF.  SUBMITTER RECOMMENDED THAT ACFT WITH WOOD SPARS BE CH	ECKED CLOSER FOR STORAGE PROBLEM AND BETTER INSPECTION AFTER STORAGE.  THIS DAMAGE NECESSITATED THE REPLACEMENT OF ALL 4	 SPARS.			1	H	7	1 	3O				A759
1998082800613	19980828	00613	SO  	1998	8	28	98ZZZX3063       	1	19980701	G	2150	11M1030	BELT            			PIPER 	PA32  	PA32300     	7103212	SO  										AIR CONDITIONER	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	31569					327840133				THIS IS THE 3RD BROKEN BELT WITHIN THE LAST 8 HRS OF ACFT OPERATION.  THIS PROBLEM DID NOT OCCUR UNTIL THE BELT CHANGED 	FROM RUBBER TO PLASTIC (OR WHATEVER IT IS MADE OF). THIS BELT RAN FOR ALMOST 2 HRS.  SUBMITTER SUGGESTED GOING BACK TO T	HE RUBBER NYLON DESIGN ASAP.				1	L	7	1 	3O				A3SO
1998082800614	19980828	00614	SO  	1998	8	28	98ZZZX3064       	2	19980722	G	8520	628488	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					INTAKE	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	5499J	1384 				310R0297	270997			DURING OIL CHANGE, NOTICED METAL PARTICLES IN FILTER.  SENT TO CONTINENTAL AND WAS FOUND TO BE LIFTER PIECES.  REMOVED E	NGINE FROM SERVICE.  HAVE HAD 7 ENGINES WITH PRE-MATURE LIFTER-CAM FAILURE.  SUBMITTER STATED THERE ARE 29 SDR'S ON THE 	SAME LIFTER PART NUMBER THAT WERE FOUND THROUGH FSDO.  SUBMITTER IS USING 15W-50 WEIGHT OIL AND THEY ARE SWITCHING TO 10	0-50 WEIGHT OIL ASAP.  CALLS TO CONTINENTAL, THEY DO NOT SEE THAT MANY PROBLEMS WITH LIFTERS.			1	L	7	2 	3O	3	O		3A10    	E5CE
1998082800615	19980828	00615	SO  	1998	8	28	98ZZZX3065       	2	19980722	G	8520	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					EXHAUST	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	5499J	1384 				310R0297	270997			DURING OIL CHANGE, NOTICED METAL PARTICLES IN FILTER.  SENT TO CONTINENTAL AND WAS FOUND TO BE LIFTER PIECES.  REMOVED E	NGINE FROM SERVICE.  HAVE HAD 7 ENGINES WITH PRE-MATURE LIFTER-CAM FAILURE.  SUBMITTER STATED THERE ARE 29 SDR'S ON THE 	SAME LIFTER PART NUMBER THAT WERE FOUND THROUGH FSDO.  SUBMITTER IS USING 15W-50 WEIGHT OIL AND THEY ARE SWITCHING TO 10	0-50 WEIGHT OIL ASAP.  CALLS TO CONTINENTAL, THEY DO NOT SEE THAT MANY PROBLEMS WITH LIFTERS.			1	L	7	2 	3O	3	O		3A10    	E5CE
1998082800616	19980828	00616	SO  	1998	8	28	98ZZZX3066       	1	19980715	G	2720	6342005	PEDAL ASSY      			PIPER 	PA28  	PA28140     	7102802	SO  										RUDDER	CRACKED         	B	S		CQVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1823T	5265 				287125206				RUDDER PEDAL ASSY CRACKED.  AIRCRAFT IS A RENTAL/TRAINER.  SUSPECT PILOT/STUDENT ABUSE.						1	L	7	1 	3O				2A13
1998082800617	19980828	00617	SO  	1998	8	28	98ZZZX3067       	1	19980713	G	7160	7814500	BOX ASSY        			PIPER 	PA34  	PA34200     	7103405	SO  										INDUCT AIR	FAILED          	D		A		O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	23	49SA					347350057				THIS BOX ASSY IS A NEW STYLE USING RUBBER GROMMETS INSTEAD OF BUSHINGS ON THE FLAPPER VALVE AND HAS A SPLIT SHAFT THAT H	OLDS THE FLAPPER DOOR.  THIS DOOR IS JUST SANDWICHED IN THE SLOT WITH NO SCREWS TO SECURE IT TO THE SHAFT.  THE VIBRATIO	N WORE THE DOOR INTO 2 SEPARATE PARTS CAUSING THE FLAPPER TO CHOKE OFF THE FORWARD SERVO AND CAUSED COMPLETE ENGINES FAI	LUE.			1	L	7	2 	3O				A7SO
1998082800618	19980828	00618	CE  	1998	8	28	98ZZZX3068       	1	19980720	G	2434	318	ALTERNATOR      	ELECTROSYS  		CESSNA	210   	T210M       	2073451	CE  										DC SYSTEM	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	7398M				8022653	21062018				ALTERNATOR FAILED OUT OF THE SHIPPING BOX.  (ELECTROSYSTEMS OVH UNIT).						1	H	7	1 	3O				3A21
1998082800619	19980828	00619	CE  	1998	8	28	98ZZZX3069       	1	19980720	G	2434	318	ALTERNATOR      	ELECTROSYS  		CESSNA	210   	210L        	2073448	CE  										DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	732CQ		54   		8012747	21061413				ALTERNATOR FAILED AFTER 30 DAYS AND 54 HOURS TIS.  (ELECTROSYSTEMS OVH UNIT).						1	H	7	1 	3O				3A21
1998082800620	19980828	00620	CE  	1998	8	28	98ZZZX3070       	1	19980720	G	8011	6462751	STARTER         	ELECTROSYS  		BEECH 	58    	58          	1152740	CE  										ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H		29   		7121093	TH219				STARTER FAILED IN 8 DAYS OF SERVICE AND 29 HOURS FLIGHT TIME.  ELECTROSYSTEMS OVH UNIT.  WIRE BROKE INSIDE.						1	L	7	2 	3O				3A16
1998082800621	19980828	00621	CE  	1998	8	28	98ZZZX3071       	1	19980720	G	2434	318	ALTERNATOR      			CESSNA	210   	210L        	2073448	CE  										DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	777BK		94   		7112141	21060560				ALTERNATOR FAILED IN 45 DAYS AND 94 HOURS TIS.  ELECROSYSTEM OVH UIT.						1	H	7	1 	3O				3A21
1998082800622	19980828	00622	CE  	1998	8	28	98ZZZX3072       	1	19980624	G	7160		HEAT VALVE      			CESSNA	172   	172G        	2072420	CE  										CARB AIR BOX	DEFECTIVE       	H		A		K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SO	14	1190F					17254785				WHILE GROUND RUNNING TO CLEAN EGT PROBLEM, A LOW IDLE (400 RPM) WAS FOUND.  ADJUSTED IDLE BY BOTTOMING OUT IDLE SCREW. I	NTAKE PIPES SEEMED UNUSUALLY HOT FOR A SHORT GROUND RUN, SO REMOVED THE LT MUFFLER TO AIRBOX AIR DUCT AND DISCOVERED THE	 AFT AIRBOX HEAT VALVE ABOUT TO FALL OFF.  ONE HINGE LINK COMPLETELY WORN THROUGH AND THE OTHERS NEARLY SO.  THE HINGE W	AS REPLACED AND THE SYSTEM RE-RIGGED.			1	H	7	1 	3O			NT	3A12
1998082800623	19980828	00623	GL  	1998	8	28	98ZZZX3073       	1	19980618	G	3230	194319	EXTENSION ASSY  			BLANCA	17    	1730A       	1220433	GL  										NLG	SEPARATED       	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4038B					7630822				ON LANDING, ROD END SEPARATED FROM NLG EXTENSION ASSEMBLY.						1	L	7	1 	3O				A18CE
1998082800624	19980828	00624	SO  	1998	8	28	98ZZZX3074       	2	19980507	G	7414	ES10357174	BREAKER ASSY    	BENDIX      	S6LN21      	CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					RT MAGNETO	FAILED          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4156F	290  				46056				RIGHT MAGNETO DEVELOPED A LOW EXCESSIVE DROP OF 150 RPM ON GROUND.  CHECKS AT 1600 RPM.  FOUND RT MAG BREAKER ASSY WITH 	BROKEN CAM FOLLOWER SPRINGLEAF NEXT TO FACTORY ASSY SCREW.  SECOND OCCURRENCE SINCE 1995.  SUSPECT ELTROSYSTEMS FAA PMA 	LEAF SPRINGS TOO BRITTLE.				1	H	7	1 	3O	3	O	NT	3A12    	E253
1998082800625	19980828	00625	SO  	1998	8	28	98ZZZX3075       	1	19980709	G	3230	9564307	BRACKET         			PIPER 	PA28  	PA28R201    	7102816	SO  										RT MLG RETRACT	WORN            	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	171M	5163 				28R7837051				ANNUAL INSPECTION FOUND THE RIGHT MAIN LANDING GEAR RETRACT BRACKET WAS VERY LOOSE.  FOUND THE EYE BOLT LOOSE IN THE BUS	HING AND THE BUSHING LOOSE IN THE BRACKET.  THIS BRACKET IS NOT INCLUDED IN THE AD 97-01-01.  REPLACED BRACKET ASSY.					1	L	7	1 	3O				2A13
1998082800626	19980828	00626	CE  	1998	8	28	98ZZZX3076       	1	19980707	G	2436	C6110010201	REGULATOR       			CESSNA	185   	A185F       	2072821	CE  										DC VOLTAGE	FAILED          	B			DYPR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			NM	09	93055	6174 				18503173				OVERVOLTAGE LIGHT CAME ON IN-FLIGHT.  REPLACED VOLTAGE REGULATOR.						1	H	7	1 	3O				3A24
1998082800627	19980828	00627	CE  	1998	8	28	98ZZZX3077       	1	19980714	G	5313	21130391	STRINGER        			CESSNA	210   	P210N       	2073454	CE  										FUSELAGE	CORRODED        	B			DYPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	104WD	1563 				P21000366				DURING ANNUAL INSPECTION, FOUND CORROSION IN THE LEFT LOWER COWL SIDE RAIL FORWARD END.  THE STRINGER HAD EXFOLIATION ON	 THE TOP OF THE STRINGER.  REPLACED WITH NEW PART.					1	H	7	1 	3O				3A21
1998082800628	19980828	00628	EA  	1998	8	28	98ZZZX3078       	2	19980820	G	8530		EXHAUST VALVE   			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	BROKE           	G		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	5248S					3240935	L847348			EXHAUST VALVE, NR 2 CYLINDER FRACTURED.  EXHAUST VALVE COMPLETE BREAK AT BOTTOM OF STEM.  STEM REMAINED IN GUIDE.  VALVE	 FACE IMBEDDED INTO CYLINDER HEAD, NR 2 CYLINDER.  OPERATOR STATED NORMAL FUEL LEANING PROCEDURE AT PEAK EGT.  EST 800 H	OURS TT.				1	L	7	1 	3O	3	O		A3SO    	1E4
1998082800629	19980828	00629	EA  	1998	8	28	98ZZZX3079       	2	19980201	G	8520		CRANKSHAFT      			BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  					ENGINE	SPLIT           	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	21	663VL	5398 	1000 			2110	L1783740C			CRANKSHAFT SPLIT.						1	H	7	2 	3O	3	O	RT	A17EU   	E295
1998082800630	19980828	00630	SW  	1998	8	28	98ZZZX3080       	1	19980604	G	3220	SFSP8A	LOCKNUT         			BBAVIA	7     	7GCB        	2110130	SW  										TAIL WHEEL	FAILED          	G		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	11	912CP					165				THE PILOT REPORTED HE FELT THE AIRCRAFT SHUDDER DURING LANDING.  POST-ACCIDENT INVESTIGATION REVEALED:  THE NUT SECURING	 THE TAIL WHEEL STEERING ASSY TOGETHER LOST ITS TORQUE.  THIS ALLOWED PARTS TO SHIFT AND AN INTERNAL LOCK RING TO BE SHE	ARED OFF.  THE TAIL WHEEL LEFT OSCILLATING TYPE MARKS ON THE RUNWAY.				1	H	7	1 	3O				A759
1998082800631	19980828	00631	SO  	1998	8	28	98ZZZX3081       	1	19980722	G	7820	5327F32	MUFFLER         			MAULE 	MX7   	MX7180      	5460185	SO  										RT EXHAUST	SEPARATED       	B	P	A	FE6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3104M	204  				20023C				THE RIGHT HAND MUFFLER OUTLET AND PERFORATED INTERNAL BAFFLE IS FOUND COMPLETELY SEPARATED FROM THE MUFFLER AFT END PLAT	E.  MUFFLER WAS MOUNTED ON AIRCRAFT WITH VERY LOW TT, 203.9 HRS, AND EVIDENCE INDICATES FAILURE HAD OCCURRED MANY HOURS 	PREVIOUSLY.  INSTALLATION HAS LONG TAILPIPE ASSY THAT MAY CONTRIBUTE TO PREMATURE FAILURE.				1	H	7	1 	3O			NC	3A23
1998082800632	19980828	00632	EA  	1998	8	28	98ZZZX3082       	1	19980628	G	3220	TW49	CLIP            		TW101SFSL12 	TRYTEK	65    	65CA        	0190922	EA  										TAILWHEEL	MISMANUFACTURED 	G		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	34482	162  				C14941				THE CONNECTOR CLIP WAS WORKED FREE TWICE.  THE SECOND TIME RESULTED IN AIRCRAFT DAMAGE.  CLIP NEEDS TO BE RE-DESIGNED TO	 BE LESS LIKELY TO COME OFF.					1	H	7	1 	3O			 	A675
1998090400165	19980904	00165	SW  	1998	9	4	98ZZZX3086       	1	19980530	G	5510	206023119109	SUPPORT         			BELL  	407   	407         		SW  										HORIZ STAB	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	2365 				53107				AFTER BEING NOTIFIED THAT ONE OTHER AIRCRAFT IN FLEET HAD LOST ITS SLAT, SUBMITTER C/W VISUAL INSPECTION AND FOUND THE H	ORIZONTAL STABILIZER SLAT SUPPORT AT THE MID-INBOARD SUPPORT CRACKED ON THE LT SLAT, ONE EACH.  ONE MID-INBOARD SLAT SUP	PORT CRACKED IN RADIUS AREA OF SUPPORT TO HORIZONTAL STABILIZER MOUNTING AREA.				1	G	7	1 	3U			O	H2SW
1998090400166	19980904	00166	SW  	1998	9	4	98ZZZX3087       	1	19980530	G	5510	206023119110	SUPPORT         			BELL  	407   	407         		SW  										HORIZ STAB	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	2365 				53054				AFTER BEING NOTIFIED THAT ONE OTHER AIRCRAFT IN FLEET HAD LOST ITS SLAT, SUBMITTER C/W VISUAL INSPECTION AND FOUND THE H	ORIZONTAL STABILIZER SLAT SUPPORT ON THE RT SIDE CRACKED.  TWO EACH.  TWO OUTBOARD SLAT SUPPORTS CRACKED IN RADIUS AREA 	OF SUPPORT TO HORIZONTAL STABILIZER MOUNTING AREA.				1	G	7	1 	3U			O	H2SW
1998090400167	19980904	00167	SW  	1998	9	4	98ZZZX3088       	1	19980530	G	5510	206023119109	SUPPORT         		407023002117	BELL  	407   	407         		SW  										LT HORIZ STAB	MISSING         	B	S	A	ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2236 				53044				DURING POST-FLIGHT INSPECTION, THE SPOILER TO THE LT SIDE OF THE HORIZONTAL STABILIZER WAS FOUND MISSING AND HAD STRUCK 	ONE TAIL ROTOR BLADE CAUSING MINOR DAMAGE.  THERE WAS NO FEED BACK IN THE CONTROLS DURING FLIGHT THAT WOULD HAVE WARNED 	OF ANY IMPACT TO THE TAIL ROTOR.  REMAINING PORTIONS OF SUPPORTS SHOW EVIDENCE OF FATIGUE CRACKS.  THE REMAINING PORTION	S OF SUPPORTS SHOW EVIDENCE OF FATIGUE CRACKS.  THE REMAINING PIECES ARE BEING SENT TO BELL FOR EVALUATION.  FLEET HAS B	EEN CHECKED, AND TWO MORE SLATS HAVE BEEN FOUND WITH CRACKS.		1	G	7	1 	3U			O	H2SW
1998090400170	19980904	00170	NE  	1998	9	4	98ZZZX3091       	1	19980427	G	6410	7610105101041	PADDLE ASSY     			SKRSKY	S76   	S76A        	8143006	NE  										T/R	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	164AG	11409	457  		A13700553	760290				DURING 500-HOUR INPSECTION, FOUND PIVOT BEARING RETAINERS DEBONDED - PADDLE 'B'.						1	G	7	2 	3U				H1NE
1998090400171	19980904	00171	SW  	1998	9	4	98ZZZX3092       	1	19980721	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL				RNFS7884	53054				25 HOUR AD 97-234-17 PTS A, B, AND E.  BOTH DISC PACKS HAD NR 1 DISC CRACKED.  NR 1 DISC PER DISC PACK CRACKED, NR 4 AND	 N4 7 T/R DRIVE SHAFT.					1	G	7	1 	3U			O	H2SW
1998090400172	19980904	00172	NE  	1998	9	4	98ZZZX3093       	1	19980727	G	6210	7615009100051	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL	7639 	431  		A08601424	760280				DISCOVERED DURING 500-HOUR INSPECTION, TIP RIB STRAP DEBONDED (RECURRING PROBLEM WITH THIS BLADE).  TIP RIB STRAPS REPLA	CED BY C.T.J. 4-4-97 TT 6,245.1 HOURS - 5-19-97 TT 6,340-1 HOURS - 12-23-98 TT 7,207.8 HOURS.					1	G	7	2 	3U				H1NE
1998090400173	19980904	00173	SW  	1998	9	4	98ZZZX3094       	1	19980727	G	5350	MW20257YP2300	HINGE           			BELL  	206   	206L4       	1182110	SW  										FAIRING	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	175AL	5616 				52117				DURING ROUTINE INSPECTION, FOUND T/R GEARBOX FAIRING HINGE WORN, FILLER DOOR MISSING.  THE FILLER DOOR HAD CONTACTED ONE	 TAIL ROTOR BLADE.  THIS BLADE WAS FOUND UNSERVICEABLE.  TAIL ROTOR HUB BLADE ASSY WAS REPLACED.  AIRCRAFT WAS VISUALLY 	INSPECTED AND RETURNED TO SERVICE.				1	G	7	1 	3U			NC	H2SW
1998090400174	19980904	00174	NE  	1998	9	4	98ZZZX3095       	1	19980727	G	5413		PYLON           			SKRSKY	S76   	S76A        	8143006	NE  										T/R	CORROSION       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376AL					760002				DURING MAJOR AIRFRAME INSPECTION, FOUND CORROSION ON PYLON SKIN AND STRAPS P/N 78286-76070-20086-101, -102.  PARTS WERE 	CONSIDERED UNSERVICEABLE AND REPLACED.  EXHAUST GASES COULD HAVE POSSIBLY ACCELERATED THE CORROSION PROCESS.  REGULAR CL	EANING OF TAIL AND APPLICATION OF CPC.				1	G	7	2 	3U				H1NE
1998090400175	19980904	00175	GL  	1998	9	4	98ZZZX3096       	2	19980713	G	7313	6899001E	NOZZLE          		23063354    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					COMBUSTION SECT	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL	511  	224  		ITMO450	53141	CAE847158			TURBINE AND FUEL NOZZLE SENT TO SHOP FOR ENGINE MAKING METAL.  REMOVED FUEL NOZZLE FROM COMBUSTION SECTION AND FOUND HEA	VY CARBON BUILD-UP ON BOTTOM OF SHROUD HOUSING AND ALSO CARBON BUILD-UP INSIDE COMBUSTION LINER.  FUEL NOZZLE WAS SHIMME	D AT .341 INCH.  CARBON BUILD-UP SEEMS TO BE CAUSED BY SMOKELESS LINERS.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998090400176	19980904	00176	GL  	1998	9	4	98ZZZX3097       	2	19980713	G	7210	6895007	BEARING         		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					AFT SIDE OF GRBX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL	1384 			1113694	53141	CAE847158			ENGINE REMOVED FROM AIRCRAFT FOR CHIP LIGHT.  UPON INSPECTION OF PARTS, FOUND EXCESSIVE GALLING ON T/M JOURNAL INNER RAC	E AND ROLLERS. EXCESSIVE GALLING ON T/M JOURNAL BEARIANG INNER RACE AND ROLLERS.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998090400177	19980904	00177	SW  	1998	9	4	98ZZZX3098       	1	19980702	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL	139  				53141				SCHEDULED INSPECTION FOUND DISK PACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998090400178	19980904	00178	SW  	1998	9	4	98ZZZX3099       	1	19980715	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1067D	2100 			A2400	45435				DISCOVERED DURING DAILY INSPECTION, M/R BLADE'S LOWER SURFACE GRIP FINGER DOUBLER DEBONDED.  (THIRD DOUBLER DEBONDED APP	ROXIMATELY 10 INCHES).					1	G	7	1 	3U				H2SW
1998090400179	19980904	00179	SW  	1998	9	4	98ZZZX3100       	1	19980623	G	7160	6038T59P02	BLOWER          			BELL  	214   	214ST       	1182106	SW  										NR 1 ENGINE	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	390AL	3839 			J2257	28198				NR 1 ENGINE PARTICLE SEPARATOR FAILED ON TAKEOFF.  FOUND PARTICLE SEPARATOR BLOWER SHAFT SHEARED.						2	G	7	2 	4U				H10SW
1998012900080	19980129	00080	WP  	1998	1	29	98ZZZX311        	1	19980109	G	2710	5642920504	SUPPORT ASSY    		5715841506  	DOUG  	DC8   	DC8*        		WP  										AILERON CONTROL	CRACKED         	B			DM4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19										INSPECTION FOUND THE AILERON CONTROL REVERSION ASSEMBLY HAS A CRACK ON BOTH SIDES OF THE SUPPORT ASSEMBLY.						2	L	7	4 	4J			F	4A25
1998090400217	19980904	00217	EA  	1998	9	4	98ZZZX3124       	2	19980713	G	7322	25765361	SERVO           			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE FC	MALFUNCTIONED   	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			CE	07	441CA	196  			61J22088	17280441	L2714051A			DURING THE MID-AFTERNOON, AIRCRAFT HAD TO DO AN ABORTED TAKEOFF AFTER AIRCRAFT JUST BROKE GROUND AND ENGINE QUIT.  AIRCR	AFT WAS REFIRED AND TAXIED TO HANGAR.  TEST RAN AIRCRAFT AND FOUND MIXTURE WAS EXCESSIVELY RICH.  SUBMITTER STATED HAVIN	G PROBLEMS WITH THE MIXTURE SETTINGS CHANGING FROM DAY TO DAY.  CESSNA IS AWARE OF THE PROBLEM.  REMOVED FUEL SERVO AND 	SENT OUT TO BE INSPECTED AND REPAIRED.			1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400218	19980904	00218	SO  	1998	9	4	98ZZZX3125       	1	19980817	G	5741	1419200	FITTING         			PIPER 	PA18  	PA18        	7101802	SO  										WING	CORRODED        	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	3977P	9560 				184768				WING FITTING CORRODED.  THERE IS NO ACCESS FOR INSPECTION OF PART.  AFTER ONE AIRCRAFT HAD WING SEPARATION AND DISCOVERE	D PART THAT CORRODED, INSPECTED ENTIRE FLEET OF 10 SUPER CUBS AND FOUND CONDITION ON 2 AIRCRAFT (THIS BEING ONE OF THEM)	.  ALL FOUND TO BE FRONT FITTINGS FORWARD SPAR.				1	H	7	1 	3O				1A2
1998090400220	19980904	00220	GL  	1998	9	4	98ZZZX3127       	3	19980807	G	6114		FERRULE         		LC7C0       	CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2134X				D9650YS			782431		THE FERRULE WAS REJECTED FOR DAMAGE TO THE SNAP RING GROOVE DUE TO A GROUND STRIKE.						1	H	7	2 	3O				A6CE    		5	C	P5EA
1998090400221	19980904	00221	GL  	1998	9	4	98ZZZX3128       	3	19980807	G	6114	D4885C61	HUB             			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2134X					3370034		782431		THE PART WAS REJECTED PER MCCAULEY SB 176C AND THE PRODUCT SUPPORT STAFF AT MCCAULEY PROPELLER SYSTEMS.  THE HUB WAS REJ	ECTED BECAUSE THE BLADES SHOW EVIDENCE OF PRE-STRAIGHTENING.					1	H	7	2 	3O				A6CE    		5	C	P5EA
1998090400222	19980904	00222	GL  	1998	9	4	98ZZZX3129       	3	19980807	G	6111	L7C0	BLADE           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2134X				D9650YS	3370034		782431		THE BLADE WAS REJECTED DUE TO VISIBLE EVIDENCE OF PRE-STRAIGHTENING.						1	H	7	2 	3O				A6CE    		5	C	P5EA
1998090400223	19980904	00223	GL  	1998	9	4	98ZZZX3130       	3	19980807	G	6114		FERRULE         			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2134X				D9636YS	3370034		782431		THE FERRULE WAS REJECTED DUE TO THE SNAP RING GROOVE BEING DAMAGED IN A GROUND STRIKE.						1	H	7	2 	3O				A6CE    		5	C	P5EA
1998090400224	19980904	00224	GL  	1998	9	4	98ZZZX3131       	3	19980807	G	6111	L76C0	BLADE           			CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	PROPELLER	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2134X				D9636YS	3370034		782431		THE BLADE WAS REJECTED DUE TO VISIBLE EVIDENCE OF PRE-STRAIGHTENING.						1	H	7	2 	3O				A6CE    		5	C	P5EA
1998090400225	19980904	00225	SO  	1998	9	4	98ZZZX3132       	1	19980810	G	7602	452606	ROD END         			PIPER 	PA28  	PA28181     	7102807	SO  										MIX CONTROL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	8441C	6000 				288290014				THROTTLE CONTROL ROD END BEARING (HPIM TYPE) CARRIER FAILED LATERALLY.  YOKE SEPARATION FROM  YOKE CARRIER COULD RESULT 	IN LOSS OF THROTTLE CONTROL.					1	L	7	1 	3O				2A13
1998090400226	19980904	00226	CE  	1998	9	4	98ZZZX3133       	1	19980814	G	5730	581000225	SKIN            			BEECH 	58    	58          	1152740	CE  										WS 23	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	9446Q	8077 				TH236				NOTED CRACKS EXTENDING FROM 2 END RIVET ATTACHING HAT CHANNNEL P/N 45-110014-647 TO SKIN, P/N 58-100022-5.  FURTHER INVE	STIGATION FOUND TOP SKIN CRACKED 6 INCHES LONG, APPROXIMATELY 3 INCHES EACH SIDE OF HAT CHANNEL, PARALLEL TO RIVETS ATTA	CHING SKIN TO BUTT RIB.  THIS AREA IS COVERED BY WING ROOT AND FUSELAGE RUBBER SEAL.  IT IS THIS AGENT'S OPINION THIS AR	EA WAS POSSIBLY SAT ON, KNEELED ON, OR STOOD ON BY LINE PERSONNEL TO CLEAN SIDE WINDOWS OR DURING WASHING OF AIRCRAFT.			1	L	7	2 	3O				3A16
1998090400227	19980904	00227	CE  	1998	9	4	98ZZZX3134       	1	19980814	G	5710	95110014647	FRAME           			BEECH 	58    	58          	1152740	CE  										WS 23	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	9446Q	8077 				TH236				NOTED CRACKS EXTENDING FROM 2 END RIVET ATTACHING HAT CHANNNEL P/N 45-110014-647 TO SKIN, P/N 58-100022-5.  FURTHER INVE	STIGATION FOUND TOP SKIN CRACKED 6 INCHES LONG, APPROXIMATELY 3 INCHES EACH SIDE OF HAT CHANNEL, PARALLEL TO RIVETS ATTA	CHING SKIN TO BUTT RIB.  THIS AREA IS COVERED BY WING ROOT AND FUSELAGE RUBBER SEAL.  IT IS THIS AGENT'S OPINION THIS AR	EA WAS POSSIBLY SAT ON, KNEELED ON, OR STOOD ON BY LINE PERSONNEL TO CLEAN SIDE WINDOWS OR DURING WASHING OF AIRCRAFT.			1	L	7	2 	3O				3A16
1998090400228	19980904	00228	CE  	1998	9	4	98ZZZX3135       	1	19980809	G	3230	S116730144	LINE            	AEROQUIP    		CESSNA	210   	210L        	2073448	CE  										NLG	FAILED          	G				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			SO	15	93184	3198 				21060297				LANDING GEAR DOWN WAS SELECTED.  THE NOSE GEAR CAME DOWN AND LOCKED.  THE NOSE GEAR DOWN LINE THEN FAILED ALLOWING THE H	YDRAULIC FLUID IN THE SYSTEM TO BE DEPLETED.  THE HYDRAULIC LINE CAME OUT OF THE FITTING.					1	H	7	1 	3O				3A21
1998090400229	19980904	00229	SO  	1998	9	4	98ZZZX3136       	1	19980728	G	3250	4686700	BRACKET         			PIPER 	PA42  	PA42720     	7104212	SO  										NOSE STEERING	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	9116Q	4347 				425501037				DURING INSPECTION, FOUND BRACKET AND DOUBLER P/N 46867-00 AND P/N 46838-00 CRACKED COMPLETELY THROUGH.  THSE PARTS SUPPO	RT THE LINKAGE THROUGH THE WHEEL WELL TO THE NOSE GEAR STEERING.  THESE PARTS ARE UNDER CONSTANT TWISTING MOTION WHEN TU	RNING THE NOSE WHEEL.  PIPER HAS INSTALLED A DOUBLER TO HELP, BUT THAT PART WAS ALSO FOUND CRACKED.				1	L	7	2 	4T				A23SO
1998090400230	19980904	00230	EA  	1998	9	4	98ZZZX3137       	2	19980519	G	8540	71652	IDLER GEAR      			BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  					NR 2 ENGINE	BROKEN          	C				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		DE	DESCENT        	1			SO	21	907VL	1438 				2192	L2411340A			STX/FDO - FLT 908 - ON DESCENT LEAVING 2,000 FEET, NR 2 ENGINE QUIT.  FOLLOWING ALL PROCEDURES, PILOT FEATHERED ENGINE A	ND LANDING AT FDO AIRPORT WITHOUT FURTHER PROBLEMS.  BROKEN GEAR ASSY FOUND AND ENGINE REMOVED FOR FURTHER INSPECTION. O	VERHAULED ENGINE, INSTALLED ON PROCESS.				1	H	7	2 	3O	3	O	RT	A17EU   	E295
1998090400231	19980904	00231	EA  	1998	9	4	98ZZZX3138       	2	19980609	G	8530		EXHAUST VALVE   			BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  					LT ENGINE	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	901VL					1003	L1874140A			PILOT REPORTED VIBRATION ON LEFT ENGINE.   COMPRESSION PERFORMED AND FOUND CYLINDER NR 4 LOW.  CYLINDER REMOVED AND FOUN	D EXHAUST VALVE SEAT LOSE AND PISTON DAMAGED BY THE VALVE.  CYLINDER REPLACED.  REPAIR STATION NOTIFIED ABOUT THE INCIDE	NT AND THEY ARE GOING TO MAKE AN INVESTIGATION.				1	H	7	3 	3O	3	O		A29EU   	E295
1998090400232	19980904	00232	GL  	1998	9	4	98ZZZX3139       	1	19980802	G	3213		STRUT           			NAMER 	T6    	SNJ6        	6400422	GL  										RT MLG	BROKEN          	G				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	19	7983C					112247				RIGHT MAIN LANDING GEAR STRUT BROKE ON LANDING.  AIRCRAFT VEERED OFF OF RUNWAY INTO GRASS.  RT WING AND PROPELLER SUSTAI	NED MAJOR DAMAGE.  BREAK OCCURRED APPROXIMATELY ONE INCH FROM BOTTOM OF SLIDING MEMBER.					1	L	7	1 	3R				A2575
1998090400233	19980904	00233	GL  	1998	9	4	98ZZZX3140       	3	19980703	G	6114		HUB             			BNORM 	BN2   	BN2B26      	1520350	EU  						HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	DAMAGED         	D				E				ENGINE SHUTDOWN         				K	J	Y	FLUID LOSS                	WARNING INDICATION        	ENGINE STOPPAGE           	CL	CLIMB          	1			WP	27	902VL	4000 	1    		AU677	2128		AU677		DURING CLIMB, ENGINE STARTED TO LEAK OIL.  PROPELLER WAS FEATHERED AND ENGINE SHUT DOWN.  INVESTIGATION REVEALED OIL LEA	K WAS BETWEEN PROPELLER DOME AND HUB.  PROPELLER REPLACED.					1	H	7	2 	3O			RT	A17EU   		5	C	P920
1998090400234	19980904	00234	CE  	1998	9	4	98ZZZX3141       	1	19980714	G	2435	534685	BEARING         			CESSNA	206   	U206G       	2073356	CE  										STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	7433N	520  				U20603660				BEARING SHOULD HAVE 519.9 HOURS IF CHANGED AT OVERHAUL.  ENGINE OVERHAULED BY T.W. SMITH ON 6-25-93.  MAY HAVE ALSO BEEN	 CAUSED BY OVERTIGHTENING OF ALTERNATOR BELT.  BEARING FAILURE RESULTED IN METAL CONTAMINATION OF THE OIL AND OIL FILTER	.				1	H	7	1 	3O				A4CE
1998090400235	19980904	00235	EU  	1998	9	4	98ZZZX3142       	1	19980701	G	2820	12636052	FUEL HOSE       			SLNSBY	T67   	T67M260     	8323006	EU  										FUEL CELL	LOOSE           	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	3045S	731  				2142				THE ENGINE QUIT WHILE PERFORMING AN ENGINE GROUND RUN-UP.  DEFUELED AIRCRAFT AND OPENED FUEL TANK FOR INSPECTION.  THE F	UEL FLAP TUB WAS REMOVED FOR INSPECTION AND AN AIR PRESSURE CHECK WAS PERFORMED.  FOUND AN AIR LEAK AT THE SCREW CLAMP S	ECURING THE FUEL HOSE AT THE NON-RETURN VALVE.  THE HOSE HAD STRETCHED IN TIME AND LOST ITS SEAL.  IT WAS REPLACED AND A	IRCRAFT RETURNED TO SERVICE.  RECOMMEND A BETTER METHOD OF SECURING HOSE TO NON-RETURN VALVE.			1	L	7	1 	3O			NT	A73EU
1998090400236	19980904	00236	SO  	1998	9	4	98ZZZX3143       	1	19980803	G	7160		HOSE            			MAULE 	MX7   	MX7160      	5470203	SO  										COWL	LEAKING         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	54HS					17004C				WHEN REMOVING ENGINE COWLING FOR SCHEDULED MAINTENANCE, THE AIR INTAKE HOSE CONTAINED APPROXIMATELY 24 OUNCES OF WATER. 	 IT HAD ACCUMULATED BETWEEN THE COWLING INTAKE AND AIR FILTER AFTER THE AIRCRAFT HAD BEEN WASHED.  THIS HAS OCCURRED ON 	THREE OTHER AIRCRAFT IN FLEET OF SAME MODEL.				1	H	7	1 	3O			NC	3A23
1998090400237	19980904	00237	CE  	1998	9	4	98ZZZX3144       	1	19980626	G	5552		LOCK NUT        			GLSDKS	DG800 	DG800A      	3805015	CE  										BELLCRANK	FAILED          	G		A		O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			WP	19	98NL					8126B55				GLIDER LANDED SHORT OF RUNWAY DUE TO NO ELEVATOR CONTROL.  INVESTIGATION REVEALED THE BOLT AND LOCKING NUT WERE MISSING 	FROM BELLCRANK FOR ELEVATOR AT AFT FUSELAGE.  ACFT HAD JUST COME OUT OF FACTORY WITH APPROX 4 HRS FLIGHT TIME.  NOTE:  B	OLT WAS FOUND IN FUSELAGE.  LOCK NUT WAS NEVER FOUND.				1	K	7	1 	3I			0	GO1CE
1998090400238	19980904	00238	GL  	1998	9	4	98ZZZX3145       	3	19980715	G	6111	90UMB0	BLADE           			CESSNA	172   	172         	2072402	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	6485B	1740 	140  		K136905	29685		861750		BLADE ACTUATING SCREWS STRIPPED OUT.  POSSIBLY DUE TO OVERTORQUE CAUSING NR 2 BLADE TO NOT FUNCTION.  CAUSED DAMAGE TO L	INK ARM AND MINOR DAMAGE TO HUB.  REPLACED BLADE.  REPAIRED OTHER MINOR DAMAGE AND RETURNED TO SERVICE.  (X)					1	H	7	1 	3O			NT	3A12    		5	C	P45GL
1998090400240	19980904	00240	CE  	1998	9	4	98ZZZX3147       	2	19980716	G	7322	63255531	LEVER           			CESSNA	207   	207A        	2073604	CE  										THROTTLE	SEPARATED       	E		A		B	A			EMER. DESCENT           	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AL	03	9956M		334  			20700763				SERRATED BUSHING IN THROTTLE CONTROL LEVER WORE THROUGH LEVER AND SEPARATED THROTTLE CABLE FROM ENGINE.  THE ENGINE IMME	DIATELY WENT TO IDLE AND PILOT LANDED AIRPLANE IN TUNDRA TOTALING THE AIRCRAFT.  THE BOLT WITH PROPER HARDWARE AND TORQU	E WAS STILL CLAMPING ROD END TO SERRATED BUSHING.  WOULD HELP IF BUSHING THINNER THAN LEVER, BUT MAIN PROBLEM IS ENGINE 	GOES TO IDLE INSTEAD OF FULL THROTTLE WHEN DISCONNECTED FROM AIRFRAME THROTTLE CABLE.  SUGGEST MODIFICATION TO FUEL SYST	EM TO CREATE FAIL SAFE DESIGN.		1	H	7	1 	3O				A16CE
1998090400241	19980904	00241	CE  	1998	9	4	98ZZZX3148       	1	19980727	G	5320	1694000117	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	836KS	2649 				M2047				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MOU	NTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998090400242	19980904	00242	CE  	1998	9	4	98ZZZX3149       	1	19980727	G	5320	1694000118	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	836KS	2649 				M2047				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MOU	NTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998090400243	19980904	00243	CE  	1998	9	4	98ZZZX3150       	1	19980727	G	5320	1694000117	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	832KS	3419 				M2218				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MOU	NTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998090400244	19980904	00244	CE  	1998	9	4	98ZZZX3151       	1	19980727	G	5320	1694000118	FRAME ANGLE     			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	832KS	3419 				M2218				INSPECTION FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FU	SELAGE SKIN.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MOU	NTING INSTRUMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1998090400245	19980904	00245	CE  	1998	9	4	98ZZZX3152       	1	19980721	G	2820	070009915	LINE            			CESSNA	182   	182N        	2072730	CE  										FUEL SYSTEM	LEAKING         	H		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	8970G	3500 				18260510				THIS FUEL LINE, THAT ATTACHES TO THE FUEL SELECTOR VALVE COMING FROM LT TANK, WAS WORN IN TWO BY THE ELEVATOR CABLE.  AC	FT HAD UNDERGONE A REPAIR FOR A BADLY DAMAGED FIREWALL AND FLOORING AFTER A HARD LANDING APPROX 6 MONTHS AND 200 HRS BEF	ORE.  AT THAT TIME, THE FUEL LINE OR CABLE WAS MISROUTED.  THE FUEL LINE WAS OVER THE CABLE INSTEAD OF BENEATH THE CABLE	 AND HAD WORN/SAWED INTO THE ALUMINUM LINE CAUSING A BAD FUEL LEAK THAT COULD NOT BE STOPPED WITHOUT DRAINING THE TANK C	REATING A POTENTIAL FIRE HAZARD.  RECOMMEND ALL FUEL LINES THAT FEED INTO AND OUT OF FUEL SELECTOR VALVE BE INSPECTED FO	R ADEQUATE CLEARANCE BETWEEN CONTROL CABLES AT EACH ANNUAL AND WHEN REPAIR WORK HAS BEEN DONE IN THAT AREA.	1	H	7	1 	3O			NT	3A13
1998090400246	19980904	00246	SW  	1998	9	4	98ZZZX3153       	1	19980712	G	6710	K951019015	PIN             			KAMAN 	K1200 	K1200       	05625F6	SW  										CYCLIC STICK	DETACHED        	H	S	A	OWVL	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	134KA	4863 				A940006				AFTER PERFORMING ENGINE VIBRATION CHECK, PILOT LANDED AND NOTICED PIN ROLLING AROUND ON FLOOR.  SHOWED PIN TO MECHANIC A	ND WAS IMMEDIATELY IDENTIFIED AS THE PIN (OWNER REMOVAL) THAT HOLDS THE CYCLIC STICK INTO THE YOKE ASSY.  FOUND THAT THE	 BALLS IN PIN WERE WORN.  KAMAN REP INFORMED THIS HAPPENED IN ANOTHER ACFT, BUT NO SL, SB, WERE ISSUED. ORDERED NEEDED P	IN, BUT INSTALLED AN4-22A BOLT WITH MS21042-4 NUT UNTIL PART ARRIVES.			1	G	7	1 	4F			NT	TR7BO
1998090400451	19980904	00451	SW  	1998	9	4	98ZZZX3155       	1	19980730	G	5302	20031329103S	FITTING         			BELL  	206   	206L3       	1182108	SW  										TAILBOOM ATTACH	CRACKED         	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09	104LP	4878 				51481				DURING 100-HOUR INSPECTION, FOUND UPPER LEFT TAILBOOM ATTACH FITTING CRACKED.  ALSO, FOUND LEFT FUSELAGE AFT LONGERON CR	ACKED.  LONGERON PIN 206-031-329-037.  ON REMOVAL, REPAIR, FITTING HAD A .020 INCH GAP BETWEEN LONGERON AND FITTING CREA	TING A LOADED CONDITION WHEN RIVETED AT FACTORY.				1	G	7	1 	3U			 	H2SW
1998090400452	19980904	00452	GL  	1998	9	4	98ZZZX3156       	2	19980706	G	7230	23009626	SEAL            		23005250    						ALLSN 	250C  	250C30      	03013	GL  					ENGINE COMP	DAMAGED         	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					CAC90398					SEAL VISUALLY INSPECTED WHEN REMOVING FROM PACKAGE.  INSPECTED AND FOUND EXCESSIVE CHIPPING OF MATING SURFACE.											3	U			E1GL
1998090400453	19980904	00453	GL  	1998	9	4	98ZZZX3157       	2	19980623	G	7230	230052711	SPLINE ADAPTER  		23005250    						ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MISMANUFACTURED 	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					68212					PERFORMED TOLERANCE INSPECTION PER OVERHAUL MANUAL.  FOUND OUTSIDE DIAMETER UNDERSIZED (.9850 INCH).  RECEIVED FROM ALLI	SON NEW.  FOUND OUTSIDE DIAMETER ON SPLINE ADAPTER MANUFACTURED UNDERSIZED.  ACTUAL MEASUREMENT WAS .9850 INCH.										3	U			E1GL
1998090400454	19980904	00454	GL  	1998	9	4	98ZZZX3158       	2	19980623	G	7230	23008014	SEAL KIT        		23001643    						ALLSN 	250C  	250C30      	03013	GL  					ENGINE	LEAKING         	B			ALGR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03					CAC91531					UPON ASSEMBLY, PRESSURED UP NR 1 SEAL AREA WITH ENGINE OIL TO CHECK FOR LEAKAGE AND FOUND SEAL WOULD NOT HOLD (EXCESSIVE	 LEAKAGE PAST SEAL).  SUSPECT HEIGHT OF CARBON SEAL TOO LOW TO SEAL PROPERLY AGAINST MATING RING.										3	U			E1GL
1998090400455	19980904	00455	GL  	1998	9	4	98ZZZX3159       	2	19980623	G	7230	23008014	SEAL KIT        		23001643    						ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	LEAKING         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC90272S					UPON ASSEMBLY, PRESSURED UP NR 1 SEAL AREA WITH ENGINE OIL TO CHECK FOR LEAKAGE AND FOUND SEAL WOULD NOT HOLD (EXCESSIVE	 LEAKAGE PAST SEAL).  SUSPECT HEIGHT OF CARBON SEAL TOO LOW TO SEAL PROPERLY AGAINST MATING RING.										3	U			E1GL
1998090400456	19980904	00456	GL  	1998	9	4	98ZZZX3160       	2	19980723	G	7320	412B0220	CONTROL CABLE   			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COCKPIT	BROKEN          	H		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	25	969W	7553 			1845	2320	CAE831274			ON LAST FLIGHT OF THE DAY, ROLLED THE GAS PRODUCER N1 CONTROL TO FLIGHT IDLE.  UNABLE TO SHUT ENGINE OFF WITH THROTTLE C	ONTROL.  ENGINE HAD TO BE SHUT DOWN MANUALLY.  UPON INVESTIGATION, FOUND CABLE ASSY BROKEN UNDER PILOT'S SEAT DECK.  FAI	LED PART, POSSIBLY BECAUSE OF FATIGUE, FAILED AT BEGINNING OF 180 DEGREE BEND IN CABLE ASSEMBLY.				1	G	7	1 	3U	3	U	 	H2SW    	E4CE
1998090400457	19980904	00457	GL  	1998	9	4	98ZZZX3161       	2	19980728	G	7240	23056130	LINER           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D	CAE833805			LINER HAS SEVERAL CRACKS ON LINER FINS.  REMOVED FROM AIRCRAFT AND SENT FOR REPAIR.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998090400458	19980904	00458	NE  	1998	9	4	98ZZZX3162       	1	19980724	G	3242	50034261	BRAKE           			SKRSKY	S76   	S76A        	8143006	NE  										RT MLG	LEAKING         	B			JZBR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	1875P		24   			760264				BRAKE ASSY LEAKING AROUND PUCKS.  4 OUT OF 9.  PREVIOUSLY, BRAKE ASSY WAS OVERHAULED AND RECEIVED FROM SIKORSKY PRODUCT 	INC.					1	G	7	2 	3U				H1NE
1998090400459	19980904	00459	GL  	1998	9	4	98ZZZX3163       	2	19980706	G	7230	23008014	SEAL            		23005250    						ALLSN 	250C  	250C30      	03013	GL  					ENGINE	DAMAGED         	B			ALGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					CAC90398					VISUALLY INSPECTED SEAL WHEN REMOVING FROM PACKAGE.  INSPECTED AND FOUND EXCESSIVE CHIPPING OF MATING SURFACE.											3	U			E1GL
1998090400460	19980904	00460	GL  	1998	9	4	98ZZZX3164       	2	19980708	G	7230	23056634	SPUR GEAR       		23063379    						ALLSN 	250C  	250C47B     		GL  					ENGINE	WORN            	B			ALGR	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03		1384 			CG120264					ENGINE HAD CHIP LIGHT.  INSPECTED PER CSL-A-6012.  WORN AFT SPLINES.  FAILED GO-NO-GO GAUGE MEASUREMENT .9295 INCH.											3	U			E1GL
1998090400461	19980904	00461	GL  	1998	9	4	98ZZZX3165       	2	19980708	G	7230	23009670	BEARING         		23063379    						ALLSN 	250C  	250C47B     		GL  					ENGINE	GALLED          	B			ALGR	K				NONE                    				J	O		WARNING INDICATION        	OTHER                     		IN	INSP/MAINT     	1			SW	03		1384 			HA2597					ENGINE HAD CHIP LIGHT.  UPON INSPECTION OF BEARINGS, FOUND HEAVY GALLING ON NR 2 BEARING.  HEAVY GALLING ON NR 2 BEARING	 BALL.										3	U			E1GL
1998090400462	19980904	00462	GL  	1998	9	4	98ZZZX3166       	2	19980617	G	7230	23009626	CARBON SEAL     		23005200    						ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC70387					UPON NR 1 CARBON SEAL LEAK CHECK, FOUND CARBON SEAL WOULD NOT OBTAIN PROPER SEAL.											3	U			E1GL
1998090400463	19980904	00463	GL  	1998	9	4	98ZZZX3167       	2	19980615	G	7230	23009626	CARBON SEAL     		23005200    						ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC70387					UPON NR 1 CARBON SEAL LEAK CHECK, FOUND CARBON SEAL WOULD NOT OBTAIN PROPER SEAL.											3	U			E1GL
1998090400464	19980904	00464	EA  	1998	9	4	98ZZZX3168       	2	19980624	G	7414		MAGNETO         	BENDIX      		PIPER 	PA28  	PA28236     	7102815	SO  	LYC   	O540  	O540J3A5    	41532	EA  					ENGINE	FAILED          	D				E				ENGINE SHUTDOWN         				W			INADEQUATE Q C            			CR	CRUISE         	1			EA	25	8106P	1    				288011007				RECEIVD BENDIX MAGNETO AS A FACTORY OVERHAULED UNIT FROM TELEDYNE CONTINENTAL.  INSTALLED MAG, RAMP TEST GROUND RUN OK. 	 AIRCRAFT FLEW FOR 45 MINUTES AND HAD COMPLETE ENGINE FAILURE DUE TO MAG FAILURE.  FOUND BOTH BREAKER POINTS NOT GROUNDI	NG TO MAG CASE.  RECOMMEND TELEDYNE REVIEW OVERHAUL PROCEDURES AND POINTS MOUNTING METHODS.				1	L	7	1 	3O	3	O	 	2A13    	E295
1998090400465	19980904	00465	SO  	1998	9	4	98ZZZX3169       	1	19980702	G	3231	AN83740	FITTING         			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG DOOR	FAILED          	B	S	A	F7ER	O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			SO	17	36BM	3315 				318252008				PILOT REPORTED THE LANDING GEAR DID NOT FULLY RETRACT FOLLOWING TAKEOFF FROM NASSAU.  ATTEMPTS TO CYCLE THE GEAR WERE UN	SUCCESSFUL.  THE GEAR WOULD NEITHER EXTEND OR RETRACT NORMALLY.  THE GEAR WAS EXTENDED BY USING THE EMERGENCY PUMP AND A	 NORMAL LANDING WAS MADE AT FLL.  INSPECTION REVEALED AN AN837-4D FITTING HAD BROKEN ON THE LEFT MLG INBOARD DOOR ACTUAT	ING CYCLINDER CAUSING ALL HYDRAULIC FLUID TO BE LOST.  SUBMITTER SUSPECTED CAUSE OF THE FITTING FAILURE WAS METAL FATIGU	E.  THE ACTUATOR MOVES WITH THE GEAR DOOR CAUSING STRESS TO BE APPLIED TO THE ALUMINUM FITTING BY THE ACTUATOR HOSE.		1	L	7	2 	3O				A20SO
1998012900086	19980129	00086	EA  	1998	1	29	98ZZZX317        	2	19980109	G	7323	25241673	GOVERNOR        	BENDIX      		BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					ENGINE	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	01	566CA		3600 		2097	LJ184	20665			POWER TURBINE GOVERNOR FLYWEIGHTS AND BUSHING FAILED CAUSING GOVERNOR TO DUMP PY AIR TO FUEL CONTROL UNIT ALLOWING POWER	 TO DROP TO 50 PERCENT.  ENGINE WAS FEATHERED AND RETURNED TO HOME BASE WHERE GOVERNOR WAS REPLACED WITH OVERHAULED UNIT	 AND CHECKED OPERATION AND FLIGHT TEST.				1	L	7	2 	3T	3	T		3A20    	E4EA
1998092200008	19980922	00008	CE  	1998	9	22	98ZZZX3170       	1	19980701	G	5551	083200056	MOUNT           			CESSNA	310   	310D        	2074212	CE  										LT HORIZ STAB	FAILED          	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	27JP	6000 				39129				LEFT HORIZONTAL STABILIZER MOUNT BRACKET FOUND LOOSE DURING ANNUAL INSPECTION.  FURTHER INSPECTION REVEALED CRACKS AND L	OOSE RIVETS.  UPON REMOVAL OF THE PART, IT FELL INTO TWO PIECES.  SUBMITTER RECOMMENDED VISUAL CHECK OF HORIZONTAL STABI	LIZER OUTBOARD MOUNTS SHOULD BE PERFORMED AT EACH ANNUAL INSPECTION FOR LOOSENESS AND RIVET FRETTING.				1	L	7	2 	3O				3A10
1998090400466	19980904	00466	EU  	1998	9	4	98ZZZX3171       	1	19980624	G	5540	TB2031010000	BEARING         			SOCATA	TB20  	TB21        	8680697	EU  										RUDDER	FROZEN          	B	P	A	OACR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	3051H	1043 				1552				WHILE REMOVING THE RUDDER FOR PAINT, FOUND UPPER RUDDER BEARING FROZEN/CORRODED.  THE BEARING SUPPORT HAD TO BE REMOVED 	TO REMOVE RUDDER.  CAUSE WAS LACK OF LUBRICATION/POOR INSPECTION.  LUBRICATE PER MM.					1	L	7	1 	3O			RT	A51EU
1998090400467	19980904	00467	SW  	1998	9	4	98ZZZX3172       	1	19980624	G	2701	2705	SOCKET          			BBAVIA	7     	7BCM        	2110106	SW  										CONTROL STICK	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	23948					7AC2631				AFT CONTROL STICK SOCKET ASSY HORIZONTAL CRACK THROUGH CASTING AT BEARING BOSS ON LEFT SIDE OF CASTING.  ITEM FOUND DURI	NG ANNUAL INSPECTION.  CONTROL STICK HAD EXCESSIVE AILERON CONTROL PLAN.  SUSPECT AREA ABOUT THE BEARING BOSS IS CAST TH	IN.  AILERON LOADS CONCENTRATING IN THIS AREA.  AIRCRAFT HAD BEEN USED FOR DUSTER APPLICATIONS 20 YEARS.				1	H	7	1 	3O				A759
1998090400468	19980904	00468	CE  	1998	9	4	98ZZZX3173       	1	19980604	G	3211	12116013	FITTING         		1290606     	CESSNA	206   	U206G       	2073356	CE  										LT MLG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	756HK	4979 				U20604102				DURING A 200-HOUR INSPECTION, BOTH MAIN GEAR OUTBOARD ATTACHMENT FITTINGS WERE FOUND CRACKED.  THIS AIRCRAFT HAD AN INCI	DENT SEVERAL HUNDRED HOURS AGO, BUT NO RECENT REPORT OF A HARD LANDING.  THIS ACFT IS SUBJECTED TO MANY LANDINGS ON GRAV	EL STRIPS WHICH MAY HAVE CONTRIBUTED TO THE CRACKING.  SUBMITTER STATED THESE FITTINGS ARE AND SHOULD BE INSPECTED CLOSE	LY AT 100-HOUR AND ANNUAL INSPECTIONS.			1	H	7	1 	3O				A4CE
1998090400469	19980904	00469	CE  	1998	9	4	98ZZZX3174       	1	19980604	G	3211	12116014	FITTING         		1290606     	CESSNA	206   	U206G       	2073356	CE  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	756HK	4979 				U20604102				DURING A 200-HOUR INPSECTION, BOTH MAIN GEAR OUTBOARD ATTACHMENT FITTINGS WERE FOUND CRACKED.  THIS AIRCRAFT HAD AN INCI	DENT SEVERAL HUNDRED HOURS AGO, BUT NO RECENT REPORT OF A HARD LANDING.  THIS ACFT IS SUBJECTED TO MANY LANDINGS ON GRAV	EL STRIPS WHICH MAY HAVE CONTRIBUTED TO THE CRACKING.  SUBMITTER STATED THESE FITTINGS ARE AND SHOULD BE INSPECTED CLOSE	LY AT 100-HOUR AND ANNUAL INSPECTIONS.			1	H	7	1 	3O				A4CE
1998090400470	19980904	00470	NM  	1998	9	4	98ZZZX3175       	1	19980618	G	2434	36B19484	PULLEY          		ALU8421     	PIPER 	PA60  	PA60601P    	7106012	NM  										ALTERNATOR	FAILED          	B	P		F7ER	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	17	343EA					61P0373120				PILOT REPORTED THE RT ENGINE ALTERNATOR WAS NOT CHARGING.  INSPECTION REVEALED THE ALTERNATOR AND AIR CONDITIONING COMPR	ESSOR BELTS WERE SHREDDED AND BROKEN.  FURTHER INSPECTION REVEALED THE KEYWAY ON THE ALTERNATOR PULLEY HAD STRIPPED ALLO	WING THE PULLEY TO MOVE ON THE ALTERNATOR SHAFT DAMAGING THE ALTERNATOR SHAFT, FAN, AND PROPELLER DE-ICE SLIP RING.  THE	 PULLEY INSTALLED ON THE ALTERNATOR WAS NOT AN AIRCRAFT PART.  IT WAS POSSIBLY AN AUTOMOTIVE OR INDUSTRIAL PULLEY.  THE 	MATERIAL COMPOSITION WAS NOT THE SAME AND THE PULLEY HAD NO IDENTIFYING MARKINGS.  THE NEW PULLEY, A LYC PART, WAS PROPE	RLY IDENTIFIED.	1	M	7	2 	3O			RT	A17WE
1998090400471	19980904	00471	SW  	1998	9	4	98ZZZX3176       	1	19980515	G	2197		WIRE            			GULSTM	114   	114B        	O145001	SW  										AIR COND SYSTEM	LOOSE           	H	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	6042X	74   				14652				THIS ACFT MANUFACTURED 9-97 WITH TT OF 73.6 HRS WAS REPORTED TO HAVE ELECTRICAL PROBLEMS SUCH AS FLUCTUATING OIL TEMP, P	ULSATING INSTRUMENT PANEL LIGHTS, AND A POSITION LIGHT C/B SWITCH THAT WOULD NOT RESET.  ALSO, ALTERNATOR NOISE IN HEADS	ETS.  AFTER INSPECTION, NOTED NUMEROUS HEAVY GAUGE WIRINGS ON AIR CONDITIONING MODULE INSTALLATION WERE FOUND LOOSE, SOM	E OF WHICH THE LOCKWASHERS WERE NOT CRUSHED.  ALSO, NUMEROUS C/B SWITCHES AND PUSH/PULL TYPE C/B'S WERE NOT SECURELY FAS	TENED TO THE BUSS BARS.		1	L	7	1 	3O			RT	A12SO
1998090400472	19980904	00472	GL  	1998	9	4	98ZZZX3177       	1	19980701	G	3246	SCOTT3200	TIRE            			AMTR  	STRDST	STARDUSTER2 		GL  										TAIL WHEEL	DEFECTIVE       	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	23	159MK	440  				MK2				AIRCRAFT BEGAN TO WEAVE ON LANDING.  AIRCRAFT BEGAN TO SKID TO THE RIGHT.  RIGHT LANDING GEAR BENT AND FOLDED UP BENEATH	 AIRCRAFT.  SUSPECT CAUSE WAS UNDER INFLATED TAIL WHEEL TIRE.					1	Q	7	1 	3O				EXPA1Q71
1998090400473	19980904	00473	GL  	1998	9	4	98ZZZX3178       	3	19980803	G	6111	B4459	ACTUATING PIN   													MCAULY	3AF32C	3AF32C93    	GL  	NR 2 BLADE	FAILED          	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23			925  							NR 2 BLADE FOUND ROTATING LOOSE IN HUB.  DISASSEMBLED AND INSPECTED.  FOUND BLADE ACTUATING PIN BROKEN OFF IN FERRULE. S	USPECT DURING O/H SB 99 NOT FULLY C/W.  THREADS NOT CUT IN FERRULE TO BOTOM OF PIN HOLE.															5	C	P22EA
1998090400474	19980904	00474		1998	9	4	98ZZZX3179       	1	19980811	G	2621	WKA842117	FITTING         	KIDDE       	899827      															SAFETY DISC	FAULTY          	B	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	19										THE SAFETY FITTINGS DISC WAS TAMPERED AND REPLACED WITH ALUMINUM MATERIAL CUT-OUT.  MORE THAN LIKELY FROM A 'COKE' CAN. 	 THE MATERIAL SERIOUSLY AFFECTS THE OPERATION OF THE EXTINGUISHER AS IT HAS AN UNKNOWN RATED PRESSURE TO STAND.
1998012900087	19980129	00087	CE  	1998	1	29	98ZZZX318        	1	19980107	G	5512		RIB             		123260029   	CESSNA	210   	T210M       	2073451	CE  										H STAB LT/RT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	732XE	3197 				2061850				DURING ANNUAL INSPECTION, A CLICKING NOISE WAS HEARD WHILE PRESSING THE LEADING EDGE OF THE HORIZONTAL STABILIZER AT THE	 RIBS.  WITH FURTHER INSPECTION, SEVERAL RIBS FOUND CRACKED ON BOTH LT AND RT SIDES OF THE STABILIZER.  ALSO, FOUND ON T	HIS ACFT, RIB PN 1232105-1 HAS BEEN BENT.  THIS IS 3RD T210 THAT HAS BEEN FOUND WITH CRACKED LEADING EDGE RIBS AND ALSO 	FOUND SEVERAL TU206 ACFT WITH THIS SAME CONDITION.  IT APPEARS THAT YEARS OF PUSHING ON STAB DURING GROUND HANDLING HAS 	HELPED TO CREATE THIS CONDITION.  TT ON ALL ACFT IS APPROXIMATELY 3,000 HRS.		1	H	7	1 	3O				3A21
1998090400475	19980904	00475		1998	9	4	98ZZZX3180       	4	19980727	G	6122	6851007	COIL            	WOODWARD    	8210104     															PROPELLER GOV	DETACHED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03					1809551					CUSTOMER SUBMITTED GOVERNOR FOR INSPECTION DUE TO HIGH CARBON CONTENT IN OIL ANALYSIS.  INSPECTION REVEALED THE SYNCHRON	IZING COIL HAD COME LOOSE IN THE COVER.  THE COIL CONTACTED THE FLYWEIGHTS WHICH CAUSED MATERIAL TO BE REMOVED FROM THE 	COIL.
1998090400476	19980904	00476	SO  	1998	9	4	98ZZZX3181       	2	19980708	G	7414	36066	GEAR            	SLICK       	4301        	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					MAGNETO DRIVE	WORN            	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	103FR					15075569	230890R			AT ANNUAL INSPECTION WHILE C/W SAIB NR CE 98-2141, FOUND BOTH MAGNETO DRIVE GEARS WORN.  THE TEETH ARE GALLED IN PLACES.	  THE WORKMANSHIP OF THE GEARS AT MFG DOES NOT LOOK LIKE THAT OF THE TWO NEW TEM GEARS INSTALLED.  IT (THE LEFT GEAR) AL	SO JUST HAS THE P/N INK STAMPED ON IT.  TT ON GEARS IS UNKNOWN.  THE MAGNETOS WERE BOTH REPLACED 525.7 HRS AGO (NEW), BU	T NOTHING IS IN THE LOGS ABOUT THE GEARS.  ENGINE TT:  3,611.7 HRS.  ENGINE TSO:  1,707.7 HRS.			1	H	7	1 	3O	3	O		3A19    	E252
1998090400477	19980904	00477	CE  	1998	9	4	98ZZZX3182       	1	19980807	G	3246	500515	WHEEL HALF      	BFGOODRICH  	31372       	CESSNA	441   	441         	2076020	CE  										RT MLG	FAILED          	B			CBCR	K				NONE                    				O			OTHER                     			LD	LANDING        	1			NM	03	88QT	1489 				4410228				AFTER A NOTICEABLE TREMBLE ON LANDING, THE AIRCRAFT WAS PARKED AND CHOCKED.  AFTER AN HOUR, THE RIGHT MAIN TIRE WAS GOIN	G FLAT; UPON FURTHER INSPECTION, THE RIGHT MAIN TIRE WAS BULGING AROUND THE INNER BEAD AREA.  THE INNER WHEEL (RIM) WAS 	MISSING A PIECE FROM THE BRAKE DISC KEY SLOT.  UPON DISC ASSEMBLY, REMOVED A 4 TO 5 INCH CHUNK OUT OF THE WHEEL RIM THAT	 HAD CRACKED.  SLIGHT DAMAGE HAD OCCURRED TO BRAKE HOUSING.			1	L	7	2 	3T			RT	A28CE
1998090400478	19980904	00478	SO  	1998	9	4	98ZZZX3183       	1	19980720	G	8120	58B19891	TANK            			PIPER 	PA46  	PA46350P    		SO  										TURBO OIL	FRACTURED       	H	S	A		A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			SW	99	321CR	265  				4636124				WITH APPROXIMATELY 265 HOURS SINCE NEW, THE ACFT DEPARTED AIRPORT (SUS) HEADED WEST AND ABOUT 15 MILES OUT EXPERIENCED A	 LOW OIL PRESSURE INDICATION AND RETURNED TO THE AIRPORT AND LANDED WITHOUT INCIDENT.  UPON INSPECTION, FOUND THE RT TUR	BO OIL TANK TUBE WELD WAS FRACTURED AT THE 90 DEGREE AND COMPLETELY SEPARATED, ALL BUT 1.5 QUARTS OF OIL WAS PUMPED OVER	BOARD.  THE PART WAS SENT TO A TESTING LAB FOR WELD INSPECTION AND LYC WAS NOTIFIED.			1	L	7	1 	3O			RT	A25SO
1998090400479	19980904	00479	EU  	1998	9	4	98ZZZX3184       	1	19980729	G	5720	205303418	BRACKET         			MRCHTI	S205  	S20522R     	8120412	EU  	FRNKLN	6AV350	6A350C1     	27043	EA  					RT WING	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	729WA	1701 				388	2611100018			WHILE C/W AD 75-17-32-R2 - LANDING GEAR OPERATING MECHANISM, A CRACK WAS FOUND IN THE RIGHT INTERNAL WING RIB BRACKET. T	HE CRACK WAS LOCATED AT THE UPPER RADIUS AND WAS APPROXIMATELY .75 INCH IN LENGTH.  SUBMITTER STATED THE CRACK WAS MOST 	LIKELY CAUSED BY IMPROPER INSTALLATION. THE BRACKET IS RIVETED TO A WING RIB AND ATTACHED TO THE REAR SPAR WITH BOLTS.  	IT APPEARS WHEN THE BRACKET WAS ATTACHED TO THE RIB, IT DID NOT CONTACT THE REAR SPAR, CONSEQUENTLY, WHEN THE BOLTS WERE	 TORQUED, THEY 'PULLED' THE BRACKET CAUSING IT TO CRACK.  SIAI MARCHETTI MANDATORY SB NR 205B37E ADDRESS THIS PROBLEM.		1	L	7	1 	3O	3	O		A9EU    	E9EA
1998090400480	19980904	00480	NE  	1998	9	4	98ZZZX3185       	1	19980617	G	5510	2220621	FITTING         			CONAER	LA4   	LA4200      	5110310	NE  										HORIZ STABILIZER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	1202L	2667 				707				WHILE C/W AD 98-10-12, THE FITTING REQUIRED REPLACEMENT PER PARA (A)(2).  INSPECTION OF THIS FITTING PER REVO SB B-78 DI	SCLOSED A CRACK IN ADDITION TO CORROSION AND FRETTING.  IT SHOULD BE NOTED EVEN AFTER REPLACEMENT OF AFFECTED FITTINGS, 	THE ACFT IN MOST CASES WILL NOT PASS THE INSPECTION CRITERIA FOR AD 98-10-12 PARA (A)(1).  SUBMITTER STATED THIS MAKES I	T CRITICAL THAT:  THE REWORK OF THE STABILIZER BEAM DOUBLER FLANGE AND BEND RADIUS AREA (REF REVO SB B-78, INSPECTION AN	D REPAIR) BE CARRIED OUT PROPERLY AND THAT AIRCRAFT RECORDS ARE PROPERLY DOCUMENTED TO PRECLUDE UNNECESSARY RE-COMPLIANC	E OF AD 98-10-12.	1	H	7	1 	3O				1A13
1998090400481	19980904	00481	GL  	1998	9	4	98ZZZX3186       	3	19980807	G	6111	C4903	RETAIN NUT      		L76C10      	CESSNA	337   	337         	2075702	CE  						MCAULY	2AF34C	D2AF34C61   	GL  	BLADE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	2134X					3370034		782431		THE RETENTION NUT WAS REJECTED DUE TO DAMAGE IN THE O-RING GROOVE DUE TO A GROUND STRIKE.						1	H	7	2 	3O				A6CE    		5	C	P5EA
1998090400482	19980904	00482	SO  	1998	9	4	98ZZZX3187       	1	19980708	G	3220	A504	ARM             		D501A       	GULSTM	AA1   	AA1         	0630610	SO  										TAIL WHEEL	FAILED          	B			AMVR	K				NONE                    				O			OTHER                     			LD	LANDING        	1			CE	05	5643L				8626	AA10043				PILOT REPORTED TAIL WHEEL SHIMMEY ON ROLLOUT, THEN, AIRCRAFT GROUND LOOPED TO LEFT.  RIGHT SIDE OF ARM ASSEMBLY P/N A-50	4 HAD BROKEN OFF APPROXIMATELY 1 INCH FROM CENTER OF ARM.  BROKEN ENDS SHOW SIGNS OF POSSIBLE CORROSION.  MAINTENANCE RE	CORDS NOT AVAILABLE TO DETERMINE PART TIME IN SERVICE OR C/W ANY STC FOR TAIL WHEEL CONVERSION.				1	L	7	1 	3O				A11EA
1998090400483	19980904	00483	SO  	1998	9	4	98ZZZX3188       	2	19980802	G	8530		ROCKER COVER    			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	5421J					340A0108	266961R			LEFT ENGINE TORQUING OVER AND CONTACTING COWLING WITH NR 6 ROCKER COVER.  THIS ACTION IS WEARING A DEEP GROOVE IN THE RO	CKER COVER.  COWLING IS SHOWING HEAT DAMAGE FROM THE EXHAUST SYSTEM.  THIS AIRCRAFT MODIFIED AT RPM IN WACO, TX TO 335 H	P UNDER RAM STC SE4327SW.  TIME SINCE STC:  21.6 HOURS.				1	L	7	2 	3O	3	O		3A25    	E8CE
1998090400484	19980904	00484	SO  	1998	9	4	98ZZZX3189       	2	19980802	G	8530		ROCKER COVER    			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					LT ENGINE	DAMAGED         	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	118RM					340A0290	L502035J			LEFT ENGINE TORQUING OVER AND CONTACTING COWLING WITH NR 6 ROCKER COVER.  THIS ACTION HAS WORN HOLES IN TWO ROCKER COVER	S AND IS WEARING ON THE THIRD ONE. THE HEAT FROM THE EXHAUST IS CAUSING DAMAGE TO COWLING.  THIS ACFT MODIFIED AT RAM IN	 WACO, TX TO 335 HP UNDER RAM STC SE4327SW.  TIME SINCE STC:  166.6 HOURS.				1	L	7	2 	3O	3	O		3A25    	E8CE
1998090400485	19980904	00485	SO  	1998	9	4	98ZZZX3190       	1	19980806	G	5540	40622000	RUDDER          			PIPER 	PA12  	PA12        	7101202	SO  										HINGE BLOCK	DAMAGED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	2657M	4286 				12970				BOTTOM RUDDER HINGE BLOCK. WELD BROKEN ON LEFT SIDE AND BARELY ATTACHED ON RT SIDE.  SUSPECT WIND DAMAGE.						1	H	7	1 	3O				A780
1998090400486	19980904	00486		1998	9	4	98ZZZX3191       	1	19980701	G	2621	899066	EXTINGUISHER    	KIDDE       																CARTRIDGE	DAMAGED         	B	S		YN2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										FIRE EXTINGUISHER CONTAINER IN FOR REPAIR DUE TO IT BEING FIRED.  DURING RECEIVING INSPECTION, OBSERVED THE DISCHARGE OU	TLET HAD EXTREME BULGING AND STRESS AS THE CARTRIDGE HAD EXPLODED AND COMPLETELY DESTROYED DISCHARGE OUTLET.  IT ALSO DE	STROYED THE SWIVEL NUT DUE TO DISCHARGE OUTLET COULD NOT BE REMOVED BY UNSCREWING.  THE SWIVEL HAD TO BE CUT OFF FROM TH	E DISCHARGE OUTLET.
1998090400487	19980904	00487		1998	9	4	98ZZZX3192       	1	19980731	G	2621	OA897776	SQUIB           	KIDDE       	8978892     															FIRE EXTING	DAMAGED         	B			YN2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01					8773EL					UNIT RECEIVED ON 7-31-98.  ON RECEIVING INSPECTION, FOUND OUTLET DAMAGED DUE TO SQUIB HAVING MUSHROOMED OUT PARTIALLY BL	OCKING DISCHARGE OUTLET PORT.  REF TO OVERLAND SB ISSUED JUNE 22, 1998 26-20-02.  CUSTOMER NOTIFIED OF DISCREPANCY.
1998090400488	19980904	00488		1998	9	4	98ZZZX3193       	1	19980803	G	2621	OA89776	SQUIB           	KIDDE       																FIRE EXTING	DAMAGED         	B			YN2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01										RECEIVED UNIT P/N 897889 ON 8-3-98.  OUTLET DAMAGED DUE TO SQUIB.  CUSTOMER NOTIFED REF: OVERALND SB 26-20-02.
1998090400489	19980904	00489		1998	9	4	98ZZZX3194       	1	19980606	G	2621	OA897776	SQUIB           	KIDDE       																FIRE EXTING	DAMAGED         	B			YN2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01					87472EK					UNIT RECEIVED AT HRD.  DURING RECEIVING INSPECTION, FOUND SQUIB AFTER BEING FIRED MUSHROOMED AND BLOCKING DISCHARGE PORT	.  REF:  SB 26-20-02.  CUSTOMER NOTIFIED.
1998090400490	19980904	00490	SO  	1998	9	4	98ZZZX3196       	1	19980806	G	3246	16101900	WHEEL           	PARKERHANFIN		PIPER 	PA31  	PA31        	7103102	SO  										MLG	CORRODED        	B			VY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	65TT	3058 				317612078				MAIN WHEEL WAS DISASSEMBLED FOR BRAKE DISC REPLACEMENT.  THE INBOARD HALF WAS SEVERELY PITTED FROM CORROSION AND HAD TO 	BE REPLACED.  THIS AREA CANNOT BE SEEN UNLESS THE DISC IS REMOVED.  THE AREA SHOULD BE LOOKED AT EVERY TIRE CHANGE.					1	L	7	2 	3O				A20SO
1998090400491	19980904	00491	EA  	1998	9	4	98ZZZX3197       	2	19980728	G	7324	ANIS4290	FLOW DIVIDER    			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	SCORED          	B			WIWR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			WP	07	181MW	559  			63322196	17280181				PILOT REPORTED ENGINE QUIT DURING RECOVERY FROM A STALL AT 3,000 FEET AGL.  PILOT WAS ABLE TO RESTART ENGINE AND FLY ACF	T BACK TO AIRPORT SAFELY.  ENGINE WAS IDLING ROUGH.  MAINTENANCE REMOVED COVER AND FOUND SCORING AND SMALL METAL FLAKES 	INSIDE OF THE FLOW DIVIDER (SPIDER). AFTER POLISHING OUT SCORING AND FLUSHING OUT FUEL SYSTEM, ACFT WAS FLOWN 18 PLUS HO	URS WITH NO FURTHER PROBLEMS.			1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400492	19980904	00492	EA  	1998	9	4	98ZZZX3198       	2	19980717	G	7322	25765361	FUEL SERVO      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	SCORED          	B	S		WIWR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	97100	734  			70131706	17280100	L2709351A			WHILE DOING A GROUND RUN-UP PRIOR TO A 100-HOUR INSPECTION, MAINTENANCE NOTICED THE ENGINE, UPON REACHING OPERATING TEMP	, BEGAN TO RUN ROUGH AT LOWER POWER SETTINGS.  THE FUEL FLOWS ALSO WERE EXTREMELY ERRATIC.  NO FURTHER ACTION HAS BEEN T	AKEN.  THIS IS AN ORIGINAL FUEL SERVO THAT WAS SHIPPED/INSTALLED AT THE FACTORY.  REMOVED FLOW DIVIDER COVER AND FOUND S	MALL METAL FLAKES ON UNDERSIDE.  ALSO, FOUND SCORING ON PISTON.  FLUSHED OUT FLOW DIVIDER AND REMOVED SCORING  WITH SCOT	CH BRITE.  ACFT HAS FLOWN 10 HOURS WITH NO FURTHER PROBLEMS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400493	19980904	00493	EA  	1998	9	4	98ZZZX3199       	2	19980717	G	7322	257635361R	FUEL SERVO      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	SCORED          	B	S		WIWR	O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			WP	07	360ES		1    		36542	17280010	L2690251A			DURING MAINTENANCE FLIGHT WHILE CHECKING THE OPERATION OF THIS FUEL SERVO, ON THE THIRD APPROACH, ENGINE STARTED TO MISS	 AT REDUCED POWER SETTINGS.  GO-AROUND, WHEN ACFT TURNED FINAL AND UPON POWER REDUCTION, THE ENGINE LOST POWER AND UPON 	ADVANCEMENT OF THE THROTTLE, ENGINE REGAINED POWER.  REMOVED COVER FROM FLOW DIVIDER (SPIDER) AND FOUND METAL CONTAMINAT	ION AND SCORING ON PISTON.  FLUSHED OUT FLOW DIVIDER AND ALL LINES.  REMOVED SCORING FROM PISTON WITH SCOTCH BRITE.  ACF	T HAS FLOWN OVER 20 HOURS SINCE WITH NO PROBLEMS.		1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400494	19980904	00494	EA  	1998	9	4	98ZZZX3200       	2	19980717	G	7322	257635361R	FUEL SERVO      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	MALFUNCTIONED   	B			WIWR	O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			WP	07	360ES		18   			17280010	L2690251A			PILOT REPORTS ERRATIC ENGINE OPERATION AT LOW POWER SETTINGS AND APPEARED TO BE 'MISFIRING' ON FINAL.  MAINTENANCE PERSO	NNEL RAN ENGINE AND NOTICED AT ANY RPM BELOW 1,500, ENGINE WOULD 'LOPE' AND WAS ACCOMPANIED BY ERRATIC FUEL FLOW INDICAT	IONS.  FUEL SERVO WAS REPLACED BY AN OVERHAULUED UNIT, S/N 36542.				1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400495	19980904	00495	EA  	1998	9	4	98ZZZX3201       	2	19980717	G	7322	257635361R	FUEL SERVO      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	MALFUNCTIONED   	B			WIWR	O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			WP	07	360ES	845  			70124311	17280010	L2690251A			PILOT REPORTED LOSS OF ENGINE POWER AT 500 FEET AGL ON TAKEOFF AND AGAIN ON FINAL.  PILOT MADE A SAFE LANDING.  DURING T	AXI BACK, MAINTENANCE PERSONNEL NOTICED ENGINE RUNNING EXTREMELY ROUGH.  DURING TROUBLESHOOTING ON SUBSEQUENT MAINT RUNS	, THE FUEL FLOW GAUGE SHOWED HIGHLY ERRATIC INDICATIONS.  THE FUEL SERVO WAS REPLACED WITH ONE FROM ANOTHER ACFT OF THE 	SAME MAKE AND MODEL AND TEST FLOWN.  ALL CHECKS WERE GOOD.  AFTER UNIT WAS REPAIRED AND REINSTALLED ON THIS ACFT AND TES	T FOWN, ALL CHECKS WERE GOOD.		1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400496	19980904	00496	EA  	1998	9	4	98ZZZX3202       	2	19980717	G	7322	257635361R	FUEL SERVO      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	MALFUNCTIONED   	B		A	WIWR	A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			WP	07	360ES	1050 			70124311	17280010	L2690251			PILOT REPORTED ENGINE QUIT IN-FLIGHT AND REQUIRED A DEAD STICK LANDING.  ENGINE RESTARTED ON THE GROUND AFTER A SAFE LAN	DING.  MAINTENANCE MADE ADJUSTMENTS TO FUEL SERVO AFTER NOTICING HIGHLY ERRATIC FUEL FLOW INDICATIONS.  ALL GROUND CHECK	S WERE NORMAL.  ACFT TEST FLOWN WITHOUT INCIDENT UNTIL THE FINAL LANDING AT WHICH TIME THE ENGINE STAMMERED AND NO RPM'S	 WERE INDICATED, BUT CAME BACK ON TIME WHEN THROTTLE WAS ADVANCED.  FUEL CONTROL/SERVO WAS REMOVED AND A KNOWN SERVICEAB	LE SERVO WAS INSTALLED.  ACFT TEST FLOWN, ALL CHECKS GOOD.		1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998090400497	19980904	00497	EA  	1998	9	4	98ZZZX3203       	2	19980716	G	7322	25765361	FUEL SERVO      			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE	MALFUNCTIONED   	B			WIWR	K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		IN	INSP/MAINT     	1			WP	07	172SJ	478  			70141303	17280291				PILOT REPORTED ON ENGINE RUN-UP AT LOWER POWER SETTING, ENGINE RAN ROUGH AND WAS DIFFICULT TO KEEP RUNNING.  MAINTENANCE	 NOTICED ON GROUND RUN-UPS, ERRATIC FUEL FLOW INDICATIONS THAT CORRESPONDED WITH THE ENGINE ROUGHNESS.  A NEW UNIT WAS I	NSTALLED AND FLIGHT TESTED NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	1E10
1998091100001	19980911	00001	NE  	1998	9	11	98ZZZX3217       	2	19980811	G	7230	50B050	SEAL SEAT       								PWA   	4056  	PW4056      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C3952					CRACKS IN CHROME SEAL FACE WHICH APPEAR TO HAVE BEEN TRANSFERRED INTO THE BASE METAL.  PWA HAS A SERVICE BULLETIN TO REP	LACE THIS PART AS AN OPTION.										4	F			E24NE
1998091100002	19980911	00002	CE  	1998	9	11	98ZZZX3218       	1	19980810	G	3244	50056PLY	TIRE            			BEECH 	95    	95B55       	1152729	CE  										NLG	FAILED          	B			GMZ2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	669PF	36   			61990774	TC2297				NLG TIRE TREAD AND CORDS DISINTEGRATED ON LANDING.  TREAD IS MISSING AND ALL CORDS SEVERED.  TIRE WAS STILL HOLDING AIR.						1	L	7	2 	3O			RT	3A16
1998091100003	19980911	00003	CE  	1998	9	11	98ZZZX3219       	1	19980717	G	2434	318	ALTERNATOR      	ELECTROSYS  		CESSNA	210   	210L        	2073448	CE  										DC SYSTEM	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	7874J		30   		8021324	21060597				ALTERNATOR FAILED IN 10 DAYS, 30 HOURS TIME IN SERVICE.						1	H	7	1 	3O				3A21
1998091100004	19980911	00004	CE  	1998	9	11	98ZZZX3220       	1	19980810	G	3241	425472	CONTROL BOX     			CESSNA	500   	550         	2076604	CE  										ANTI SKID	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	19	10EG				735A	5500055				RECEIVED AN 'EXHANGE' ANTI-SKID CONTROL BOX FROM SERVICE CENTER.  UPON INITIAL INSTALLATION INTO THE AIRCRAFT WHEN THE A	NTI-SKID SWITCH WAS SELECTED 'ON', THE ANTI-SKID FAIL 'AMBER' LIGHT REMAINED ILLUMINATED.  INVESTIGATED PROBLEM AND DETE	RMINED THE 'EXCHANGE' CONTROL BOX RH CHANNEL WAS TOTALLY INOPERABLE. THIS BASIC PROBLEM INDICATION IS IDENTICAL TO THE R	EASON THIS CONTROL BOX WAS REMOVED BY THE LAST CUSTOMER.  SUBMITTER STATED CONTROL BOX OVERHAUL AGENCY PERFORMED A FUNCT	IONAL TEST ONLY DURING THE LAST SHOP VISIT AND RETURNED THE UNIT TO SERVICE WITHOUT REPAIR.  WORK ORDER STATES UNIT TEST	ED SATISFACTORY PER LATEST MANUFACTURER'S SPECS.	1	L	7	2 	4F			 	A22CE
1998091100005	19980911	00005	CE  	1998	9	11	98ZZZX3221       	1	19980730	G	3320	18996	INVERTER        			CESSNA	500   	550         	2076604	CE  										LIGHTING	BURNED          	B			IW1R	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	25	998BC	2541 			6597	5500665				AT FL 31, SMOKE REPORTED IN CABIN.  EMERGENCY LANDING REQUEST MADE.  AIRCRAFT LANDED UNEVENTFULLY, AIRCRAFT INSPECTED FO	R FERRY FLIGHT TO SWF WITH INDIRECT LIGHTING POWER INVERTERS DISABLED.  INSPECTION REVEALED BURNED INVERTER, NO INDICATI	ON OF CAUSE.  SUSPECT ISOLATE INCIDENT.  DATE OF MFG:  7-90.				1	L	7	2 	4F				A22CE
1998091100007	19980911	00007	NE  	1998	9	11	98ZZZX3223       	2	19980801	G	7230	50B050	SEAL SEAT       								PWA   	4056  	PW4056      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C6037					CRACKS FOUND IN BASE METAL AFTER CHROME SEAL FACE IS REMOVED.  SUSPECT CAUSE IS HEAT.  CRACKS IN CHROME ARE TRANSFERRED 	INTO BASE METAL.										4	F			E24NE
1998091100008	19980911	00008	NE  	1998	9	11	98ZZZX3224       	2	19980811	G	7230	50B050	SEAL SEAT       								PWA   	4056  	PW4056      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C3951					CRACKS IN CHROME SEAL FACE WHICH APPEAR TO HAVE BEEN TRANSFERRED INTO THE BASE METAL.  PWA HAS A SERVICE BULLETIN TO REP	LACE THIS PART AS AN OPTION.										4	F			E24NE
1998091100009	19980911	00009	WP  	1998	9	11	98ZZZX3225       	1	19980801	G	7160	ATL7027135	PANEL           			DOUG  	DC10  	DC1030      	3023501	WP  										NR 2 ENG INLET	MISMANUFACTURED 	B			R1XR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07										THIS BELLMOUTGH PANEL INSTALLS B.D.C. ON THE NR 2 ENGINE INLET.  THE BACK SIDE SHOULD HAVE A STAGGER ROW OF 14 HOLES TO 	ALLOW DRAINAGE.  DURING INCOMING INSPECTION, NOTED ALL 14 HOLES HAVE BEEN WELDED OVER.					2	L	7	3 	4F			 	A22WE
1998091100010	19980911	00010	GL  	1998	9	11	98ZZZX3226       	3	19980209	G	6114	57C084061	HUB             													HARTZL	HC12X	HC12X207    	GL  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		1548 			6289					FOUND CRACK LOCATED IN WELD AREA WHERE THE GUIDE LUGS ARE WELDED TO THE HUB.																5	C	P845
1998091100011	19980911	00011	SW  	1998	9	11	98ZZZX3227       	1	19980811	G	3244	850108PLY	TIRE            	GOODYEARAERO		GULSTM	500   	500S        	0141107	SW  										TREAD CORD	SEPARATION      	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	40TC	549  			43141241	3091				TIRE HAS SEVERE CORD SEPARATION BETWEEN TREAD.						1	H	7	2 	3O				6A1
1998091100012	19980911	00012	SO  	1998	9	11	98ZZZX3228       	1	19980729	G	5411	12022766001	FRAME           			EMB   	120   	EMB120RT    		SO  										ENGINE NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09						120065				DURING PERFORMANCE OF C-CHECK INSPECTION  TASK ON NR 1 FRAME OF ENGINE NACELLE.  CRACKS WERE VISUALLY DETECTED IN THE VI	CINITY OF THE MOUNT HOLES FOR THE TORQUE MOUNT.  THE LEFT MOUNT CRACKS WERE FOUND ON THE INBOARD AND OUTBOARD (LEFT) FRA	ME INBOARD SIDE HAS A CRACK APPROXIMATELY .25 INCH IN LENGTH.  THE OUTBOARD SIDE HAS A CRACK APPROXIMATELY .85 INCH IN L	ENGTH. RIGHT FRAME INNER SIDE HAS CRACK APPROXIMATELY 1.6 INCHES IN LENGTH.  THE OUTBOARD SIDE HAS CRACKS IN 2 PLACES BO	TH APPROXIMATELY .5 INCH IN LENGTH.  A .25 INCH APART CRCKS ARE COMING TOGETHER.		2	L	7	2 	4T			RT	A31SO
1998091100013	19980911	00013	SO  	1998	9	11	98ZZZX3229       	1	19980729	G	5400	MS2113409005	BOLT            			EMB   	120   	EMB120RT    		SO  						HAMSTD	14SF	14SF*       	NE  	NACELLE FITTING	SHEARED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	241AS					120065				DURING PERFORMANCE OF C-CHECK INSPECTION, TASK ON LEFT INBOARD FORWARD NACELLE FITTING ASSY P/N 120-00361-001, FOUND ALL	 OUTER BOLTS P/N MS21134-04005 SHEARED AND AFT INNER BOLT LOOSE.					2	L	7	2 	4T			RT	A31SO   		6	C	P7NE
1998012900092	19980129	00092	GL  	1998	1	29	98ZZZX323        	2	19980106	G	7323	252466712	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE PT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K		1576 		22981	2040				GOVERNOR SLOW TO RESPOND TO POWER CHANGES (HIGH AND LOW SIDE).						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998091100014	19980911	00014		1998	9	11	98ZZZX3230       	4	19980805	G	3424	C6610320101	INDICATOR       	AEROMECH    	A10504      	CESSNA	500   	550         	2076604	CE  										INST PANEL	SHORTED         	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	12549				831024	5500501				PIN APEARS TO BE GROUNDED TO CHASSIS.  UNIT OPERATES ON BENCH, BUT WHEN INSTALLED INSTRUMENT PANEL, IT TRIPS THE CIRCUIT	 BREAKER.					1	L	7	2 	4F				A22CE
1998091100015	19980911	00015	EA  	1998	9	11	98ZZZX3231       	1	19980811	G	3222	200811606	STRUT           	ROTOL       	6018500211  	CNDAIR	CL600 	CL6002B16   	1900305	EA  										NLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	914X				DCL35795	5185				CORROSION  OUND IN NLG SHOCK STRUT MAIN FITTING INNER BORE.  THE AREA IS APPROXIMATELY 1 INCH LONG BY .250 INCH HIGH WIT	H PITS RANGING FROM .001 INCH - .003 INCH DEEP.  CORROSION IS IN BAND 'D' OF MAIN FITTING PER CMM 32-20-03.  ALSO, FOUND	 CORROSION ON NLG LOWER BEARING HOUSING IN TWO AREAS.  BOTH AREAS ARE ON THE LOWER AFT HALF ON HOUSING WITH PITS FROM .0	01 INCH - .002 INCH DEEP.  REPLACED MAIN FITTING AND LOWER BEARING HOUSING WITH NEW COMPONENTS.  LANDINGS, 1,673.			2	L	7	2 	4F			RT	A21EA
1998091100016	19980911	00016	CE  	1998	9	11	98ZZZX3232       	1	19980709	G	3411	654A59	PRESSURE SWITCH 			BEECH 	MU300 	400A        	1155402	CE  										PITOT SYSTEM	LEAKING         	B			KI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	85CR				122	RK22				DURING UNSCHEDULED TEST OF PILOT'S PITOT/STATIC SYSTEM, DETERMINED A SUBSTANTIAL LEAK EXISTED.  THE LEAK WAS TRACED TO T	HE HORIZONTAL STABILIZER DE-ICE SYSTEM DIFFERENTIAL PRESSURE SWITCH (REF:  DESIGNATION S39B).  THE UNIT IS LEAKING FROM 	PITOT TO STATIC SIDE INTERNALLY.  RECOMMEND CHECKING PITOT/STATIC SYSTEM FOR LEAKS WHENEVER THERE IS A SIGNIFICANT MISMA	TCH BETWEEN NR 1 AIRSPEED AND NR ALTIMETER.			2	H	7	2 	4F			RT	A16SW
1998091100017	19980911	00017	EU  	1998	9	11	98ZZZX3233       	1	19980817	G	2820	YA001295	HOSE            			BRAERO	DH125 	HS125700A   	4230170	EU  										ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	810GS					257061				MAIN FUEL FEEL LINE FROM PYLON TO ENGINE WAS FOUND COLLAPSED MORE THAN 50 PERCENT.  THIS CONDITION IS DIFFICULT TO DETEC	T DUE TO THE FIRE SLEEVE COVERING THE HOSE.  SUBMITTER SUGGESTED TWISTING OF THE LINE DURING TIGHTENING OF THE B-NUTS AT	 INSTALLATION.  CARE SHOULD BE USED TO PREVENT TWISTING DURING TIGHTENING BY USING WRENCH TO BACK UP LINE.				2	L	7	2 	4F				A3EU
1998091100018	19980911	00018	CE  	1998	9	11	98ZZZX3234       	1	19980814	G	7120	595104815	MOUNT           			CESSNA	425   	425         	2076018	CE  										LT ENGINE	CRACKED         	B		A	BWRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	12268					4250227				LEFT ENGINE OUTBOARD ENGINE MOUNT BRACKET HAS SMALL CRACK ON THE FORWARD LOWER SIDE OF MOUNT.						1	L	7	2 	3T			RT	A7CE
1998091100019	19980911	00019		1998	9	11	98ZZZX3235       	2	19980806	G	8530	654961A2	CYLINDER        			AMTR  		PARAKEET    			CONT  		IO520*      							ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			WP	05	18252		1000 			107				CYLINDER SEPARATION OCCURRED IN-FLIGHT.  AIRCRAFT PUT ON GROUND SAFELY.  SUBMITTER SUGGESTS MORE FREQUENT CYCLINDER INSP	ECTIONS.  THIS IS THE 6TH CYLINDER ASSY OBSERVED HAVING SEPARATIONS SUCH AS THIS.  POSSIBLY A 25 HOUR CHECK MIGHT FIND M	ORE DEFECTS SOONER.							0
1998091100020	19980911	00020	SW  	1998	9	11	98ZZZX3236       	1	19980604	G	3240		CONTROL ROD     			BBAVIA	7     	7GCB        	2110130	SW  										RT BRAKE	BROKEN          	G		A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	11	912CP					165				THE AIRCRAFT WAS BEING OPERATED FROM THE FRONT SEAT WITH 2 PEOPLE ON BOARD WHEN THE AIRCRAFT VEERED TO THE LEFT DURING L	ANDING ROLL OUT AND GROUND LOOPED.  POST-ACCIDENT INVESTIGATION REVEALED THE RT FORWARD BRAKE SYSTEM HAD FAILED.  THIS O	CCURRED WHEN THE CONTROL ROD ATTACHMENT POINT LOCATED ON THE RT AFT PEDAL, BROKE OFF.  'BOTH RT PEDALS ARE INTERCONNECTE	D BY A CONTROL ROD'.  THE AFT BRAKE PEDAL APPEARS TO HAVE PREVIOUS STRESS TYPE CRACKS WHERE THE CONTROL ROD ATTACHES AND	 ON THE PEDAL PIVOT END.		1	H	7	1 	3O				A759
1998091100021	19980911	00021	CE  	1998	9	11	98ZZZX3237       	1	19980731	G	3010	66002011	ANTI ICE        			LEAR  	35    	35A         	5170602	CE  										E/E BAY	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	183FD	8604 			443	183				WING ANTI-ICE VALVE SUTCK IN THE OPEN POSITION.  THIS ALLOWED THE WING DUCT IN THE CABIN TO OVERHEAT.  THE FLIGHT WAS IN	TERRUPTED, BUT THERE WERE NO INJURIES.					2	L	7	2 	4F				A10CE
1998091100024	19980911	00024	EA  	1998	9	11	98ZZZX3239       	2	19980810	G	7322	105135	FLOAT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CARBURETOR	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	28360				CK613012	287916403	L888439A			FIRE IN ENGINE COWL AREA.  HOT START.  PROBLEM TRACED TO FAILED FLOAT IN CARBURETOR.  TANK CAME LOOSE DUE TO MANUFACTURE	R DEFECT - MISSED SOLDER POINT.					1	L	7	1 	3O	3	O		2A13    	E274
1998091100025	19980911	00025	SO  	1998	9	11	98ZZZX3240       	2	19980817	G	8530	6466R	VALVE           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	1794Q						20582570A			EXHAUST VALVE CRACKED AT 130 HOUR SMOH, AT OVERHAUL, ALL CYLINDER ASSEMBLIES REPLACED WITH NEW.						1	H	7	1 	3O	3	O		3A19    	E252
1998091100026	19980911	00026	SO  	1998	9	11	98ZZZX3241       	2	19980817	G	8530	653421	GUIDE           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	1794Q					15073094	20582570A			JUNE, 1997, ENGINE OVERHAULED.  ALL NEW CYLINDERS INSTALLED AT 130 HOURS.  NR 4 CYLINDER STUCK ON EXHAUST VALVE.  CYLIND	ER WAS REPLACED.					1	H	7	1 	3O	3	O		3A19    	E252
1998091100027	19980911	00027	SO  	1998	9	11	98ZZZX3242       	2	19980817	G	8530	646612	VALVE           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	17023					15073789	231264R			262 HOURS SMOH.  NR 2 CYLINDER STUCK IN EXHAUST VALVE.  ALL NEW CYLINDERS WERE INSTALLED AT OVERHAUL.						1	H	7	1 	3O	3	O		3A19    	E252
1998091100028	19980911	00028	SO  	1998	9	11	98ZZZX3243       	2	19980817	G	8530	653421	GUIDE           			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	17023					15073789	231264R			262 HOURS SMOH.  NR 2 CYLINDER STUCK IN EXHAUST VALVE.  ALL NEW CYLINDERS WERE INSTALLED AT OVERHAUL.						1	H	7	1 	3O	3	O		3A19    	E252
1998091100030	19980911	00030	EA  	1998	9	11	98ZZZX3245       	2	19980817	G	8520	13B27121	CRANKSHAFT      								LYC   	IO360 	IO360L2A    		EA  					ENGINE	FLAKING         	B			QX2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11		77   			I32965		L2734351A			THE PAINTED INSIDE DIAMETER OF CRANKSHAFT PER AD 98-02-08 AND SB 530, WAS PEELING OFF EXPOSING BARE METAL.  THIS ENGINE 	WAS TAKEN APART DUE TO A PROPELLER SUDDEN STOPPAGE.										3	O			1E10
1998091100031	19980911	00031		1998	9	11	98ZZZX3246       	4	19980810	G	2561	KS9P0101HC2	LIFE VESST      	EAAEROMARINE																CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					B64598					VEST FAILED MFG RECOMMENDED 2 PSI TEST IAW 25-6-1. VEST MANUFACTURED DEC 1980.
1998091100032	19980911	00032		1998	9	11	98ZZZX3247       	4	19980724	G	2561	H2L8	LIFE VEST       	AMERICANSFTY																CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					4298087					VEST FAILED MFG RECOMMENDED 2 PSI TEST IAW 25-60.  VEST MANUFACTURED FEB 1980.
1998091100033	19980911	00033	WP  	1998	9	11	98ZZZX3248       	2	19980602	G	7321	21011445	COMPUTER        			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313     	01518	WP  					ENGINE FUEL	FAILED          	B			AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	92RP				191152	257022	P80153			FUEL COMPUTER DROPS OFF-LINE WHEN THROTTLE IS ADVANCED ABOVE IDLE.  THIS IS THE THIRD FAULTY FUEL COMPUTER RECEIVED IN T	HE PAST 3 WEEKS.  ALL COMPUTERS RECEIVED SHOW NCFR ON TEST SHOOTS S8130-3.  HOWEVER, THEY FAIL WHEN INSTALLED IN AIRCRAF	T IN THE SAME MANNER AS NOTED ON TEST SHEET PRIOR TO RE-CERTIFICATION.				2	L	7	2 	4F	4	F		A3EU    	E6WE
1998091100034	19980911	00034	CE  	1998	9	11	98ZZZX3249       	1	19980731	G	5330		SKIN            			CESSNA	650   	650         	2076802	CE  										FUSELAGE	CRACKED         	B			PJYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	72ST	5160 				6500072				AT ES 239.49 IS LOCATED A RIB BONDED AND RIVETED TO THE INTERNAL AND EXTERNAL SKINS.  ON THE OUTSIDE SKIN THERE ARE AREA	S OF FATIGUE THAT TAP TESTED BAD AND HAD PAINT CRACKS ORIGINATING AT THE LAST RIVET HEAD ON THE UPPER AND LOWER ENDS OF 	THE RIB.  THE CRACKS WENT ALL THE WAY TO THE THORSTRAND LAYER (THE OUTER LAYER) OF THE COMPOSITE STRUCTURE.  THERE WERE 	NO CRACKS IN THE KEVLAR, BUT THERE WERE SIGNS OF FATIGUE.   AGAIN, THESE VISIBLE SIGNS OF STRESS WERE COMMON TO BOTH AFT	 BODIES AS WELL AS THE AFT BODIES ON A PREVIOUS PHASE 44 INSPECTION ON DIFFERENT ACFT.  CYCLES:  3,317.		2	L	7	2 	4F				A9NM
1998091100035	19980911	00035	CE  	1998	9	11	98ZZZX3250       	1	19980731	G	5330		SKIN            			CESSNA	650   	650         	2076802	CE  										FUSELAGE	CRACKED         	B			PJYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	72ST	5160 				6500072				BOTH AFT BODIES HAD A KEVLAR CRACK AND DELAMINATION AT THE 12 O'CLOCK POSITION.  BOTH DEFECTS CAUSED BY A METAL BRACKET 	RIVETED TO COMPOSITE STRUCTURE AFT OF FWD ATTACH FLANGE.  2 RIVETS GOING DOWN THRU OUTSIDE SKIN INTO BRACKET ARE FLATTEN	ING OUTSIDE CURVE OF AFT BODY CAUSING STRESS AND DELAMINATION.				2	L	7	2 	4F				A9NM
1998091100036	19980911	00036	CE  	1998	9	11	98ZZZX3251       	1	19980731	G	5330		SKIN            			CESSNA	650   	650         	2076802	CE  										FUSELAGE	CRACKED         	B			PJYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	72ST	5160 				6500072				AT 6 O'CLOCK POSITION, A CRACK WAS VISIBLE COMING OFF THE T/E OF THE OUTER SKIN AT ES 239.49 WHERE THE THRUST REVERSER M	EETS THE OUTER SKIN OF THE AFT BODY (WHEN THE THRUST REVERSER IS IN THE STOWED POSITION).  UPON INVESTIGATING, DETERMINE	D THE OUTER SKIN PANELS WERE OIL SATURATED.  THE .1250 INCH NOMEX HONEYCOMB CORE WAS FILLED WITH OIL.  WHEN THE PAINT AN	D FILLER LAYERS WERE SANDED AWAY AND THE KEVLAR EXPOSED, OIL IMMEDIATELY BEGAN SEEPING THROUGH THE KEVLAR.   IN SOME ARE	A, ENGINE OIL ACTUALLY DRIPPED OUT.		2	L	7	2 	4F				A9NM
1998091100037	19980911	00037	SO  	1998	9	11	98ZZZX3252       	1	19980727	G	2435	MZ4222R	STARTER         			PIPER 	PA28  	PA28236     	7102815	SO  										STARTER/GEN	FAILED          	B			R7LR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	25	2889D		43   			287911227				STARTER MOTOR OVERHAULED.  STARTER INSTALLED ON 6-16-98.  AFTER 43 HRS, BENDIX DRIVE STUCK IN ENGAGED POSITION AND DESTR	OYED STARTER MOTOR AND STARTER RING GEAR P/N 72566.  PILOT UNAWARE OF PROBLEM UNTIL NEXT RESTART.  THIS COULD HAVE CAUSE	D CATASTROPHIC ENGINE FAILURE.				1	L	7	1 	3O				2A13
1998091100038	19980911	00038	CE  	1998	9	11	98ZZZX3253       	1	19980819	G	3700	211CC	VACUUM PUMP     	RAPCO       		CESSNA	177   	177RG       	2073709	CE  										ENGINE	FAILED          	H				O				OTHER                   				C	J		F.O.D.                    	WARNING INDICATION        		LD	LANDING        	1			SO	25	34807	29   			70370	1774G1014				PART FAILED UPON THROTTLE REDUCTION FOR LANDING AFTER A 2.9 HOUR FLIGHT.  LOW-VAC WARNING LIGHT ILLUMINATED.  THE ALTERN	ATE VAC STANDBY SYSTEM OPERATED AUTOMATICALLY.  PART INSTALLED TO REPLACE ORIG VAC PUMP WHICH FAILED AT 1872.1 HRS.  AT 	INSTALLATION OF THIS RAPCO REBUILT UNIT, A COMPLETE VAC SYSTEM INSPECTION CONDUCTED.  ALL FILTERS REPLACED, AND THE HOSE	S BLOWN DOWN AND REPLACED AS NECESSARY.  NO SYSTEM DEFECTS FOUND.  UPON DISASSEMBLY, RAPCO REPORTED FAILURE DUE TO 'FORE	IGN OBJECT INJECTION', AND 'OIL CONTAMINATION'.  SUBMITTER SUSPECTS FAULTY OVERHAUL.  RAPCO UNIT REPLACED WITH A SIGMA-T	EK NEW UNIT WHICH HAS OPERATED FOR OVER 50 HRS TO-DATE WITHOUT FAILURE.	1	H	7	1 	3O				A20CE
1998091100039	19980911	00039	SO  	1998	9	11	98ZZZX3254       	2	19980814	G	8520	631716	CRANKSHAFT      			GULSTM	500   	500A        	0141104	SW  	CONT  	O520  	IO520F      	17032	SO  					RT ENGINE	BROKEN          	D	P			A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	13	444G	3413 	1714 		4488	124974	574887			WHILE CRUSING AT 5,000 FEET, 2,300 RPM, 23 INCH MP, 62 PERCENT POWER, ENGINE SHUDDERED AND LOCKED UP.  PROPELLER WAS FEA	THERED AND A NORMAL LANDING MADE.  ENGINE TEAR DOWN REVEALED THAT THE VAR CRANKSHAFT FAILED AT THE FORWARD CHEEK OF NR 2	 ROD.				1	H	7	2 	3O	3	O		6A1     	E5CE
1998091100040	19980911	00040		1998	9	11	98ZZZX3255       	1	19980814	G	7160	206301027	FAN FRAME       								LYC   	ALF502	ALF502R     	41580	NE  					ENGINE	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					W117		5972			EXTENSIVE FOD ON BOTH SIDE OF INNER STRUTS.  SEVERE EROSION ON LEADING EDGE OF OUTER STRUTS RESULTING IN SIGNIFICANT LOS	S OF PARENT MATERIAL.										4	F			E6NE
1998091100041	19980911	00041	SO  	1998	9	11	98ZZZX3256       	1	19980807	G	5315	12005807001	FLOORBEAM       			EMB   	120   	EMB120RT    		SO  										BS 4214	CORRODED        	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	229AS					120042				DURING C-CHECK INSPECTION TASKS, THE OMEGA FLOOR BEAM WAS FOUND CORRODED THROUGH IN SEVERAL PLACES.  HEAVY SURFACE CORRO	SION FOUND ON THE ADJACENT CROSS BEAMS, P/N 120-14243-001.  THE CORROSION IS IN THE AREA OF THE PASSENGER ENTRY DOOR AND	 THE INGRESS OF WATER AND OTHER ELEMENTS POSSIBLY LED TO THE CURRENT STATE OF THE BEAMS.  THIS AREA IS DIFFICULT TO INSP	ECT SINCE THE SEAT RAIL AND CAP COVER THE OMEGA BEAM.  PERIODIC BORESCOPE INSPECTION MAY HELP TO ALERT OPERATORS OF IMPE	NDING PROBLEMS.		2	L	7	2 	4T			RT	A31SO
1998091100042	19980911	00042	SO  	1998	9	11	98ZZZX3257       	1	19980820	G	5720		WINGLET         			GULSTM	G1159 	G1159A      	3970109	SO  										LT WING	DAMAGED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	308HG					308				WINGLET, 0012L, LEFT WING ATTACH HARDWARE.  WINGLET WAS BEING REPLACED BECAUSE OF DAMAGE AND THE ATTACH HARDWARE WAS SEV	ERELY CORRODED.  SUSPECT WATER INTRUSION INTO SEALED AREA.  INSTALLED NEW WINGLET AND SEALED IAW MFG PROCEDURES.  PARTS 	REPLACED:  BOLT P/N NAS 1165-51L, -65L.  SLEEVES P/N 1159WM30707-11, AND -15.				2	L	7	2 	4F				A12EA
1998091100043	19980911	00043	EU  	1998	9	11	98ZZZX3258       	1	19980710	G	2410	9207614000	BEARING SUPPORT 		2687A1      	AEROSP	SA316 	SA315B      	8680615	EU  										START/GEN MOUNT	CRACKED         	B	S		LH3R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			WP	07	3128G	1994 	1006 		453	2488				STARTER/GENERATOR MOUNTING FLANGE CRACKED.  AIRCRAFT VIBRATION LEVELS EXCESSIVE DUE TO LACK OF PREVENTIVE MAINTENANCE.						1	G	7	1 	4U				H1IN
1998091100044	19980911	00044	EU  	1998	9	11	98ZZZX3259       	1	19980710	G	7160	0202127300	AIR INTAKE      			AEROSP	SA316 	SA315B      	8680615	EU  										MOUNT	CRACKED         	B			LH3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	3128G					2488				TWO UPPER AND 4 LOWER AIR INTAKE HALVES CRACKED AT MOUNTING POINTS.  THIS IS A RECURRING PROBLEM AND HAS BEEN NOTED ON N	UMEROUS AIRCRAFT.  SUGGEST A REINFORCED MOUNTING ASSEMBLY.					1	G	7	1 	4U				H1IN
1998091100045	19980911	00045	WP  	1998	9	11	98ZZZX3261       	1	19980710	G	6220	12E5143712	HUB             			HILLER	UH12  	UH12E       	4360122	WP  										M/R	CRACKED         	B	S		CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09					10285					DURING OVERHAUL NDT INSPECTION, FOUND THE 4 CRACKS FROM THE T.T. PIN BORES.						1	G	7	1 	3O				4H11
1998091100046	19980911	00046	WP  	1998	9	11	98ZZZX3262       	1	19980710	G	6210	52121	TERMINAL        			HILLER	UH12  	UH12E       	4360122	WP  										M/R	CRACKED         	B	S		CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09										DURING OVERHAUL NDT INSPECTION, FOUND CRACKED TERMINAL BORE.  CRACK ABOUT .100 INCH INTO THE BORE AND ACROSS THE CLEVIS 	FACE.  REF:  CHI WO C7289.  WORKSHEET 7-2-98 ITEM 37.					1	G	7	1 	3O				4H11
1998091100047	19980911	00047	NM  	1998	9	11	98ZZZX3263       	1	19980715	G	6720	900F2443400101	DIVERTER PLATE  			DOUG  	MD900 	MD900       	3027375	NM  										NOTAR STATOR	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	903LF	793  				90000030				FOUND BUSINGS FOR NOTAR CENTER BELLCRANK WORKING IN DIVERTER PLATE.						1	G	7	2 	3U			NC	H19NM
1998091100048	19980911	00048	NM  	1998	9	11	98ZZZX3264       	1	19980713	G	2810	900P3662014101	HOSE            			DOUG  	MD900 	MD900       	3027375	NM  										FUEL VENT	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	903LF	795  				90000030				HOSE FOUND DETERIORATED AND LEAKING DURING 1 YEAR FUEL VENT SYSTEM PRESSURE DECAY TEST.  HOSE IS MADE FROM POOR QUALITY 	MATERIAL. SUBMITTER STATED SECOND AIRCRAFT WITH THIS PROBLEM.  ALSO ACFT, S/N 0031.					1	G	7	2 	3U			NC	H19NM
1998091100049	19980911	00049		1998	9	11	98ZZZX3265       	1	19980601	G	2530	620223XX	RELIEF VALVE    																	COFFEEMAKER	STICKS          	B	L		A43R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15										RELIEF VALVES STICKS.  WILL NOT RELIEVE AT RATED PRESSURE.  THIS PHENOMENA HAS BEEN OBSERVED AS LITTLE AS TWO MONTHS AFT	ER A PREVIOUS STOP VISIT.  SUBMITTER BELIEVES THE CONDITION RESULTS FROM THE RUBBER COMPOSITION OF THE VALVE FACE MAKING	 CONTACT AND STICKING.  NOTE:  IT IS IMPERATIVE THAT THE RELIEF VALVE (20, IPL FIGURE 7) BE CHECKED FOR PROPER OPERATION	 EVERY SIX MONTHS/1500 FLIGHT HOURS, OR EVERY SHOP VISIT.
1998091100051	19980911	00051	CE  	1998	9	11	98ZZZX3267       	1	19980710	G	6120		CONTROL ARM     			BEECH 	35    	V35B        	1151548	CE  										PROPELLER GOV	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	6658R	1892 				D10323				DURING ANNUAL INSPECTION FOUND PROPELLER GOVERNOR ADAPTER ARM BRACKET BOLT HOLE/PROP CABLE RED END ATTACH BOLT LOOSE AND	 HOLE ELONGATED.  APPROXIMATELY 650 HOURS SMOH, LAST TIME BOLT INSTALLED.  THIRD 'LOOSE' BOLT FOUND LAST 3 YEARS DIFFERE	NT TCM TYPE INSTALLATIONS.  APPEARS FRONT 8 INCH BY 6 INCH.  INSPECTION COVER IS NOT BEING REMOVED FOR PROPER INSPECTION	 OF GOVERNOR AND CABLE.			1	L	7	1 	3O				3A15
1998091100052	19980911	00052	EA  	1998	9	11	98ZZZX3268       	2	19980730	G	7414	10382681G	CAPACITOR       		D3000       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MAGNETO	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	135PB					317952035				FOR THE FOURTH TIME IN TWELVE MONTHS, A TCM P/N 10-382681 CAPACITOR FAILED CAUSING THE D3000 MAG TO BE DEAD.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998091100053	19980911	00053	CE  	1998	9	11	98ZZZX3269       	1	19980811	G	8010	07707192	DIODE           			CESSNA	177   	177RG       	2073709	CE  										BUSS RELAY	SHORTED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	2691V					177RG0658				AUXILIARY POWER WAS PLUGGED IN AND PROPELLER STARTED SPINNING.  FOUND DIODE ON BUSS RELAY SHORTED.						1	H	7	1 	3O				A20CE
1998091100054	19980911	00054	SO  	1998	9	11	98ZZZX3270       	1	19980804	G	3246	5517768	WHEEL           	PARKERHANFIN		PIPER 	PA23  	PA23250     	7102308	SO  										RT MLG	FAILED          	B			VY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	32WW					2708054036				WHILE TOWING AIRCRAFT, THE RT MAIN WHEEL FAILED ALLOWING THE BRAKE DISC TO CONTACT THE STRUT ASSY. THIS LOCKED THE WHEEL	 FROM ROTATING.  AIRCRAFT WAS MOVED WITH A DOLLY.  IT WAS DETERMINED THE INNER WHEEL BEARING FAILED AND ALLOWED EXCESSIV	E HEAT TO THE WHEEL.  SUBMITTER BELIEVES THIS MADE THE METAL IN THE WHEEL BRITTLE AND, THUS, FAILED.  THIS WOULD HAVE HA	PPENED ON LANDING OR TAKEOFF, IT MAY HAVE BEEN CATASTROPHIC.  WHEEL, BEARINGS, BRAKE DISC, AND LOWER STRUT HAD TO BE REP	LACED.		1	L	7	2 	3O				1A10
1998091100055	19980911	00055	CE  	1998	9	11	98ZZZX3271       	1	19980731	G	2731	0400107130	CONTROL CABLE   			CESSNA	150   	150M        	2071830	CE  										ELEVATOR TRIM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	45700					15077026				DURING A ROUTINE PRE-FLIGHT INSPECTION, PILOT REPORTED THE TRIM (ELEVATOR) DID NOT WORK.  AFTER ACCESS WAS GAINED IN THE	 TAIL SECTION, IT WAS APPARENT THE CABLE BROKE INTO TWO PARTS DUE TO EXTREME RUST.  THE AREA IN WHICH THIS OCCURRED IS V	ERY DIFFICULT TO ACCESS AND ATTRIBUTED TO THE LACK OF VISUAL INSPECTION.				1	H	7	1 	3O			 	3A19
1998091100056	19980911	00056	CE  	1998	9	11	98ZZZX3272       	1	19980731	G	2731	0400107157	CONTROL CABLE   			CESSNA	150   	150M        	2071830	CE  										ELEVATOR TRIM	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	45700					15077026				DURING A ROUTINE PRE-FLIGHT INSPECTION, PILOT REPORTED THE TRIM (ELEVATOR) DID NOT WORK.  AFTER ACCESS WAS GAINED IN THE	 TAIL SECTION, IT WAS APPARENT THE CABLE BROKE INTO TWO PARTS DUE TO EXTREME RUST.  THE AREA IN WHICH THIS OCCURRED IS V	ERY DIFFICULT TO ACCESS AND ATTRIBUTED TO THE LACK OF VISUAL INSPECTION.				1	H	7	1 	3O			 	3A19
1998091100057	19980911	00057	CE  	1998	9	11	98ZZZX3273       	1	19980801	G	5310		STRUCTURE       			CESSNA	172   	172RG       	2072438	CE  										BELLY	CORRODED        	B			PAZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	4706V					172RG0367				DURING ANNUAL INSPECTION, CORROSION WAS FOUND IN BELLY OF AIRCRAFT IN MAIN GEAR WHEEL AREA BETWEEN FS 72.0 AND FS 133.0.	  GEAR WELL CENTER SUPPORT TUNNEL WAS ALSO CORRODED SEVERELY.  REPAIR ACCOMPLISHED BY REPLACING SKINS, DOUBLERS, BULKHEA	DS, AND REAR DOOR POST WITH NEW PARTS.  GEAR SUPPORT TUNNEL WAS NOT AVAILABLE AND A D.E.R. APPROVED REPAIR WAS REQUIRED 	WHICH WAS AN ADDED COST AS THE AIRCRAFT AGE, CORROSION PROBLEMS SEEM TO BE A MORE COMMON PROBLEM ESPECIALLY THE CESNA AI	RCRAFT WITH OPEN GEAR WELLS WHICH ALLOW EXHAUST, ETC., TO GET IN THESE AREAS.  ACFT TT:  2,457.6 HOURS.		1	H	7	1 	3O				3A17
1998091100058	19980911	00058	CE  	1998	9	11	98ZZZX3274       	1	19980806	G	2710	0510105116	CONTROL CABLE   			CESSNA	185   	A185E       	2072818	CE  										AILERON	FRAYED          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	4743Q	4596 				18501197				AILERON CABLE FRAYED WHERE IT WENT OVER A PULLEY.  PULLEY WAS NOT MOVING.						1	H	7	1 	3O			 	3A24
1998091100059	19980911	00059	SO  	1998	9	11	98ZZZX3275       	2	19980729	G	7414	103493943	HOUSING         	BENDIX      	S6RN1205    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					MAGNETO	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	60RR		504  		J268726FR	421C0885				FOUND THE MAGNETO HOUSING CRACKED IN TWO PLACES OPPOSITE EACH OTHER ON THE POLE SHOE HOUSING.  THE CRACKS GO ALL THE WAY	 THROUGH THE HOUSING.					1	L	7	2 	3O	3	O		A7CE    	E7CE
1998091100060	19980911	00060	SO  	1998	9	11	98ZZZX3276       	2	19980730	G	7414	103493943	HOUSING         	BENDIX      	S6RN1201    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					MAGNETO	CRACKED         	B			BXSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	60RR		504  		CO18812FR	421C0885				FOUND THE MAGNETO HOUSING CRACKED IN TWO PLACES OPPOSITE EACH OTHER ON THE POLE SHOE HOUSING.  THE CRACK GOES ALL THE WA	Y THROUGH THE HOUSING.  SEE PAGES 7-8, FIGURE 716 OF THE MM FOR AN EXAMPLE.					1	L	7	2 	3O	3	O		A7CE    	E7CE
1998091100061	19980911	00061		1998	9	11	98ZZZX3277       	4	19980729	G	2562	AK450	ELT             	AMERIKING   		BEECH 	23    	B19         	1151215	CE  										COCKPIT	INTERMITTENT    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	6651R				4303401	MB742				INSPECTION FOUND ELT INTERMITTENT.						1	L	7	1 	3O				A1CE
1998091100062	19980911	00062	SO  	1998	9	11	98ZZZX3278       	1	19980721	G	2410	7988604	BRAKCET         			PIPER 	PA28  	PA28181     	7102807	SO  										ALTERNATOR MOUNT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6932F	100  				287990174				BRACKET GOES FROM ALTERNATOR MOUNT ON ENGINE TO ALTERNATOR.  THIS IS THE 4TH ONE TO CRACK ON THIS PLANE IN 500 HOURS.  A	LL FAIL AT SOME POINT.  CHECKED SIDE VIEW FOR ALIGNMENT PROBLEM, NONE FOUND.   SUSPECT STRESS PROBLEMS DUE TO WELDING.					1	L	7	1 	3O				2A13
1998091100063	19980911	00063	CE  	1998	9	11	98ZZZX3279       	1	19980423	G	2823	459200361	HOUSING         		35921155603 	BEECH 	36    	A36         	1151604	CE  										FUEL SELECTOR	MISMANUFACTURED 	B		A	GN1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	3122U	1251 				E2431				DURING ANNUAL INSPECTION, A VISUAL INSPECTION OF THE FUEL SCREEN AND HOUSING REVEALED AN UNMACHINED AREA WHERE THE FUEL 	SCREEN MEETS THE INTERNAL STOP (UP INSIDE HOUSING).  THE UNMACHINED PIECE (SLAG) IS BREAKING AWAY FROM PARENT METAL.  PI	ECE IS .1250 INCH BY 2 INCHES.  NO PIECES FOUND IN FUEL SCREEN OR FUEL INJECTION CONTOL SCREEN.  APPEARS TO BE A MANUFAC	TURING DEFECT.  BEECH SHOULD ISSUE A SERVICE BULLETIN FOR A ONE-TIME INSPECTION OF THE FUEL BOWL HOUSING.  PIECES ARE LA	RGE ENOUGH TO RESTRICT FUEL FLOW.  REMOVED FUEL SCREEN HOUSING, SENT TO FAA FOR INSPECTION.		1	L	7	1 	3O			 	3A15
1998091100064	19980911	00064	EU  	1998	9	11	98ZZZX3280       	1	19980729	G	3230	205624811	CLEVIS ROD END  		205624811   	MRCHTI	S205  	S20522R     	8120412	EU  										LT MLG CONTROL	FAILED          	D	S	A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	729WA	1701 				388				UPON LANDING, THE LT MLG CONTROL ASSY ROD END SHEARED CAUSING THE LT MAIN LANDING GEAR TO COLLAPSE.  THE DIAMETER OF THE	 THREADED PORTION OF THE ROD END APPEARS TO BE TOO SMALL FOR THE LOADS IMPOSED UPON IT.  IT SEEMS A LANDING GEAR CONTROL	 ASSY INCORPORATING A LARGER DIAMETER ROD END WOULD BE BETTER SUITED TO THIS INSTALLATION.				1	L	7	1 	3O				A9EU
1998091100065	19980911	00065	SO  	1998	9	11	98ZZZX3281       	2	19980813	G	7314	653359	DRIVE SHAFT     		6493689A2   	BEECH 	36    	B36TC       	1151609	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					FUEL PUMP	SEIZED          	B				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	07	3236Z	236  			J109610BR	EA526	809321R			ENGINE DRIVEN FUEL PUMP SEIZED AND SHEARED THE DRIVE SHAFT.  THE AIRCRAFT MADE A NORMAL LANDING AND ENGINE SHUT DOWN ON 	THE PARKING RAMP.  UPON ENGINE START-UP, THE SHAFT APPARENTLY SHEARED BECAUSE IT WOULD NOT CONTINUE RUNNING WITHOUT THE 	ELECTRIC BOOST PUMP RUNNING.				1	L	7	1 	3O	3	O		3A15    	E8CE
1998091100066	19980911	00066	EU  	1998	9	11	98ZZZX3282       	2	19980802	G	7414	996538	STATOR          	ROTAX       		DIAMON	DA20A1	DA20A1      	05626UX	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE IGNITION	SHORTED         	H				O				OTHER                   				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			WP	03	716LG					10096	4412532			ENGINE FAILURE DUE TO LOSS OF BOTH MAGNETOS. TWO WIRES FROM THE STATOR PROVIDING POWER FOR THE LEFT AND RIGHT INGITION S	YSTEMS SHORTED TOGETHER.  INSULATION WAS SOFT AND FAILED.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
1998091100067	19980911	00067	CE  	1998	9	11	98ZZZX3283       	1	19980821	G	5280	1241150207	SKIN            			CESSNA	210   	T210N       	2073456	CE  										LT MLG DOOR	DELAMINATED     	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	99	6048N					21062916				LEFT MAIN GEAR DOOR P/N 121150-207 DELAMINATED AND SKIN RIPPED OFF IN CRUISE FLIGHT HITTING THE LEFT SIDE OF HORIZONTAL 	STABILZER DENTING LEADING EDGE AND PUTTING A HOLE IN TOP OF HORIZONTAL STABILIZER.  ALL GEAR DOORS WERE REPLACED WITH SE	RVICEABLE DOOR AT TACH TIME OF 1,066.0, TTIS 1,577.0 ON 7-29-96.  THE RT DOOR HAD SPOT WELDS AROUND SKIN, LT WAS NOT SPO	T WELDED, LAMINATED TOGETHER ONLY.			1	H	7	1 	3O				3A21
1998091100069	19980911	00069	SO  	1998	9	11	98ZZZX3284       	2	19980724	G	8530		CYLINDER        			CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470R       	17026	SO  					ROCKER LUGS	BROKEN          	H	P			O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SW	99	52096	2689 	1412 			18052497	459698			ENGINE WAS AT CRUISE POWER. LOUD BANG.   SMALLER BANGS.  ENGINE RAN, BUT DID NOT PRODUCE APPRECIABLE POWER.  FORCED LAND	ING IN TUNDRA NEAR NOATAK, ALASKA FOLLOWED.  NO DAMAGE.  FOUND SUPPORT LUGS FOR EXHAUST VALVE ROCKER ARM FAILED ON NR 6 	CYLINDER.  INTAKE MANIFOLD WAS SEPARATED AT RUBBER COUPLING ON RT FWD SIDE OF ENGINE AND CROSS TUBE WAS BENT FORWARD AGA	INST COWLING ALLOWING ENGINE TO INTAKE OUTSIDE AIR.			1	H	7	1 	3O	3	O		5A6     	E273
1998091800369	19980918	00369	CE  	1998	9	18	98ZZZX3305       	1	19980628	G	3211	AN720A	BOLT            		07410017    	CESSNA	180   	180H        	2072618	CE  										LT MLG	MISSING         	G	S	A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	09	4803E	10350				18052033				AIRCRAFT EXPERIENCED A LEFT MAIN GEAR FAILURE SHORTLY AFTER LANDING.  INVESTIGATION DISCLOSED THAT THE LEFT MLG INBOARD 	BOLT P/N AN7-20-A W25 MISSING.  ALSO, THE BOLT HOLE WAS ELONGATED.  SUBMITTER RECOMMENDS SPECIAL EMPHASIS BE PLACED ON T	HIS AREA DURING INSPECTION.				1	H	7	1 	3O				5A6
1998091800371	19980918	00371	CE  	1998	9	18	98ZZZX3306       	1	19980807	G	2810	S21061	DRAIN VALVE     			CESSNA	182   	182G        	2072716	CE  										FUEL TANK	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2105R	27   				18255305				OWNER STATED ONE VALVE WOULD NOT OPEN AND A 'GREENISH STICKY' SUBSTANCE WAS FOU ND IN THE OTHER.  REPLACED BOTH WING TAN	K DRAIN VALVES.  CHECKED AND CLEANED ALL FUEL SYSTEM SCREENS AND FILTERS.  NO DEFECTS NOTED.  DRAINED 5 GALLONS FROM EAC	H TANK, NO DEBRIS NOTED.  EXAMINED VALVES, O-RINGS APPEARED TO HAVE DETERIORATED.  ALSO, POSSIBLE THAT SEALING COMPOUND 	FROM BLADDERS MAY HAVE BEEN THE CAUSE.  BOTH BLADDERS WERE REPLACED RECENTLY (1 NEW, 1 REBUILT).			1	H	7	1 	3O			NT	3A13
1998091800372	19980918	00372	EA  	1998	9	18	98ZZZX3307       	2	19980727	G	8520		BEARING         			GULSTM	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320E2G     	41508	EA  					ENGINE	SPUN            	G				A	B			UNSCHED LANDING         	EMER. DESCENT           			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	03	1931T	2400 				AA50744				AIRCRAFT HAD A LOSS OF POWER AND A LOSS OF OIL PRESSURE DURING NORMAL FLIGHT.  INSPECTION OF ENGINE AFTER EMERGENCY LAND	ING REVEALED A SPUN BEARING ON CRANKSHAFT AND THE NR 3 ROD WAS BROKEN.					1	L	7	1 	3O	3	O		A16EA   	E274
1998091800373	19980918	00373		1998	9	18	98ZZZX3308       	4	19980824	G	3418		DETECTOR        	SMITHSIND   																STALL	DAMAGED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09										TESTED OVERHAULED STALL DETECTOR PRIOR TO INSTALLATION IN AIRCRAFT.  STALL DETECTOR DID NOT MEET MAINTENANCE AND MANUAL 	PUBLISHED SPECIFICATIONS.  THESE UNITS ARE SENSITIVE TO SHOCK.  SUSPECT SHIPPING MAY HAVE CAUSED OUT OF LIMIT CONDITION.
1998091800374	19980918	00374	GL  	1998	9	18	98ZZZX3309       	3	19980812	G	6114		HUB             			CESSNA	188   	188B        	2073007	CE  						MCAULY	2A34C	D2A34C98    	GL  	NR 1 SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	FOGQE		694  					710994		EDDY CURRENT INSPECTION SHOWS A 350 M/A INDICATION IN NR 1 SOCKET IN 6TH THREAD TRAILING EDGE.						1	L	7	1 	3O				A9CE    		5	C	P3EA
1998091800375	19980918	00375		1998	9	18	98ZZZX3310       	4	19980820	G	2562	110317	ANTENNA         			CESSNA	150   	152         	2071835	CE  										FUSELAGE	SEPARATED       	D				O				OTHER                   				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			SW	09	772SA	20   				15284551				DURING ROUTINE PRE-FLIGHT INSPECTION, ANTENNA WAS FOUND BROKEN.  THE WHIP HAD COME DISCONNECTED FROM BASE DURING A PRIOR	 FLIGHT.  THE POTTING COMPOUND SECURING THE ANTENNA PARTS WAS SOFTENED AS LIKE PUTTY.  APPARENTLY, EITHER THE POTTING CO	MPOUND WAS IMPROPERLY MIXED, OR BECAME SOFT WITH HEAT FROM SUN.  SOME POTTING RESIDUE WAS STUCK TO SKIN AFT OF ANTENNA; 	POSSIBLY LEFT DURING SEPARATION.			1	H	7	1 	3O			NT	3A19
1998091800376	19980918	00376	EA  	1998	9	18	98ZZZX3311       	2	19980820	G	8520	67687	GEAR            			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					CRANKSHAFT	FRACTURED       	H	S	A		E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			SW	09	61SD		188  			3551	L125451A			ENGINE FAILED WITHOUT WARNING.  UPON INVESTIGATION, FOUND TIMING GEAR FRACTURED STOPPING THE MAGS.  SUBMITTER STATED SUP	PLIER REPORTED THEY HAVE HAD AT LEAST 5 OF THESE FAILURES IN THE LAST 5 YEARS.  THEY CANNOT COME UP WITH A REASON, THEY 	SAID POSSIBLY TIMING MAY BE SLIGHTLY OFF, TIMING ON THIS ENGINE WAS ON CENTER AND RAN VERY SMOOTH.  SUBMITTER SUGGESTED 	REPLACING THIS GEAR AT OVERHAUL WITH NEW.			1	G	7	1 	3O	3	O		2H3     	E279
1998091800377	19980918	00377	CE  	1998	9	18	98ZZZX3312       	1	19980813	G	5414	9598000190	SKIN            			BEECH 	95    	D95A        	1153408	CE  										RT NACELLE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	800CW	4685 				TD602				DURING A ROUTINE ANNUAL INSPECTION, THE LOWER AFT RT NACELLE SKIN WAS FOUND CHAFING INTO THE WING SKIN DIRECTLY AFT OF T	HE FORWARD LOWER SPAR CAP.  IT HAD ALSO CHAFED A LINE INTO THE SPAR CAP TO A DEPTH OF .008 INCH.  BEECHCRAFT TECHNICAL S	UPPORT WAS CONTACTED, ENGINEERING DEPT NOTIFIED AND REPAIRS MADE IAW THEIR RECOMMENDATIONS.  THIS DISCREPANCY WAS FOUND 	AFTER READING FAA AC 43-16A DATED JULY '98.			1	L	7	2 	3O				3A16
1998091800379	19980918	00379	EU  	1998	9	18	98ZZZX3314       	1	19980826	G	3211	PC531014	BRACKET         			RHNFLU	EA300 	EA300S      	1130864	EU  										MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9K	45   				022				SUBMITTER STATES LANDING GEAR BRACKETS HAVE HAD PROBLEMS CRACKING UNDER NORMAL USE.  WELDS HAVE A TENDENCY TO CRACK AND 	BREAK UNDER TENSION LOADS.  BRACKETS ARE A BAD DESIGN AND NEED TO BE RE-DESIGNED.  FOURTH OCCURRENCE WITH THIS PROBLEM.					1	M	7	1 	3O			NC	A67EU
1998091800380	19980918	00380	EU  	1998	9	18	98ZZZX3315       	1	19980826	G	3211	PC531011	BRACKET         			RHNFLU	EA300 	EA300S      	1130864	EU  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	9K	45   				022				SUBMITTER STATES LANDING GEAR BRACKETS HAVE HAD PROBLEMS CRACKING UNDER NORMAL USE.  WELDS HAVE A TENDENCY TO CRACK AND 	BREAK UNDER TENSION LOADS.  BRACKETS ARE A BAD DESIGN AND NEED TO BE RE-DESIGNED.  FOURTH OCCURRENCE WITH THIS PROBLEM.					1	M	7	1 	3O			NC	A67EU
1998091800381	19980918	00381	CE  	1998	9	18	98ZZZX3316       	1	19980820	G	2120	11728888	VENTS           			BEECH 	23    	B19         	1151215	CE  										FUSELAGE	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	6560R	2796 				MB722				THE FRESH AIR DUCTING (P/N 111728-888) THAT SUPPLIES AIR TO THE REAR SEATS WAS ORIGINAL AND IN A TOTALLY UNUSABLE CONDIT	ION.  THE DUCTING COMES OUT OF THE FLOOR AT STA 133 AND RUNS UP THE SIDE OF THE DOOR FRAMES ON BOTH SIDES TO THE OUTLETS	 IN THE HEADLINER.  WHERE THE STEEL WIRE IN THE DUCTING TOUCHED STRUCTURAL PARTS, IN THIS AREA, IT CAUSED DISSIMILAR MET	AL (ELECTROLYSIS) CORROSION.  THESE PARTS WERE DESTROYED MAKING REPLACEMENT NECESSARY.  SUBMITTER RECOMMENDATIONS: CAREF	ULLY INSPECT THE ROUTING OF THIS DUCTING AND REPLACE IT WHEN IT SHOWS ANY SIGN OF DETERIORATION.		1	L	7	1 	3O				A1CE
1998091800382	19980918	00382	CE  	1998	9	18	98ZZZX3317       	1	19980820	G	2120		DUCTING         			CESSNA	210   	T210M       	2073451	CE  										FUSELAGE	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	732VH	3018 				21061805				IN THE FLOOR OF THE AIRCRAFT, A FRESH AIR DUCT WAS TOUCHING A BRAKE LINE.  IT CAUSED DISSIMILAR METAL CORROSION TO FORM 	ON THE BRAKE LINE WHICH THEN LEAKED.					1	H	7	1 	3O				3A21
1998091800383	19980918	00383	GL  	1998	9	18	98ZZZX3318       	3	19980805	G	6114		HUB             			CESSNA	210   	210L        	2073448	CE  						MCAULY	3A32C	D3A32C88    	GL  	NR 2 SOCKET	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	732BL					21061386		737282		EDDY CURRENT INSPECTION SHOWS 300 M/A DROP IN SOCKET NR 2, 7TH THREAD DOWN AT 6:30.  EXCEEDS SPECIFICATIONS.						1	H	7	1 	3O				3A21    		5	C	P21EA
1998091800384	19980918	00384	NE  	1998	9	18	98ZZZX3320       	2	19980806	G	7250	500200401	BLADE           								PWA   	JT8   	JT8D217A    	52053	NE  					ENGINE	FRACTURED       	B			RA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05							P709855			ENGINE REMOVED FROM SERVICE FOR 'METAL IN THE TAILPIPE'.  DISASSEMBLY OF THE ENGINE REVEALED A FRACTURED 4TH STAGE COMPR	ESSOR BLADE.   CAUSE OF FAILURE IS UNDER INVESTIGATION AT GEES.										4	F			E9NE
1998091800385	19980918	00385	CE  	1998	9	18	98ZZZX3321       	1	19980827	G	3244	AH52339	TIRE            			RAYTHN	DH125 	HAWKER800XP 		CE  										NLG	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1102U				US097	258343				RUBBER IS BULGED BETWEEN PLYS APPROXIMATELY 1 INCH BY 3 INCH ON INNER SIDEWALL.  AIRCRAFT IS NEW, 25 HOURS WITH 12 LANDI	NGS.					2	L	7	2 	4F			RT	A3EU
1998091800386	19980918	00386	NE  	1998	9	18	98ZZZX3322       	3	19980112	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8437 	4603 		1493NR			HJ30A		FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TWO CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998091800387	19980918	00387	NE  	1998	9	18	98ZZZX3323       	3	19980217	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4748 			3749NR			HJ437		FOUND FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TWO CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998091800388	19980918	00388	NE  	1998	9	18	98ZZZX3324       	3	19980209	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4642 			2944NR			HJ529		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  THREE CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998091800389	19980918	00389	CE  	1998	9	18	98ZZZX3325       	1	19980726	G	3246	184F08	WHEEL           			CESSNA	500   	550         	2076604	CE  										NLG	OUT OF BALANCE  	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	2GG					5500286				AIRCRAFT EXPERIENCED VIBRATION ON ROTATION.  AIRCRAFT RETURNED TO BASE AND FOUND LOOSE BALANCE PATCH IN NOSE TIRE.  SEE 	PAGE 4 OF AUGUST '98 ALERTS FOR SIMILAR INCIDENTS.					1	L	7	2 	4F				A22CE
1998091800390	19980918	00390	CE  	1998	9	18	98ZZZX3326       	1	19980827	G	2131	214C40257	SENSOR          			RAYTHN	DH125 	HAWKER800XP 		CE  										CABIN	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	23207				U04857	258350				CABIN PRESSURE SENSOR COMES ON EARLY.  AIRCRAFT NEW, 24.4 HOURS.						2	L	7	2 	4F			RT	A3EU
1998091800392	19980918	00392	CE  	1998	9	18	98ZZZX3328       	1	19980827	G	5321	256FC1455	PANEL           			RAYTHN	DH125 	HAWKER800XP 		CE  										CABIN	DELAMINATED     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2321V					258353				FLOOR PANEL DELAMINATED, LEFT SIDE OF AIRCRAFT.  AIRCRAFT IS NEW.  TT:  25 HOURS.						2	L	7	2 	4F			RT	A3EU
1998091800393	19980918	00393	CE  	1998	9	18	98ZZZX3329       	1	19980827	G	5321	25FC174711	PANEL           			RAYTHN	DH125 	HAWKER800XP 		CE  										CABIN	DELAMINATED     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	2321V					258353				FLOOR PANEL DELAMINATED AT FORWARD LEFT QUARTER.  AIRCRAFT TT:  25 HOURS.  THIS IS A NEW AIRCRAFT.						2	L	7	2 	4F			RT	A3EU
1998091800394	19980918	00394	EU  	1998	9	18	98ZZZX3330       	1	19980818	G	3411	257SF20735A	PITOT DRAIN     			BRAERO	DH125 	BAE125800A  	1500285	EU  										COCKPIT	CHAFED          	B	P		JGVR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	09	330X	4563 				258060				A FLIGHT CONTROL CABLE RUBBED A HOLE IN A PITOT DRAIN LINE (P/N 257SF20735A) THAT CONNECTS TO A PITOT DRAIN VALVE.  THIS	 LINE IS LOCATED UNDER THE COPILOT SEAT AREA.  ATTENTION SHOULD BE GIVEN TO THIS AREA DURING INSPECTION TO ENSURE CABLE 	CLEARANCES.				2	L	7	2 	4F			RT	A3EU
1998091800395	19980918	00395	NE  	1998	9	18	98ZZZX3331       	2	19980826	G	7230	310370101	BLADE           			BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	444MF		689  			LA81	PCE92218			ENGINE RECEIVED FOR SUSPECTED COMPRESSOR TURBINE BLADE FAILURE.  UPON INSPECTION, ONE OR MORE CT BLADES WERE FOUND TO HA	VE FAILED.  ENGINE TOTAL TIME 4,827.5 HOURS.  TIME SINCE OVERHAUL 689 HOURS.					1	L	7	2 	4T	4	T		A31CE   	E4EA
1998091800396	19980918	00396	EA  	1998	9	18	98ZZZX3332       	1	19980818	G	7331		TRANSMITTER     			CNDAIR	CL600 	CL6002B16   	1900305	EA  										NR 2 ENGINE	FOD             	C				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			SW	05	700KC					5017				AIRCRAFT WAS CLIMBING THROUGH 27,000 FEET WHEN THE NR 2 FUEL FLOW INDICATION FAILED.  TEN MINUTES LATER IN CRUISE FLIGHT	 AT 33,000 FEET OVER MCALESTER, OK (MLC), THE NR 2 ENGINE SHUT DOWN.  ACFT RETURNED TO DALLAS (DAL).  TROUBLESHOOTING FO	UND YELLOW PLASTIC IN THE NR 2 FUEL FLOW TRANSMITTER.  FURTHER INVESTIGATION, FOUND RIM OF A PLASTIC CAP UNDER THE SEAL 	OF THE INTAKE ON THE NR 2 FUEL PUMP.  IT APPEARS THE CAP WAS NOT REMOVED WHEN THE PUMP WAS INSTALLED AT HOT SECTION 170 	HRS EARLIER.  THE PLUG PART OF THE CAP RIPPED OFF AND WENT THROUGH THE FUEL PUMP, WAS GROUND-UP AND PUMPED DOWN STREAM A	ND TRAPPED IN FUEL FLOW XMITTER SHUTTING OFF FUEL TO THE ENGINE.	2	L	7	2 	4F			RT	A21EA
1998091800397	19980918	00397	CE  	1998	9	18	98ZZZX3333       	1	19980826	G	3246	9561071	WHEEL RIM       			RKWELL	NA265 	NA26580     	7630108	CE  										MLG	DAMAGED         	B			SE2R	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	03	7148J				JUN78864	38033				AFTER AIRCRAFT TAXIED TO PARKING, THE TIRE WAS FOUND FLAT.  INSPECTION DISCOVERED THE INBOARD SIDE OF RIM BROKEN.  THE M	ISSING PART WAS FOUND ON THE TAXIWAY.  THE RIM/TIRE ASSY WAS INSTALLED ON THE AIRCRAFT ON 5-29-98.					2	L	7	2 	4F				A2WE
1998091800398	19980918	00398	CE  	1998	9	18	98ZZZX3334       	1	19980801	G	5610	10138402516	WINDSCREEN      			BEECH 	B300  	B300        	1159232	CE  										COCKPIT	FAILED          	B			HY1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	733NM	1502 			92352H2916	FL104				DURING A ROUTINE FLIGHT, THE INSIDE PANE OF THE WINDSHIELD SHATTERED.  THE AIRCRAFT LANDED WITHOUT INCIDENT, AND THE WIN	DSHIELD WAS REPLACED.  THERE WERE NO NOTED DEFECTS IN THE WINDSHIELD PRIOR TO THE FLIGHT (ONLY THE INSIDE PANE SHATTERED	).				2	L	7	2 	4T			RT	A24CE
1998091800399	19980918	00399	CE  	1998	9	18	98ZZZX3335       	1	19980801	G	3244	265F864	TIRE            	GOODYEAR    		BEECH 	B300  	B300        	1159232	CE  										NLG	OUT OF BALANCE  	B			HY1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	733NM	55   			61140872	FL104				PILOT NOTICED VIBRATION IN NOSE OF AIRCRAFT FROM TAKEOFF UNTIL LANDING GEAR RETRACTION.  UPON INSPECTION OF NOSE WHEEL A	ND TIRE ASSEMBLY WHICH INCLUDED DISASSEMBLY, FOUND THE BALANCE PATCH THAT IS GLUED TO THE INSIDE OF THE TIRE HAD COME LO	OSE AND WAS SLIDING AROUND.  INSTALLATION OF NEW TIRE STOPPED VIBRATION.  THE TIRE WAS A GOODYEAR FLIGHT CUSTOM II 22X.7	5-10 8 PR.			2	L	7	2 	4T			RT	A24CE
1998091800401	19980918	00401	WP  	1998	9	18	98ZZZX3337       	1	19980624	G	6230	269A5473	BOOT            			HUGHES	269   	269*        	       	WP  										M/R	UNBONDED        	B			PN5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03										DURING INCOMING PARTS INSPECTION, A DEFECT WAS FOUND INSIDE OF BOOT AT ONE OF THE MOLDING SEAMS.  THE RUBBER WAS NOT BON	DED COMPLETELY AND THIS MAKES A WEAK SPOT WHICH WILL SPLIT WHEN BOOT IS INSTALLED.					1	G	7	1 	3O			 	4H12
1998091800402	19980918	00402	NE  	1998	9	18	98ZZZX3338       	1	19980824	G	3240	7025001004101	PIN             			SKRSKY	S76   	S76C        	8143008	NE  										PARKING BRAKE	SEPARATED       	B		A	JZBR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	165ML		174  		3462	760471				ROLL PIN SEPARATED FROM THE ARM THAT IS A PART OF THE BRAKE VALVE ASSY.  THE ROLL PIN ACTIVATES A MICROSWITCH THAT OPERA	TES THE PACKING BRAKE LIGHT.  IF THE PIN SEPARATES FROM THE ARM, PARKING BRAKE INDICATOR LIGHT STAYS ILLUMINATED.  SUBMI	TTER STATES THIS IS THE THIRD TIME THIS VALVE HAS BEEN REPLACED FOR THE SAME DISCREPANCY WITHIN EIGHT MONTHS.				1	G	7	2 	3U			NC	H1NE
1998091800403	19980918	00403	WP  	1998	9	18	98ZZZX3339       	1	19980801	G	6210	369A1100503	BLADE           			HUGHES	369   	369HS       	4470728	WP  										MAIN ROTOR	CRACKED         	D	P	A		O				OTHER                   				E			VIBRATION/BUFFET          			LD	LANDING        	1			WP	27	4467V	1106 			0850	1203635				HELICOPTER INBOUND FOR LANDING WHEN PILOT NOTICED VIBRATION, MADE NORMAL LANDING.  MAINT EXAM OF ROTOR SYS FOUND YELLOW 	BLADE CRACKED FROM TRAILING EDGE OF BLADE, BOTH TOP AND BOTTOM TO MAIN SPAR.  CRACK LOCATED AT BLADE STA 71 OR 19.3750 I	NCHES FROM END OF ADJUSTABLE TAB.  CRACK BEGAN AT T/E WITH A NICK ABOUT .0312 INCH AND FOLLOWED CRACKS THROUGH BOTH SIDE	S.  ALSO ALONG THE CRACKS WAS A DENT FROM UNKNOWN CAUSES.   ACFT HAD GONE THROUGH 100-HOUR INSP LESS THAN 6 HRS BEFORE T	HIS  MALFUNCTION AND NO DAMAGE OR CRACKING  DETECTED.  CAUSE OF CRACK UNKNOWN.  ADVISE ATTEN TO ROTOR SYS ON PRE-FLIGHT 	AND POST-FLIGHT INSP.  NEW BLADE INSTALLED, AND TRACKED PER CHAP 7 OF MDHC MM.  INSPECTED OTHER BLADES, NO DAMAGE OR NIC	1	G	7	1 	3U				H3WE
1998091800404	19980918	00404	WP  	1998	9	18	98ZZZX3340       	1	19980801	G	2520	AJC75101	PANEL           			DOUG  	DC10  	DC1030      	3023501	WP  										CABIN	DAMAGED         	B			R1XR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	05										SUSPECT PANEL, DURING RECEIVING, WAS NOTED FOR A CORNER BEING KNOCKED IN.  APPROXIMATELY A 1 INCH SQUARED AREA PUSHED CO	MPLETELY IN.  BELIEVE THIS PANEL WAS DROPPED CAUSING THE DAMAGE.  DC10 SRM 52-10-01 HAS THE REQUIRED REPAIR.					2	L	7	3 	4F				A22WE
1998091800405	19980918	00405	CE  	1998	9	18	98ZZZX3341       	1	19980805	G	5754	2651700301	SLAT            			RKWELL	NA265 	NA26580     	7630108	CE  										LT WING	SEPARATED       	H				O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			NM	08	773W				75006	38020				ON POST-FLIGHT INSPECTION, LT INBD SLAT WAS DISCOVERED MISSING (38) RIVETS ON THE UNDERSIDE AND BOTH INBD RIBS CRACKED A	ND BROKEN, HOLES VERY ELONGATED.  ALSO, WING LEADING EDGE SKIN IMMEDIATELY AFT, MISSING (5) RIVETS, RIBS CRACKED (OLD CR	ACKS).  1ST STAGE COMPRESSOR BLADES (16) AND (2) FAN BUCKETS FOD DAMAGED.  (2) TOP MOUNT BUSHINGS HAD BEEN REPLACED 42 H	RS PRIOR AT THE ISO HR INSP ON THIS SLAT PRIOR TO WEAR.  RIBS ALL MADE FROM .020 INCH MATERIAL.			2	L	7	2 	4F				A2WE
1998091800783	19980918	00783	NE  	1998	9	18	98ZZZX3342       	2	19980806	G	7230	419403	BEARING         			SKRSKY	S64   	S64F        		NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					NR 2 ENGINE	DAMAGED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	157AC	1449 				64065	672498			BEARING REMOVED FROM AN ENGINE DURING REPAIR WITH A TOTAL BEARING TIME OF 1,449.4 HOURS WITH NO PREVIOUS OVERHAULS.  NO 	OTHER BEARING IN THE ENGINE WAS DISCREPANT.  DURING OVERHAUL, THE BEARING WAS INSPECTED AND ONE UNUSUAL CONDITION WAS FO	UND:  THE BALLS EXHIBITED SEVERE SCRATCHES.  THIS IS THE SECOND BEARING EXHIBITING A MANUFACTURING DEFECT WHICH CAUSES S	URFACE DAMAGE TO THE BEARING BALLS.  A PREVIOUS MDR WAS SUBMITTED ON 9-30-97 ON THE SAME PART NUMBER.  THE PREVIOUS BEAR	ING WAS ANALYZED AND A MANUFACTURING DEFECT WAS CONFIRMED.		2	G	7	2 	4U	4	U		H6EA    	E15EA
1998091800784	19980918	00784	SW  	1998	9	18	98ZZZX3343       	1	19980622	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										M/R	DELAMINATED     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	2443 			A401	53054				FIFTY HOUR INSPECTION FOUND M/R BLADE POTTING COMPOUND DELAMINATION AT OUTBOARD WEIGHT POCKET.						1	G	7	1 	3U			O	H2SW
1998091800785	19980918	00785	SW  	1998	9	18	98ZZZX3344       	1	19980622	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										M/R	DELAMINATED     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	2443 			A365	53054				FIFTY HOUR PHASE INSPECTION FOUND M/R BLADE POTTING COMPOUND DELAMINATING AT OUTBOARD WEIGHT POCKET.						1	G	7	1 	3U			O	H2SW
1998091800786	19980918	00786	SW  	1998	9	18	98ZZZX3345       	1	19980622	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										M/R	DELAMINATION    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	2443 			A358	53054				FIFTY HOUR INPSECTION FOUND M/R BLADE PTTING COMPOUND DELAMINATION AT OUTBOARD WEIGHT POCKET.						1	G	7	1 	3U			O	H2SW
1998091800787	19980918	00787	SW  	1998	9	18	98ZZZX3346       	1	19980622	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										M/R	DELAMINATED     	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	2443 			A393	53054				FIFTY HOUR INSPECTION FOUND M/R BLADE POTTING COMPOUND DELAMINATED AT OUTBOARD WEIGHT POCKET.						1	G	7	1 	3U			O	H2SW
1998091800788	19980918	00788	SW  	1998	9	18	98ZZZX3347       	1	19980606	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL					53141				DURING PHASE INSPECTION AND C/W AD 97-24-17, 25-HOUR INSPECTION FOUND CRACKED DISK (9TH) FACING AFT.						1	G	7	1 	3U			O	H2SW
1998091800789	19980918	00789	SW  	1998	9	18	98ZZZX3348       	1	19980610	G	6210		BLADE           			BELL  	206   	206B        	1181511	SW  										M/R BLADE SPAR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3912Q	1365 			A3199	3271				MAJOR INSPECTION FOUND INTERGRANULAR CORROSION ON TIP END OF BLADE SPAR.						1	G	7	1 	3U				H2SW
1998091800790	19980918	00790	SW  	1998	9	18	98ZZZX3349       	1	19980702	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	268  				53107				SCHEDULED INSPECTION FOUND DISC COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800791	19980918	00791	SW  	1998	9	18	98ZZZX3350       	1	19980702	G	6510	407040303105A	BEARING         			BELL  	407   	407         		SW  										T/R	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437AL	1037 				53141				SCHEDULED INSPECTION FOUND NR 2 DRIVE SHAFT BEARING ROUGH AND NOISY.						1	G	7	1 	3U			O	H2SW
1998091800792	19980918	00792	SW  	1998	9	18	98ZZZX3351       	1	19980702	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427AL	65   				53107				SCHEDULED INSPECTION FOUND CORROSION AND COUPLING (PACK) SEPARATED WHEN BOLTS ARE TORQUED.						1	G	7	1 	3U			O	H2SW
1998091800793	19980918	00793	SW  	1998	9	18	98ZZZX3352       	1	19980702	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL	89   				53054				SCHEUDLED INSPECTION FOUND DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800794	19980918	00794	SW  	1998	9	18	98ZZZX3353       	1	19980702	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	547AL	143  				53240				SCHEDULED INSPECTION FOUND NR 7 SHAFT DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800795	19980918	00795	SW  	1998	9	18	98ZZZX3354       	1	19980702	G	6510	206040340101	DISC            			BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	547AL	171  				53240				SCHEDULED INSPECTION FOUND DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800796	19980918	00796	SW  	1998	9	18	98ZZZX3355       	1	19980702	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	443  				53203				SCHEDULED INSPECTION FOUND T/R DISC PACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800797	19980918	00797	GL  	1998	9	18	98ZZZX3356       	2	19980807	G	7210	6893673	GEAR            		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457AL	1835 			NN145141	53151	CAE847048			ENGINE REMOVED FOR EXCESSIVE METAL ON BOTH PLUGS.  DISASSEMBLED AND FOUND T/M GEAR TO PINION GEAR GALLING CAUSING METAL 	CONTAMINATION.  SUBMITTER STATES IMPROPER MESHING BETWEEN T/M GEAR AND PINION GEAR WAS CAUSE FOR GALLING.  SECONDARY DAM	AGE - PINION GEAR P/N 6893672 S/N NN76130, TT: 1,834.7 HOURS.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998091800798	19980918	00798	NE  	1998	9	18	98ZZZX3357       	1	19980727	G	5330	7620203001138	SKIN            			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547N					760088				CRACK DISCOVERED ON SERVICE CHECK INSPECTION OF AIRCRAFT.  DISCOVERED CRACK ON RT SIDE OF ROOF AT AREA OF HYDRAULIC ACCE	SS DOOR.  REMOVED PASSENGER OVEHREAD TRIM AND FOUND BEAM AND CAP ANGLE CRACKED UNDERNEATH ROOF SKIN CRACK.					1	G	7	2 	3U				H1NE
1998091800799	19980918	00799	GL  	1998	9	18	98ZZZX3358       	2	19980728	G	7321	2537576	DRIVE BODY      	BENDIX      	252464492   	AEROSP	AS355 	AS355F1     	8680810	EU  	ALLSN 	250C  	250C20      	03013	GL  					FUEL CONTROL	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	376E	5618 	1062 		321550	5213				DURING DISASSEMBLY OF FUEL CONTROL FOR REPAIR, FOUND DRIVE BODY CRACKED.						1	G	7	2 	3U	3	U		H11EU   	E4CE
1998091800800	19980918	00800	GL  	1998	9	18	98ZZZX3359       	2	19980724	G	7532	MS200730317	BOLTS           		23005366    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					BLEED VALVE	LOSE            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	567AL	395  			FF58447	53246				PRIOR TO INSTALLING BLEED VALVE ON TEST BENCH, AN INSPECTION OF ALL SAFETIES WAS ACCOMPLISHED AND FOUND 3 EACH BOLTS WER	E SAFTIED BUT LOOSE.  THESE BOLTS WERE IMPROPERLY TORQUED AND CAUSED A MAJOR AIR LEAK AT SPLIT LINES OF BLEED VALVE.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998091800801	19980918	00801	GL  	1998	9	18	98ZZZX3360       	2	19980702	G	7250	23032328	SEAL            		23063354    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					NR 5 BEARING	FAILED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	850  			CAT44316	53203	CAE847197			ENGINE WAS REMOVED FOR MAKING METAL.  REMOVED NR 5 BEARING AND FOUND METAL IN BEARING CAVITY.  REMOVED NR 5 BEARING FOR 	INSPECTION AND FOUND METAL SLIVERS UNDER NR 5 BEARING NUT AND CAP LOCK WASHER.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998091800802	19980918	00802	GL  	1998	9	18	98ZZZX3361       	2	19980616	G	7322	2537576	DRIVE BODY      	BENDIX      	252464429   	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20      	03013	GL  					FUEL CONTROL	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	90761	11299	2470 		319312	S160	CAE821438F			DURING OVERHAUL (2,500 HOUR), FOUND FUEL CONTROL WITH A CRACKED MAIN DRIVE BODY.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998091800803	19980918	00803	GL  	1998	9	18	98ZZZX3362       	2	19980724	G	7532	MS200760317	BOLT            		23005366    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					BLEED VALVE	LOOSE           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	547AL	664  			FF57529	53240	847258			BLEED VALVE WAS SET UP ON TEST BENCH AND A RE-ALIGNMENT OF 90 DEGREE ELBOW WAS NEEDED TO INSTALL TEST ORIFICE AND JUMPER	 TUBE AND NOTICED THAT UPON SLIGHT TENSION, BOLT WHICH WAS SAFTIED, MOVED.  THESE BOLTS HAVE A 30 TO 35 INCH/POUND TORQU	E ATTACHED AND UPON FAILURE FOR TORQUING CORRECTLY, THIS CAUSES EXCESSIVE AIR LEAKAGE ON LEAK TEST.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998091800804	19980918	00804	SW  	1998	9	18	98ZZZX3363       	1	19980807	G	6320		INSERT          		23063393    	BELL  	407   	407         		SW  										GEARBOX	LOOSE           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457AL	1835 			CAG47047	53151				UPON VISUAL INSPECTION OF ALL PARTS, FOUND 1 EACH INSERT PULLED OUT AND 2 EACH INSERTS LOOSE AT EXCITER BOX MATING SURFA	CE ON GEARBOX HOUSING.  ONE EACH INSERT P/N NAS1394-3L PULLED OUT AND 2 EACH INSERTS LOOSE.  POSSIBLY CAUSED BY EXCESSIV	E CLEARANCE BETWEEN EXCITER BOX AND GEARBOX CAUSING BOX TO GET HUNG UP OR HIT ON ENGINE REMOVAL.				1	G	7	1 	3U			O	H2SW
1998091800805	19980918	00805	SW  	1998	9	18	98ZZZX3364       	1	19980811	G	2430		RELAY           			BELL  	206   	206L3       	1182108	SW  										DC SYSTEM	MALFUNCTIONED   	B			ZV1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2616	272  				51418				UNIT STAYED ON WITH SWITCH OFF CAUSING OVERHEATING.						1	G	7	1 	3U				H2SW
1998091800806	19980918	00806	SW  	1998	9	18	98ZZZX3365       	1	19980723	G	7931		INDICATOR       		0211        	BELL  	407   	407         		SW  										COCKPIT	FAILED          	B			C8LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AA	785  				53167				DURING GROUND RUN AFTER ANNUAL INSPECTION, ENGINE OIL PRESSURE GAUGE WENT FROM A NORMAL INDICATION TO ZERO.  TROUBLESHOO	TING THE PROBLEM, FOUND ENGINE OIL PRESSURE INDICATOR FAILED.  REMOVED FAULTY INDICATOR AND INSTALLED NEW INDICATOR.  FU	NCTIONAL CHECK OK.				1	G	7	1 	3U			O	H2SW
1998091800807	19980918	00807	SW  	1998	9	18	98ZZZX3366       	1	19980717	G	5530		VERTICAL FIN    			BELL  	407   	407         		SW  										TAILBOOM	DAMAGED         	B			C8LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	973AA	785  			BP2113	53167				DURING C/W ASB 407-98-17, THE VERTICAL FIN WAS FOUND DAMAGED BEYOND THE MAXIMUM LIMIT.  ACTUAL DEPTH IS APPROXIMATE DEPT	H OF .027 INCH.  REPLACED FIN WITH NEW FIN P/N 206-020-113-255A S/N BP-2653.					1	G	7	1 	3U			O	H2SW
1998091800808	19980918	00808	SW  	1998	9	18	98ZZZX3367       	1	19980807	G	6320		INSERTS         		23063393    	BELL  	407   	407         		SW  										GEARBOX	LOOSE           	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	1164 				53044				UPON VISUAL INSPECTION OF PARTS, FOUND 1 EACH INSERT PULLED OUT OF GEARBOX HOUSING AND 2 EACH INSERTS LOOSE AT EXCITER B	OX MATING SURFACE.  ONE EACH INSERT P/N NAS1394-3L WAS PULLED OUT AND 2 EACH INSERTS WERE FOUND LOOSE.  POSSIBLE CAUSE I	S EXCESSIVE CLEARANCE BETWEEN BOX AND HOUSING CAUSING BOX TO GET HUNG UP OR HIT ON ENGINE REMOVAL.				1	G	7	1 	3U			O	H2SW
1998091800809	19980918	00809	SW  	1998	9	18	98ZZZX3368       	1	19980811	G	6220	407010103101	HORN            		407010100103	BELL  	407   	407         		SW  										M/R HUB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2452 			A259	53044				AT 2,500 HOUR OVERHAUL OF M/R HUB, DISCOVERED 1 EACH PITCH HORN CORRODED BEYOND LIMITS UNDER PLATE, 3 EACH PITCH HORNS C	ORRODED BEYOND LIMITS IN DOWEL PIN BORE.					1	G	7	1 	3U			O	H2SW
1998091800810	19980918	00810	SW  	1998	9	18	98ZZZX3369       	1	19980811	G	6220	407010103101	HORN            		407010100103	BELL  	407   	407         		SW  										M/R HUB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2452 			A263	53044				AT 2,500 HOUR OVERHAUL OF M/R HUB, DISCOVERED 1 EACH PITCH HORN CORRODED BEYOND LIMITS UNDER PLATE, 3 EACH PITCH HORNS C	ORRODED BEYOND LIMITS IN DOWEL PIN BORE.					1	G	7	1 	3U			O	H2SW
1998012900106	19980129	00106	NE  	1998	1	29	98ZZZX337        	3	19980115	G	6114	B468	FORK SPACER     		E3932       	BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER HUB	SEPARATED       	B			SJ3R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	05			1090 					HJ500		ONE OF FOUR B-468 FORK SPACERS SEPARATED FROM THE D495 FORK AND WAS FLOATING FREELY INSIDE THE HUB CAVITY CAUSING A RATT	LING SOUND.  SIGNIFICANT DAMAGE INCURRED TO THE FORWARD AND AFT HALVES OF THE INTERIOR CENTRAL WEB AREA OF THE PROPELLER	 HUB.  SUSPECT CAUSE OF FAILIURE IS B-468 IS TOO HARD AND BRITTLE.  CALL OUT FOR HARDNESS IS ROCKWELL 33-37 RC.  SUBJECT	 PIECE TESTS AT 44.9 RC.			2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998091800811	19980918	00811	SW  	1998	9	18	98ZZZX3370       	1	19980811	G	6220	407010103101	HORN            		407010100103	BELL  	407   	407         		SW  										M/R HUB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2452 			A257	53044				AT 2,500 HOUR OVERHAUL OF M/R HUB, DISCOVERED 1 EACH PITCH HORN CORRODED BEYOND LIMITS UNDER PLATE, 3 EACH PITCH HORNS C	ORRODED BEYOND LIMITS IN DOWEL PIN BORE.					1	G	7	1 	3U			O	H2SW
1998091800812	19980918	00812	SW  	1998	9	18	98ZZZX3371       	1	19980811	G	6220	407010103101	HORN            		407010100103	BELL  	407   	407         		SW  										M/R HUB	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL	2452 			A258	53044				AT 2,500 HOUR OVERHAUL OF M/R HUB, DISCOVERED 1 EACH PITCH HORN CORRODED BEYOND LIMITS UNDER PLATE, 3 EACH PITCH HORNS C	ORRODED BEYOND LIMITS IN DOWEL PIN BORE.					1	G	7	1 	3U			O	H2SW
1998012900107	19980129	00107	CE  	1998	1	29	98ZZZX338        	1	19980109	G	3244	65X10	TIRE            			BEECH 	90    	E90         	1152914	CE  										NLG	IMBALANCE       	D				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	07	228RA	66   				LW197				TIRE SUDDENLY BECAME UNBALANCED DUE TO THE RUBBER BALANCE PATCH ON THE INTERIOR BECOMING DETACHED.  SUBMITTER STATED MAN	UFACTURER'S DEFECT.  92 LANDINGS, 1.8 MONTHS IN SERVICE.  NORMAL OPERATING CONDITIONS.					1	L	7	2 	3T				3A20
1998091800831	19980918	00831	NM  	1998	9	18	98ZZZX3390       	1	19980812	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 1006	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	59SW	61079				21811				EIGHT EACH FASTENER HOLES CRACKED IN THE FUSELAGE SKIN AT STA 1006, STR 14L.  REPAIRED PER DALFORD AEROSPACE, L.P. XEA X	2-53-214, REV 1 DATED 7-29-98 AND 737 SRM 53-30-3 FIGURE 42.					2	L	7	2 	4F				A16WE
1998092500180	19980925	00180	SW  	1998	9	25	98ZZZX3408       	1	19980203	G	6220		FITTING         			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	206MY					51514				STRAP FITTING STRAP PIN HOLE EXCEEDS MAXIMUM DIMENSION OF 0.8755 INCH, RECORDED DIMENSION IS 0.8757 INCH - 0.8758 INCH P	ER BHT 206L.					1	G	7	1 	3U			 	H2SW
1998092500181	19980925	00181	SW  	1998	9	25	98ZZZX3409       	1	19980720	G	5312		BULKHEAD        			BELL  	206   	206B        	1181511	SW  										FUSELAGE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	181AA	1778 				3277				BULKHEAD WAS CRACKED AT THE LT UPPER CORNER AT THE T/R GEARBOX ATTACHMENT POINT THROUGH THE UPPER ADJACENT RIVET HOLE AN	D BACK THROUGH THE BULKHEAD RADIUS RE-CONNECTING WITH ANOTHER CRACK PROGRESSING FROM THE ATTACHMENT POINT HOLE FORWARD T	OWARD THE TOP RADIUS OF THE PART.  DURING THE REPAIR OF THE BULKHEAD, DISCOVERED THE UPPER T/R BELLCRANK SUPPORT PLATE W	AS LOOSE.  FURTHER INVESTIGATION REVEALED THE RIVETS SECURING THE PLATE WERE LOOSE, THE WORKING RIVETS WERE REPLACED.			1	G	7	1 	3U				H2SW
1998092500182	19980925	00182	SW  	1998	9	25	98ZZZX3410       	1	19980702	G	5312		BULKHEAD        			BELL  	206   	206B        	1181511	SW  										FUSELAGE	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	181AA					3277				BULKHEAD WOULD NOT FIT, OUTSIDE DIMENSION ON THE TWO UPPER OUTSIDE EDGES IS LARGER THAN THE ORIGINAL PART CAUSING MISALI	GNMENT OF THE UPPER PLATE.  INSTALLED NEW PART.					1	G	7	1 	3U			 	H2SW
1998092500183	19980925	00183	SO  	1998	9	25	98ZZZX3411       	1	19980801	G	5711		SPAR            			PIPER 	PA28  	PA28140     	7102802	SO  										LT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	95388					2825910				FOUND EXFOLIATION BLISTER ON LT WING SPAR ON LOWER REAR FLANGE OF I-BEAM SPAR; ABOUT 6 INCHES TO 8 INCHES OUTBOARD OF FU	SELAGE OR JUST INBOARD OF WS 37.2.  CORROSION WAS ABOUT 8 INCHES LONG AND COVERED WIDTH OF FLANGE.  THE CRACKED APPEARAN	CE WAS ACTUALLY LAYERS OF CORRROSION IN THE METAL.  SB 789A HAS BEEN C/W TO PROVIDE INSPECTION PLATE AFT OF SPAR.  DAMAG	E COULD NOT BE SEEN OTHERWISE.  RECOMMEND SB 789A BECOME AD TO INSTALL INSPECTION PLATES.			1	L	7	1 	3O				2A13
1998092500184	19980925	00184	CE  	1998	9	25	98ZZZX3412       	1	19980801	G	3211	0541153	BOLT            		0541121     	CESSNA	172   	172I        	2072426	CE  										MLG	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	35513					17256807				THE FORWARD NUT BROKE OFF ON THE LANDING GEAR U-BOLT WHICH CAUSED THE OUTER LANDING GEAR SUPPORT BRACKET TO CRACK.  THIS	 IS A RENTAL AIRPLANE AND NO ONE REPORTED A HARD LANDING OR ANYTHING ELSE (BOTH SIDES BROKE; LT BOLT, LT SUPPORT.  RT BO	LT, RT SUPPORT.				1	H	7	1 	3O			NT	3A12
1998092500185	19980925	00185		1998	9	25	98ZZZX3413       	1	19980909	G	2434	ALU1003	HOUSING         	PRESTOLITE  	ALX9425B    															SUPPORT WEB	CRACKED         	B			KC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		150  			6100396					DRIVE END HOUSING FAILED AFTER 150 HOURS TIS ON THIS GEAR DRIVE UNIT.  THIS COULD HAVE CAUSED ALTERNATOR TO FAIL AND SEV	ERELY DAMAGE ENGINE.  HAVE SEEN SAME PROBLEM WITH OTHER UNITS OF THIS SAME MODEL. CRACKS ORIGINATED IN SHARP CORNERS OF 	SUPPORT WEBS.
1998092500186	19980925	00186	EA  	1998	9	25	98ZZZX3414       	2	19980901	G	7322		BOWL            	PRECISION   	MA45        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CARBURETOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145C	50   			75072604	2843151	L36114361			CARBURETOR BOWL ASSY (PN 10-3075) FOUND CRACKED NEAR THROTTLE BODY TO BOWL ATTACH SCREW BOSS ON THE LEFT SIDE OF THE BOW	L ASSEMBLY.  THE CRACK IS APPROXIMATELY .50 INCH IN LENGTH AND APPEARS TO BE CASTING FLAW.  THIS CRACK ALLOWED FUEL TO S	EEP FROM THE CARBURETOR CONTINUOUSLY.				1	L	7	1 	3O	3	O		2A13    	E286
1998092500187	19980925	00187	EA  	1998	9	25	98ZZZX3415       	2	19980723	G	8520	68864	CAMSHAFT        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	1555U		976  			17267171	L3886827A			CORROSION PITS BEHIND EXPANSION PLATE IN CRANKSHAFT.  PITS ALONG EDGE BETWEEN EXPANSION PLATE AND ID OF CRANKSHAFT.  MIS	TAKENLY C/W AD 98-02-08.  CORROSION PITS NOTED, BUT NO CRACKS.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998092500188	19980925	00188	CE  	1998	9	25	98ZZZX3416       	1	19980811	G	3230	24411009	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										MLG	CRACKED         	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6623Z	2500 				172RG0240				WHILE REMOVING A CRACKED ACTUATOR, THE LT MAIN GEAR PIVOT WAS ALSO FOUND CRACKED.  THIS PIVOT IS OF THE NEW STYLE AND PA	RT NUMBER.  THIS IS AN ONGOING PROBLEM WITH THIS DESIGN.  SUBMITTER STATED MECHANIC SHOULD COMPLY WITH SB 90-1 AT LEAST 	EVERY 500 HOURS AND SET PARKING BRAKES DAILY WHICH WILL ALLOW BRAKE FLUID TO SEEP THROUGH THE CRACKS AND INDICATE IMMINE	NT FAILURE OF THE PIVOT ASSEMBLY.			1	H	7	1 	3O				3A17
1998092500189	19980925	00189	SO  	1998	9	25	98ZZZX3417       	1	19980901	G	2810	CCA1550	DRAIN VALVE     	CURTIS      		PIPER 	PA31  	PA31310     	7103103	SO  										FUEL SUMP	MISMANUFACTURED 	H	P	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	16	107FC					31612				PILOT NOTICED ON PRE-FLIGHT THAT DRAIN WAS LOCKED IN DIFFERENT POSITION THAN OTHER DRAINS.  MECHANIC CHANGED DRAIN.  PAR	T LOOKS AS IF MANUFACTURED WITH PROBLEM.  PART THAT LOCKS NOT MADE SAME AS NEW PARTS.					1	L	7	1 	3O			RT	A20SO
1998092500190	19980925	00190	NM  	1998	9	25	98ZZZX3418       	1	19980831	G	2730		CABLES          			GRTLKS	2T1   	2T1A2       	3910101	NM  										ELEVATOR	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	3793F	1577 				0767				DUIRNG INSPECTION, FOUND UPPER ELEVATOR CABLE HAD 2 OR 3 BROKEN STANDS WHERE THE CABLE RUBBED A FAIRLEAD IN THE AFT FUEL	AGE.  UPON REPLACEMENT OF THE CABLE, A MUCH WORSE SPOT WAS FOUND FURTHER UP ON THE CABLE.  THIS WAS CAUSED BY THE UPPER 	CABLE RUBBING ON THE LOWER CABLE.  INSPECTION OF THE LOWER CABLE SHOWED IT WAS AS BAD OR WORSE THAN THE UPPER.  BOTH CAB	LES WERE REPLACED, BUT THEY STILL RUB.  THIS AREA CANNOT BE EASILY SEEN DURING INSPECTION.  RECOMMEND AN OPENING BE PUT 	IN AFT FUSELAGE TO FACILITATE INSPECTION.		1	Q	7	1 	3O				A18EA
1998092500191	19980925	00191	EA  	1998	9	25	98ZZZX3419       	2	19980826	G	8530	LW12993	HEAD            			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					CYLINDER NR 1	SEPARATED       	B	P		A5OR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			SO	09	2756V	2660 	894  			177RG0682	L1342151A			PILOT REPORTED FAILURE OCCURRED AFTER TAKEOFF WHILE TURNING DOWN WIND AT 1,100 FEET AGL.  A LOUD BAG HEARD FROM THE ENG 	WITH SMOKE AND OIL COVERING W/S FOLLOWED BY A LOSS IN OIL PRESSURE.  ENG SHUT DOWN, UNEVENTFUL DEAD STICK LANDING MADE. 	 INVEST REVEALED A HOLE IN THE COWLING AND ACFT COVERED WITH OIL FROM ENG.  REMOVED TOP COWLING TO FIND NR 1 CYL HEAD SE	PARATED FROM CYL BARREL.  ENG HAS 894.0 HRS SMOH WITH CERMICROME CYL.  A COMP TEST, 20 HRS BEFORE FAILURE OCCURRED, WAS 	72/80.  NO INDICATION OF LEAKAGE; CYL HEAD APPEARED CRACKED ABOUT HALF-WAY AROUND CYL BARREL FOR SOME TIME.  FAILURE OCC	URRED WHERE CYL HEAD THREADS ON TO BARREL.  RECOMMEND FAA INVESTIGATE.  SUSPECT CAUSE TO BE MFG OR CYL O/H PROCESS.	1	H	7	1 	3O	3	O		A20CE   	1E10
1998012900110	19980129	00110	CE  	1998	1	29	98ZZZX342        	1	19980109	G	3244	850X10	TIRE            			BEECH 	90    	E90         	1152914	CE  										MLG	IMBALANCE       	D				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	07	987GM	185  				LW65				TIRE SUDDENLY BECAME UNBALANCED DUE TO THE RUBBER BALANCE PATCH ON THE INTERIOR BECOMING DETACHED UNDER NORMAL CONDITION	S, 281 LANDINGS, 185 HOURS, 3.7 MONTHS IN SERVICE.  SUBMITTER STATED MANUFACTURER'S DEFECT.					1	L	7	2 	3T				3A20
1998092500192	19980925	00192	SO  	1998	9	25	98ZZZX3420       	1	19980806	G	7810	MH100583410	CLAMP           			PIPER 	PA31  	PA31        	7103102	SO  										EXHAUST STACK	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	65TT					317612078				EXHAUST CLAMP CAME LOOSE IN-FLIGHT ALLOWING EXHAUST STACK TO COME LOOSE FROM THE TURBOCHARGER EXIT PORT ON THE LEFT ENGI	NE.  HOT EXHAUST GASSES BLISTERED THE PAINT ON THE AFT CENTER OF THE COWLING.  ENGINE WAS SECURED/FEATHERED AND UNEVENTF	UL LANDING ACCOMPLISHED.				1	L	7	2 	3O				A20SO
1998092500193	19980925	00193	SW  	1998	9	25	98ZZZX3421       	1	19980812	G	3710	211CC	PUMP            			MOONEY	M20   	M20K        	5870220	SW  										ENGINE	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	4097H				O7AL002306	250416				AIRBORNE 211CC INSTALLED AT 952.8; 49.1 HOURS LATER, PUMP FAILED.  AT 1,001.9 HOURS, AIRBORNE 211CC INSTALLED (UNDER WAR	RANTY). PUMP FAILED AT 1,246.0 HOURS.  ALL REPLACEMENTS USED NEW SEALS, HOSES, AND FILTERS.  OVERHEAT NOT INDICATED.					1	L	7	1 	3O				2A3
1998092500195	19980925	00195	SO  	1998	9	25	98ZZZX3423       	2	19980713	G	7414	36066	GEAR            	SLICK       	4330        	PIPER 	J3    	J3C65       	7100510	SO  	CONT  	A65   	A658        	17003	SO  					MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	51516	150  			9307036	10155	5180968			GEAR TEETH WORN IN MAGNETO.						1	H	7	1 	3O	3	O		A691    	E205
1998092500196	19980925	00196	CE  	1998	9	25	98ZZZX3424       	1	19980817	G	5330	1613151K212	SKIN            			CESSNA	188   	A188B       	2073005	CE  										FUSELAGE	TORN            	H			BFHG	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	731XR					18803242				VIBRATION CAUSED SKIN TO TEAR AND PEEL PACK, ACTING AS A SPEED BRAKE.						1	L	7	1 	3O				A9CE
1998092500197	19980925	00197	SO  	1998	9	25	98ZZZX3425       	2	19980819	G	8530	649263	INDUCTION TUBE  			MOONEY	M20   	M20K        	5870220	SW  	CONT  	O360  	TSIO360*    	17025	SO  					ENGINE	CRACKED         	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	998EC	84   				252020	321755			FOUND CLYINDERS NR 3 (PN 649263) AND NR 4 (PN 649264) INDUCTION TUBES CRACKED UNDER THE INDUCTION TUBE FLANGES (PN 64693	3).					1	L	7	1 	3O	3	O		2A3     	E9CE
1998092500198	19980925	00198		1998	9	25	98ZZZX3426       	4	19980903	G	2562	AK450	SWITCH          	AMERIKING   		PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					ELT	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	110SK	395  			355713	31P7630006	L71162			UNIT REMOVED FOR C/W FAR 91-207D.  FOUND INERTIA SWITCH INOPERATIVE.  SUBMITTER STATES THIS IS THE THIRD UNIT TO FAIL TH	E TEST.  UNIT IS ONLY 2 YEARS OLD.					1	L	7	2 	3O	3	O		A8EA    	E19EA
1998092500199	19980925	00199	SO  	1998	9	25	98ZZZX3427       	2	19980817	G	7414	S6LSC251O5005563	MAGNET          			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360KB     	17025	SO  					ENGINE MAG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	758SZ	399  			I30960BD	R1723336	288675R			MAGNETO WAS DISASSEMBLED DUE TO BAD POINTS.  INSPECTION OF ROTATING MAGNET SHOWED CRACKS ON THE BACK FACE.  MAGNTO WAS R	EPLACED WITH NEW.					1	H	7	1 	3O	3	O		3A17    	E1CE
1998092500201	19980925	00201	CE  	1998	9	25	98ZZZX3429       	1	19980803	G	2823	MS29513	O-RING          			CESSNA	182   	182D        	2072710	CE  										FUEL SELECTOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		2200 								O-RING SWELLED PREVENTING FUEL SELECTOR PORT FROM OPENING.						1	H	7	1 	3O			NT	3A13
1998012900111	19980129	00111	CE  	1998	1	29	98ZZZX343        	1	19980115	G	2810		TANK            			LEAR  	35    	35LEAR      	5170600	CE  										FUSELAGE	DEFECTIVE       	H			GQFG	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	2FOR					441				BLIND RIVETS ON INNER WALL OF AFT FUSELAGE TANK SKIN TO FRAME WERE INCORRECTLY INSTALLED.  RIVETS DID NOT EXTEND THROUGH	 SUFFICIENTLY TO FASTEN ALL MATERIAL.  LEFT SIDE OF AIRCRAFT FR 22-25, STR 10-14.  TT:  4,971.5 HOURS.  LANDINGS:  3,301	.				2	L	7	2 	4F				A10CE
1998092500202	19980925	00202	EA  	1998	9	25	98ZZZX3430       	1	19980817	G	7603	MS203651032C	NUT             			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1F5   	41532	EA  					THROTTLE	MISSING         	D				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			NE	01	3645T					600852816124				RT ENGINE FAILED TO RESPOND TO THROTTLE CONTROL MOVEMENT IN-FLIGHT.  A SAFE LANDING WAS MADE AND ACFT DELIVERED TO MAINT	.  INVESTIGATION FOUND THE RT THROTTLE CONTROL CABLE DISCONNECTED FROM THE THROTTLE ARM.  CONNECTING HARDWARE WAS MISSIN	G.  THE PARTS MANUAL SHOWS AN AN3-10A UNDRILLED BOLT AND MS20365-1032C STEEL LOCKNUT USED TO SECURE THE CABLE ROD END TO	 THE THROTTLE ARM.  SUBMITTER SUGGESTED THE PROPER HARDWARE SHOULD BE AN AN3-10 DRILLED SHANK BOLT WITH AN AN310-3 CASTE	LLATED NUT SECURED BY AN MS24665 COTTER PIN.  SUSPECT THE ORIGINAL MS20365-1032C NUT LOST ITS LOCKING ABILITY, LOOSENED,	 AND FELL OFF.	1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998092500203	19980925	00203	SO  	1998	9	25	98ZZZX3431       	1	19980801	G	2750	6273400	PIN             			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP HANDLE	SHEARED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	1793J					2824219				THE PIN WHICH HOLDS THE FLAP HANDLE IN SELECTED POSITIONS WAS FOUND MISSING.  IT APPEARS THE PIN FRACTURED IN HALF AT TH	E ROLL PIN HOLE AND FELL OUT OF THE PLUG, PIPER P/N 62734-00.  THE PIN COULD NOT BE LOCATED IN THE AIRCRAFT OR AT THE AC	CIDENT SITE.  THERE HAS BEEN THREE PREVIOUS FAILURES REPORTED BY SDR'S.  THIS IS AN OLDER STYLE OF THIS PIN WHICH MEASUR	ES .190 THOUSANDTHS OF AN INCH.  THE PIN HAD BEEN RE-DESIGNED IN 1968 INCREASING THE DIAMETER TO .250 THOUSANDTHS OF AN 	INCH.  RECOMMEND THIS PIN BE INSPECTED EVERY 100 HOURS BY PULLING ON BOTH ENDS OF THE PIN TO ASSURE STRUCTURAL INTEGRITY	 OF THE PIN.	1	L	7	1 	3O				2A13
1998092500204	19980925	00204	CE  	1998	9	25	98ZZZX3432       	1	19980814	G	3221	52130409	WEB             			CESSNA	402   	402C        	207590R	CE  										LT TRUNNION	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	57PB	14510				402C0300				DURING NOSE INSPECTION, FOUND CRACKS ON WEB ASSEMBLIES AROUND THE ATTACH BOLTS FOR THE NOSE GEAR TRUNNION BEARINGS.  POS	SIBLY, SIDE LOADS ON NOSE GEAR DUE TO IMPROPER GROUND HANDLING PROCEDURES.					1	L	7	2 	3O				A7CE
1998092500205	19980925	00205	CE  	1998	9	25	98ZZZX3433       	1	19980814	G	3221	521304010	WEB             			CESSNA	402   	402C        	207590R	CE  										RT TRUNNION	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	57PB	14510				402C0300				DURING NOSE INSPECTION, FOUND CRACKS ON WEB ASSEMBLIES AROUND THE ATTACH BOLTS FOR THE NOSE GEAR TRUNNION BEARINGS.  POS	SIBLY, SIDE LOADS ON NOSE GEAR DUE TO IMPROPER GROUND HANDLING PROCEDURES.					1	L	7	2 	3O				A7CE
1998092500206	19980925	00206	CE  	1998	9	25	98ZZZX3434       	1	19980910	G	5312	0713631Z	BULKHEAD        			CESSNA	182   	182J        	2072722	CE  										NLG WW	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	3304F	4109 				18257304				DURING ROUTINE INSPECTION, CRACK IN BULKHEAD FOUND.  RECOMMEND CLOSE INSPECTION DURING ANNUAL INSPECTIONS.						1	H	7	1 	3O			NT	3A13
1998092500208	19980925	00208	CE  	1998	9	25	98ZZZX3436       	1	19980811	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										LT/RT MLG	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6623Z	5400 				172RG0240				DURING A ROUTINE INSPECTION, BOTH MLG ACTUATORS WERE FOUND CRACKED JUST BELOW THE BEARING CUPS.  THIS IS AN ONGOING PROB	LEM WITH THE DESIGN OF THE ACTUATOR.  MECHANICS MUST INSPECT THESE ACTUATORS CAREFULLY EACH INSPECTION FOR CRACKS.					1	H	7	1 	3O				3A17
1998092500209	19980925	00209	SO  	1998	9	25	98ZZZX3437       	1	19980820	G	2720	82815023	CONTROL CABLE   			PIPER 	PA46  	PA46350P    	7104602	SO  										RUDDER	WORN            	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	788ES	505  				4636058				ON THIS AIRCRAFT AND RECENTLY ONE OTHER, THE RIGHT RUDDER CABLE TENDS TO WEAR AT THE INTERCONNECT FOR THE AILERON WHERE 	IT PASSES THROUGH THE INTERCONNECT ARMS.  THE CABLE OF SAID AIRCRAFT IS WORN ENOUGH TO NOT BE ABLE TO DISTINGUISH THE CA	BLE STRANDS.  (A SUGGESTED FIX FOR THIS PROBLEM WOULD BE THE ADDITION OF PHENOLIC BLOCKS BEING ADDED TO THE INSIDE OF TH	E ARMS WHERE THE CABLE PASSES THROUGH).			1	L	7	1 	3O			RT	A25SO
1998092500210	19980925	00210	NE  	1998	9	25	98ZZZX3438       	3	19980901	G	6114	A1532	FLYWEIGHT       		F848LZ      	BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER HUB	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					E292T					CUP STYLE FLYWEIGHT HAS INDICATION ON OUTSIDE OF CUP APPROXIMATELY6 .75 INCHES LONG.  CORRESPONDING INDICATION ON INSIDE	 OF CUP.  THIS WAS A STOCK GOVERNOR FOR INVENTORY.					2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998092500211	19980925	00211	CE  	1998	9	25	98ZZZX3439       	1	19980831	G	2820	652635523	LINE            			CESSNA	500   	550         	2076604	CE  										FUEL SYSTEM	CHAFED          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	37201					5500655				DURING PHASE 5K INPSECTION OF FUEL SYSTEM  IN RT WING ROOT, A .023 INCH CHAFE WAS FOUND ON THE PRESS LINE TO THE EJECTOR	 TRANSFER PUMP.  REF:  CESSNA IPC 28-20-01 FIG 01 SHET 01 ITEM 40.  CHAFED LINE (ITEM 40) IS LOCATED IN THE 'Y' (ITEM 28	) OFF THE MAIN FUEL LINE TO THE ENG DRIVEN FUEL PUMP.  IT CHAFED ON THE WIGGINS COUPLING (ITEM 6) ON THE T-CONNECTION BE	TWEEN THE MANUAL FUEL S/O (ITEM NR 1) AND FUEL FILTER (ITEM B).  IF CHAFING HAD CONTINUED UNTIL IT WORE THROUGH, FUEL UN	DER MINIMUM 21.4 PSI WOULD HAVE SPRAYED INTO THE COMPONENTS FUEL LOSS.  THE IS 2ND FUEL LINE PN 6526355-23 FOUND IN SAME	 MANNER.	1	L	7	2 	4F				A22CE
1998092500212	19980925	00212	GL  	1998	9	25	98ZZZX3440       	3	19980904	G	6114		HUB             			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19								R773416		CESSNA152 PROPELLER WAS RECEIVED FOR AD 9521-01 HUB INSPECTION.  AFTER STRIPPING HUB, DISCOVERED CRACK AT LEADING EDGE B	OLT HOLES.  NR 1 AND NR 2 BLADES RUNNI NG ABOUT 2 INCHES LONG.  PROPELLER RETURNED TO CUSTOMER.					1	H	7	1 	3O			NT	3A19    		5	N	P50GL
1998092500213	19980925	00213	SO  	1998	9	25	98ZZZX3441       	2	19980810	G	7414	10353060	BEARING         	BENDIX      		CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					MAG CAM	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	411MZ		165  		7080833	421C1002	277166R			DURING ROUTINE INSPECTION OF THE AIRCRAFT MAGNETO TO ENGINE TIME CHECK REVEALED 15 DEGREE DISCREPANCY.  FURTHER INSPECTI	ON FOUND MAGNETO CAMSHAFT LOOSE IN THE HOUSING.  SUBMITTER STATES EXTREME WEAR OF CAM BEARING DUE TO INADEQUATE LUBRICAT	ION OF BEARING DURING O/H BUILD-UP AT ELECTROSYSTEMS.  COMPONENT P/N 1200S103492204				1	L	7	2 	3O	3	O		A7CE    	E7CE
1998092500214	19980925	00214	SO  	1998	9	25	98ZZZX3442       	2	19980810	G	7414	10353060	BEARING         	BENDIX      		CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  					MAG CAM	WORN            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	411MZ		106  		7100040	421C1002	245881H			DURING ROUTINE INSPECTION OF THE AIRCRAFT, MAGNETO TO ENGINE TIME CHECK REVEALED 15 DEGREE DISCREPANCY.  FURTHER INSPECT	ION FOUND MAGNETO CAMSHAFT LOOSE IN THE HOUSING.  SUBMITTER STATES EXTREME WEAR OF CAM BEARING DUE TO INADEQUATE LUBRICA	TION OF BEARING DURING OVERHAUL BUILD-UP AT ELECTROSYSTEMS.  COMPONENT P/N 1200S103492204				1	L	7	2 	3O	3	O		A7CE    	E7CE
1998092500215	19980925	00215	SO  	1998	9	25	98ZZZX3443       	2	19980904	G	8530	TCM539988	VALVE           			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					RT ENG INTAKE	MISMANUFACTURED 	B	S		DPOR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07	678DB	359  				4210876	219220R			DURING A PHASE INSPECTION, FOUND RIGHT ENGINE NR 5 CYLINDER LOW COMPRESSION 20/80, LEAKING BY INTAKE VALVE.  REMOVED CYL	INDER AND FOUND INTAKE VALVE HAD APPROXIMATELY .005 INCH RIDGE COMPLETELY AROUND VALVE ABOVE SEAT.  SUSPECT VALVE WAS NO	T PROPERLY HARDENED DURING MANUFACTURING PROCESS.				1	L	7	2 	3O	3	O		A7CE    	E7CE
1998092500216	19980925	00216	CE  	1998	9	25	98ZZZX3444       	1	19980821	G	7910	TCM535823	GASKET          		6406209     	CESSNA	182   	182N        	2072730	CE  										OIL CAP	MISSING         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	9282G					18260822				DURING ACCIDENT INVESTIGATION, OIL FILTER CAP WAS NOT ATTACHED TO FILLER TANK.  CAP WAS FOUND IN ENGINE COMPARTMENT.  TH	E CHAIN AND HOOK WERE AFFIXED TO CAP.  THE GASKET UNDER SIDE OF CAP WAS MISSING.  THE CAP WOULD NOT LOCK OR FIT SNUGGLY 	TO FILLER TANK.  EVIDENCE OF OIL ON TOP OF ENGINE UNDER SIDE OF TOP COWL, AND OUTSIDE OF TOP COWL, STREAKING OUT OF FILL	ER DOOR.  TRACES OF OIL SPECS ON WINDSHIELD ALSO,			1	H	7	1 	3O			NT	3A13
1998092500217	19980925	00217		1998	9	25	98ZZZX3445       	4	19980821	G	6113	6779400	CUFF            			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	SPINNER	FAILED          	D	S			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	2510Q	4406 				32R7780249				CUFF FAILED (CRACK) AND RIPPED SPINNER WHILE IN-FLIGHT.						1	L	7	1 	3O				A3SO    		5	C	P920
1998092500219	19980925	00219	SO  	1998	9	25	98ZZZX3447       	1	19980801	G	8120	58B19890	DRAIN           		46C19839    	PIPER 	PA46  	PA46350P    		SO  										TURBOCHARGER	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	648DH	106  				4636137				THE TURBO DRAIN WAS DYE-PENETRANT CHECKED.  THE 90 DEGREE WELD ON THE PART SHOWED EVIDENCE OF CRACKING ALONG THE WELD AR	EA.  SUBMITTER STATED THIS HAS BEEN A PROBLEM IN MORE THAN ONE AIRCRAFT.					1	L	7	1 	3O			RT	A25SO
1998092500220	19980925	00220	SO  	1998	9	25	98ZZZX3448       	1	19980801	G	8120	58B19891	DRAIN           		46C19839    	PIPER 	PA46  	PA46350P    		SO  										TURBOCHARGER	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	648DH	106  				4636137				THE TURBO DRAIN WAS DYE-PENETRANT CHECKED.  THE 90 DEGREE WELD ON THE PART SHOWED EVIDENCE OF CRACKING ALONG THE WELD AR	EA.  SUBMITTER STATES THIS HAS BEEN A PROBLEM IN MORE THAN ONE AIRCRAFT.					1	L	7	1 	3O			RT	A25SO
1998092500221	19980925	00221	CE  	1998	9	25	98ZZZX3449       	1	19980831	G	2710	04115341	BRACKET         			CESSNA	120   	120         	2071402	CE  										RT AILERON	BROKEN          	H		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	1867N					12111				UPPER RIGHT AILERON PULLEY BRACKET BROKE.  OLD UNDETECTED CRACK.  PARTIAL LOSS OF AILERON CONTROL.  BRACKETS CANNOT BE I	NSPECTED PROPERLY WITHOUT REMOVAL.  SUGGEST ONE TIME INSPECTION.					1	H	7	1 	3O				A768
1998092500222	19980925	00222		1998	9	25	98ZZZX3450       	4	19980911	G	2562	0004006A	BATTERY         	ARTEX       	754193      	CESSNA	172   	172M        	2072418	CE  										ELT	DESTROYED       	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	64414	47   			302145	17265211				AT PRE-FLIGHT FOUND CONTENTS OF ONE BATTERY CELL ON AREA CARPET.  FOUND ELT CASING CRACKED AND PIECES BROKEN AWAY IN BAG	GAGE AREA.					1	H	7	1 	3O			NT	3A12
1998092500223	19980925	00223	EU  	1998	9	25	98ZZZX3451       	1	19980825	G	2160	104568	VALVE           			HWKSLY	DH125 	BH125400A   	4230138	EU  										E/E BAY	FAILED          	D		A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			GL	07	900WG					NA757				AFTER APPROXIMATELY 2 HOURS OF CRUISE FLIGHT, AUXILIARY HEAT WAS SELECTED TO WARM COCKPIT.  AFTER SYSTEM WAS TURNED ON F	OR APPROXIMATELY 3 SECONDS, SMOKE AND EXCESSIVE HEAT WERE NOTED IN CABIN AND COCKPIT.  SELECTING DECREASE OR (COLD) HAD 	NO EFFECT.  RAN CHECKLIST AND FOUND NO REFERENCE TO THIS PROBLEM.  THE ONLY ACTION WAS TO REDUCE POWER ON RT ENGINE TO I	DLE AND LAND AT FIRST AVAILABLE AIRPORT.  CHANGED VALVE AND SYSTEM FOUND TO OPERATE NORMALLY.			2	L	7	2 	4J				A3EU
1998092500224	19980925	00224	EA  	1998	9	25	98ZZZX3452       	2	19980827	G	8530	73806	PUSH ROD        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	89927		1363 			15282918	L2256315			DURING 100-HOUR INSPECTION NOTED DURING COMPRESSION TEST THAT NR 1 AND NR 3 CYLINDERS WERE LEAKING BY EXHAUST VALVES.  W	HEN CYLINDERS WERE REMOVED FOR REPAIR, FOUND NR 3 CYLINDER INTAKE PUSH ROD WAS DAMAGED.  CAP PORTION AT ROCKER ARM END P	ULLED OUT OF ROD AS IT WAS BEING REMOVED.  UPON MEASURING OLD PUSH ROD P/N 73806 AGAINST NEW, IT WAS FOUND TO BE .1250 I	NCH SHORTER.  ENGINE HAS 1,363.27 HOURS SMOH AND A TOTAL TIME OF 3,806.27 HOURS.			1	H	7	1 	3O	3	O	NT	3A19    	E223
1998092500225	19980925	00225	GL  	1998	9	25	98ZZZX3453       	3	19980828	G	6114		HUB             													HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	CORRODED        	B			B2PR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					CH11414			CH11414		SENT HUB TO HARTZELL FOR REPAIR OF ROD BORE.  WHILE AT HARTZELL, THEIR INSPECTION DEPARTMENT REJECTED THE HUB DUE TO COR	ROSION IN THE FILLET RADIUS.															5	C	P920
1998092500226	19980925	00226	CE  	1998	9	25	98ZZZX3454       	1	19980903	G	2823	07161114	VALVE           			CESSNA	172   	172R        	2072401	CE  										FUEL SOV	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	18AF	1378 				17280072				DURING 100-HOUR INSPECTION, FUEL SHUT-OFF VALVE LOCATED UNDER RIGHT SIDE FLOOR PLATE FORWARD OF HEADER TANK WAS FOUND LE	AKING FUEL FROM THE VALVE BODY SEAL AND SHAFT.  FUEL SMELL WAS EVIDENT IN CABIN AND FOUND RT SIDE SUB-FLOOR WAS COVERED 	IN FUEL DYE.  UNIT WAS REPLACED.				1	H	7	1 	3O			NT	3A12
1998092500227	19980925	00227	CE  	1998	9	25	98ZZZX3455       	1	19980801	G	3233	AN175M22A	BOLT            			CESSNA	210   	T210N       	2073456	CE  										MLG ACTUATOR	LOOSE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	6224Y	3091 				21064300				ON MAIN LANDING GEAR ACTUATOR CAP DURING PHASE 4 INSPECTION FOUND ONE AN175M22A BOLT BACKED OUT APPROXIMATELY .3750 INCH	; ALL BOLTS FOUND LOOSE.  SUBMITTER STATES THIS HAS BEEN A RECURRING PROBLEM ON 172RG, R182, AND 210 SERIES AIRCRAFT AT 	THIS FACILITY.				1	H	7	1 	3O				3A21
1998092500228	19980925	00228	SO  	1998	9	25	98ZZZX3456       	1	19980827	G	3230	6702506	TRUSS           			PIPER 	PA28  	PA28R180    	7102809	SO  										RT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	4620J	5216 				28R30503				DURING MAINTENANCE TO RT GEAR SIDE BRACE TO REMOVE EXCESSIVE FREE PLAY, A CRACK WAS FOUND IN FORKED END AT ATTACHMENT TO	 PN 6697-05 LINK.  CRACK WAS AT THE BASE OF MACHINED SURFACE TO FORM FORK, AND APPEARED TO BE A DEEPER MACHINE MARK.  DY	E PENETRANT INSPECTION PROVED THE CRACKS.  PART WAS REPLACED, GEAR RIGGED AND RETURNED TO SERVICE.				1	L	7	1 	3O				2A13
1998092500229	19980925	00229		1998	9	25	98ZZZX3457       	2	19980827	G	8520	76094	CAMSHAFT        			AMTR  		ACROSPORTII 			LYC   		O290D2      							ENGINE	WORN            	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			CE	01	190TT					529				ENGINE PURCHASED WITH A PARTIALLY ASSEMBLED HOMEBUILT AIRCRAFT.  INFORMATION IN LOG INDICATED THE ENGINE HAS BEEN OVERHA	ULED APPROXIMATELY 6 HRS PRIOR TO AIRCRAFT COMPLETION.  ON FIRST FLIGHT, PILOT COMPLAINT WAS LOW POWER.  AFTER SEVERAL H	OURS OF TROUBLESHOOTING, IGNITION, INTERNAL TIMING, AND OTHER ITEMS, TWO CAMSHAFT LOBES WERE FOUND WORN.  SUBMITER STATE	D CAUSE IS SUSPECTED TO BE NO LUBRICATION DURING INITIAL RUNNING OF THE ENGINE.						0
1998092500230	19980925	00230	SO  	1998	9	25	98ZZZX3458       	1	19980827	G	7602	24889407	CONTROL CABLE   			PIPER 	PA31  	PA31        	7103102	SO  										ENGINE	BROKEN          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	83RA					31638				PILOT REPORTED HAVING NO CONTROL OF MIXTURE.  INSPECTION FOUND MIX IN FULL RICH POSITION ON FUEL SERVO AND CONTROL CABLE	 BROKEN.  BREAK WAS DETERMINED TO BE INSIDE CABLE HOUSING AT CONSOLE END.  NO RECORD OF CABLE REPLACEMENT FOUND.  AIRCRA	FT HAS 10,600 HOURS.  MIXTURE, THROTTLE AND PROPELLER CABLES WERE REPLACED FOR THE RIGHT ENGINE OF AIRCRAFT.				1	L	7	2 	3O			 	A20SO
1998092500231	19980925	00231	CE  	1998	9	25	98ZZZX3459       	1	19980809	G	3230	MS203922017	PIN             			CESSNA	210   	210G        	2073430	CE  										MLG	MISSING         	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	09	5869F					21058869				RIGHT MAIN LANDING GEAR FAILED TO UNLOCK WHEN EXTENDED.  PILOT TRIED NUMEROUS TIMES TO GET GEAR TO EXTEND INCLUDING MANU	ALLY PUMPING.  HE ELECTED TO LAND GEAR UP.  DURING INCIDENT INVESTIGATION, FOUND THE UPLOCK LEVER TO CONTROL LINK PIN MI	SSING.  MAINTENANCE DID NOT COTTER PIN THE PIN.  THE OPPOSITE PIN WAS ALSO MISSING COTTER PIN, BUT WAS STILL IN PLACE.				1	H	7	1 	3O				3A21
1998012900114	19980129	00114	SO  	1998	1	29	98ZZZX346        	1	19980102	G	5711	0822031	SPAR            			LUSCOM	8     	8A          	8190104	SO  										WING ROOT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2013B	3599 				6440				DURING ACCOMPLISHMENT OF AD 96-24-17 (AMEND NR 39-9841 EFF 1-27-97) INTERGRANULAR CORROSION WAS FOUND ON THE REAR SPAR A	PPROXIMATELY 12 INCHES OUTBOARD OF WING ATTACH POINTS ON THE REAR SURFACE TOP OF REAR SPAR.  AREA WAS SLIGHTLY BULGED WI	TH A .50 INCH IN DIAMETER PIT WITH FLAKING ALUMINUM INSIDE THE DEFECT.				1	H	7	1 	3O				A694
1998092500232	19980925	00232		1998	9	25	98ZZZX3460       	4	19980821	G	6122	49F624Z	GOVERNOR        			PIPER 	PA31  	PA31350     	7103110	SO  										LT ENGINE	MALFUNCTIONED   	B			BIOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	64JP				D2675TJ	317652156				ON RUN-UP, ENGINE WOULD ONLY PRODUCE 2,200 RPM.  FOUND UPPER END OF GOVERNOR CONTROL BINDING INTERNALLY.  REPLACED GOVER	NOR WITH OVERAULED UNIT.  OPS CHECK GOOD.					1	L	7	2 	3O				A20SO
1998092500233	19980925	00233	EU  	1998	9	25	98ZZZX3461       	1	19980908	G	3240		CONTROL CABLE   			STEMME	S10   	S10         	1130868	EU  										BRAKE	FAILED          	B			UNER	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	03	94FT					14014				THE ACFT WHEEL BRAKING SYSTEM IS ACTIVATED BY A CONTROL STICK PULL LEVER (SIMILAR TO MOTORCYCLE BRAKE LEVER) WHICH IS CO	NNECTED TO A CABLE ASSY TO A MOTORCYCLE MASTER CYLINDER.  THE MACHINED BRASS TERMINAL BALL ENDS ARE BRAZED OR SOLDERED T	O THE CABLE ENDS.  THE BRASS BALLS ON 2 DIFFERENT CABLE ASSYS HAVE BROKEN OFF THE TERMINAL ENDS.  IF ONE OF THE CABLE AS	SYS FAILS DURING BRAKING, THE SAILPLANE PILOT MUST REACH FOR THE OTHER CONTROL STICK TO ACTIVATE THE BRAKING SYSTEM.  SU	BMITTER SUGGESTED USING THESE CABLE ASSYS WITH STAINLESS STEEL TERMINAL BALL ENDS SOLDERED TO THE CABLE.		1	K	7	1 	3O			RC	G58EU
1998092500234	19980925	00234	CE  	1998	9	25	98ZZZX3462       	1	19980804	G	2432		WIRE            			BEECH 	90    	E90         	1152914	CE  										BATTERY	BURNED          	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8111P	7389 				LW72				DURING COMPLETE PHASE INSPECTION, FOUND BATTERY WIRES FROM BATTERY BUS TO RT AND LT MAIN BUS (P83A0, P83B0) CURRENT LIMI	TERS (325 AMPS) TO BE SEVERELY BURNT FROM THE CURRENT LIMITER CONNECTIONS APPROXIMATELY 6 INCHES ALONG THE WIRE.  SUBMIT	TER STATES IT APPEARS TO HAVE BEEN CAUSED BY CORROSION IN THE WIRE STARTING AT THE TERMINAL LUG.				1	L	7	2 	3T			 	3A20
1998092500235	19980925	00235	SO  	1998	9	25	98ZZZX3463       	1	19980810	G	7920	LW131768S050	HOSE            	GARRTT      	46C19839    	PIPER 	PA46  	PA46350P    		SO  										TURBO DRAIN	MISINSTALLED    	B			AMYR	K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CE	05	788ES	505  			ZCN27145	463058				THIS HOSE IS MADE FROM TEFLON.  IF INSTALLED INCORRECTLY OR CARELESSLY, THESE HOSES TEND TO TWIST.  HOSES ON SAID AIRCRA	FT APPEAR TWISTED WHICH CAN RESULT IN RESTRICTED OR BLOCKED OIL FLOW.  AFTER OPERATING AIRCRAFT WITH HOSES TWISTED, THEY	 TEND TO HOLD THEIR TWISTED SHAPE.  WHEN INSTALLING THESE HOSES, THREE WRENCHES MUST BE USED, ONE ON THE HOSE BODY, ONE 	TO TIGHTEN HOSE B-NUT, AND ONE TO SUPPORT FITTING ON TURBO DRAIN TANK.			1	L	7	1 	3O			RT	A25SO
1998092500236	19980925	00236	SO  	1998	9	25	98ZZZX3464       	1	19980810	G	7920	LW131768S050	HOSE            	GARRTT      	46C19839    	PIPER 	PA46  	PA46350P    		SO  										TURBO DRAIN	TWISTED         	B		A	AMYR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	321CR	200  				4636124				SAID HOSE IS MADE FROM TEFLON.  IF INSTALLED INCORRECT OR CARELESSLY, CAN TEND TO TWIST.  AFTER A RECENT TURBOCHARGER IN	STALL, ALL THREE OF NOTED HOSES WERE TWISTED.  THIS CAN RESULT IN RESTRICTED OR BLOCKED OIL FLOW.  WHEN INSTALLING THESE	 HOSES USE THREE WRENCHES; ONE ON HOSE BODY FITTING, ONE TO TIGHTEN HOSE B-NUT, AND ONE TO SUPPORT TURBO DRAIN TANK FITT	ING.			1	L	7	1 	3O			RT	A25SO
1998092500237	19980925	00237	SO  	1998	9	25	98ZZZX3465       	1	19980810	G	7920	LW131768S050	HOSE            	GARRTT      	46C19839    	PIPER 	PA46  	PA46350P    		SO  										TURBO DRAIN	MISINSTALLED    	B			AMYR	K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			CE	05	788ES	505  			VCN29302	463058				THIS HOSE IS MADE FROM TEFLON.  IF INSTALLED INCORRECTLY OR CARELESSLY, THESE HOSES TEND TO TWIST.  HOSES ON SAID AIRCRA	FT APPEAR TWISTED WHICH CAN RESULT IN R ESTRICTED OR BLOCKED OIL FLOW.  AFTER OPERATING AIRCRAFT WITH HOSES TWISTED, THE	Y TEND TO HOLD THEIR TWISTED SHAPE.  WHEN INSTALLING THESE HOSES, THREE WRENCHES MUST BE USED, ONE ON THE HOSE BODY, ONE	 TO TIGHTEN HOSE B-NUT, AND ONE TO SUPPORT FITTING ON TURBO DRAIN TANK.			1	L	7	1 	3O			RT	A25SO
1998092500238	19980925	00238	SO  	1998	9	25	98ZZZX3466       	1	19980718	G	5347		SEAT RAIL       			PIPER 	PA14  	PA14        	7101402	SO  										SEAT LATCH	MALFUNCTIONED   	G		A		O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AL	03	5133H					14144				PILOT SEAT LATCH RELEASED DURING TAKEOFF ALLOWING PILOT TO SLIDE AFT.  PILOT WAS UNABLE TO REACH CONTROLS CAUSING ACCIDE	NT.  THE SEAT RAILS AND SEATS INSTALLED WERE OF CESSNA DESIGN AND TYPE.  SUBMITTER STATES THIS ALTERATION HAS BEEN INCOR	PORATED ON MANY PIPER PA-14 AIRCRAFT AND SHOULD REQUIRE THE ACCOMPLISHMENT OF THE CESSNA AD NOTE 87-20-03R2 AT EACH ANNU	AL.			1	H	7	1 	3O				A797
1998092500239	19980925	00239	SW  	1998	9	25	98ZZZX3467       	2	19980821	G	8550	620067007	BREATHER        			MOONEY	M20   	M20K        	5870220	SW  										ENGINE	CHAFED          	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	998EC	84   				252020				THE CRANKCASE BREATHER TUBE P/N 620062007 CHAFES AGAINST CYLINDER NR 6 INDUCTION TUBE P/N 649266-1 AND IF LEFT UNCORRECT	ED WILL CHAFE A HOLE INTO THE TUBES.  RECOMMEND ADDING ANTI-CHAFE MATERIAL TO BOTH TUBES.					1	L	7	1 	3O				2A3
1998092500240	19980925	00240	SW  	1998	9	25	98ZZZX3468       	2	19980821	G	8530	6492662	INDUCTION TUBE  			MOONEY	M20   	M20K        	5870220	SW  										ENGINE	CHAFED          	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	998EC	84   				252020				CYLINDER NR 6 INDUCTION TUBE SETTLES ONTO THE UPPER CRANKCASE AND IF LEFT UNCORRECTED WILL CHAFE A HOLE INTO THE INDUCTI	ON TUBE (P/N 649266-2.  RECOMMEND ADDING ANTI-CHAFE MATERIAL TO THE INDUCTION TUBE.					1	L	7	1 	3O				2A3
1998092500241	19980925	00241	SW  	1998	9	25	98ZZZX3469       	1	19980821	G	7160	600406501	AIRBOX          			MOONEY	M20   	M20K        	5870220	SW  										ENGINE	CHAFED          	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	998EC	84   				252020				THE INDUCTION SYSTEM AIRBOX P/N 600406-501 COMES IN CONTACT WITH THE ADJACENT ENGINE MOUNT WHICH IN TURN CHAFES ENGINE M	OUNT.  RECOMMEND ADDING CHAFE PROECTION MATERIAL TO ENGINE MOUNT.					1	L	7	1 	3O				2A3
1998092500242	19980925	00242	CE  	1998	9	25	98ZZZX3470       	1	19980808	G	2810	07166149	VENT LINE       			CESSNA	172   	172R        	2072401	CE  										RT WING	BLOCKED         	B			PRIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	03	9392F	226  				17280205				OWNER COMPLAINED OF NO FUEL FLOW FROM RT FUEL TANK SINCE TAKING DELIVERY OF ACFT WITH 88.2 HRS ON ACFT.  ATTEMPTED TO RE	-POSITION VENT LINES, CHECK VENT SYS AND FUEL FLOW, BUT COULD NOT FIX PROBLEM.  TECH REP CONTINUED TO T/S SYS EACH TIME 	CHECKING A DIFFERENT LOCATION.  AFTER INSP FUEL VENTS INTERNAL OF TANK, VISUALLY, COULD NOT FIND PROBLEM UNTIL AIR WAS A	TTEMPTED TO PASS FROM 1 TANK TO NEXT.  FOUND NO AIR FLOW.  DISASSEMBLED VENT LINE AT TOP OF RT TANK AND FOUND LINE BLOCK	ED BY FUEL TANK SEALANT.  NO PREVIOUS WORK HAS BEEN DONE SINCE MFG.  SUSPECT SEALANT USED TO SEAL VENT LINE DURING ASSY.	  REMOVED BLOCKAGE IN PLASTIC VENT LINE AT RUBBER HOSE CONNECTION, RE-ASSEMBLED ACFT, AND TEST FLEW,  FOUND OK.	1	H	7	1 	3O			NT	3A12
1998092500244	19980925	00244	CE  	1998	9	25	98ZZZX3472       	1	19980901	G	3244	0613160	TIRE            			CESSNA	421   	421C        	2076016	CE  										NLG	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	2724M				7112P00167	421C1238				INSTALLED NEW NOSE TIRE.  UPON FIRST GEAR RETRACTION LOUD NOSE WAS HEARD.  GEAR CYCLED NORMALLY.  UPON INVESTIGATION, FO	UND NOSE TIRE HITTING A FITTING ON FORWARD PRESSURE BULKHEAD.  IT WOULD ONLY HIT WHEN TIRE WAS SPINNING AT TAKEOFF SPEED	.  NEW TIRE FIXED PROBLEM.				1	L	7	2 	3O				A7CE
1998092500245	19980925	00245	EA  	1998	9	25	98ZZZX3473       	2	19980817	G	7414	10400325	MAGNETO         	BENDIX      		CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					ENGINE	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	07	6341S		4    		L229702G	R18201662	L2270640A			CAM ASSY P/N 10-400167-13, HAS WOODRUFF KEY SLOT IN THE WRONG LOCATION.  IT CAUSED MAGNETO TO HAVE ZERO DEGREE LAG.  IMP	ULSE WOULD FIRE AT 23 DEGREES BTC.  COMPONENT P/N LW-785126-105-3000.					1	H	7	1 	3O	3	O		3A13    	E295
1998092500247	19980925	00247	SW  	1998	9	25	98ZZZX3475       	1	19980826	G	3244	850108	TIRE            	GOODYEAR    		GULSTM	500   	500S        	0141107	SW  										MLG	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	4QS	481  			43141279	17551				TIRE DEVELOPED SEVERE CORD SEPARATION, PRODUCED A BUBBLE ON OUTSIDE OF TIRE, AND HAD AIR BETWEEN THE PLYS.						1	H	7	2 	3O				6A1
1998092500248	19980925	00248	WP  	1998	9	25	98ZZZX3476       	1	19980731	G	3222	500644571	FORK            			DOUG  	DC3   	DC3C        	3021457	WP  										TAIL WHEEL	SEPARATED       	G	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	305SF	29857			32081	6208				ON 7-31-98, A DOUGLAS DC-3 AIRCRAFT SUSTAINED SUBSTANTIAL DAMAGE DURING LANDING AT ANCHORAGE, ALASKA.  THE PILOT REPORTE	D THAT DURING LANDING, THE TAIL WHEEL C ASTING SEPARATED, DRAGGING THE TAIL CONE AND DAMAGING THE TAIL CONE'S ATTACHMENT	 BULKHEAD.  THE TAIL WHEEL CASTING-YOKE LUG WERE BROKEN/CRACKED IN THE AIRFRAME ATTACH LUG.				2	L	7	2 	4R				A669
1998092500249	19980925	00249	WP  	1998	9	25	98ZZZX3477       	1	19980731	G	3222	5006445TT	FORK            			DOUG  	DC3   	DC3C        	3021457	WP  										TAIL WHEEL	BROKE           	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AL	05	305SF	29857			32081	6208				UPPER PIVOT POINT OF MAIN TAIL WHEEL FORK BROKE ON LANDING.						2	L	7	2 	4R				A669
1998092500250	19980925	00250	CE  	1998	9	25	98ZZZX3478       	1	19980721	G	5330	1700127	SKIN            			CESSNA	206   	U206G       	2073356	CE  										FUSELAGE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	756GF	1991 				U20604074				CORROSION UNDER THE VIBRATION ABSORBING PADS DUE TO WATER BEING TRAPPED WHERE THE BONDING OF THE PAD TO THE SKIN HAS FAI	LED.  SUBMITTER STATES THIS IS A COMMON PROBLEM WITH CESSNA AIRCRAFT.					1	H	7	1 	3O				A4CE
1998092500251	19980925	00251	SO  	1998	9	25	98ZZZX3479       	2	19980825	G	8530	636697	INTAKE SEAT     								CONT  	O520  	GTSIO520L   	17032	SO  					CYLINDER HEAD	MISMANUFACTURED 	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19		5    					2459448R			INTAKE SEAT P/N 636697 WOULD NOT REMAIN SEATED IN CYLINDER HEAD DURING 5-HOUR ENGINE RUN.  INSTALLED AS NEW FROM TELEDYN	E CONTINENTAL MOTORS.  MANUFACTURE DATE:  5-98.										3	O			E7CE
1998012900116	19980129	00116	EA  	1998	1	29	98ZZZX348        	2	19980106	G	8530	LW12427	CYLINDER        			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					NR 4	CRACKED         	H				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	11	31754	1546 				287890478	L2483336A			PILOT EXPERIENCED ROUGH ENGINE OPERATION AND RETURNED TO AIRPORT WITH UNEVENTFUL LANDING.  INSPECTION BY MAINTENANCE PER	SONNEL DISCOVERED NR 4 CYLINDER HAD ZERO COMPRESSION.  CYLINDER WAS REMOVED AND FORWARDED TO ENGINE OVERHAUL SHOP WHERE 	FURTHER INSPECTION REVEALED CYLINDER WAS CRACKED APPROXIMATELY HALF WAY AROUND CIRCUMFERENCE BETWEEN CYLINDER BORE TO HE	AD THREAD.  NO HISTORY OF OPERATIONAL PROBLEMS WITH EITHER THIS CYLINDER OR OTHERS MOUNTED TO THIS ENGINE.			1	L	7	1 	3O	3	O		2A13    	E286
1998092500252	19980925	00252	GL  	1998	9	25	98ZZZX3480       	4	19980902	G	6113	2250121	BULKHEAD        		22501233    	CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C214   	GL  	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	747BF					R18201581				NEW SPINNER BULKHEAD AND MOUNTING BRACKETS CRACKED AFTER 30.9 HOURS AFTER INSTALLATION.  REPLACED CRACKED PARTS, ALSO RE	PLACED SPINNER ASSY AND PROPELLER CYLINDER FOR WEAR.  REPLACED MOUNTING STUDS AND BOLTS.  CHECKED PROPELLER FOR BALANCE,	 CHECKED PROP SHAFT FOR RUN OUT AND CHECKED TRACK ON PROP, ALL CHECKED OKAY.  STILL EXPERIENCED CONSIDERABLE WOBBLING OF	 SPINNER.  ADDED NYLON TAPE TO PROP CYLINDER TO TIGHTEN FIT BETWEEN CYLINDER AND SPINNER INTERNAL BULKHEAD.  RUN-UP SHOW	ED SPINNER SMOOTH.		1	H	7	1 	3O			RT	3A13    		5	C	P7EA
1998092500253	19980925	00253	SO  	1998	9	25	98ZZZX3481       	2	19980824	G	8520	SA646277FF	TAPPET          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	6461F	235  				18264197	462906			FOUND METAL (FILINGS) IN ONE FILTER DURING ROUTINE OIL/FILTER CHANGE.  THEY APPEARED TO BE IRON.  UPON REMOVING, SEVERAL	 TAPPETS FROM ENGINE.  FOUND ALL FACES ON REMOVED TAPPETS TO BE DEEPLY SPALLED.					1	H	7	1 	3O	3	O	NT	TA13    	E273
1998092500254	19980925	00254	SO  	1998	9	25	98ZZZX3482       	2	19980824	G	8520	SA628488JQ	TAPPET          			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	SPALLED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	6461F	235  				18264197	462906			FOUND METAL (FILINGS) IN ONE FILTER DURING ROUTINE OIL/FILTER CHANGE.  THEY APPEARED TO BE IRON.  UPON REMOVING, SEVERAL	 TAPPETS FROM ENGINE.  FOUND ALL FACES ON REMOVED TAPPETS TO BE DEEPLY SPALLED.					1	H	7	1 	3O	3	O	NT	TA13    	E273
1998092500255	19980925	00255	SO  	1998	9	25	98ZZZX3483       	1	19980605	G	2842	6810102	FLOAT           			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					LT FUEL CELL	LOOSE           	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	423JW	2554 				327840163	L1825748A			PILOT REPORTED LEFT OUTBOARD FUEL GAUGE READ ZERO AT ALL TIMES.  FUEL WAS DRAINED FROM TANK TO ALLOW INSPECTION.  FLOAT 	(BLACK FOAM) WAS FOUND DETACHED DUE TO SEVERE WEAR.   THIS AREA CAN ONLY BE INSPECTED WITH TANKS DRAINED.  NEW SENDER WA	S INSTALLED.				1	L	7	1 	3O	3	O		A3SO    	1E4
1998092500256	19980925	00256	EA  	1998	9	25	98ZZZX3484       	2	19980603	G	7322	30766	FLOAT           			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CARBURETOR	FAILED          	B			MOGR	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	25	504MA	4784 	731  			17275917	L1256639A			PILOT REPORTED ENGINE RUNNING ROUGH.  FOUND FUEL DRIPPING FROM CARBURETOR HEAT BOX.  DISASSEMBLY OF CARBURETOR REVEALED 	BRASS FLOAT HAD LEAKED AND SUNK RESULTING IN EXTREME RICH MIXTURE.  REPLACED FLOAT ASSEMBLY.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998092500257	19980925	00257	EA  	1998	9	25	98ZZZX3485       	2	19980603	G	7322	233615	VALVE           	FACET       	MA4SPA      	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					CARBURETOR	CRACKED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	504MA	4784 	731  		CK818043	17275917	L1256639A			WHILE REPLACING FLOAT AND LEVER ASSY, FOUND RUBBER TIP OF FLOAT VALVE CRACKED AND DETERIORATED.  REPLACED UNIT.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998092500536	19980925	00536	NM  	1998	9	25	98ZZZX3486       	1	19980802	G	5315		FLOORBEAM       			BOEING	727   	727224      	1384076	NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED AFT RT LAVATORY AREA FLOORBEAM BOTTOM T-CHORD FS 1130 RBL 56.						2	L	7	3 	4F				A3WE
1998092500537	19980925	00537	NM  	1998	9	25	98ZZZX3487       	1	19980827	G	5313		STRINGER        			BOEING	727   	727224      	1384076	NM  										BS 1148	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON STRINGER 22L STA 1148.						2	L	7	3 	4F				A3WE
1998092500538	19980925	00538	NM  	1998	9	25	98ZZZX3488       	1	19980827	G	5240		HINGE           			BOEING	727   	727224      	1384076	NM  										SERVICE DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON AFT LAVATORY SERVICE DOOR UPPER AND LOWER HINGES.						2	L	7	3 	4F				A3WE
1998092500539	19980925	00539	NM  	1998	9	25	98ZZZX3489       	1	19980827	G	5320		SPLICE          			BOEING	727   	727224      	1384076	NM  										BS 1148-1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON STRINGER SPLICE STR 30 STA 1148 - STA 1166.						2	L	7	3 	4F				A3WE
1998092500540	19980925	00540	NM  	1998	9	25	98ZZZX3490       	1	19980827	G	5320		SUPPORT         			BOEING	727   	727224      	1384076	NM  										BS 312	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON FORWARD LAVATORY FLOOR SUPPORT APPROXIMATELY FS 312 JUST UNDER LAVATORY SINK CABI	NET.					2	L	7	3 	4F				A3WE
1998092500541	19980925	00541	NM  	1998	9	25	98ZZZX3491       	1	19980827	G	5210		FUSELAGE SKIN   			BOEING	727   	727224      	1384076	NM  										PASSENGER DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON SKIN OF R2 DOOR FORWARD OF UPPER HINGE						2	L	7	3 	4F				A3WE
1998092500542	19980925	00542	NM  	1998	9	25	98ZZZX3492       	1	19980827	G	5320		SUPPORT         			BOEING	727   	727224      	1384076	NM  										BS 312-344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON FLOOR SUPPORT FORWARD LAVATORY INBOARD WALL APPROXIMATELY RBL 15 STA 312 - STA 34	4.  (X)					2	L	7	3 	4F				A3WE
1998092500543	19980925	00543	NM  	1998	9	25	98ZZZX3493       	1	19980827	G	5210	65569924	SKIN            			BOEING	727   	727224      	1384076	NM  										PASSENGER DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719				BW222	20388				DURING C-CHECK, CORROSION WAS NOTED ON EXTERIOR SKIN OF R-2 DOOR (PILLOWING MANY AREAS AND POPPED RIVETS).						2	L	7	3 	4F				A3WE
1998092500544	19980925	00544	NM  	1998	9	25	98ZZZX3494       	1	19980827	G	5210		SKIN            			BOEING	727   	727224      	1384076	NM  										PASSENGER DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON SKIN OF 42 DOOR (LOWER HINGE).						2	L	7	3 	4F				A3WE
1998092500545	19980925	00545	NM  	1998	9	25	98ZZZX3495       	1	19980827	G	5330		SKIN            			BOEING	727   	727224      	1384076	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED UNDER L1 DOOR RAIN GUTTER.						2	L	7	3 	4F				A3WE
1998092500546	19980925	00546	NM  	1998	9	25	98ZZZX3496       	1	19980827	G	5311		FRAME           			BOEING	727   	727224      	1384076	NM  										BS 440	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED IN E/E COMPARTMENT FRAME 440 AT STR 27R.						2	L	7	3 	4F				A3WE
1998092500547	19980925	00547	NM  	1998	9	25	98ZZZX3497       	1	19980827	G	5320		SUPPORT         			BOEING	727   	727224      	1384076	NM  										BS 1130-1148	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON LT AFT LAVATORY ON FLOORBOARD SUPPORT LBL 15 FS 1130 - FS 1148.						2	L	7	3 	4F				A3WE
1998092500548	19980925	00548	NM  	1998	9	25	98ZZZX3498       	1	19980827	G	5315		FLOORBEAM       			BOEING	727   	727224      	1384076	NM  										BS 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON FLOORBEAM BOTTOM T-CHORD AROUND NUTPLATES FS 1110 APPROXIMATELY RBL 50.						2	L	7	3 	4F				A3WE
1998092500549	19980925	00549	NM  	1998	9	25	98ZZZX3499       	1	19980802	G	5330		SKIN            			BOEING	727   	727224      	1384076	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON EXTERIOR FUSELAGE ON PASSENGER WINDOW FRAME NR 35 BOTTOM AND FORWARD EDGES.						2	L	7	3 	4F				A3WE
1998012900118	19980129	00118	CE  	1998	1	29	98ZZZX350        	1	19980114	G	2434	318	ALTERNATOR      	FORD        		CESSNA	185   	A185F       	2072821	CE  										DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	4640E		563  		3061373	18503824				ALTERNATOR FAILED.  FOUND BRUSHES COMPLETELY WORN OUT.						1	H	7	1 	3O				3A24
1998092500550	19980925	00550	NM  	1998	9	25	98ZZZX3500       	1	19980827	G	5320		STRAP           			BOEING	727   	727224      	1384076	NM  										BS 1050-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED AFT GALLEY AREA.  LOWER T-CHORD STRAP FS 1050 - FS 1070 APPROXIMATELY RBL 24.						2	L	7	3 	4F				A3WE
1998092500551	19980925	00551	NM  	1998	9	25	98ZZZX3501       	1	19980827	G	5320		WEB             			BOEING	727   	727224      	1384076	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED ON SHEAR WEB AROUND SINK DRAIN AFT RT LAVATORY.						2	L	7	3 	4F				A3WE
1998092500552	19980925	00552	NM  	1998	9	25	98ZZZX3502       	1	19980827	G	5320		STRAP           			BOEING	727   	727224      	1384076	NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED AFT RT LAVATORY AREA BOTTOM T-CHORD OF FLOORBEAM ATTACH STRAP FS 1130 APROXIMATELY R	BL 20.					2	L	7	3 	4F				A3WE
1998092500553	19980925	00553	NM  	1998	9	25	98ZZZX3503       	1	19980827	G	5320		STRAP           			BOEING	727   	727224      	1384076	NM  										BS 1050-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED AFT GALLEY AREA ON FLOORBEAM LOWER T-CHORD STRAP APPROXIMATELY 45 RBL STA 1050 - 107	0.					2	L	7	3 	4F				A3WE
1998092500554	19980925	00554	NM  	1998	9	25	98ZZZX3504       	1	19980827	G	5347		SEAT TRACK      			BOEING	727   	727224      	1384076	NM  										BS 420-460	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	32719					20388				DURING C-CHECK, CORROSION WAS NOTED FORWARD LAVATORY/GALLEY AREA SEAT TRACK RBL 24 - FS 420 - FS 460.						2	L	7	3 	4F				A3WE
1998092500563	19980925	00563	SW  	1998	9	25	98ZZZX3509       	1	19980713	G	6310	2060401173	COUPLING        			BELL  	206   	206B        	1181511	SW  										M/R DRIVESHAFT	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718				A2031456	1917				COUPLING GEARS WORN BEYOND LIMITS.   REMOVED AND REPLACED.  NORMAL RUN-OUT.						1	G	7	1 	3U				H2SW
1998092500564	19980925	00564	SW  	1998	9	25	98ZZZX3510       	1	19980713	G	6310	2060401173	COUPLING        			BELL  	206   	206B        	1181511	SW  										M/R DRIVESHAFT	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718				A2031474	1917				COUPLING GEARS WORN BEYOND LIMITS.  REMOVED AND REPLACED.  NORMAL RUN-OUT.						1	G	7	1 	3U				H2SW
1998092500565	19980925	00565	WP  	1998	9	25	98ZZZX3511       	1	19980710	G	7714	369A45167	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW				1183	470117D				TACHOMETER NEEDLE HANGS AT BELOW 10 PERCENT.  REMOVED, REPLACED, SENT FOR REPAIR.						1	G	7	1 	3U				H3WE
1998092500566	19980925	00566	WP  	1998	9	25	98ZZZX3512       	1	19980710	G	7714	369H4551	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE N1	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW		540  		326	470117D				TACHOMETER HANGS UP ON START.  EPO BOX COMES ON AT START.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998092500575	19980925	00575	SW  	1998	9	25	98ZZZX3518       	1	19980807	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R DRIVE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	487AL				RNFS7748	53204				DURING 25 HOUR INSPECTION, FOUND GAP BETWEEN DISC NR 1 AND NR 2, NR 9 AND NR 10, EXCEED LIMITS.  (TOTAL NUMBER OF DISCS 	IN THE DISC PACK IS 10).					1	G	7	1 	3U			O	H2SW
1998092500576	19980925	00576	SW  	1998	9	25	98ZZZX3519       	1	19980807	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R DRIVESHAFT	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	487AL				RNFS7044	53204				DURING 25 HOUR INSPECTION, GAP BETWEEN DISCS NR 1 AND NR 2, NR 2 AND NR 3, OF THE 10-DISC PACK EXCEED LIMITS.						1	G	7	1 	3U			O	H2SW
1998012900120	19980129	00120	CE  	1998	1	29	98ZZZX352        	1	19980115	G	2434	318	ALTERNATOR      	FORD        		CESSNA	185   	A185F       	2072821	CE  										DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	61423		609  		5111176	18504180				ALTERNATOR FAILED.  FOUND BRUSHES COMPLETELY WORN OUT.						1	H	7	1 	3O				3A24
1998092500578	19980925	00578	SW  	1998	9	25	98ZZZX3521       	1	19980803	G	6510	406040340101	DISC            			BELL  	407   	407         		SW  										T/R DRIVE	WORN            	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	487AL				RNFS7660	53204				DURING 25 HOURS INSPECTION, FOUND GAP BETWEEN DISCS 9 AND 10 OF THE 10-DISC PACK EXCEED LIMITS.						1	G	7	1 	3U			O	H2SW
1998012900121	19980129	00121	CE  	1998	1	29	98ZZZX353        	1	19980109	G	3397		WIRE            			BEECH 	36    	A36         	1151604	CE  										NAV LIGHT	SHORTED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	72567	1272 				E2280				RT NAVIGATION LIGHT POWER WIRE ROUTED THROUGH WING ALONG CHANNEL UNDER TOP WING SKIN.  NOTHING TO SECURE WIRE IN PLACE A	ND NO CHAFE PROTECTION PROVIDED.  WIRE CAME OUT OF CHANNEL, CHAFED ON RIB EVENTUALLY CAUSING A SHORT AND BURNED WIRE IN 	TWO.  INSPECTION OF LT SIDE REVEALED SAME PROBLEM, BUT HAS NOT CHAFED THROUGH YET.  PROBLEM RESOLVED BY ADDING CHAFE PRO	TECTION AND RE-ROUTING WIRE.  THIS AREA CANNOT BE INSPECTED WITHOUT REMOVING WING TIP.			1	L	7	1 	3O			 	3A15
1998012900122	19980129	00122	CE  	1998	1	29	98ZZZX354        	1	19980115	G	2434	315	ALTERNATOR      	FORD        		CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  					DC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	86109		699  		5021026	18503153	293197R			ALTERNATOR QUIT WORKING.  FOUND BRUSHES TOTALLY WORN OUT.						1	H	7	1 	3O	3	O		3A24    	E5CE
1998100200033	19981002	00033	EU  	1998	10	2	98ZZZX3541       	1	19980904	G	5754	A5351027120000	SWIVEL          			AIRBUS	300   	A300B4*     		EU  										LE FLAP	SHEARED         	B			B39Y	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35					A53510200000	MSN173				DISCOVERED DURING KRUEGER FLAP REMOVAL FOR ACCESS DURING AIRCRAFT D-CHECK.  THE INBOARD OF THE TWO KEUGER FLAP ATTACHMEN	T BOLTS WAS FOUND TO HAVE SHEARED AT THE WASHER ABUTEMENT FLANGE.  SUBMITTER SUSPECTED THE WRONG THICKNESS OF WASHER FIT	TED (A300 IPC 27-81-03 FIG 13, ITEMS 150 TO 157), CAUSING NUT TO BE OVERTORQUED DURING COTTER PIN FIT.  THIS FACT IS NOT	 HIGHLIGHTED IN AMM 27-81-48 PAGE 401 PARA D (2) (KRUEGER FLAP REMOVAL/INSTALLATION).			2	L	7	2 	4F			RT	A35EU
1998100200034	19981002	00034	NE  	1998	10	2	98ZZZX3542       	3	19980813	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	03		4614 						HJ570		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FOUR CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998100200035	19981002	00035	SW  	1998	10	2	98ZZZX3543       	1	19980901	G	6320	476206283	BEARING         		4762060027  	BELL  	47    	47G3B1      	1181028	SW  										TRANSMISSION	MISINSTALLED    	B		A	ECGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	100VB				1131	3552				BEARING FAILED AFTER INCORRECT INSTALL.  INSP OF WHAT APPEARED TO BE EXCESS BACKLASH ON THE 47-620-497-1 FAN DRIVE GEAR 	ASSY.  UPON REMOVAL OF FAN DRIVE QUILL ASSY, NOTED NEW GEAR PATTERN AFT AND HIGH RUNNING OFF HEEL OF 530 GEAR.  UPON REM	OVAL OF CLUTCH, DETERMINED 47-620-628-3 DUPLEX BEARING SET FAILED DUE TO IMPROPER INSTALL WHEN NEW CLUTCH ASSY INSTALLED	 56.7 HRS PRIOR.  PER BELL TECH BULLETIN NR 47-75-4, REV A, PAGE 4 OF 4, FIG 4, DUPLEX BEARING SET IS TO BE INSTALLED WI	TH THRUST SIDE OF EACH BEARING OTBD AS WRITTEN ON BEARING RACE.  HOWEVER, BEARING SET HAD BEEN INSTALLED IN A TANDUM CON	FIG AND FAILED WITHIN 56.7 HOURS.  TRANS TSO:  165.1 HRS.  DUPLEX BEARING:  56.7 HRS SINCE INCORRECT ASSY AND INSTALL.	1	G	7	1 	3O				2H3
1998100200036	19981002	00036	EU  	1998	10	2	98ZZZX3544       	1	19980817	G	2913	704A34310006	PUMP            			SNIAS 	350   	AS350B      	8680801	EU  										HYDRAULIC	FAILED          	B			OF1R	A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	12J					1412				PILOT LOST HYDRAULIC PRESSURE IN-FLIGHT.  LANDED UNEVENTFULLY AT WILMINGTON AIRPORT.  INVESTIGATION FOUND HYDRAULIC PUMP	 SEIZED AND SHAFT SHEARED.					1	G	7	1 	3U				H9EU
1998100200037	19981002	00037	GL  	1998	10	2	98ZZZX3545       	2	19980713	G	7230	23057142	CASE HALVES     			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DAMAGED         	B			HDNR	A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			SW	03	911HR		290  		16266	S646	CAE835324			FAILURE OF THE STATOR CAUSED A COMPRESSOR FAILURE RESULTING IN LOSS OF POWER ON THE ENGINE.  A SINGLE ENGINE LANDING WAS	 ACCOMPLISHED WITH NO FURTEHR INCIDENT.					1	G	7	2 	3U	3	U	NC	H3EU    	E4CE
1998100200038	19981002	00038		1998	10	2	98ZZZX3546       	4	19980713	G	2312	KY195B	TRANSCEIVER     			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J	1150 			5299	900801D				VOLUME CONTROL NOT WORKING.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100200039	19981002	00039		1998	10	2	98ZZZX3547       	4	19980713	G	2312	KY195B	TRANSCEIVER     			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	1097J		4    		9543	900801D				RADIO RECEIVES GARBLED.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100200040	19981002	00040	SW  	1998	10	2	98ZZZX3548       	1	19980710	G	6310	204040620003	DRIVESHAFT      			BELL  	204   	UH1H        	1181407	SW  										TAIL ROTOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	51AG				AM205879	7120178				BALANCED WEIGHT NOT INSTALLED.  DRIVESHAFT WAS REPLACED.						1	G	7	1 	4U				EXPA1G71
1998100200041	19981002	00041	SW  	1998	10	2	98ZZZX3549       	1	19980710	G	6220	CSC5204	DAMPER          			BELL  	204   	UH1H        	1181407	SW  										MAIN ROTOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG				A21381	7221588				SIGHT GLASS CLOUDY.  REMOVED AND REPLACED.						1	G	7	1 	4U				EXPA1G71
1998012900123	19980129	00123		1998	1	29	98ZZZX355        	4	19980121	G	3416	5035P2	ALTIMETER       	UNITEDINST  																ENCODER MESH	BINDING         	B			EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15					20110					WHEN RECEIVED, THIS ALTIMETER WAS STUCK AT 7,000 FEET.  DISASSEMBLY REVEALED 2 CONDITIONS THAT CAUSED THE HANG-UP PROBLE	M.  THE ENCODER MESH WAS BINDING AND THERE WAS NO END SHAKE IN THE ROCKING SHAFT.  THE MOUNTING CONFIGURATION FOR THE EN	CODER IS INADEQUATE FOR SUPPORTING THE GEAR MESH ACCURATELY.  THE MECHANISM CASTING IS UNSTABLE WHICH ALLOWS THE END SHA	KES ON THE CRITICAL SHAFTS TO CLOSE IN.  NOTE:  THIS WAS A FACTORY SEALED ALTIMETER.
1998100200042	19981002	00042	SW  	1998	10	2	98ZZZX3550       	1	19980710	G	3340		GEAR            			BELL  	204   	UH1H        	1181407	SW  										LIGHT	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				GEAR ON MOTOR SHAFT HAS WORN BUSHING ALLOWING GEAR TO DIS-ENGAGE FROM LIGHT GEAR.  REMOVED AND REPLACED.						1	G	7	1 	4U				EXPA1G71
1998100200043	19981002	00043	SW  	1998	10	2	98ZZZX3551       	1	19980710	G	6220	SGT5206	DAMPER          			BELL  	204   	UH1H        	1181407	SW  										MAIN ROTOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG				16685	7221588				SIGHT GLASS CLOUDY.  REMOVED AND REPLACED.						1	G	7	1 	4U				EXPA1G71
1998100200044	19981002	00044	SW  	1998	10	2	98ZZZX3552       	1	19980901	G	5302	206033004177	SKIN            			BELL  	206   	206L4       	1182110	SW  										TAIL BOOM	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	802DS	2228 			52052	52052				CRACK FOUND ACROSS TOP SKIN BETWEEN HORIZONTAL STABILIZER.						1	G	7	1 	3U			NC	H2SW
1998100200045	19981002	00045	SW  	1998	10	2	98ZZZX3553       	1	19980825	G	2910	1560038D0106	HOSE            	STRATOFLEX  		BELL  	206   	206L3       	1182108	SW  										HYDRAULIC SYSTEM	FAILED          	B		A	GFLR	A	B			UNSCHED LANDING         	EMER. DESCENT           			F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			NM	13	868H	1938 				51318				THE AIRCRAFT EXPERIENCED A TOTAL HYDRAULIC FAILURE IN-FLIGHT.  THE PILOT MADE AN EMERGENCY LANDING WITHOUT INCIDENT.  TH	E HYDRAULIC SYSTEM WAS INSPECTED AND IT WAS DETERMINED THAT THE SUCTION LINE FROM THE RESERVOIR TO THE HYDRAULIC PUMP HA	D FAILED INTERNALLY.  THERE WERE NO VISIBLE DEFECTS ON THE OUTSIDE OF THE LINE.  THERE WAS NO HYDRAULIC FLUID LEAKING FR	OM THE LINE ON PRE-FLIGHT.			1	G	7	1 	3U				H2SW
1998100200046	19981002	00046	SW  	1998	10	2	98ZZZX3554       	1	19980713	G	2432	RG206	BATTERY         			BELL  	206   	206B        	1181511	SW  										FUSELAGE	OVERHEATED      	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	90322				R32718	1736				BATTERY OVERHEATED.  VOTLAGE REGULATOR WAS OUT OF ADJUSTMENT.  ADJUSTED VOLTAGE REGULATOR AND REPLACED BATTERY.						1	G	7	1 	3U				H2SW
1998100200047	19981002	00047	SW  	1998	10	2	98ZZZX3555       	1	19980713	G	2432		BATTERY         		RG206       	BELL  	206   	206B        	1181511	SW  										FUSELAGE	DISCHARGED      	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K				R36025	2040				BATTERY WILL NOT CRANK AIRCRAFT PAST 12 PERCENT N1.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1998100200050	19981002	00050	SO  	1998	10	2	98ZZZX3556       	1	19980824	G	2510	510232826	BRACKET         			GULSTM	AA5   	AA5B        	3960105	SO  										PILOT'S SEAT	BROKEN          	H	S	A		O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			WP	09										DURING LANDING APPROACH, BACK OF PILOT'S SEAT BROKE LOOSE.  LANDING WAS MADE WITHOUT INCIDENT.  SEAT BACK BRACKET ON RIG	HT SIDE OF PILOT'S SEAT (P/N 5102328-26) HAD BROKEN CLEAN THROUGH.  EXAMINATION INDICATED PART HAD PREVIOUSLY BEEN CRACK	ED AND FINALLY PARTED.  SUBMITTER RECOMMENDED SEAT BRACKETS BE PERIODICALLY INSPECTION.				1	L	7	1 	3O				A16EA
1998100200051	19981002	00051	EA  	1998	10	2	98ZZZX3557       	2	19980718	G	8530	LW13428	PUSHROD SPRING  			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A2B     	41508	EA  					CYLINDER HEAD	BROKEN          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4860A	150  				224019	319927			PILOT NOTED THE ENGINE WOULD MISS THEN RUN.  PILOT MADE PRECAUTIONARY LANDING.  THE VALVE COVER ON CYLINDER NR 2 HAD A H	OLE IN IT.  INVESTIGATION SHOWED THE PUSHROD TUBE SPRING LYC P/N LW14995 BROKE AND SEPARATED AT THE HOLE FOR THE HOLD-DO	WN STUD.  THE BROKEN PART JAMMED BETWEEN THE VALVE COVER AND THE INTAKE VALVE CAUSING THE ENGINE TO MISS.  INSPECTION OF	 THE REMAINING 3 CYLINDERS REVEALED ALL 4 OF THE LW13428 LOCKPLATES WERE CRACKED OR BROKEN.  THE PARTS HAD A TT OF 150 H	RS AND WERE PLACED IN SERVICE 3-14-94.  THIS INVESTIGATION IS ONGOING.		1	H	7	1 	3O	3	O		1A6     	E274
1998100200052	19981002	00052	EA  	1998	10	2	98ZZZX3558       	2	19980821	G	8530	LW12416	CYLINDER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG CYL NR 4	MISMANUFACTURED 	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	9621V				A264616	17264401	L3469527A			ENGINE L-34695-27A O/H BY TEXTRON LYC 11-8-97.  INSTALLED 2-20-98.  FOLLOWING TEST FLIGHT AND BREAK-IN,  ACFT RELEASED F	OR FLIGHT TRAINING.  AT ENG SMOH 16.8 HRS ON TAKEOFF, A LOSS OF RPM AND DEGRADED CLIMB PERFORMANCE REQUIRED IMMEDIATE RE	TURN.  SUBMITTER STATED THE DEFECT THAT CAUSED LOW POWER WAS 4 MISMFG'D CYLINDERS.  THEY WERE NEW LYC CYLS P/N LW 12416 	THAT DID NOT HAVE INTERNAL INTAKE PORTS RADIUSED.  WHEN AMBIENT TEMP AND DENSITY ALTITUDE INCREASED WITH ONSET OF A HOT 	SUMMER DAY,  CYLS CAUSED ENG TO RUN ROUGH AND LOSE POWER.  FOUR NEW LYC FURNISHED CYLINDERS P/N LW 12416 WERE INSTALLED 	WITH PROPER RADIUS OF THE INTERNAL INTAKE PORTS.  SUBSEQUENT OPER HAS BEEN SATISFACTORY WITH THE ACCUMULATION OF 98 HRS	1	H	7	1 	3O	3	O	NT	3A12    	E274
1998100200053	19981002	00053	EA  	1998	10	2	98ZZZX3559       	2	19980821	G	8530	LW12416	CYLINDER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG CYL NR 3	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	9621V				A268612	17264401	L3469527A			ENGINE L-34695-27A O/H BY TEXTRON LYC 11-8-97.  INSTALLED 2-20-98.  FOLLOWING TEST FLIGHT AND BREAK-IN,  ACFT RELEASED F	OR FLIGHT TRAINING.  AT ENG SMOH 16.8 HRS ON TAKEOFF, A LOSS OF RPM AND DEGRADED CLIMB PERFORMANCE REQUIRED IMMEDIATE RE	TURN.  SUBMITTER STATED DEFECT THAT CAUSED LOW POWER WAS 4 MISMFG'D CYLINDERS.  THEY WERE NEW LYC CYLS P/N LW 12416 THAT	 DID NOT HAVE INTERNAL INTAKE PORTS RADIUSED.  WHEN AMBIENT TEMP AND DENSITY ALTITUDE INCREASED WITH ONSET OF A HOT SUMM	ER DAY,  CYLS CAUSED ENG TO RUN ROUGH AND LOSE POWER.  FOUR NEW LYC FURNISHED CYLINDERS P/N LW 12416 WERE INSTALLED WITH	 PROPER RADIUS OF THE INTERNAL INTAKE PORTS.  SUBSEQUENT OPER HAS BEEN SATISFACTORY WITH THE ACCUMULATION OF 98 HRS SMOH	1	H	7	1 	3O	3	O	NT	3A12    	E274
1998100200054	19981002	00054	EA  	1998	10	2	98ZZZX3560       	2	19980821	G	8530	LW12416	CYLINDER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG CYL NR 2	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	9621V				A263611	17264401	L3469527A			ENGINE L-34695-27A O/H BY TEXTRON LYC 11-8-97.  INSTALLED 2-20-98.  FOLLOWING TEST FLIGHT AND BREAK-IN,  ACFT RELEASED F	OR FLIGHT TRAINING.  AT ENG SMOH 16.8 HRS ON TAKEOFF, A LOSS OF RPM AND DEGRADED CLIMB PERFORMANCE REQUIRED IMMEDIATE RE	TURN. SUBMITTER STATED DEFECT THAT CAUSED LOW POWER WAS 4 MISMFG'D CYLINDERS.  THEY WERE NEW LYC CYLS P/N LW 12416 THAT 	DID NOT HAVE INTERNAL INTAKE PORTS RADIUSED.  WHEN AMBIENT TEMP AND DENSITY ALTITUDE INCREASED WITH ONSET OF A HOT SUMME	R DAY,  CYLS CAUSED ENG TO RUN ROUGH AND LOSE POWER.  FOUR NEW LYC FURNISHED CYLINDERS P/N LW 12416 WERE INSTALLED WITH 	PROPER RADIUS OF THE INTERNAL INTAKE PORTS.  SUBSEQUENT OPER HAS BEEN SATISFACTORY WITH THE ACCUMULATION OF 98 HRS SMOH.	1	H	7	1 	3O	3	O	NT	3A12    	E274
1998100200055	19981002	00055	EA  	1998	10	2	98ZZZX3561       	2	19980521	G	8530	LW12416	CYLINDER        			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG CYL NR 1	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	9621V				A267611	17264401	L3469527A			ENGINE L-34695-27A O/H BY TEXTRON LYC 11-8-97.  INSTALLED 2-20-98.  FOLLOWING TEST FLIGHT AND BREAK-IN,  ACFT RELEASED F	OR FLIGHT TRAINING.  AT ENG SMOH 16.8 HRS ON TAKEOFF, A LOSS OF RPM AND DEGRADED CLIMB PERFORMANCE REQUIRED IMMEDIATE RE	TURN. SUBMITTER STATED DEFECT THAT CAUSED LOW POWER WAS 4 MISMFG'D CYLINDERS.  THEY WERE NEW LYC CYLS P/N LW 12416 THAT 	DID NOT HAVE INTERNAL INTAKE PORTS RADIUSED.  WHEN AMBIENT TEMP AND DENSITY ALTITUDE INCREASED WITH ONSET OF A HOT SUMME	R DAY,  CYLS CAUSED ENG TO RUN ROUGH AND LOSE POWER.  FOUR NEW LYC FURNISHED CYLINDERS P/N LW 12416 WERE INSTALLED WITH 	PROPER RADIUS OF THE INTERNAL INTAKE PORTS.  SUBSEQUENT OPER HAS BEEN SATISFACTORY WITH THE ACCUMULATION OF 98 HRS SMOH.	1	H	7	1 	3O	3	O	NT	3A12    	E274
1998100200056	19981002	00056	SO  	1998	10	2	98ZZZX3562       	1	19980714	G	2912	46D635AN62341	FILTER          			PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC SYSTEM	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AL	03	76RA	6898 				317752089				HYDRAULIC FILTER ASSY CUP CRACKED AT THREADS ON RT ENGINE.  MOST FLUID LOST.  GEAR HAD TO BE PUMPED DOWN BY HAND.  RT EN	GINE DRIVEN PUMP ALSO FAILED SEVERAL HOURS LATER.  SUSPECT FROM LACK OF FLUID.					1	L	7	2 	3O				A20SO
1998100200057	19981002	00057	SO  	1998	10	2	98ZZZX3563       	1	19980819	G	3230	6701200	TORQUE LINK     		6792703     	PIPER 	PA28  	PA28R180    	7102809	SO  										RT MLG	SEIZED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3299R					28R31270				A POST-FLIGHT INSPECTION REVEALED NUMEROUS RIVETS PULLED THROUGH THE SKIN ABOVE THE RT MLG, AND A CRACK IN THE WING SKIN	.  UPON REMOVAL OF THE SKIN, THE WING RIB OTBD OF THE LANDING GEAR WAS ALSO FOUND CRACKED.  WHEN THE LANDING GEAR WAS RE	MOVED TO FACILITATE THE REPAIR, MAINTENANCE PERSONNEL FOUND THE STRUT WOULD NOT COMPRESS WHEN IT WAS DEFLATED.  FURTHER 	INVESTIGATION REVEALED THE TORQUE LINKS WERE FROZEN DUE TO A LACK OF LUBRICATION.  SUBMITTER STATES ADHERING TO THE MANU	FACTURER'S LUBRICATION RECOMMENDATIONS SHOULD PREVENT OCCURRENCES LIKE THIS.		1	L	7	1 	3O				2A13
1998100200058	19981002	00058	CE  	1998	10	2	98ZZZX3564       	1	19980603	G	5320	051212443	SPAR            			CESSNA	172   	172G        	2072420	CE  										FUSELAGE	CORRODED        	C		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	3732L	2300 				17253901				THE ACFT HAS BEEN OUTSIDE ON A TIE-DOWN FOR MANY YEARS.  DURING THE ANNUAL INSPECTION, NOTED THAT PITTING CORROSION WAS 	ACTIVE ON THE REAR SPAR CARRY-THROUGH EVIDENCED BY ITS WHITE POWDER APPEARANCE.   THE LEADING EDGE OF THE SPAR CHANNEL H	AD EVIDENCE IN THE AREA AS MOISTURE HAD ENTERED THE CHANNEL VIA THE HEADLINER.  THE INTERNAL SPAR CORROSION CAN ONLY BE 	SEEN WHEN THE WINGS ARE REMOVED AS IN THIS INSTANCE.  SUBMITTER RECOMMENDED THE L/E OF THE SPAR CHANNEL BE SEALED WITH A	 NON-ACIDIC-CURING TYPE PRODUCT TO PREVENT MOISTURE FROM ENTERING THIS AREA.		1	H	7	1 	3O			NT	3A12
1998100200059	19981002	00059	SO  	1998	10	2	98ZZZX3565       	1	19980817	G	3250	9555123	BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  										NLG	CRACKED         	H		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	9573C					347870198				THE LOWER RETAINING BRACKET FOR THE STEERING ARM ASSY P/N 95395-00 IS CRACKED ALONG WELD.  THIS ALLOWS STEERING ARM ASSY	 TO BE PUSHED OUT OF POSITION DURING GEAR EXTENSION AND RETRACTION.					1	L	7	2 	3O				A7SO
1998100200060	19981002	00060	EA  	1998	10	2	98ZZZX3566       	2	19980810	G	7414	M3333	IMPULSE COUPLING	SLICK       	6351        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					MAGNETO	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8127K	97   			96030011	327940268	L2070048A			SUBMITTER FOUND IMPULSE COUPLING RETAINER NUT LOOSE ON SHAFT WITH COTTER PIN STILL IN PLACE.  THE IMPULSE ASSY COULD BE 	PULLED FROM TAPERED SHAFT WITH ONLY SLIGHT PRESSURE.  A BLUEING COMPOUND WAS APPLIED TO THE TAPERED SHAFT AND THE IMPULS	E ASSY WAS RESEATED.  IT WAS FOUND THE SHAFT HAD A HIGH AREA THAT WOULD NOT ALLOW THE IMPULSE ASSY TO SEAT PROPERLY.  A 	DIAL INDICATOR READING SHOWED APPROX .002 INCH - .003 INCH HIGH AREA IN A SEMI-CIRCLE SHAPE EXTENDING FROM THE KEY SLOT 	ABOUT .3750 INCH HIGH AROUND SHAFT TAPER.   SECOND INSTANCE FOUND OF AN IMPULSE ASSY LOOSENING ON SHAFT WITH LESS THAN 1	00 HRS IN SERVICE.  SUBMITTER RECOMMENDED TO SET ASSY WITH NUT TORQUE, REMOVE NUT AND TEST FIT BY PULLING WITH PULLER.	1	L	7	1 	3O	3	O		A3SO    	1E4
1998100200061	19981002	00061	EA  	1998	10	2	98ZZZX3567       	2	19980806	G	7414	M3333	IMPULSE         	SLICK       	6351        	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					LT MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8127Q	592  			96010052	327940269	L1396448A			ACCOMPLISHED INSPECTION OF MAG IMPULSE COUPLING AND FOUND EVIDENCE OF EXCESSIVE WEAR ON COILED SPRING ASSEMBLY.  OBSERVE	D WEAR OF PAWL AT PIN LOCATION AND NOT MEETING CORRECT MEASUREMENT CRITERIA AS APPLIED UTILIZING SLIDE TOOL T-155 RIVET 	GAUGE.				1	L	7	1 	3O	3	O		A3SO    	1E4
1998100200062	19981002	00062	CE  	1998	10	2	98ZZZX3568       	1	19980717	G	2720	1260U563	PEDAL           			CESSNA	206   	U206F       	2073333	CE  										LT TORQUE TUBE	BROKEN          	B	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	7487Q	2047 			ABC139720	U20602221				LEFT HAND VERTICAL STABILIZER FOR LT/PILOT'S RUDDER PEDAL BROKE OUT OF TORQUE TUBE AT WELD.						1	H	7	1 	3O				A4CE
1998100200063	19981002	00063	CE  	1998	10	2	98ZZZX3569       	1	19980713	G	3211	12116011	FITTING         			CESSNA	206   	U206G       	2073356	CE  										LT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5200X	8560 				U20605591				LT MLG FITTINGS CRACKED, BUSH OPERATIONS.						1	H	7	1 	3O				A4CE
1998012900125	19980129	00125	SO  	1998	1	29	98ZZZX357        	2	19980116	G	8530		SPRING SEAT     			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENG EXH VALVE	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	6822U					414A0808	R519904			REMOVED ROCKER COVER TO INSPECT FOR AD APPLICABILITY AND FOUND PARTICLES OF SPRING SEAT LAYING IN BOTTOM OF ROCKER COVER	.  DISASSEMBLED EXHAUST VALVE SPRING.  FOUND SEAT BROKEN AROUND INNER RADIUS.  SUBMITTER STATED EXHAUST VALVE GUIDE APPE	ARED TO BE .0625 INCH FARTHER OUT OF HEAD THAN REQUIRED.  APPEARED AS IF VALVE GUIDE HAD WORKED LOOSE IN HEAD.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1998100200064	19981002	00064	CE  	1998	10	2	98ZZZX3570       	1	19980713	G	3211	1211602	FITTING         			CESSNA	206   	U206G       	2073356	CE  										RT MLG	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5200X	8560 				U20605591				FITTINGS CRACKED, BUSH OPERATIONS.						1	H	7	1 	3O				A4CE
1998100200067	19981002	00067	EU  	1998	10	2	98ZZZX3572       	1	19980825	G	4990	T62T40C	OIL TANK        			BRAERO	DH125 	BAE125800A  	1500285	EU  										APU BAY	CHAFED          	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	484RA	2257 				25803				THE TOP OF THE APU OIL SUMP TANK HAD A HOLE CHAFED THROUGH CAUSED BY LACK OF CLEARANCE BETWEEN THE OIL SUMP TANK AND THE	 ENGINE MOUNT BEAM SHEET METAL.  REMOVED SHEET METAL INTERFERENCE.					2	L	7	2 	4F			RT	A3EU
1998100200068	19981002	00068	EU  	1998	10	2	98ZZZX3573       	1	19980825	G	5751	258WG101	AILERON         			BRAERO	DH125 	BAE125800A  	1500285	EU  										LT WING	CORRODED        	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	5G	4129 				258053				WATER INGRESS FOUND IN THE LT AILERON DURING A 48 MONTH X-RAY INSPECTION.  UPON REPAIRING AILERON PER RAYTHEON R.I.L. DR	AWING, WATER WAS NOT FOUND, HOWEVER, CORROSION IN THE HONEYCOMB AND PITTING ON THE LOWER AILERON SKIN WAS FOUND.  X-RAYS	 TAKEN PER THE NDT INSPECTION MANUAL WERE FOLLOWED AND LOWER SKIN CORROSION WAS NOT DETECTED.  SUGGEST THAT AN ALTERNATE	D METHOD OF CORROSION DETECTION BE FOUND.			2	L	7	2 	4F			RT	A3EU
1998100200069	19981002	00069	EU  	1998	10	2	98ZZZX3574       	1	19980825	G	5751	258WG101	AILERON         			BRAERO	DH125 	BAE125800A  	1500285	EU  										LT WING	CORRODED        	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330X	4563 				258060				WATER INGRESS FOUND IN THE LT AILERON DURING A 48 MONTH X-RAY INSPECTION.  UPON REPAIR PER RAYTHEON R.I.L. DRAWING, WATE	R WAS NOT FOUND AS INDICATED BY THE X-RAY.  CORROSION WAS FOUND IN THE HONEYCOMB AND ON THE LOWER SKIN OF THE AILERON. P	ITTING IN ONE AREA HAD ADVANCED THROUGH THE LOWER AILERON SKIN.  THE REPAIR WAS COMPLETED PER RAYTHEON DRAWINGS.  X-RAYS	 PER THE RAYTHEON NON-DISTRUCTIVE MANUAL ARE NOT INDICATING THE PRESENCE OF CORROSION IN THE AILERONS.  SUGGEST ALTERNAT	E METHOD OF CORROSION DETECTION.		2	L	7	2 	4F			RT	A3EU
1998100200070	19981002	00070	SO  	1998	10	2	98ZZZX3575       	1	19980908	G	7820	84030114	MUFFLER         			GULSTM	G1159 	GIV         	3980115	SO  										LT ENGINE	CRACKED         	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	79RP	3688 			557A	1220				ACOUSTICAL MUFFLER DEVELOPED A CRACK DUE TO POSSIBLE EXCESSIVE VIBRATION.  RECOMMENDATION TO PREVENT RECURRENCE IS TO SH	OCK MOUNT THE COMPONENT.					2	L	7	2 	4F			RT	A12EA
1998100200071	19981002	00071	EU  	1998	10	2	98ZZZX3576       	1	19980826	G	3230	KY10093	LEVER           			ISRAEL	1124  	1124        	4500102	EU  										COCKPIT	STUCK           	B			BTVR	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	23	140VJ					435				BIV - FLT 407498 - ATTEMPTED SELECTION OF GEAR UP, LANDING GEAR SELECTOR HANDLE JAMMED IN THE GEAR DOWN POSITION.  FLIGH	T CREW MADE 2ND ATTEMPT TO SELECT GEAR UP, AND AN INSTRUMENT SCREW FELL OUT OF GEAR SELECTOR LEVER SLOT IN THE FACE OF T	HE INSTRUMENT PANEL.  GEAR HANDLE WAS THEN FREE TO MOVE, AND GEAR SELECTED UP.  GEAR RETRACTED NORMALLY.  ACFT LANDED (L	ANDING GEAR OPERATED NORMALLY).  ACFT FERRIED TO PTK.  LANDING GEAR WAS OPERATED THROUGH 6 CYCLES WITH NO  EFECTS.  SCRE	W REINSTALLED WITH A LOCK WASHER.		2	M	7	2 	4F				A2SW
1998100200072	19981002	00072	NM  	1998	10	2	98ZZZX3577       	1	19980911	G	5711		FASTENERS       			BOEING	727   	727254      	138408L	NM  										RT WING	LOOSE           	B			XE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	912TS					20438				LOOSE FASTENERS AT RT WING FRONT SPAR UPPER CHORD.  WS 330.5.						2	L	7	3 	4F				A3WE
1998100200074	19981002	00074	SW  	1998	10	2	98ZZZX3579       	1	19980817	G	2710	2770001019	CONTROL CABLE   			SWRNGN	SA227 	SA227AC     	8780603	SW  										YOKE	MISINSTALLED    	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	781C	1993 				AC535				DURING PHASE NR 1 ENGINE RUN, NOTICED A SLIGHT GRINDING NOISE WHEN PILOT'S CONTROL WHEEL WAS TURNED LT OR RT.  A SLIGHT 	AMOUNT OF 'RATCHETING' COULD ALSO BE FELT IN THE WHEEL.  BEYOND THAT, THE CONTROL WHEEL MOVED FREELY WITH NO BINDING.  A	FTER REMOVING PILOT'S CONTROL WHEEL AND UPPER YOKE ASSY, DISCOVERED THE AILERON CONTROL CABLE HAD BEEN MISROUTED.  TWO C	ABLES WERE ROUTED THROUGH ONE PULLEY AND WERE RUBBING AGAINST EACH OTHER.  SUBMITTER STATED PROPER INSTALLATION SHOULD H	AVE ONE CABLE PASSING AFT OF PULLEY AND NOT IN PULLEY GROOVE.		2	L	7	2 	4T			RT	A8SW
1998100200075	19981002	00075	CE  	1998	10	2	98ZZZX3580       	1	19980908	G	7920		LINE            			BEECH 	58    	58P         	1152744	CE  										RT/LT WINGS	CHAFED          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	3RS	3623 				TJ102				ON REMOVING INBOARD SECTION OF LEADING EDGE TO REPLACE MIXTURE CONTROL CABLE ON LEFT SIDE, FOUND OIL PRESSURE LINE WORN 	OVER HALF WAY THROUGH WHERE LINE WAS RUBBING ON NOSE RIB FLANGE ON LEADING EDGE.  REMOVED RT SIDE AND FOUND OIL LINE ON 	THAT SIDE RUBBING ALSO.  SUBMITTER STATED LINES SHOULD BE REPOSITIONED FOR CLEARANCE.				1	L	7	2 	3O				A23CE
1998100200076	19981002	00076	NM  	1998	10	2	98ZZZX3581       	1	19980904	G	2120	27521	FILTER          		2673        	BOEING	767   	767         	1385102	NM  										AIR DISTRIBUTION	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23					567					MALFUNCTION WAS CAUSED BY THE FAILURE OF AN EMI FILTER CAPACITOR.  A SB WAS ISSUED TO CHANGE OLD STYLE FILTER TO THE NEW	 REPLACEMENT MODEL.  SUBMITTER STATED THIS INCIDENT IS THE THIRD KNOWN INCIDENT OF OVER 4,500 UNITS IN OPERATION.					2	L	7	2 	4F				EXPA2L72
1998100200078	19981002	00078	CE  	1998	10	2	98ZZZX3583       	1	19980817	G	5320	2005052	ANCHOR          			CESSNA	500   	500CESSNA   	2076602	CE  										FUSELAGE	CORRODED        	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	62BR	6285 				5000093				ALL 8 P/N 20050 ANCHOR PLATES INSTALLED ON THE VERTICAL REAR PRESSURE BULKHEAD INSIDE CABIN WERE SEVERELY CORRODED AND E	XFOLIATED.  THE WINDOW SHADE RAILS AND HEADLINER ALIGNMENT RAILS WERE ALSO CORRODED ALTHOUGH NOT AS SEVERELY.  THIS COND	ITION IS USUALLY ENCOUNTERED WHEN AN 'UTLTRA-SUEDE' HEADLINER AND SIDE PANELS HAVE BEEN PREVIOUSLY INSTALLED.  IT WOULD 	APPEAR TO BE RELATED TO THE FIREPROOFING CHEMICALS USED ON THE FABRIC.  THE CORROSION IS ISOLATED TO AREAS TOUCHING THE 	FABRIC.  THE AIRFRAME ITSELF IS NOT CORRODED.		1	L	7	2 	4F				A22CE
1998100200079	19981002	00079	NM  	1998	10	2	98ZZZX3584       	1	19980814	G	7920	1339M69401	SWITCH          			BOEING	747   	74745E      	1384947	NM  										ENGINE OIL	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	03	406EV					27898				FAILED TO SECURE THE TUBE B-NUT OF ENGINE LOW OIL PRESSURE SWITCH IN ENGINE SHOP THAT CAUSED NR 2 ENGINE OIL LEAK AND OI	L QUANTITY DROP DOWN TO 4 QUARTS AND PILOT SHUT DOWN NR 2 ENGINE DURING FLIGHT ROUTE OF SFO/TPE, ON 8-14-98.  SUBMITTER 	SUGGESTED SECURING AND DOUBLECHECKING ALL B-NUTS OF TUBE BEFORE ENGINE SHOP-OUT.				2	L	7	4 	4F			RT	A20WE
1998100200080	19981002	00080	EA  	1998	10	2	98ZZZX3585       	2	19980820	G	7250		BEARING         			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  					TURBINE	FAILED          	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	25	603PA					LJ403	PCE21765			IN-FLIGHT, ENGINE POWER LOSS.  LT ENGINE SLOWED AND LOST POWER.  PILOT FEATHERED PROPELLER.  FLIGHT LANDED WITHOUT INCID	ENT.  ENGINE REMOVED.  ENGINE, SN PCE21765, PT6A-20, DISASSEMBLED.  BEARING NR 2 FOUND FAILED.  BEARING EXAMINED FOR LUB	RICATION STARVATION.  NO EVIDENCE OF LACK OF LUBRICATION.  ENGINE TOTAL TIME AT FAILIURE 11,445.0 HOURS.  TIME SINCE ENG	INE OVERHAUL 2,725.4 HOURS.  BEARING TIME UNKNOWN.			1	L	7	2 	3T	3	T		3A20    	E4EA
1998100200082	19981002	00082	WP  	1998	10	2	98ZZZX3587       	1	19980828	G	5711	ARB26062	SPAR            			DOUG  	DC10  	DC1030F     	3023504	WP  										RT WING	CORRODED        	B			MZAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	321FE					47836				RT WING UPPER SURFACE JUST INBOARD AND FORWARD OF NR 2 SPOILER HAS CORROSION THAT RUNS FROM (XORS 480) TO (XORS 492).  R	EPAIR WAS C/W BY DOUGLAS PROVIDED E.A.  NOTE:  MAXIUM DEPTH OF CORROSION WAS .050 INCH.					2	L	7	3 	4F			RT	A22WE
1998100200083	19981002	00083	SW  	1998	10	2	98ZZZX3588       	1	19980420	G	2120	57033	BLOWER          			GULSTM	560   	560         	0141402	SW  										AIR DISTRIBUTION	INOPERATIVE     	B			BXSR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	500UB	3080 			1040	5600052				BLOWER MOTOR FAILED BEFORE ITS 3,500 HOUR TBO.  THIS BLOWER CLEARS THE WINDSHIELD AND COCKPIT SIDE WINDOWS ON THE INSIDE	.					1	H	7	2 	3O				6A1
1998100200084	19981002	00084	CE  	1998	10	2	98ZZZX3589       	1	19980713	G	2612	24403915	SENSOR          	EDISON      		LEAR  	35    	35A         	5170602	CE  										LT ENGINE	FAILED          	B			BIOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	288JP	8397 				288				ON PRE-FLIGHT, PILOT NOTICED LEFT ENGINE FIRE DETECTION WOULD NOT TEST.  TROUBLESHOT SYSTEM AND FOUND OPEN CIRCUIT IN AC	CY GEARBOX AREA SENSING ELEMENT.  INSTALLED NEW ELEMENT AND SYSTEM TEST NORMAL.					2	L	7	2 	4F				A10CE
1998100200085	19981002	00085	NE  	1998	10	2	98ZZZX3590       	2	19980918	G	7230	50B050	SEAT SEAT       								PWA   	4460  	PW4460      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C7130					CRACKS IN CHROME SEAL FACE APPEAR TO BE TRANSFERRING INTO BASE MATERIAL.											4	F			E24NE
1998100200086	19981002	00086	CE  	1998	10	2	98ZZZX3591       	1	19980812	G	5320		WEB             			RKWELL	NA265 	NA26580     	7630108	CE  										NLG WW	CRACKED         	B	P		JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	2200A	12968				38026				WHILE PERFORMING A VISUAL INSPECTION OF THE NOSE GEAR WHEEL WELL DURING A SCHEDULED 150 HOUR INSPECTION, CRACKS WERE DIS	COVERED INSIDE THE NOSE GEAR WELL AT THE LANDING GEAR WEB AREA.  THESE CRACKS ARE LOCATED ON BOTH THE LT AND RT SIDE OF 	THE WHEEL WELL BETWEEN FUSELAGE STA 99 AND STA 108 TRAVELING FROM THE UPPER AFT HINGE CUT OUT TO THE UPPER AFT RIVET.  E	ACH CRACK IS APPROX 1 INCH LONG AND TERMINATES AT THE RIVET.  THE POSSIBLE CAUSE FOR THIS CRACKING IS LOADING OF THE NOS	E GEAR DOOR HINGES BY THE AIR STREAM WHEN THE GEAR IS LOWERED FOR LANDINGS.		2	L	7	2 	4F				A2WE
1998100200087	19981002	00087	CE  	1998	10	2	98ZZZX3592       	1	19980812	G	5320		WEB             			RKWELL	NA265 	NA26580     	7630108	CE  										NLG WW	CRACKED         	B	P		JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	7148J	13541				38033				WHILE PERFORMING A VISUAL INSPECTION OF THE NOSE GEAR WHEEL WELL DURING A SCHEDULED 150 HOUR INSPECTION, CRACKS WERE DIS	COVERED INSIDE THE NOSE GEAR WELL AT THE LANDING GEAR WEB AREA.  THESE CRACKS ARE LOCATED ON BOTH THE LT AND RT SIDE OF 	THE WHEEL WELL BETWEEN FUSELAGE STA 99 AND STA 108 TRAVELING FROM THE UPPER AFT HINGE CUT OUT TO THE UPPER AFT RIVET.  E	ACH CRACK IS APPROX 1 INCH LONG AND TERMINATES AT THE RIVET.  THE POSSIBLE CAUSE FOR THIS CRACKING IS LOADING OF THE NOS	E GEAR DOOR HINGES BY THE AIR STREAM WHEN THE GEAR IS LOWERED FOR LANDINGS.		2	L	7	2 	4F				A2WE
1998100200088	19981002	00088	CE  	1998	10	2	98ZZZX3593       	1	19980812	G	5312		WEB             			RKWELL	NA265 	NA26580     	7630108	CE  										NLG WW	CRACKED         	B	P	A	JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	71460	13766				38005				WHILE PERFORMING A VISUAL INSPECTION OF THE NOSE GEAR WHEEL WELL DURING A SCHEDULED 150 HOUR INSPECTION, CRACKS WERE DIS	COVERED INSIDE THE NOSE GEAR WELL AT THE LANDING GEAR WEB AREA.  THESE CRACKS ARE LOCATED ON BOTH THE LT AND RT SIDE OF 	THE WHEEL WELL BETWEEN FUSELAGE STA 99 AND STA 108 TRAVELING FROM THE UPPER AFT HINGE CUT OUT TO THE UPPER AFT RIVET.  E	ACH CRACK IS APPROX 1 INCH LONG AND TERMINATES AT THE RIVET.  THE POSSIBLE CAUSE FOR THIS CRACKING IS LOADING OF THE NOS	E GEAR DOOR HINGES BY THE AIR STREAM WHEN THE GEAR IS LOWERED FOR LANDINGS.		2	L	7	2 	4F				A2WE
1998100200089	19981002	00089	CE  	1998	10	2	98ZZZX3594       	1	19980812	G	5320		WEB             			RKWELL	NA265 	NA26580     	7630108	CE  										NLG WW	CRACKED         	B	P	A	JR2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	12659	13192				38016				WHILE PERFORMING A VISUAL INSPECTION OF THE NOSE GEAR WHEEL WELL DURING A SCHEDULED 150 HOUR INSPECTION, CRACKS WERE DIS	COVERED INSIDE THE NOSE GEAR WELL AT THE LANDING GEAR WEB AREA.  THESE CRACKS ARE LOCATED ON BOTH THE LT AND RT SIDE OF 	THE WHEEL WELL BETWEEN FUSELAGE STA 99 AND STA 108 TRAVELING FROM THE UPPER AFT HINGE CUT OUT TO THE UPPER AFT RIVET.  E	ACH CRACK IS APPROX 1 INCH LONG AND TERMINATES AT THE RIVET.  THE POSSIBLE CAUSE FOR THIS CRACKING IS LOADING OF THE NOS	E GEAR DOOR HINGES BY THE AIR STREAM WHEN THE GEAR IS LOWERED FOR LANDINGS.		2	L	7	2 	4F				A2WE
1998100200163	19981002	00163	NE  	1998	10	2	98ZZZX3597       	1	19980910	G	3212		SWITCH          			SKRSKY	S76   	S76         	8143010	NE  										CYCLIC GRIP	LOOSE           	B			ALGR	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			SW	03	701AL					760238				INADVERTANT FLOAT INFLATION DURING FINAL APPROACH TO OFFSHORE PLATFORM.  FOUND COPILOT CYCLIC GRIP CRACKED AROUND FLOAT 	INFLATION SWITCH.  SWITCH WAS LOOSE IN GRIP.  WHEN SWITCH WAS MOVED, INFLATION RELAY WOULD ENERGIZE.  SUBMITTER RECOMMEN	DS EXAMINATION OF GRIP ASSEMBLIES FOR SECURITY OF FLOAT INFLATION SWITCH.  COMPONENT P/N 7645002010102.				1	G	7	2 	3U				H1NE
1998012900128	19980129	00128	GL  	1998	1	29	98ZZZX360        	3	19980106	G	6110	C2222	GUIDE COLLAR    			TMPSON	NAVION	NAVION*     	6150130	SW  						HARTZL	HCA2X	HCA2X204    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	4414K	1646 				NAV41414		AK329		PROPELLER COLLAR GUIDE PARTS HAD CRACKS EXTENDING UP TO 1.5 INCHES ORIGINATING AT THREADED HOLE AND EXTENDING AROUND COR	NERS.  PROPELLER HAD NOT BEEN REMOVED FROM AIRCRAFT SINCE INSTALLED IN MARCH, 1973.					1	L	7	1 	3O				A782    		5	C	P908
1998100200169	19981002	00169	SW  	1998	10	2	98ZZZX3601       	1	19980813	G	3213	412050010111A	CROSSTUBE       			BELL  	412   	412         	1182202	SW  										MLG	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	397AL	569  			A406	36012				DURING 12-MONTH INSPECTION, FOUND CORROSION PITTING IN CROSS TUBE BEYOND LIMITS.						1	G	7	2 	4U				H4SW
1998100200329	19981002	00329	GL  	1998	10	2	98ZZZX3602       	1	19980826	G	7910	956435	OIL TANK        	ROTAX       	956501      	DIAMON	DA20A1	DA20A1      	05626UX	GL  										FUSELAGE	MISINSTALLED    	H				O				OTHER                   				W	Y		INADEQUATE Q C            	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			WP	09	221DA	576  				10221				ENGINE FAILURE.  SUBMITTER SUGGESTED CAUSE BEING LACK OF OIL TO ENGINE DUE TO OIL BEING TRAPPED IN OIL TANK.  ON INSPECT	ION AFTER FAILURE, PART OF OIL TANK WAS DETERMINED TO HAVE BEEN SUCKED UP AGAINST PICK-UP TUBE DUE TO IMPROPER ASSEMBLY.	  SUGGEST SUGGEST THAT PICK-UP TUBE HAVE DOUBLE SCARF CUT ON END OR SCREEN INSTALLED.  ALSO SUGGEST THAT THE BOTTOM INTE	RNAL SCREEN BE ATTACHED TO THE SCREEN.			1	L	7	1 	3O			NT	TA4CH
1998100200331	19981002	00331	SW  	1998	10	2	98ZZZX3604       	1	19980911	G	6710	2060015499	IDLER ARM       			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	792CA					51351				DURING THE INSPECTION OF A BHT 206-L3 HELICOPTER BEING IMPORTED FROM PAPUA NEW GUINEA IAW FAR 21.18Z(D):  THE NR 1 HYDRA	ULIC SERVO IDLER ARM WAS FOUND CRACKED AT THE ATTACH POINT BOSS AND HAD BEEN REPAIRED USING EPOXY TYPE GLUE. THIS IDLER 	ARM IS A COMPONENT IN THE MAIN ROTOR FLIGHT CONTROL SYSTEM.				1	G	7	1 	3U				H2SW
1998100200332	19981002	00332	EU  	1998	10	2	98ZZZX3605       	1	19980914	G	2910	109051758103	TUBE            			AGUSTA	A109  	A109C       	0260118	EU  										NLG WW	LEAKING         	B			E8UY	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	35	109TW	1126 				7650				FOLLOWING LANDING, PILOT NOTED HYDRAULIC LEAK FROM NOSE BAY AREA.  DEFECT REPORTED.  EXAMINATION REVEALED LEAK TO ORIGIN	ATE FROM TUBE ASSY.  SUBMITTER STATED CAUSE WAS CHAFING OF PIPE BY NOSE WHEEL DOOR ACTUATING ROD.  DIFFICULT TO LOCATE D	UE TO PROXIMITY OF STRUCTURE.  FLEET A/C BEING CHECKED FOR SATISFACTORY CLEARANCE BETWEEN TUBES AND ACTUATING ROD.				1	G	7	2 	3U				H7EU
1998100200335	19981002	00335	CE  	1998	10	2	98ZZZX3608       	1	19980909	G	2434		WIRE            			CESSNA	172   	172M        	2072418	CE  										ALTERNATOR	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	4368R	5900 				17263119				ALTERNATOR OUTPUT AND FIELD WIRES CHAFED AGAINST BAFFLE BEHIND ALTERNATOR.  FIELD AND OUTPUT SHORTED TOGETHER CAUSING AL	TERNATOR RUNAWAY.  VOLTAGE RUINED MANY ELECTRICAL COMPONENTS.  POTENTIAL FIRE.  MASTER SWITCH WOULD NOT SHUT OFF RUNAWAY	.  SUBMITTER SUGGESTED WIRING INSPECTION AND INSTALLATION OF 60 AMP PULL-TYPE CIRCUIT BREAKER.				1	H	7	1 	3O			NT	3A12
1998100200336	19981002	00336	CE  	1998	10	2	98ZZZX3609       	1	19980817	G	5320	52130409	WEB             			CESSNA	402   	402C        	207590R	CE  										NLG WW	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	402MQ	12537				402C0095				DURING HOSE INSPECTION, FOUND CRACKS ON WEB ASSEMBLIES AROUND THE ATTACH BOLTS FOR THE NOSE GEAR TRUNNION BEARINGS.  SUB	MITTER SUGGESTED CAUSE COULD BE SIDE LOADS ON NOSE GEAR DUE TO IMPROPER GROUND HANDLING PROCEDURES.					1	L	7	2 	3O				A7CE
1998012900129	19980129	00129		1998	1	29	98ZZZX361        	4	19980106	G	6122	C4191	DRIVE GEAR      	HARTZL      	F27A        	PIPER 	PA28  	PA28R180    	7102809	SO  										PROPELLER GOV	DEFECTIVE       	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	3878T	3940 			5747W	28R30203				GOVERNOR DRIVE GEAR HAS SHARP INDICATION AT BASE OF TOOTH EXTENDING AROUND CORNER.						1	L	7	1 	3O				2A13
1998100200337	19981002	00337	CE  	1998	10	2	98ZZZX3610       	1	19980817	G	5320	521304010	WEB             			CESSNA	402   	402C        	207590R	CE  										NLG WW	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	402MQ	12537				402C0095				DURING HOSE INSPECTION, FOUND CRACKS ON WEB ASSEMBLIES AROUND THE ATTACH BOLTS FOR THE NOSE GEAR TRUNNION BEARINGS.  SUB	MITTER SUGGESTED CAUSE COULD BE SIDE LOADS ON NOSE GEAR DUE TO IMPROPER GROUND HANDLING PROCEDURES.					1	L	7	2 	3O				A7CE
1998100200338	19981002	00338	CE  	1998	10	2	98ZZZX3611       	1	19980830	G	3233	98820152	ACTUATOR        			CESSNA	172   	172RG       	2072438	CE  										LT MLG	CRACKED         	B			DXTR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	4726V	6332 			5913	172RG0370				LEFT GEAR WOULD NOT EXTEND FOR LANDING.  PILOT TRIED TO BRING GEAR UP, LEFT GEAR JUST HUNG HALF WAY.  AIRCRAFT LANDED WI	TH GEAR UP.  INVESTIGATION REVEALED LEFT GEAR ACTUATOR WAS CRACKED AND SECTOR GEAR COULD NOT ENGAGE.					1	H	7	1 	3O				3A17
1998100200339	19981002	00339	CE  	1998	10	2	98ZZZX3612       	1	19980911	G	8120	4656804	TURBOCHARGER    	GARRTT      		CESSNA	210   	P210N       	2073454	CE  										ENGINE	WORN            	H				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	08	3EM	886  			KD0106	P21000722				SMOKE FROM THE ENGINE EXHAUST.  OIL LEAKAGE AT BEARING SEALS.  WORN OUT.  NOTE:  MECHANIC STATED OPERATORS ARE NOT DOING	 A COOL DOWN PERIOD AFTER OPERATION WHICH HELPS THE BEARING SEALS TO LAST LONGER IN THE TURBOCHARGER.  TURBOCHARGERS SHO	ULD GO TO TB 1,500 HOURS.				1	H	7	1 	3O				3A21
1998100200671	19981002	00671	EA  	1998	10	2	98ZZZX3613       	2	19980904	G	7314	RD34725	COUPLING DRIVE  	LEARSIEGLER 	RG34720A    						PWA   	PT6   	PT6A27      	52043	EA  					FUEL PUMP	WORN            	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27					B4585					UNITS COUPLING TURNS WITHOUT ENGAGING PUMP.  UPON FURTHER INSPECTION, FOUND SPLINE ON COUPLING AND ROTOR COMPLETELY ROUN	DED OFF.										4	T			E4EA
1998100200672	19981002	00672	CE  	1998	10	2	98ZZZX3614       	1	19980914	G	7920	4810649001	FITTING         			CESSNA	421   	421C        	2076016	CE  										LT ENGINE	STRIPPED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	749CA		904  		PRC0103	421C1239				PILOT REPORTED LEFT ENGINE OIL LEAK.  FURTHER INSPECTION REVEALED THE WASTEGATE OIL INLET LINE WAS LOOSE AT THE WASTEGAT	E OIL INLET BOSS.  IT WAS DETERMINED THAT THE THREADS OF THE BOSS HAD FAILED.  SUBMITTER RECOMMENDED MORE DETAILED INSPE	CTION OF WASTEGATE OIL LINES AND FITTINGS AT PERIODIC AND ROUTINE INSPECTIONS.				1	L	7	2 	3O				A7CE
1998100200673	19981002	00673	NE  	1998	10	2	98ZZZX3615       	2	19980626	G	7250	51L532	BLADE           								PWA   	4168  	PW4168      		NE  					TURBINE	DAMAGED         	B			WA2D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							P733358			UPON ATTAINING CRUISE ALTITUDE FL 290, ENGINE STALLED AND FIRE WARNING ACTIVATED.  DISASSEMBLY INSPECTION REVEALED TWELV	E 2ND STAGE TURBINE BLADES BROKEN AT PLATFORM AND AN ADDITIONAL 10 BLADES BROKEN APPROXIMATELY ONE INCH ABOVE PLATFORM. 	 HPT MODULE 851 HOURS/371 CYCLES SINCE REPAIR.  FRACTURED BLADES HAVE BEEN FOWARDED TO PRATT & WHITNEY ENGINEERING FOR A	NALYSIS.								4	F			E36NE
1998100200674	19981002	00674	SW  	1998	10	2	98ZZZX3616       	1	19980907	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										MAIN ROTOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	37LP	247  			A355	53049				CRACKS FOUND IN M/R BLADE TRIM TAB AREA.  SUSPECT TRIM TAB BENDING TOOL.						1	G	7	1 	3U			O	H2SW
1998100200675	19981002	00675	SW  	1998	10	2	98ZZZX3617       	1	19980907	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										MAIN ROTOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	37LP	247  			A391	53049				CRACKS FOUND IN M/R BLADE TRIM TAB AREA.  SUSPECT TRIM TAB BENDING TOOL.						1	G	7	1 	3U			O	H2SW
1998100200676	19981002	00676	EU  	1998	10	2	98ZZZX3618       	1	19980831	G	3244	M08301	TIRE            			AMD   	FALC20	FALCON      	2720302	EU  										NLG	FAILED          	B				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			NM	11	24TW					80				DURING A TAKEOFF ATTEMPT, ENTIRE TREAD CAP ON RT NOSE WHEEL SEPARATED FROM TIRE. TAKEOFF ABORTED.  TIRE FOUND TO STILL B	E INFLATED AND CORD BIAS VISIBLE.  NDT DONE ON WHEEL HALVES.  NO DEFECTS.  NEW TIRE INSTALLED.					2	L	7	2 	4F				A7EU
1998100200677	19981002	00677	EA  	1998	10	2	98ZZZX3619       	1	19980823	G	3244		TIRE            	GOODYEARAERO		CNDAIR	CL600 	CL6002B16   	1900305	EA  										MLG	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	793CT					5148				NR 4 TIRE FAILED CAUSING TWO HYDRAULIC LINES TO LEAK DEPLENISHING NR 2 HYDRAULIC SYSTEM.  THE INBOARD FLAP FORWARD FACE 	WAS DENTED.  DAMAGE WAS ENCOUNTERED TO THE MLG DOOR AND ACTUATING LINK.  SEVERAL PARTS WERE REPLACED AND INSPECTIONS COM	PLETED INCLUDING A HEAVY WEIGHT LANDING INSPECTION AND FUSIBLE PLUG RELEASE INSPECTION.				2	L	7	2 	4F			RT	A21EA
1998100200678	19981002	00678	EU  	1998	10	2	98ZZZX3620       	1	19980914	G	2913	4005303	PUMP            	ABEX        		AMD   	FALC10	FALCON10    	2730101	EU  										NR 2 ENGINE	FAILED          	E				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	23	77SF		789  		AH16055A	141				DURING START OF THE RIGHT (NR 2) ENGINE, THE CREW NOTICED AN UNUSUAL NOISE THAT LASTED APPROXIMATELY 30 SECONDS.  SCANNI	NG THE INSTRUMENTATION REVEALED THE 'HYD 2' LIGHT ILLUMINATED AND THE HYDRAULIC PRESSURE GAUGE INDICATED ZERO.  EXAMINAT	ION OF THE RT ENGINE DRIVEN HYDRAULIC PUMP AFTER REMOVAL REVEALED THE DRIVESHAFT WAS INTACT, HOWEVER, IT ROTATED WITH LI	TTLE RESISTANCE INDICATING AN INTERNAL FAILURE.  PUMP TBO IS 3,000 HOURS, HOWEVER, THIS INTERVAL IS RARELY ACHIEVED.			2	L	7	2 	4F				A33EU
1998100200679	19981002	00679	CE  	1998	10	2	98ZZZX3621       	1	19980904	G	5610		WINDSHIELD      			CESSNA	425   	425         	2076018	CE  										COCKPIT	CRACKED         	B			BWRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	39A					4250138				DURING REMOVAL OF COPILOT'S WINDSHIELD, NOTED 2 CRACKS EXTENDING FROM BOLT HOLES TO THE EDGE OF THE WINDSHIELD.						1	L	7	2 	3T			RT	A7CE
1998100200680	19981002	00680		1998	10	2	98ZZZX3622       	4	19980914	G	2330	216	AMPLIFIER       			BEECH 	300   	300BEECH    	1152930	CE  										CABIN	SHORTED         	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			CE	03	100BG	3729 			134	FL6				A STRONG ELECTRICAL SMOKE SMELL AND LOUD SQUEAL FROM THE CABIN ADDRESS SPEAKERS WAS CAUSED BY AN INTERNALLY SHORTED CABI	N SPEAKER AMPLIFIER.  THIS PROBLEM COULD NOT BE ISOLATED UNTIL THE 'CABIN AMP' BREAKER WAS PULLED.  THE BREAKER DID NOT 	TRIP ON ITS OWN AND CONTINUED TO FEED THE SHORT.				2	L	7	2 	4T				A24CE
1998100200682	19981002	00682		1998	10	2	98ZZZX3624       	3	19980915	G	6112	660710924	SLIDE BLOCK     	ROTOL       	R389        	SAAB  	SF340 	340B        	7860101	EU  										PROPELLER	DAMAGED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		21594	5571 		DRG487287					PROPELLER RECEIVED FROM CUSTOMER IN DISASSEMBLED CONDITION WITH 2 EACH DAMAGED SLIDE BLOCKS AND DAMAGED CROSSHEAD.  CROS	SHEAD AND SLIDE BLOCKS WERE IN PRE-SB SF340-61-89 CONFIGURATION.					2	L	7	2 	4T			RT	A52EU
1998100200683	19981002	00683	CE  	1998	10	2	98ZZZX3625       	1	19980902	G	3240	21139	BRAKE ASSY      			BEECH 	90    	C90A        	1152911	CE  										RT MLG	MISADJUSTED     	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	1568Y					LJ1368				DURING A ROUTINE BRAKE ASSEMBLY REPLACEMENT (2 EACH), FOUND THIS TSO: ZERO ASSEMBLY WAS IMPROPERLY ADJUSTED PER THE COMP	ONENT OVERHAUL MANUAL.  THE BRAKES WOULD NOT HOLD.  OVERHAUL BY AVIALL AT TEB  NJ.  CRS NR VFTR16RL NR 04AW09716 AND OHA	W09715.  323-98.  AVIALL WAS NOTIFIED.				1	L	7	2 	3T			RT	3A20
1998100200684	19981002	00684	CE  	1998	10	2	98ZZZX3626       	1	19980902	G	3240	21139	BRAKE ASSY      			BEECH 	90    	C90A        	1152911	CE  										MLG	MLG             	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	1568X					LJ1368				DURING A ROUTINE BRAKE ASSY REPLACEMENT (2 EACH), FOUND THE TSO:  ZERO ASSY WAS IMPROPERLY ADJUSTED PER THE COMPONENT OV	ERHAUL MANUAL.  THE BRAKES WOULD NOT HOLD.  OVERHAUL BY AVIALL AT TEB NJ CRIS NR VFTR164L NR 04PW13371 AND 04PW13372.  8	-14-98.  AVIALL WAS NOTIFIED.				1	L	7	2 	3T			RT	3A20
1998100200685	19981002	00685	CE  	1998	10	2	98ZZZX3627       	1	19980812	G	2913	23800861	PUMP            			LEAR  	24    	24          	5170302	CE  										HYDRAULIC SYSTEM	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	45ED					104				APPROVED AIRCRAFT ACCESSORIES INC., CRS US2R225L OVERHAULED HYDRAULIC PUMP.  WHEN INSTALLED, PUMP WOULD NOT PICK UP PRES	SURE.  BLED PUMP WITH NO RESULTS.  WHEN THE PUMP WAS REMOVED, NOTED THE SNAP-RING IN THE BASE OF THE PUMP HAD COME OUT. 	 THE INSIDE OF THE PUMP HAD SHIFTED TOWARD THE SHAFT CAUSING PUMP FAILURE.				2	L	7	2 	4J				A10CE
1998100200686	19981002	00686		1998	10	2	98ZZZX3628       	4	19980801	G	2563	66001803	DRAG CHUTE      			LEAR  	35    	35A         	5170602	CE  										FUSELAGE	MALFUNCTIONED   	C				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			GL	19	811DD					384				DRAG CHUTE DEPLOYED WITHOUT BEING ACTIVATED DURING FLIGHT.  IN A DESCENT APPROXIMATELY FL 230, 320 KNOTS, INDICATED AROU	ND THE STW VOR.  SUBMITTER STATED CAUSE UNKNOWN.					2	L	7	2 	4F				A10CE
1998012900131	19980129	00131		1998	1	29	98ZZZX363        	4	19980105	G	6122	F65A	GOVERNOR        	HARTZL      																FLYWEIGHT	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17					B1709T					GOVERNOR FLYWEIGHT HAS SHARP INDICATION IN BASE AT DRIVE GEAR HOLE.
1998100200688	19981002	00688	CE  	1998	10	2	98ZZZX3630       	1	19980813	G	5512		SKIN            			CESSNA	500   	500CESSNA   	2076602	CE  										RT HORIZ STAB	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	125DS					5000258				DISBONDING OF SKINS ON UPPER AND LOWER SURFACES OF RT HORIZONTAL STABILIZER IN EXCESS OF  MANUFACTURER'S SPECIFICATIONS.						1	L	7	2 	4F				A22CE
1998100200689	19981002	00689	CE  	1998	10	2	98ZZZX3631       	1	19980921	G	3222	2342100	STRUT           			LEAR  	35    	35A         	5170602	CE  										NLG	GOUGED          	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	436BL	5207 				436				NOSE GEAR DOOR MECHANISM ROD ATTACH POINT BOLT P/N AN24-30 TO NOSE STRUT BEING INCORRECTLY INSTALLED AND IS CAUSING GOUG	ING TO THE SKIN AT FRAME 5, BS 160.77.  IN REFERENCE TO THE ILLUSTRATION, THE POSITION OF THE BOLT HEAD SHOULD BE INSTAL	LED WITH THE BOLT HEAD FACING OTBD TO MAINTAIN CLEARANCE BETWEEN THE BOLT HEAD AND FRAME SKIN.  THE GOUGING OCCURS WHEN 	THE BOLT HEAD IS BEING INSTALLED IN THE INBD POSITION AND THE THREADED PORTION OF THE BOLT IS GOUGING THE FRAME SKIN.  T	HERE IS NO WRITTEN NOTE/CAUTION IN THE LEARJET MM TO THE CORRECT INSTALLATION OF THIS BOLT.		2	L	7	2 	4F				A10CE
1998100200690	19981002	00690	CE  	1998	10	2	98ZZZX3632       	1	19980817	G	3221		TRUNNION        	MENASCO     	50107359    	RKWELL	NA265 	NA26540     	6402608	CE  										NLG	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	313NT				352	28294				DURING SCHEDULED INSPECTION, THE NOSE LANDING GEAR UPPER BARREL ASSY WAS FOUND WITH A CRACK COMPLETELY THROUGH THE RT TR	UNNION PIN HOLE.  THE TRUNNION/BEARING PIN AND RETAINING BOLT WERE IN PLACE AND HOLDING THE TRUNNION PORTION OF THE UPPE	R BARREL TOGETHER.  THE UPPER BARREL WAS REMOVED TO BE REPLACED WITH A NEW ASSY.  SUBMITTER RECOMMENDED A DETAILED INSPE	CTION OF THIS AREA AT EACH SCHEDULED INSPECTION.  NOTE:  AT DISASSY, THE RT TRUNNION BEARING WAS FOUND TO BE DRY, RUSTY,	 AND FROZEN.  ACFT TT:  9,059.8 HRS.  LANDINGS:  7,535.		2	L	7	2 	4J				A2WE
1998100200691	19981002	00691		1998	10	2	98ZZZX3633       	4	19980914	G	3416	0900409901	ENCODER         			BELL  	204   	UH1H        	1181407	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	51AG				19526	7120178				ENCODER TRIPS CIRCUIT BREAKER.  REMOVED AND REPLACED.						1	G	7	1 	4U				EXPA1G71
1998100200692	19981002	00692	SW  	1998	10	2	98ZZZX3634       	1	19980910	G	2436	15891F	REGULATOR       			BELL  	206   	206B3       	1181506	SW  										DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX		1383 		30598	2872				GENERATOR DROP, OFFLINE, WILL NOT ADJUST ON VOLTAGE.  REPLACED AND SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998100200693	19981002	00693	SW  	1998	10	2	98ZZZX3635       	1	19980909	G	7712	212701	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	8530B		176  		2034	30702				NR 2 TRIPLE TORQUE CIRCUIT BREAKER TRIPS WHEN POWER APPLIED.  SAME PROBLEM IN DIFFERENT INSTALLATIONS.  REMOVED AND REPL	ACED.					1	G	7	1 	4U				H4SW
1998100200694	19981002	00694	WP  	1998	10	2	98ZZZX3636       	1	19980914	G	6420	369D2172121	FORK            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				WORN BEARINGS.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100200695	19981002	00695	SW  	1998	10	2	98ZZZX3637       	1	19980910	G	2436	CSV115212AB	REGULATOR       			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	51AG		148  		CF1101					WILL NOT REGULATE VOLTAGE.  REPLACED.						1	G	7	1 	4U				EXPA1G71
1998100200696	19981002	00696		1998	10	2	98ZZZX3638       	4	19980913	G	3416	AT3000	ENCODER         			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P	415  			18302	611002D				ALTITUDE READING OFF 1,000 FEET.  REPLACED.  RECERTIFIED.						1	G	7	1 	3U				H3WE
1998100200697	19981002	00697	WP  	1998	10	2	98ZZZX3639       	1	19980916	G	6220	369A76132	LINK            			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				WORN BEYOND LIMITS.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998012900132	19980129	00132	GL  	1998	1	29	98ZZZX364        	3	19980105	G	6110		BEARING         			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCE2Y	HCE2YR2     	GL  	PROP ASSY	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	9EF	2592 				277305092		BP6228		INSPECTION FOUND PROPELLER ASSY BEARING CRACKED.						1	L	7	2 	3O				1A10    		5	C	P9EA
1998100200698	19981002	00698	WP  	1998	10	2	98ZZZX3640       	1	19980831	G	6710	A21810064603	SWITCH          			HUGHES	369   	369D        	4470706	WP  										PILOT CYCLIC	FAILED          	B		A	LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				LONGITUDINAL RUN AWAY AND INTERMITTENT.  UNREPAIRABLE.  REPLACED CYCLIC SWITCH.						1	G	7	1 	3U				H3WE
1998100200699	19981002	00699	WP  	1998	10	2	98ZZZX3641       	1	19980831	G	6420	369A2172121	FORK            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					29045D				ELASTOMERIC CONNICALS DETERIORATED AND CRACKED.  REMOVED AND REPLACED T/R FORK.						1	G	7	1 	3U				H3WE
1998100200700	19981002	00700	WP  	1998	10	2	98ZZZX3642       	1	19980914	G	6420	369D217313	LINK            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				BEARING WORN BEYOND LIMITS.  REPLACED.						1	G	7	1 	3U				H3WE
1998100200701	19981002	00701	GL  	1998	10	2	98ZZZX3643       	2	19980909	G	7323	2305870	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	LACK OF LUBE    	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	21535			21535	900801D				GOV HAS BLUE GREASE WASHED OUT.  SENT FOR REPAIR.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998100200702	19981002	00702	WP  	1998	10	2	98ZZZX3644       	1	19980914	G	2435	23032027	STARTER         			HUGHES	369   	369D        	4470706	WP  										ENGINE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J		769  		17714	900801D				STARTER FAILED.  IPS 2.5.  SENT FOR REPAIR OF VIBRATION.						1	G	7	1 	3U				H3WE
1998100200703	19981002	00703	WP  	1998	10	2	98ZZZX3645       	1	19980916	G	7714	369H4551	INDICATOR       		5825        	HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				N1 SHOW TO COME UP ON STARTS.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100900448	19981009	00448	SW  	1998	10	9	98ZZZX3646       	1	19980831	G	6310	206040241001	HOUSING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322				B126204	1736	CAE83057			OIL FITTING HAS STRIPPED THREADS IN HOUSING.  REMOVED AND REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998100900449	19981009	00449	WP  	1998	10	9	98ZZZX3647       	1	19980916	G	7810	369A8230503	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	21   				900801D				PILOT FOUND CRACK AT WELD. REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100900450	19981009	00450	WP  	1998	10	9	98ZZZX3648       	1	19980916	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	1    				900801D				PILOT DISCOVERED CRACKS DURING POST-FLIGHT INSPECTION.  REMOVED AND REPLACED EXHAUST STACK.						1	G	7	1 	3U				H3WE
1998100900451	19981009	00451	WP  	1998	10	9	98ZZZX3649       	1	19980916	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				PILOT FOUND CRACKS DURING POST-FLIGHT INSPECTION.  REMOVED AND REPLACED EXHAUST STACK.						1	G	7	1 	3U				H3WE
1998100900452	19981009	00452	WP  	1998	10	9	98ZZZX3650       	1	19980916	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	19   				900801D				PILOT INSPECTED EXHAUST AFTER FLIGHT AND FOUND IT TO BE CRACKED.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100900453	19981009	00453	WP  	1998	10	9	98ZZZX3651       	1	19980916	G	7810	369A823054	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	14   				900801D				PILOT FOUND CRACKS DURING POST-FLIGHT INSPECTION.  REMOVED AND REPLACED EXHAUST STACK.						1	G	7	1 	3U				H3WE
1998100900454	19981009	00454	WP  	1998	10	9	98ZZZX3652       	1	19980916	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P	23   				611002D				PILOT FOUND CRACKS DURING POST-FLIGHT INSPECTION.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998100900455	19981009	00455	GL  	1998	10	9	98ZZZX3653       	2	19980916	G	7230	6898607	BEARING         		6890550     	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	FAILED          	B			CUHR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	2995W	10352	2983 		L1348	1192	CAE822653			PARTIAL POWER LOSS, TOT, RISE, AND ENGINE NOISE DURING FLIGHT (LEVEL).  ENGINE TEAR-DOWN REVEALED COMPRESSOR BLADES RUBB	ING CASE HALVES.  COMPRESSOR TEAR-DOWN REVEALED NR 1 BEARING FAILURE OF BALL CAGE.  SUBMITTER STATED CAUSE UNKNOWN.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998100900456	19981009	00456	SW  	1998	10	9	98ZZZX3654       	1	19980831	G	6710	2060626211	ACTUATOR        			BELL  	206   	206B        	1181511	SW  										M/R CONTROL	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	49718				5151A	1917				ELECTRICAL STUD BROKEN.  SENT OUT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998100900457	19981009	00457	SW  	1998	10	9	98ZZZX3655       	1	19980913	G	7722	6887761	HARNESS         			BELL  	206   	206B3       	1181506	SW  										TOT	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY				0348	2871				NO TOT READING.  SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998100900458	19981009	00458	SW  	1998	10	9	98ZZZX3656       	1	19980831	G	7714	32005023	TACH GENERATOR  			BELL  	206   	206B3       	1181506	SW  										ENGINE RPM	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322				231950	1736				SHAFT WORN OUT.  SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998100900459	19981009	00459	CE  	1998	10	9	98ZZZX3657       	1	19980910	G	2730	319A280	MOTOR           			BEECH 	90    	C90A        	1152911	CE  										ELEVATOR	MISSING PARTS   	B	S		NN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	479JA	4794 				LJ1177				TWO AIRCRAFT HAVE 3 OF 4 SCREWS MISSING FROM BASE PLATE.  FOURTH SCREW LOOSE.  RTV HELD BASE PLATE TO THE GEARBOX AND MO	TOR ASSY.  RTV INSTALLED PER BEECH SB 2028 REV IV.  THIRD AIRCRAFT HAD TWO SCREWS MISSING FROM BASE PLATE WITH ONE LOOSE	 AND ONE TIGHT.  THE MOTOR ATTACH SCREWS WERE ALSO LOOSE.  RECOMMEND LOCK TIGHTENING SCREWS OR SOME TYPE OF LOCKING TABS	 TO SECURE SCREWS.			1	L	7	2 	3T			RT	3A20
1998100900460	19981009	00460	CE  	1998	10	9	98ZZZX3658       	1	19980910	G	2730	319A280	MOTOR           			BEECH 	90    	C90A        	1152911	CE  										ELEVATOR	MISSING PARTS   	B	S		NN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	484JA	4794 				LJ1196				TWO AIRCRAFT HAVE 3 OF 4 SCREWS MISSING FROM BASE PLATE.  FOURTH SCREW LOOSE.  RTV HELD BASE PLATE TO THE GEARBOX AND MO	TOR ASSY.  RTV INSTALLED PER BEECH SB 2028 REV IV.  THIRD AIRCRAFT HAD TWO SCREWS MISSING FROM BASE PLATE WITH ONE LOOSE	 AND ONE TIGHT.  THE MOTOR ATTACH SCREWS WERE ALSO LOOSE.  RECOMMEND LOCK TIGHTENING SCREWS OR SOME TYPE OF LOCKING TABS	 TO SECURE SCREWS.			1	L	7	2 	3T			RT	3A20
1998100900461	19981009	00461	CE  	1998	10	9	98ZZZX3659       	1	19980910	G	2730	319A280	MOTOR           			BEECH 	90    	C90A        	1152911	CE  										ELEVATOR	MISSING PARTS   	B	S		NN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	486JD					LJ1198				TWO AIRCRAFT HAVE 3 OF 4 SCREWS MISSING FROM BASE PLATE.  FOURTH SCREW LOOSE.  RTV HELD BASE PLATE TO THE GEARBOX AND MO	TOR ASSY.  RTV INSTALLED PER BEECH SB 2028 REV IV.  THIRD AIRCRAFT HAD TWO SCREWS MISSING FROM BASE PLATE WITH ONE LOOSE	 AND ONE TIGHT.  THE MOTOR ATTACH SCREWS WERE ALSO LOOSE.  RECOMMEND LOCK TIGHTENING SCREWS OR SOME TYPE OF LOCKING TABS	 TO SECURE SCREWS.			1	L	7	2 	3T			RT	3A20
1998100900462	19981009	00462	CE  	1998	10	9	98ZZZX3660       	1	19980911	G	3240	66000514	BRAKE CABLE     			LEAR  	24    	24A         	5170304	CE  										BRAKE ASSY	FAILED          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	23	93BP	9500 				24169				RIGHT MAIN BRAKES LOCKED ON LANDING AT YIP.  WHEELS WORN THROUGH RIMS AND BRAKES AND TORQUE PLATE LOST ABOUT 1 INCH OF M	ATERIAL.  FOUND RIGHT PARKING BRAKE CABLE KINKED AT PARKING BRAKE VALVE.  REPLACED CABLE AND IMPROVED ROUTING TO PREVENT	 RECURRENCE.				2	L	7	2 	4J			 	A10CE
1998100900463	19981009	00463	CE  	1998	10	9	98ZZZX3661       	1	19980917	G	2121	30715648	BREATHER VALVE  			LEAR  	35    	35A         	5170602	CE  										ENGINE	FAILED          	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	72CK				2796	165				CREW NOTICED THE PRESENCE OF OILY SMOKE ENTERING CABIN DURING CRUISE FLIGHT.  UNEVENTFUL LANDING WAS MADE.  REPLACED FAU	LTY RT BREATHER PRESSURIZATION VALVE.  OPERATIONALLY CHECK AND LEAK CHECKED NORMAL.					2	L	7	2 	4F				A10CE
1998100900464	19981009	00464	SW  	1998	10	9	98ZZZX3662       	1	19980914	G	3211	2120304361	CAP ASSY        			BELL  	212   	212         	1181420	SW  										MLG	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530B					30702				CAP ASSY WORN BEYOND LIMITS.  REPLACED.						1	G	7	1 	4U				H4SW
1998101600001	19981016	00001	EA  	1998	10	16	98ZZZX3663       	1	19980911	G	7930	6013702057	SHAFT           			CNDAIR	CL600 	CL6002B19   		EA  										LT/RT NACELLE	DAMAGED         	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	150  				7008				DURING REMOVAL/INSTALLATION OF LT AND RT ENGINES, NOTED THAT AFT MOUNT SHAFTS AND AFT MOUNT FITTINGS FOR BOTH LT AND RT 	SIDES HAD CIRCUMFERENTIAL SCORING FROM COMING IN CONTACT WITH ONE ANOTHER.  THE SHAFT AND FITTING ARE NOT TO COME IN CON	TACT WITH EACH OTHER IAW MM PRACTICES.  THE PROBLEM OCCURS BECAUSE THE SHAFT AND FITTINGS ARE NOT SOLD TOGETHER AS A PRE	-MATCHED SET.			2	L	7	2 	4F			RT	A21EA
1998101600002	19981016	00002	EA  	1998	10	16	98ZZZX3664       	1	19980911	G	7930	6013701413	SHAFT           			CNDAIR	CL600 	CL6002B19   		EA  										LT/RT NACELLE	DAMAGED         	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	150  				7008				DURING REMOVAL/INSTALLATION OF LT AND RT ENGINES, NOTED THAT AFT MOUNT SHAFTS AND AFT MOUNT FITTINGS FOR BOTH LT AND RT 	SIDES HAD CIRCUMFERENTIAL SCORING FROM COMING IN CONTACT WITH ONE ANOTHER.  THE SHAFT AND FITTING ARE NOT TO COME IN CON	TACT WITH EACH OTHER IAW MM PRACTICES.  THE PROBLEM OCCURS BECAUSE THE SHAFT AND FITTINGS ARE NOT SOLD TOGETHER AS A PRE	-MATCHED SET.			2	L	7	2 	4F			RT	A21EA
1998101600003	19981016	00003	EA  	1998	10	16	98ZZZX3665       	1	19980911	G	7830	22850201481	TORQUE BOX      		22850200803 	CNDAIR	CL600 	CL6002B19   		EA  										LT NACELLE	CRACKED         	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4487 			009	7008				LEFT THRUST REVERSER TORQUE BOX IS CRACKED JUST UNDER FORWARD END OF LEFT SIDE, 6 O'CLOCK, SOUND ATTENUATING MATERIAL (S	AM) SUPPORT BRACKET.  CRACK WAS FOUND DURING ROUTINE ENGINE CHANGE MAINTENANCE PRACTICES.					2	L	7	2 	4F			RT	A21EA
1998101600004	19981016	00004	SO  	1998	10	16	98ZZZX3666       	1	19980915	G	5320	120444540001	SUPPORT         			EMB   	120   	EMB120RT    		SO  										WINDSHIELD	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	233AS					120031				DURING C-CHECK INSPECTION, WINDSHIELD CENTER POST ATTACH SUPPORT FITTINGS ARE INSPECTION IAW ASA EO-120-53-0021.  THE UP	PER SUPPORT FITTING WAS FOUND CRACKED ON THE LEFT SUPPORT LEG IN THE RADIUS.  THE CRACK WAS DETECTED BY VISUAL INSPECTIO	N.  CRACK RUNS FROM BACK OF LEG FORWARD .75 INCH.				2	L	7	2 	4T			RT	A31SO
1998101600005	19981016	00005		1998	10	16	98ZZZX3667       	1	19980911	G	2913	142820	BEARING         																	HYDRAULIC PUMP	MISMANUFACTURED 	B	P		JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09										SUBMITTER RECEIVED 3 PARTS FROM STOCK OVER A PERIOD OF TIME THAT HAD THE BEARING PARTIALLY DISASSEMBLED.  ONE RECEIVED I	NTACT.  INSTALLED THE ASSY IN THE PUMP AND DURING THE RUN-IN PROCESS, THE LOWER BEARING CAME APART CAUSING FAILURE TO TH	E PUMP.  SUBMITTER STATED BETTER QUALITY INSPECTIONS REQUIRED.
1998101600006	19981016	00006	CE  	1998	10	16	98ZZZX3668       	1	19980902	G	2913		PUMP            			CESSNA	210   	210M        	2073450	CE  										HYDRAULIC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	732QA					21061679				AIRCRAFT BROUGHT IN FOR MAINTENANCE.  FOUND PUMP MOTOR CONTINUING TO RUN.  TROUBLESHOOTING REVEALED THAT UNIT WOULD NOT 	PRODUCE PROPER PRESSURE TO TRIP PRESSURE SWITCH.  REMOVED AND INSTALLED OVERHAULED UNIT.  SYSTEM OPS NORMAL.					1	H	7	1 	3O				3A21
1998101600007	19981016	00007	CE  	1998	10	16	98ZZZX3669       	1	19980902	G	2913		PUMP            			CESSNA	210   	210M        	2073450	CE  										HYDRAULIC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	6554B		300  			21062785				UNIT WOULD NOT PRODUCE PRESSURE TO TURN OFF PUMP.  REMOVED AND SENT FOR OVERHAUL.  INSTALLED SAME BACK IN AFTER OVERHAUL	.  REMOVED UNIT AND SENT FOR EXCHANGE.  THIS OVERHAUL UNIT INSTALLED AND WORKED NORMALLY.  AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3O				3A21
1998101600008	19981016	00008	CE  	1998	10	16	98ZZZX3670       	1	19980922	G	2510		SEAT BELT       			BEECH 	58    	58P         	1152744	CE  										COCKPIT	MALFUNCTIONED   	B			DEBR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	03	158TT	55   				TJ333				SEAT BELT LATCHES INTERMITTENTLY.						1	L	7	2 	3O				A23CE
1998101600009	19981016	00009	CE  	1998	10	16	98ZZZX3671       	1	19980901	G	5720	05230201	ANGLE           			CESSNA	172   	172         	2072402	CE  										WING SPAR	CORRODED        	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7248A	3937 				29348				DURING ROUTINE INSPECTION, SEVERAL AREAS OF INTERGRANULAR CORROSION IN UPPER SPAR ANGLES P/N 0523020-1 AND 2 WERE DISCOV	ERED.  AFTER REMOVAL, THE ANGLES WERE BROKEN IN TWO WITH LIGHT HAND PRESSURE.  DETECTION WAS DIFFICULT AS THERE ARE VERY	 FEW INSPECTION HOLES IN OLDER CESSNA WINGS, AND THE PART IS SANDWICHED BETWEEN OTHER PARTS.  THERE WAS EVIDENCE OF CORR	OSION THROUGHOUT THE WINGS, LIGHT SURFACE CORROSION WHICH WAS EASY TO TREAT, AND GAVE NO INDICATION OF THE EXTENT OF DAM	AGE TO THE SPAR ANGLES.  SUBMITTER SUGGESTED MANUFACTURER DATA ON ADDITIONAL INSPECTION HOLES; CORROSION DETECTION.		1	H	7	1 	3O			NT	3A12
1998101600010	19981016	00010	GL  	1998	10	16	98ZZZX3672       	3	19980921	G	6114	57A2433	BOLT            													HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER HUB	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19			1930 					AU7863		PROPELLER RECEIVED FOR STANDARD OVERHAUL.  DURING NDT INSPECTION, HUB HALF BOLT CRACKED BETWEEN HEAD AND SHANK, 60 DEGRE	ES AROUND.															5	C	P920
1998101600011	19981016	00011	CE  	1998	10	16	98ZZZX3673       	1	19980904	G	7722		HARNESS         			CESSNA	441   	441         	2076020	CE  										ENGINE	DAMAGED         	B			WTXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	07	6855P					4410233				LEFT TORQUE FLUCTUATES IN-FLIGHT IN COMPUTER MODE CAUSING AIRCRAFT TO YAW EXCESSIVELY.  SUBMITTER STATED CAUSE FOUND TO 	BE EGT SIGNAL FLUCTUATION.  EGT SIGNAL TO COMPUTER FOUND TO GO HIGH CAUSING LIMITER TO GIVE UNCOMMANDED DECELERATION TO 	IDLE.  PROBLEM NOT RESOLVED AT THIS TIME.  TROUBLESHOT EGT HARNESS SYSTEM AND FOUND A BENT PIN IN HARNESS.  REPAIRED.  S	UBMITTER STATED THIS IS THE THIRD INCIDENT OF EGT HARNESS PROBLEMS ON THIS MODEL ENGINE.			1	L	7	2 	3T			RT	A28CE
1998101600012	19981016	00012	SO  	1998	10	16	98ZZZX3674       	1	19980601	G	2510	1834300	BLANKET         			PIPER 	PA23  	PA23160     	7102304	SO  										NG WW	LOOSE           	H		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	4395P					231904				PIPER BLANKET, P/N 18343-00, DETERIORATED, FELL INTO NOSE GEAR OLEO AND DOWNLOCK MECHANISM CAUSING LIGHT SWITCH, P/N 487	-805, TO BLINK AND 2 LINKS, P/N 16667-00, ALSO TO BLINK.  SUBMITTER STATED THIS BLANKET SHOULD BE INSPECTED AT 100-HOUR 	INTERVALS FOR DETERIORATION AND INTEGRITY AND SECURE CLAMP AT LOWER END OF NOSE GEAR ACTUATOR LOWER END.				1	L	7	2 	3O				1A10
1998101600013	19981016	00013	CE  	1998	10	16	98ZZZX3675       	1	19980814	G	2435	7121895	STARTER         			BEECH 	58    	58          	1152740	CE  										RT ENGINE	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	329H				P039871	TH219				STARTER FAILED ON RIGHT ENGINE TIS 64.9 HOURS SINCE FACTORY NEW ENGINE INSTALLED ON 7-14-98.  FAILED ON THIS DATE, 8-14-	98.  (30 DAYS).					1	L	7	2 	3O				3A16
1998101600014	19981016	00014	CE  	1998	10	16	98ZZZX3676       	1	19980814	G	2434	ALT9422	ALTERNATOR      	ELECTROSYS  		BEECH 	58    	58          	1152740	CE  										RT ENGINE	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	329H				8030668	TH219				ALTERNATOR FAILED ON RT ENGINE.  TIS 64.9 HOURS SINCE FACTORY NEW ENGINE INSTALLATION ON 7-14-98.  THIS DATE, 8-14-98, F	AILED.  (30 DAYS).					1	L	7	2 	3O				3A16
1998101600015	19981016	00015	SO  	1998	10	16	98ZZZX3677       	1	19980926	G	2434		WIRE            		454712      	PIPER 	PA31  	PA31350     	7103110	SO  										ALTERNATOR	MISINSTALLED    	B		A	VT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	66859					317405168				DURING TROUBLESHOOTING FOR AN INTERMITTENT ALTERNATOR FAILURE, NOTED WHEN EITHER ALTERNATOR IS SWITCHED OFF, THE REMAINI	NG ALTERNATOR ALSO TURNS OFF.  INSPECTION SHOWED THE CABLE FROM THE ALTERNATOR SHUNT TO THE ALTERNATOR CIRCUIT BREAKER S	WITCH (WIRE PIEC AND P2EC) WERE SWAPPED AT THE SWITCH.  WHEN SWITCH IS OPENED, THE OPPOSITE FIELD IS ALSO OPENED.  CORRE	CTLY CONNECTED SWITCHES AND WIRES, FUNCTIONAL CHECK OK.			1	L	7	2 	3O			 	A20SO
1998101600016	19981016	00016	EA  	1998	10	16	98ZZZX3678       	2	19980916	G	7421	HSR86	SPARK PLUG      			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	991CC	285  				241054				DURING THE COURSE OF AN ANNUAL INSPECTION, ALL BOTTOM PLUGS WERE FOUND TO HAVE CENTER ELECTRODE FAILURE.  ALL CENTER ELE	CTRODES WERE FOUND WEAKENED AT THE CERAMIC AND BENT OVER TOWARD THE GROUND.  SUBMITTER STATED CAUSE IS UNDETERMINED.					1	L	7	1 	3O	3	O		2A3     	1E10
1998101600017	19981016	00017		1998	10	16	98ZZZX3679       	4	19980915	G	3130	94E421	SWITCH          																	CABIN PRESSURE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										DIAPHRAGM IN SWITCH NOT WORKING PROPERLY.  SWITCH INOPERABLE.  (RUPTURED DIAPHRAGM).
1998101600018	19981016	00018	GL  	1998	10	16	98ZZZX3680       	2	19980824	G	7322		CABLE           			AMTR  	VP2   	VP2         	05626LF	GL  	AMTR  	AMTR  	4AR1200VOLKS	99999	GL  					CARBURETOR	DETACHED        	G				O				OTHER                   				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	15	2099J					V21759				THROTTLE CABLE ATTACHMENT CAME LOOSE AT CARBURETOR.  A .0625 INCH CABLE WAS THROUGH A BARREL AND SECURED WITH A NR 6 SET	 SCREW.  THE CABLE CAME LOOSE FROM THE LINKAGE CAUSING LOSS OF THROTTLE CONTROL RESULTING IN LOSS OF POWER AND THROTTLE 	CONTROL AND SUBSEQUENT CRASH AND DESTRUCTION OF THE AIRCRAFT.  SUBMITTER RECOMMENDED THAT A BACK-UP CLAMP BE INSTALLED O	N CABLE END PROTRUDING THROUGH CABLE BARREL.			1	L	7	1 	3O	3	O	NT	EXPA1L71	EXP3O
1998101600019	19981016	00019		1998	10	16	98ZZZX3681       	1	19980816	G	3230		ARMATURE        			AMTR  		CP301       												MLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	104S					WIS				DURING ANNUAL CONDITION INSPECTION, THE MAIN LANDING GEAR ATTACHMENT TO THE SPAR WAS FOUND CRACKED ON BOTH SIDES OF THE 	AIRCRAFT INCLUDING DAMAGE TO SPAR FACE PLATE.								0
1998101600020	19981016	00020	NE  	1998	10	16	98ZZZX3682       	2	19980818	G	7250	50L906	CASE            			BOEING	767   	767         	1385102	NM  	PWA   	PW4062	PW4062      		NE  					ENGINE	DAMAGED         	B			WA2D	A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			T	X	J	ENGINE CASE PENETRATION   	ENGINE FLAMEOUT           	WARNING INDICATION        	CL	CLIMB          	1			NE	03	CCCEB	1404 			CKLBC52166		P724746			DURING CLIMB FROM MIAMI, THE ENGINE (POS NR 1) EXPERIENCED TWO SURGES WITH EGT EXCEEDING 796 DEGREES CELSIUS FOR 15 SECO	NDS.  AN IN-FLIGHT SHUT DOWN AND AIR TURN BANK EFFECTED.  DISASSEMBLY INSPECTION AT PWORC REVEALS 360 DEGREE FAILURE OF 	THE HPT CASE WALL APPROXIMATELY .400 INCH AFT OF THE FRONT FLANGE.  SUBSEQUENT DAMAGE WAS FAILURE OF ALL 2ND STAGE TURBI	NE BLADES DUE TO CLASHING WITH T/E OF 2ND STAGE VANES.  PRATT & WHITNEY, E.H. IS CONDUCTING INVESTIGATION TO DETERMINE F	AILURE CAUSE AND CORRECTIVE ACTION.  CYCLES, 327.		2	L	7	2 	4F	4	F		EXPA2L72	E24NE
1998101600021	19981016	00021	SO  	1998	10	16	98ZZZX3683       	2	19980820	G	7520	652293	LINE            			CESSNA	414   	414A        	2075907	CE  	CONT  	O550  	TSIO550A    	41516	SO  					COOLING SYSTEM	CRACKED         	B			VA1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	19	300SQ					414A0416	L800543			CRACKED COOLANT LINE CAUSED LOSS OF COOLANT AND ENGINE SHUT DOWN.  LOG BOOKS NOT AVAILABLE AT TIME OF THIS REPORT.						1	L	7	2 	3O	3	O		A7CE    	E5SO
1998101600022	19981016	00022		1998	10	16	98ZZZX3684       	1	19980724	G	2410	642589	NUT             	TELEDYNECNTL	649304      															ALTERNATOR	CRACKED         	B	P		XA12	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					G1795050					NEW REPLACEMENT ALTERNATOR CAME WITH THIS NUT ON DRIVESHAFT.  THE CRACK WAS FOUND WHEN NUT WAS REMOVED TO INSTALL DRIVE 	COUPLING.  COULD BE VERY BAD AS NUT IS INSIDE ENGINE WHEN ASSEMBLED.  SUBMITTER SUSPECTS HYDROGEN EMBRITTLEMENT.
1998101600023	19981016	00023	SO  	1998	10	16	98ZZZX3685       	1	19980918	G	5551	7B105181	BRACKET         			GULSTM	GA7   	GA7         	3960401	SO  										HORIZONTAL STAB	CRACKED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	784GA	5974 				GA70071				DURING A ROUTINE 100-HOUR INSPECTION, MAINTENANCE PERSONNEL FOUND THE RT HORIZONTAL STABILIZER FORWARD ATTACHMENT BRACKE	T FRACTURED NEAR THE BOLT HOLE WHICH ATTACHES THE STABILIZER FORWARD SPAR TO THE AFT TAIL CONE BULKHEAD.  THE TAIL CONE 	BULKHEAD WAS ALSO FOUND CRACKED ADJACENT TO THE BRACKET.  THIS FAILURE MAY HAVE RESULTED FROM PRE-LOAD DURING INITIAL AS	SEMBLY.			1	L	7	2 	3O				A17SO
1998101600024	19981016	00024	CE  	1998	10	16	98ZZZX3686       	1	19980911	G	3230	5217840134	HOSE            			CESSNA	177   	177RG       	2073709	CE  										NLG	BURST           	G				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	13	52660	1250 				177RG1235				CRUISE FLIGHT AT 5,500 FEET, PILOT HEARD A BANG.  NO ABNORMAL ENGINE CHANGES.  AIRSPEED DROPPED 10-15 KNOTS.  PILOT DECI	DED TO LAND AT NEAREST AIRPORT.  LANDING GEAR WOULD NOT EXTEND.  FLY-BY SHOWED GEAR HANGING.  MANUAL EXTENSION WOULD NOT	 LOWER GEAR.  PILOT LANDED ON BELLY OF AIRCRAFT.  FOUND UP LINE HOSE TO NOSE GEAR ACTUATOR BURST.				1	H	7	1 	3O				A20CE
1998101600025	19981016	00025	GL  	1998	10	16	98ZZZX3687       	3	19980820	G	6114	C5270	BEARING         			CESSNA	421   	421C        	2076016	CE  						MCAULY	3FF32	3FF32C501   	GL  	PROPELLER HUB	MISMANUFACTURED 	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	421PA		113  			421C0224		803986		WRONG SIZE BEARING INSTALLED CAUSING BEARING RACE TO BRAKE GETTING INTO HUB.  HUB WAS REJECTED.						1	L	7	2 	3O				A7CE    		5	C	P45GL
1998101600026	19981016	00026	EA  	1998	10	16	98ZZZX3688       	2	19980916	G	7510	63610D0184	LINE            			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A28      		EA  					LT ENGINE	RUPTURED        	C				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	05	671LL	11900				LJ148	PCE4462			AS ICE DOORS WERE DEPLOYED, A LARGER THAN NORMAL TORQUE LOSS WAS NOTED.  UPON LANDING, FOUND LEFT ENGINE BLEED AIR LINE 	FAILED.  THIS LINE WAS MANUFACTURED IN MARCH '66.  INNER NYLON OF LINE WAS HARD AND BRITTLE AND IS SUBJECT TO HOT BLEED 	AIR.				1	L	7	2 	3T	4	T		3A20    	E4EA
1998101600027	19981016	00027		1998	10	16	98ZZZX3689       	1	19980831	G	3233	99810057651	ACTUATOR        	BEECH       																MLG	MALFUNCTIONED   	B			BXSR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	09					349					NEWLY OVERHAULED ACTUATOR USED ON KING AIR 200'S WAS FOUND TO TURN IN THE INCORRECT DIRECTION; THUS, IT WOULD GO UP WHEN	 THE OTHER GEAR WOULD GO DOWN, AND VISE VERSA.
1998101600028	19981016	00028	CE  	1998	10	16	98ZZZX3690       	1	19980923	G	2424	ALT9422R	ALTERNATOR      	ELECTROSYS  		BEECH 	58    	58          	1152740	CE  										ENGINE	INOPERATIVE     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H				8021772	TH219				FOUND ALTERNATOR NOT OPERATING.  TIS 44.4 HOURS.						1	L	7	2 	3O				3A16
1998101600029	19981016	00029	SO  	1998	10	16	98ZZZX3691       	2	19980917	G	7414	6310	MAGNETO         	SLICK       		BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE	INOPERATIVE     	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	329H	38   			98052050	TH219	298664R			FOUND RT MAGNETO INOPERATIVE.  ROTATES, BUT DOES NOT PRODUCE HIGH VOLTAGE SPARK.  TIS: 38.2 HOURS SINCE NEW.						1	L	7	2 	3O	3	O		3A16    	E5CE
1998101600030	19981016	00030	SO  	1998	10	16	98ZZZX3692       	2	19980617	G	8530	5637750	BOLT            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					CYLINDER HEAD	BROKEN          	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	01	88604	1550 				421C0604	292084R			PILOT NOTICED WHITE SMOKE COMING FROM LEFT TOP COWLING LOUVERS.  SHUT ENGINE DOWN AND LANDED.  MAINTENANCE FOUND BROKEN 	ROCKER SHAFT BOLT.  REPLACED BOTH BOLTS AND GASKET.  PERFORMED LEAK CHECK AND RUN-UP.  ALL CHECKED GOOD.					1	L	7	2 	3O	3	O		A7CE    	E7CE
1998101600031	19981016	00031		1998	10	16	98ZZZX3693       	4	19980911	G	2562	0004006A	BATTERY         	LEIGH       		CESSNA	172   	172M        	2072418	CE  										CABIN	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	64414	247  			302145	17265211				AT PRE-FLIGHT, OWNER FOUND CONTENTS OF ONE BATTERY CELL IN BAGGAGE AREA CARPET.  FOUND ELT CASING CRACKED AND PIECES BRO	KEN AWAY IN BAGGAGE AREA.  ELT BATTERY EXPLODED INSIDE UNIT.					1	H	7	1 	3O			NT	3A12
1998101600032	19981016	00032	EA  	1998	10	16	98ZZZX3694       	2	19980828	G	7210	310152501	GEAR            			AYRES 	S2    	S2RT15NORMAL	0970105	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ENGINE	FAILED          	B			CP2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	4015P		1101 			T15004	PCE56015			THE SUN GEAR OF THE 1ST STAGE FAILED.  INSTALLED NEW, 1.101.3 HRS AGO.						1	L	7	1 	3T	4	T		A3SW    	E4EA
1998101600033	19981016	00033	WP  	1998	10	16	98ZZZX3695       	2	19980915	G	7260	3101836	HOUSING         			CASA  	C212  	C212CC      	2410204	EU  	GARRTT	TPE331	TPE33110    	01514	WP  					ACCESSORY DRIVE	CRACKED         	B	P		EHAR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	423CA	14535	2425 			240	P37050C			HOUSING ASSY ACCESSORY DRIVE P/N 3101836 HAS A CRACK IN THE MOUNTING PAD BOSS.  FOUR BOLTS ATTACH THE RT ENGINE MOUNT TO	 THE BOSS.  THE LOWER OUTBOARD BOLT INSERT CRACKED OUT.					2	H	7	2 	4T	4	T		A43EU   	E4WE
1998101600034	19981016	00034	CE  	1998	10	16	98ZZZX3696       	1	19980914	G	3244	184F081	TIRE            	GOODYEAR    		CESSNA	500   	550         	2076604	CE  										NLG	OUT OF BALANCE  	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	23	57SF	147  			60821303	5500402				THE INTERNAL BALANCE WEIGHT/PATCH BECAME LOOSE FROM THE NOSE TIRE CAUSING AN UNBALANCED CONDITION OF THE TIRE/WHEEL ASSE	MBLY.					1	L	7	2 	4F				A22CE
1998101600044	19981016	00044	SW  	1998	10	16	98ZZZX3705       	1	19980914	G	3211	2120504361	CAP ASSEMBLY    			BELL  	212   	212         	1181420	SW  										MLG	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8530B					30702				CAP ASSEMBLY WORN BEYOND LIMITS.  REPLACED TWO EACH.						1	G	7	1 	4U				H4SW
1998101600146	19981016	00146	WP  	1998	10	16	98ZZZX3719       	1	19980914	G	6322	A266331	IMPELLER        			HUGHES	369   	369D        	4470706	WP  										BLOWER	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				IMPELLER BLOWER HAD FIVE CRACKED VANES BEYOND LIMITS.  REMOVED AND REPLACED, RESHIMMED.						1	G	7	1 	3U				H3WE
1998102300001	19981023	00001	SO  	1998	10	23	98ZZZX3745       	1	19980904	G	3230	9572402	MOUNT           			PIPER 	PA34  	PA34200     	7103405	SO  										NLG ACTUATOR	CRACKED         	G	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	22JL	3007 				347250198				AFTER THE FAILURE OF THIS PART ON N NR 56187, THE PAINT WAS REMOVED FROM THE UPPER LEFT CORNER WHERE THE NOSE GEAR ACTUA	TOR ATTACHES TO THIS BRACKET.  A CRACK WAS THEN FOUND EMANATING FROM THE BOLT HOLE TO THE EDGE.					1	L	7	2 	3O				A7SO
1998102300002	19981023	00002	SO  	1998	10	23	98ZZZX3746       	1	19980904	G	3230	9572402	MOUNT           			PIPER 	PA34  	PA34200     	7103405	SO  										NLG ACTUATOR	CRACKED         	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	56187	3086 				347350302				PART FAILED ON A NORMAL LANDING AT THE UPPER LEFT CORNER THAT HOLDS THE NOSE GEAR ACTUATOR AND LINK ASSY IN PLACE.  THIS	 ALLOWED THE DRAG LINK TO NOT GO OVER CENTER RESULTING IN THE NOSE GEAR COLLAPSING ON ROLL-OUT.					1	L	7	2 	3O				A7SO
1998102300003	19981023	00003	SO  	1998	10	23	98ZZZX3747       	2	19980909	G	7310	627658A1	ELBOW           			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					CARBURETOR	LOOSE           	D				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			NM	09	1661M	1500 				18264406	463621			INTAKE MANIFOLD ELBOW ABOVE CARBURETOR PULLED OUT OF COUPLER HOSE DURING TAXI.  SUBMITTER STATED WOULD HAVE CAUSED ENGIN	E FAILURE IN-FLIGHT.					1	H	7	1 	3O	3	O	NT	TA13    	E273
1998102300004	19981023	00004	SW  	1998	10	23	98ZZZX3748       	1	19980826	G	5753		SKIN            			MOONEY	M20   	M20J        	5870219	SW  										FLAP	LOOSE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	9152N					243408				DURING FLIGHT, FLAPS WERE MOVED FROM FULL DOWN TO APPROACH THEN TO FULL UP AT WHICH TIME A SPLIT FLAP CONDITION OCCURRED	.  UPON INSPECTION, IT WAS DETERMINED A SKIN SEAM WAS HANGING DOWN AND CATCHING ON THE FLAP SKIN PREVENTING IT FROM GOIN	G FULL UP.				1	L	7	1 	3O				2A3
1998102300005	19981023	00005	NE  	1998	10	23	98ZZZX3749       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROP BLADE	ERODED          	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1759 					HJ450		RE-SECURED AND TAP TESTED EROSION SHIELD IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300006	19981023	00006		1998	10	23	98ZZZX3750       	2	19980904	G	7314	RA9093	SPRING          	ROMEC       	RG37060A    															BYPASS VALVE	DISINTEGRATED   	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27					B321019					UNIT RECEIVED FOR REPAIR.  UPON INSPECTION, FOUND BYPASS VALVE SPRING DISINTEGRATED AND RELIEF VALVE HOUSING VALVE, LINE	R, BLADES, AND ROTOR DAMAGED DUE TO SPRING ENTERING PUMP THROUGH RELIEF VALVE HOUSING.
1998102300007	19981023	00007		1998	10	23	98ZZZX3751       	2	19980904	G	7314	RG348971	COUPLING        	ROMEC       	RG37060A    															FUEL PUMP	WORN            	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27		4353 			B1440					UNIT RECEIVED FOR REPAIR.  UPON INSPECTION, NOTED DRIVE COUPLING INTERNAL SPLINE COMPLETELY WORN (ROUNDED OFF).  ALSO, O	THER PROBLEMS FOUND INTERNALLY WITH UNIT LEADING TO PUMP FAILURE.
1998102300008	19981023	00008		1998	10	23	98ZZZX3752       	2	19980904	G	7314	RA9093	SPRING          	ROMEC       	RG37060A    															BYPASS VALVE	DISINTEGRATED   	B			OL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27		4353 			B1440					UNIT RECEIVED FOR REPAIR.  UPON INSPECTION, FOUND BYPASS VALVE SPRING MISSING AND RELIEF VALVE HOUSING, VALVE, LINER, BL	ADES, AND ROTOR DAMAGED DUE TO SPRING ENTERING PUMP THROUGH RELIEF VALVE HOUSING.
1998102300009	19981023	00009	NE  	1998	10	23	98ZZZX3753       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2798 					HJ200A		REPAIRED EROSION SHIELD ON NR 1 BLADE IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300010	19981023	00010	NE  	1998	10	23	98ZZZX3754       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2611 					HJ200A		REPAIRED EROSION SHIELD ON NR 1 BLADE IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300011	19981023	00011	NE  	1998	10	23	98ZZZX3755       	3	19980923	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2337 					HJ163A		REPAIRED EROSION SHIELD DUE TO DEBONDING.																5	C	P10NE
1998102300012	19981023	00012	NE  	1998	10	23	98ZZZX3756       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			CE	01			1020 					HJ181A		COMPLETE EROSION SHIELD FROM BLADE S/N 811 FLEW OFF THE PROPELLER AT 500 FEET ON TAKEOFF FROM DEN.  PILOT HEARD A LOUD '	BANG' AND FELT VIBRATION FROM LT ENGINE. ON LANDNG, FOUND DEPARTING SHIELD HAD STRUCK LT FUSELAGEOF A/C 251YV PENETRATIN	G IT AND FLYING ACROSS THE CABIN STRIKING THE INNER PASSENGER.  WINDOW ON SEAT 2C.  OTHER FUSELAGE DAMAGE ALSO OCCURRED.	  INCIDENT IS UNDER NTSB/FAA INVESTIGATION.													5	C	P10NE
1998102300013	19981023	00013	NE  	1998	10	23	98ZZZX3757       	3	19980923	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2361 					HJ847		REPLACED EROSION SHIELD ON BLADES NR 3 AND NR 4 IAW MFG CMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300014	19981023	00014	NE  	1998	10	23	98ZZZX3758       	3	19980923	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3683 					HJ205A		REPLACED EROSION SHIELD ON BLADES NR 2 AND NR 3 IAW MFG CMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300015	19981023	00015	NE  	1998	10	23	98ZZZX3759       	3	19980923	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			817  					HJ610		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO .75 INCH SQUARE DEBOND.																5	C	P10NE
1998102300016	19981023	00016	NE  	1998	10	23	98ZZZX3760       	3	19980923	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1251 					HJ30A		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG CMM DUE TO DEBOND.																5	C	P10NE
1998102300017	19981023	00017	NE  	1998	10	23	98ZZZX3761       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			590  					HJ901		REPLACED EROSION SHIELD ON NR 3 BLADE IAW MFG CMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300018	19981023	00018	NE  	1998	10	23	98ZZZX3762       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			561  					HJ901		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300019	19981023	00019	NE  	1998	10	23	98ZZZX3763       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2021 					HJ894		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300020	19981023	00020	NE  	1998	10	23	98ZZZX3764       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2829 					HJ200A		REPAIRED EROSION SHIELD ON NR 1 BLADE IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300021	19981023	00021	NE  	1998	10	23	98ZZZX3765       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2251 					HJ196A		SENT BLADE NR 1 TO AIRCRAFT PROPELLER SERVICE FOR EROSION SHIELD AND DE-ICE BOOT REPLACEMENT DUE TO DEBONDING.																5	C	P10NE
1998102300022	19981023	00022	NE  	1998	10	23	98ZZZX3766       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			809  					HJ869		REPLACED EROSION SHIELD ON NR 1 BLADE IAW MFG COMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300023	19981023	00023	NE  	1998	10	23	98ZZZX3767       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2618 					HJ809		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG COMM DUE TO DEBONDING.																5	C	P10NE
1998102300024	19981023	00024	NE  	1998	10	23	98ZZZX3768       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2467 					HJ809		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG COMM DUE TO DEBONDING.																5	C	P10NE
1998102300025	19981023	00025	NE  	1998	10	23	98ZZZX3769       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2769 					HJ809		REPLACED EROSION SHIELD IAW MFG COMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300026	19981023	00026	NE  	1998	10	23	98ZZZX3770       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			189  					HJ593		REPLACED EROSION SHIELD IAW MFG COMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300027	19981023	00027	NE  	1998	10	23	98ZZZX3771       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			617  					HJ651		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG COMM DUE TO DEBOND.																5	C	P10NE
1998102300028	19981023	00028	NE  	1998	10	23	98ZZZX3772       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	LOOSE           	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			454  					HJ651		RE-ATTACHED EROSION SHIELD IAW MFG COMM.																5	C	P10NE
1998102300029	19981023	00029	NE  	1998	10	23	98ZZZX3773       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2876 					HJ717		REPLACED EROSION SHIELD ON NR 2 BLADE IAW MFG CMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300030	19981023	00030	NE  	1998	10	23	98ZZZX3774       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2891 					HJ569		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBOND.																5	C	P10NE
1998102300031	19981023	00031	NE  	1998	10	23	98ZZZX3775       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3688 					HJ568		REPLACED EROSION SHIELD ON NR 1 BLADE IAW MFG COMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998102300032	19981023	00032	NE  	1998	10	23	98ZZZX3776       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1704 					HJ547		EROSION SHIELD DEBONDING.  RESECURED EROSION SHIELD IAW MFG CMM.																5	C	P10NE
1998102300033	19981023	00033	NE  	1998	10	23	98ZZZX3777       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2810 					HJ573		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBONDING.																5	C	P10NE
1998102300034	19981023	00034	NE  	1998	10	23	98ZZZX3778       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1023 					HJ599		REPLACED EROSION SHIELD ON NR 1 AND NR 2 BLADES IAW MFG CMM DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300035	19981023	00035	NE  	1998	10	23	98ZZZX3779       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2876 					HJ536		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300036	19981023	00036	NE  	1998	10	23	98ZZZX3780       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			984  					HJ514		REPLACED EROSION SHIELD ON NR 2 BLADE IAW MFG COMM DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300037	19981023	00037	NE  	1998	10	23	98ZZZX3781       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			990  					HJ508		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300038	19981023	00038	NE  	1998	10	23	98ZZZX3782       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1232 					HJ508		REPAIRED 3 BLADES WITH DEBONDED AREAS IAW MFG CMM.																5	C	P10NE
1998102300039	19981023	00039	NE  	1998	10	23	98ZZZX3783       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2784 					HJ508		REPLACED EROSION SHIELD ON NR 4 BLADE IAW MFG COMM DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300040	19981023	00040	NE  	1998	10	23	98ZZZX3784       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2259 					HJ450		REPLACED EROSION SHIELD ON NR 3 BLADE IAW MFG MM DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300041	19981023	00041	NE  	1998	10	23	98ZZZX3785       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2535 					HJ447		REPAIRED EROSION SHIELD ON NR 1 AND NR 3 BLADES IAW MFG CMMD UE TO DEBONDS.																5	C	P10NE
1998102300042	19981023	00042	NE  	1998	10	23	98ZZZX3786       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3144 					HJ447		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300043	19981023	00043	NE  	1998	10	23	98ZZZX3787       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2892 					HJ447		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300044	19981023	00044	NE  	1998	10	23	98ZZZX3788       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1713 					HJ211		REPAIRED EROSION SHIELD ON NR 1 BLADE IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300045	19981023	00045	NE  	1998	10	23	98ZZZX3789       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			974  					HJ186A		REPALCED EROSION SHIELD ON NR 4 DUE TO DEBOND BEYOND LIMITS.  REPAIRED EROSION SHIELD ON NR 2 BLADE.																5	C	P10NE
1998102300046	19981023	00046	NE  	1998	10	23	98ZZZX3790       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			691  					HJ194A		REPLACED EROSION SHIELD DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300047	19981023	00047	NE  	1998	10	23	98ZZZX3791       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1919 					HJ196A		REPAIRED EROSION SHIELD ON NR 2 BLADE IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300048	19981023	00048	NE  	1998	10	23	98ZZZX3792       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2136 					HJ203A		REPAIRED NR 2 AND NR 3 BLADES IAW HARTZELL  MANUAL DUE TO DEBONDS OF THE EROSION SHIELD.																5	C	P10NE
1998102300049	19981023	00049	NE  	1998	10	23	98ZZZX3793       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1645 					HJ203A		REPAIRED EROSION SHIELD ON NR 3 BLADE IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300050	19981023	00050	NE  	1998	10	23	98ZZZX3794       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3086 					HJ194A		REPAIRED EROSION SHIELD IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300051	19981023	00051	NE  	1998	10	23	98ZZZX3795       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2145 					HJ427		REPLACED EROSION SHIELD O NR 1 BLADE IAW MFG CMM DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300052	19981023	00052	NE  	1998	10	23	98ZZZX3796       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1881 					HJ427		REPLACED EROSION SHIELD ON NR 4 BLADE IAW MFG COMM DUE TO DEBONDS BEYOND LIMITS.  REPAIRED EROSION SHIELD ON NR 2 BLADE 	IAW MFG CMM DUE TO DEBONDS.															5	C	P10NE
1998102300053	19981023	00053	NE  	1998	10	23	98ZZZX3797       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2928 					HJ229		REPLACED EROSION SHIELD ON NR 1 BLADE DUE TO DEBONDS BEYOND LIMITS.  REPLACED IAW MFG CMM.																5	C	P10NE
1998102300054	19981023	00054	NE  	1998	10	23	98ZZZX3798       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			233  					HJ337		REPLACED EROSION SHIELD ON NR 1 AND NR 3 BLADES IAW MFG CMM DUE TO DEBONDS BEYOND LIMITS.  REPAIRED EROSION SHIELD ON NR	 4 BLADE IAW MFG COMM DUE TO DEBONDS.															5	C	P10NE
1998102300055	19981023	00055	NE  	1998	10	23	98ZZZX3799       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1199 					HJ211		REPAIRED EROSION SHIELD DUE TO DEBONDS.  REPAIRED IAW MFG CMM.																5	C	P10NE
1998102300056	19981023	00056	NE  	1998	10	23	98ZZZX3800       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			589  					HJ211		REPAIRED EROSION SHIELD ON NR 1 AND NR 4 BLADES IAW MFG CMM DUE TO DEBONDS.																5	C	P10NE
1998102300057	19981023	00057	NE  	1998	10	23	98ZZZX3801       	3	19980917	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1984 					HJ211		REPLACED EROSION SHIELD ON NR 1 BLADE DUE TO DEBONDS BEYOND LIMITS.																5	C	P10NE
1998102300058	19981023	00058	CE  	1998	10	23	98ZZZX3802       	1	19980914	G	5412	0851601201	BULKHEAD        			CESSNA	340   	340A        	2076405	CE  										ENGINE BAY	CORRODED        	B			EIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	34BJ	2400 				340A1003				DURING A C OF A INSPECTION (ANNUAL), LEFT ENGINE COMPARTMENT CANTED BULKHEADS WERE FOUND SEVERELY CORRODED (EXFOLIATION 	TYPE CORROSION).  BOTH FWD AND AFT CANTED BULKHEADS REPLACED WTIH FACTORY NEW PARTS.					1	L	7	2 	3O				3A25
1998102300059	19981023	00059	CE  	1998	10	23	98ZZZX3803       	1	19980914	G	5412	085160127	BULKHEAD        			CESSNA	340   	340A        	2076405	CE  										ENGINE BAY	CORRODED        	B			EIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	34BJ	2400 				340A1003				DURING A C OF A INSPECTION (ANNUAL), LEFT ENGINE COMPARTMENT CANTED BULKHEADS WERE FOUND SEVERELY CORRODED (EXFOLIATION 	TYPE CORROSION).  BOTH FWD AND AFT CANTED BULKHEADS REPLACED WTIH FACTORY NEW PARTS.					1	L	7	2 	3O				3A25
1998102300060	19981023	00060	CE  	1998	10	23	98ZZZX3804       	1	19980918	G	2913	206201	FINGER          	AIRIGHT     	502004      	BEECH 	90    	C90         	1152913	CE  										POWER PACK	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	90WP				605	LJ1383				DURING ROUTINE INSPECTION, FOUND SHOULDER SEPARATED FROM SCREEN.  THIS CONDITION COULD LEAD TO POSSIBLE INJESTION OF SCR	EEN.					1	L	7	2 	3T				3A20
1998102300061	19981023	00061	SO  	1998	10	23	98ZZZX3805       	1	19980910	G	3230	2084607	BUNGEE ARM      			PIPER 	PA30  	PA30        	7103002	SO  										LT/RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	8352Y					301499				DURING ROUTINE ANNUAL INSPECTION AND WHILE INSPECTING MAIN GEAR AND RETRACT SYSTEM (INCLUDING BUNGEES), FOUND BOTH MAIN 	GEAR BUNGEE ARM ASSEMBLIES CRACKED AND BOTH SHOWED SIGNS OF HEAT DISCOLORATION ON BOTH SHAFTS WHICH SUBMITTER SUGGESTED 	WAS A LACK OF LUBRICATION.				1	L	7	2 	3O				A1EA
1998102300063	19981023	00063	SO  	1998	10	23	98ZZZX3807       	2	19980917	G	8530	G25615	COVER           			CESSNA	210   	T210R       	2073459	CE  	CONT  	O520  	TSIO520CE   	17040	SO  					NR 4 CYLINDER	MISMANUFACTURED 	H				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	01	7681U					21064975	268578R			FOUND LARGE OIL LEAK AT NR 4 CYLINDER ROCKER COVER DURING FIRST GROUND RUN OF THIS ENGINE FROM CONTINENTAL.  FOUND NR 4 	UPPER RT MOUNT MACHINED INCORRECTLY.  THIS IS A CONTINENTAL REBUILT ENGINE.					1	H	7	1 	3O	3	O	RT	3A21    	E8CE
1998102300065	19981023	00065	SO  	1998	10	23	98ZZZX3809       	2	19980810	G	8530	SA10200A20P	CYLINDER        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 1	FAILED          	G				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	704UV	1912 				15078893	19985991A			CYLINDER SEPARATED THREE-FOURTHS THE WAY AROUND AT MID-BARREL.  SUBSEQUENT OIL RING FAILURE.						1	H	7	1 	3O	3	O		3A19    	E252
1998102300066	19981023	00066	CE  	1998	10	23	98ZZZX3810       	1	19980924	G	8010	S1580A1	CONTACTOR       			CESSNA	337   	P337H       	2075731	CE  										STARTER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	5KX	2000 				P3370339				CONTACTOR FAILED CLOSED (WELDED?).  SUBMITTER STATED THIS CAUSED STARTER TO EVENTUALLY FAIL, GROUNDED, CLOSED DOWN ENTIR	E ELECTRICAL SYSTEM.  NO INCIDENT OCCURRED BECAUSE PILOT RETURNED SAFELY AND SKILLFULLY.					1	H	7	2 	3O				A6CE
1998102300067	19981023	00067	CE  	1998	10	23	98ZZZX3811       	1	19980924	G	8011	6462751	STARTER         	ELECTROSYS  		BEECH 	58    	58          	1152740	CE  										ENGINE	INOPERATIVE     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	329H		14   		7121893	TH219				FOUND RIGHT STARTER INOPERABLE.  TIS:  78.9 HOURS ON ENGINE.  TIS OF STARTER REMOVED:  14 HOURS.						1	L	7	2 	3O				3A16
1998102300068	19981023	00068	CE  	1998	10	23	98ZZZX3812       	1	19980928	G	2750	0512128	BRACKET         			CESSNA	185   	185         	2072802	CE  										FS 65.33	BROKEN          	D		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	99	23FG	8600 				18504035				PILOT REPORTED A 'POP' WAS HEARD WHEN SELECTING 4TH NOTCH OF FLAPS ON LANDING.  POST-FLIGHT INSPECTION WAS UNABLE TO LOC	ATE SOURCE.  AT NEXT TAKEOFF WITH FIRST NOTCH OF FLAPS AIRCRAFT ROLLED TO THE RIGHT.  FLAPS WERE RETRACTED AND SAFE LAND	ING ACCOMPLISHED.  IN-DEPTH INSPECTION FOUND BRACKET UNDER CABIN FLOOR BROKEN.  FLAPS WORKED NORMALLY, HOWEVER, WHEN FOR	CE WAS APPLIED TO RT FLAP, IT MOVED UPWARD APPROXIMATELY 15 DEGREES.			1	H	7	1 	3O			NC	3A24
1998102300069	19981023	00069		1998	10	23	98ZZZX3813       	2	19980925	G	8520	78027	BOLT            																	CONNECTING ROD	MISMANUFACTURED 	B			NX42	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15										WHILE CONDUCTING PRE-ASSEMBLY INSPECTION OF PARTS DURING ENGINE OVERHAUL, NOTICED THE CONNECTING ROD NUT WOULD NOT THREA	D COMPLETELY ON ONE CONNECTING ROD BOLT.  THE THREAD MAJOR DIAMETER ON THE DEFECTIVE BOLT WAS FOUND TO  BE .378 INCH WHI	CH RESULTED IN AN INTERFERENCE FIT WITH THE NUT.  NORMAL THREAD MAJOR DIAMETER SHOULD BE .373 INCH.  SUBMITTER SUGGESTED	 CAUSE WAS A MACHINE TOOL TOLERANCE ERROR DURING PRODUCTION.
1998102300070	19981023	00070	GL  	1998	10	23	98ZZZX3814       	2	19980914	G	7230	23057142	CASE HALVES     			BELL  	206   	OH58A       	1181579	SW  	ALLSN 	250C  	T63A720     	03002	GL  					COMPRESSOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	58AG		553  		40722	7221131	AE406078			LINER FLAKING - REMOVED AND REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998102300189	19981023	00189	SW  	1998	10	23	98ZZZX3826       	1	19980815	G	2910	70010F000Y154	HOSE            			BELL  	206   	206B3       	1181506	SW  										CYCLIC SERVO	RUPTURED        	B		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	70DB	247  				1730				AIRCRAFT LOST HYDRAULIC POWER TO FLIGHT CONTROLS DUE TO RUPTURED RIGHT HAND CYCLIC SERVO FLEX LINE.  LINE SUPPLIES HYDRA	ULIC FLUID TO AFT END OF SERVO.  IMPROPER ASSEMBLY OF FITTING TO HOSE IS SUSPECTED.  REF:  QUALITY AVIATION SERVICES, R/	S QS7R937J.				1	G	7	1 	3U				H2SW
1998102300365	19981023	00365	WP  	1998	10	23	98ZZZX3852       	1	19980721	G	6420	369A16023	BOLT            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	MISMANUFACTURED 	B			NZBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05										UPON UNSUCCESSFUL INSTALLATION ATTEMPT OF A NEW BOLT, THE BOLT WAS SUBSEQUENTLY MEASURED AND DETERMINED THAT THE OUTSIDE	 DIAMETER WAS OVERSIZED BY .001 INCH.  THE REMAINING SPARE BOLTS FROM THE SAME BATCH WERE THEN MEASURED, AND ONE ADDITIO	NAL BOLT WAS FOUND TO EXCEED THE CORRECT DIAMETER BY .001 INCH.				1	G	7	1 	3U				H3WE
1998102300366	19981023	00366		1998	10	23	98ZZZX3853       	1	19980923	G	6420	3160S333005400	BEARING         																	TAIL ROTOR	ROUGH           	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11		145  								S/N'S A33752, A33751, A33383 - ALL BEARINGS (3 EACH) ARE ROUGH AND STICKING UNDER LOAD.
1998102300367	19981023	00367	EA  	1998	10	23	98ZZZX3854       	2	19981006	G	8520		ROD             			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					NR 3 CYLINDER	FAILED          	D		A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			HO	HOVERING       	1			EA	13	536X					170574	L1250651A			AIRCRAFT WAS HOVERING.  LOUD BANG WAS HEARD, FOLLOWED BY ENGINE SUDDEN STOPPAGE.  AIRCRAFT CONTACTED GROUND HARD CAUSING	 LANDING GEAR DAMAGE.  SUBMITTER STATED IT APPEARED THE NR 3 CYLINDER PISTON CONNECTING ROD FAILED.  ENGINE WAS DUE OVER	HAUL IN APPROXIMATELY 200 HOURS.  SUBMITTER STATED UNABLE TO TELL HOW LONG PART WAS IN SERVICE, HOW MANY OVERHAULS IT HA	D BEEN THROUGH, OR IF ENGINE HAD BEEN OVERSPED BEFORE CURRENT OWNER BOUGHT AIRCRAFT.			1	G	7	1 	3O	3	O		4H12    	1E10
1998102300368	19981023	00368	EA  	1998	10	23	98ZZZX3855       	2	19981004	G	8530		LINE            			HUGHES	269   	269A        	4470402	WP  	LYC   	O360  	HIO360B1A   	41514	EA  					NR 1 CYLINDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	72LT					580863				INJECTION LINE NR 1 CYLINDER CRACKED AND SEPARATED AT INJECTION SERVO.  HOBBS TIME 1,596.2 HOURS.						1	G	7	1 	3O	3	O		4H12    	1E10
1998102300369	19981023	00369	WP  	1998	10	23	98ZZZX3856       	1	19980406	G	6520	369D25400	GEARBOX         			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	MAKING METAL    	B			LS1R	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	13	369AW		1195 		1543	40117D				PILOT LANDED AIRCRAFT AFTER T/R CHIP LIGHT CAUTION LIGHT ILLUMINATED.  TAIL ROTOR CHIP DETECTOR WAS INSPECTED.  A LARGE 	AMOUNT OF METAL ACCUMULATION WAS EVIDENT.  TAIL ROTOR GEARBOX WAS REMOVED AND REPLACED AND SENT FOR EVALUATION.  UPON TE	ARDOWN INSPECTION, ONE TOOTH ON INPUT DRIVE GEAR WAS FOUND BROKEN.  FURTHER INVESTIGATION IS IN PROGRESS.				1	G	7	1 	3U				H3WE
1998102300370	19981023	00370	WP  	1998	10	23	98ZZZX3857       	1	19980922	G	7714	369H4551	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J				5825	900801D				N1 SLOW TO COME UP ON STARTS.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998102300371	19981023	00371		1998	10	23	98ZZZX3858       	4	19980923	G	2340	18486601	COMM BOX        			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J				1090068	900801D				UNABLE TO COMMUNICATE INSIDE AIRCRAFT OR TO GROUND.  REPLACED COMM BOX.						1	G	7	1 	3U				H3WE
1998102300372	19981023	00372	WP  	1998	10	23	98ZZZX3859       	1	19980923	G	7714	369H4551	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J				1015	900801D				N1 GAUGE DID NOT COME UP.  REPLACED.						1	G	7	1 	3U				H3WE
1998102300373	19981023	00373		1998	10	23	98ZZZX3860       	4	19980923	G	3452	KT76A	TRANSPONDER     			BELL  	204   	UH1H        	1181407	SW  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	51AG		9    		24077	7120178				TRANSPONDER WOULD NOT TEST.  SENT FOR REPAIR.						1	G	7	1 	4U				EXPA1G71
1998102300374	19981023	00374	SW  	1998	10	23	98ZZZX3861       	1	19980831	G	7714	206375010101	TACHOMETER      			BELL  	206   	OH58A       	1181579	SW  										COCKPIT	ERRATIC         	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	58AG				1008D	7221131				TACH ERRATIC, UNRELIABLE CORE RETURN.						1	G	7	1 	3U				H2SW
1998102300375	19981023	00375	WP  	1998	10	23	98ZZZX3862       	1	19980922	G	6220	369A76132	LINK            			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				LINK ASSEMBLY WORN BEYOND LIMITS.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998102300376	19981023	00376	WP  	1998	10	23	98ZZZX3863       	1	19980923	G	6420	369A1802	BEARING         			HUGHES	369   	369E        	4470707	WP  										TAIL ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	8330P					0330E				TAIL ROTOR BEARING WORN.						1	G	7	1 	3U				H3WE
1998102300377	19981023	00377		1998	10	23	98ZZZX3864       	1	19980826	G	2434	ALV9510	ALTERNATOR      	PRESTOLITE  																ENGINE	FAILED          	B			NI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03					2K000041T					ALTERNATOR WAS FOUND UNAIRWORTHY 'OUT OF THE BOX' DUE TO LOCKED CONDITION OF THE ROTOR ASSEMBLY.  SUBMITTER STATED ALTER	NATOR WAS NEWLY OVERHAULED.
1998102300379	19981023	00379	SO  	1998	10	23	98ZZZX3866       	1	19980826	G	2913		SPLINE          		1213HGD310  	PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC PUMP	CORRODED        	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	867CJ				1730	318152105				THIS PUMP REMOVED DUE TO SHEARED DRIVE SPLINE.  TOTAL TIME - NEW FROM PIPER FACTORY.  EXAMINATION REVEALED CORROSION ON 	THE INSIDE OF THE SPLINE SHAFT.					1	L	7	2 	3O				A20SO
1998102300380	19981023	00380	SO  	1998	10	23	98ZZZX3867       	1	19980826	G	2913		SPLINE          		1213HGB310  	PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC PUMP	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	867CJ	2051 			1260	318152105				THIS PUMP REMOVED DUE TO SHEARED DRIVE SPLINE.  TOTAL TIME - 2,051. HOURS. EXAMINATION REVEALED CORROSION ON THE INSIDE 	OF THE SPLINE SHAFT.					1	L	7	2 	3O				A20SO
1998102300381	19981023	00381	EA  	1998	10	23	98ZZZX3868       	2	19980901	G	7414	M3333	MAGNETO         	SLICK       	6331        	PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	8216T	407  			95070029	328206037	L1795348A			ROUTINE CHECK OF IMPULSE COUPLING REVEALED BOTH PAWLS EXCEED NORMAL GAP BETWEEN PAWLS AND PLATE BY AN EXTREME AMOUNT.  A	LSO, ONE PAWL PIN WAS OBVIOUSLY BENT SO THE HEAD TIPPED OUTBOARD FROM CENTER.  THIS PART HAD BEEN INSPECTED 100 HOURS PR	IOR AND FOUND TO BE NORMAL IN ALL RESPECTS.  THESE COUPLERS SEEM TO BE TOTALLY UNPREDICTABLE FOR SERVICE LIFE.  SUBMITTE	R STATED HAVE FOUND FAILURES AS LOW AS 50 HOURS IN SERVICE.			1	L	7	1 	3O	3	O		A3SO    	1E4
1998102300382	19981023	00382	GL  	1998	10	23	98ZZZX3869       	3	19980901	G	6111	F84750D4	BLADE           			PIPER 	PA32  	PA32300     	7103212	SO  						HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	SNAPPED         	H				B				EMER. DESCENT           				F	E		FLT CONT AFFECTED         	VIBRATION/BUFFET          		CR	CRUISE         	1			AL	05	8127K		1906 		D82990	327940268		CH2376		WHILE AT CRUISE RPM, PILOT HEARD LOUD BANG FOLLOWED BY A SEVERE VIBRATION.  REDUCING RPM MADE VIBRATION WORSE.  A HIGHER	 RPM SETTING WAS USED AND AIRCRAFT RETURNED TO LAND SAFELY.  UPON EXAMINATION, FOUND APPROXIMATELY 8 INCHES OF ONE PROPE	LLER BLADE SEPARATED FROM BLADE.  SUBMITTER STATED THE BREAK WAS CLEAN AND SHOWED NO SIGN OF A PRE-EXISTING CRACK.				1	L	7	1 	3O				A3SO    		5	C	P920
1998102300383	19981023	00383	GL  	1998	10	23	98ZZZX3870       	1	19980901	G	6720	0428	CONTROL CABLE   			AMTR  	500   	MINI500     	13015HW	GL  										TAIL ROTOR	LOOSE           	H				O				OTHER                   				F			FLT CONT AFFECTED         			HO	HOVERING       	1			NM	10	248F	5    				402B				UPON LIFTING THE HELICOPTER INTO A HOVER, SUBMITTER NOTICED IT WAS IMPOSSIBLE TO CONTROL THE SWING OF THE TAIL EVEN WHIL	E HOLDING THE PEDALS STILL.  DISASSEMBLED THE TAIL BOOM AND REMOVED THE TAIL ROTOR PUSH/PULL CABLE.  FURTHER INSPECTION 	REVEALED .50 INCH OF SLOP IN THE CABLE.  CONTROL OF THE TAIL ROTOR WITH THIS MUCH PLAY IS IMPOSSIBLE.  SUBMITTER STATED 	THIS CABLE SHOULD BE REPLACED WITH ONE HAVING CLOSER TOLERANCES TO MINIMIZE LASH-UP.			1	G	7	1 	3I			NC	EXPA1G71
1998102300385	19981023	00385	EA  	1998	10	23	98ZZZX3872       	2	19980923	G	8550		GASKET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			GL	07	35453					318052006	L167861A			RIGHT ENGINE LOST OIL PRESSURE.  LANDED IN LAN.  FOUND GASKET UNDER VACUUM PUMP BAD.  REMOVED AND REPLACED GASKET.  SERV	ICED WITH OIL.  OPS CHECK GOOD.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998102300386	19981023	00386		1998	10	23	98ZZZX3873       	4	19980902	G	2562	002200601	BATTERY PACK    	ARTEX       	G7          	PIPER 	PA18  	PA18150     	7101828	SO  										ELT	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	40558					187509127				FUNCTION TESTED ELT AS PART OF ROUTINE INSPECTION OF AIRCRAFT.  FIVE MINUTES AFTER TEST, ELT WAS WARM TO TOUCH.  REMOVED	 BATTERY PACK, ESTIMATED TEMPERATURE TO BE 130 DEGREES FAHRENHEIT.  WIRES NOT TOUCHING, STAYED WARM FOR 15 MINUTES.  NEW	 BATTERY PACK IN ELT CHECKED GOOD, DID NOT OVERHEAT.				1	H	7	1 	3O				1A2
1998102300387	19981023	00387		1998	10	23	98ZZZX3874       	4	19980928	G	2562		BATTERY PACK    	ARTEX       		PIPER 	PA46  	PA46350P    		SO  										ELT	LEAKING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	92821	287  			57991	4636081				ELT BATTERY LEAKED ACID AND BROKE THE BATTERY CASE,  ELT CASE, AND HOLD-DOWN BRACKET.  ELT IS LOCATED IN THE TAIL OF AIR	CRAFT.					1	L	7	1 	3O			RT	A25SO
1998102300389	19981023	00389	SO  	1998	10	23	98ZZZX3876       	2	19980717	G	8530		CYLINDER        			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360EB  	17025	SO  					RT ENGINE	CRACKED         	B				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			EA	21	33401		482  			347570115	306334H			PILOT STATED IN CRUISE, THE RT ENGINE STARTED RUNNING SLIGHTLY ROUGH.  AFTER A CHECK OF THE ENGINE GAUGES, PILOT NOTED A	 SLIGHT DROP IN THE MANIFOLD PRESSURE FOLLOWED BY A DECREASE IN OIL PRESSURE.  THE ENGINE WAS FEATHERED AND SECURED AND 	A SINGLE ENGINE LANDING WAS MADE AT LYH.  AFTER EXAMINING THE RT ENGINE, FOUND THE NR 2 CYLINDER HAD CRACKED AROUND THE 	MID-SECTION CAUSING THE CYLINDER HEAD TO FAIL.			1	L	7	2 	3O	3	O		A7SO    	E9CE
1998102300390	19981023	00390	SO  	1998	10	23	98ZZZX3877       	1	19980922	G	2823	6973505	VALVE           			PIPER 	PA32  	PA32R301    	7103218	SO  										FUEL SELECTOR	FAILED          	B			BCBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	324G	469  				3246003				REF:  PA-32R-300 PARTS INDEX 53 1K7. THE ABOVE AIRCRAFT, SINCE NEW, HAD AN INTERMITTENT PROBLEM OF THE FUEL NOT SHUTTING	 OFF COMPLETELY AFTER ACTUATING THE DRAIN.  THE PROBLEM WAS FINALLY TRACED TO THE SECURING COTTER PIN, REF:  ITEM 45, P/	N 424-058.  WHEN INSTALLED IN A NORMAL MANNER, THE FWD LEG WOULD EXTEND UNDER THE HANDLE LOOP WITH JUST ENOUGH BINDING T	O CAUSE THE DRAIN NOT TO ALWAYS SEAT.			1	L	7	1 	3O				A3SO
1998102300391	19981023	00391	EA  	1998	10	23	98ZZZX3878       	2	19980918	G	8530	LW11625	PIN PLUG        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 1 CYLINDER	WORN            	B			LJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	49224	1861 				15281202	L7452815			FOUND EXCESSIVE ALUMINUM FLAKES IN OIL FILTER.  SUCTION SCREEN OK.  COMP CHECK OK.  REMOVED ALL CYLINDERS.  PIN PLUG WOR	N, NR 1 CYL ASSY.  SCUFFED CYLINDER WALL.					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998102300392	19981023	00392	SW  	1998	10	23	98ZZZX3879       	1	19980922	G	3710	860059001E	VACUUM LINE     			MOONEY	M20   	M20J        	5870219	SW  										COCKPIT	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	10074					243096				THESE LINES ARE MADE OF SURGICAL TUBING AND CRACK AND ROLL AFTER A FEW YEARS.  IN THIS CASE, OWNER STARTED AIRCRAFT AND 	NO VACUUM WAS AVAILABLE.					1	L	7	1 	3O				2A3
1998102300393	19981023	00393	SO  	1998	10	23	98ZZZX3880       	1	19980903	G	5700		STRUTS          			PIPER 	PA12  	PA12        	7101202	SO  										LT/RT WING AFT	CRACKED         	B			CO4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	3624M					122494				PARA 'A' OF AD NOTE 93-10-06 C/W USING AN FAA APPROVED X-RAY METHOD.  LT FRONT STRUT AIRWORTHY.  LT REAR STRUT UNAIRWORT	HY.  RT FRONT STRUT AIRWORTHY.  RT REAR STRUT UNAIRWORTHY.  X-RAYS ARE ON FILE AT THIS REP STA UNDER W/O NR A-2831.  SUB	MITTER STATED UNAIRWORTHY DUE TO TOO MUCH CORROSION.				1	H	7	1 	3O				A780
1998102300394	19981023	00394	CE  	1998	10	23	98ZZZX3881       	1	19980930	G	2720	50524326602209	PEDAL ARM       			BEECH 	99    	99A         	1154003	CE  										RUDDER PEDAL	WORN            	B			TIMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	99GH	31795				U112				HINGE POINT FROM RUDDER PEDAL TO RUDDER ARM BUSHING IS WEARING DEEP GROOVES INTO TANGS ON RUDDER PEDAL ARMS.						1	L	7	2 	3T				A14CE
1998102300395	19981023	00395	CE  	1998	10	23	98ZZZX3882       	1	19980930	G	2720	50524326602210	PEDAL ARM       			BEECH 	99    	99A         	1154003	CE  										RUDDER PEDAL	WORN            	B			TIMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	99GH	31795				U112				HINGE POINT FROM RUDDER PEDALS TO RUDDDER ARM BUSHING IS WEARING DEEP GROOVES INTO TANGS ON RUDDER PEDAL ARMS.						1	L	7	2 	3T				A14CE
1998102300396	19981023	00396	CE  	1998	10	23	98ZZZX3883       	1	19980925	G	3230	514122216	UPLOCK HOOK     			CESSNA	402   	402C        	207590R	CE  										LT MLG	FAILED          	C		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	6879R	1532 				402C0611				THE LT MAIN GEAR UPLOCK HOOK FAILED ON RETRACTION.  FAILURE OCCURRED ACROSS THE UPLOCK HOOK BOSS SEPARATING THE UPLOCK A	CTUATOR FROM THE HOOK PORTION OF THE UPLOCK ASSY CAUSING THE GEAR TO REMAIN LOCKED IN WHEEL WELL UPON EXTENSION.  EMERGE	NCY PROCEDURES FAILED TO RELEASE THE GEAR AND THE CREW WAS FORCED TO LAND WITH ONLY THE NOSE AND RT MAIN EXTENDED.  MINI	MAL DAMAGE SUSTAINED TO THE ACFT.  SUBMITTER SUGGESTED BETTER MACHINING AROUND CUT-OUT FOR SWITCH.  CYCLES:  4,300.			1	L	7	2 	3O				A7CE
1998102300397	19981023	00397	SO  	1998	10	23	98ZZZX3884       	1	19981001	G	8120		TURBOCHARGER    			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	LOOSE           	D		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	9292S	283  				4636115	L984761A			TURBO ON RT SIDE HAD ATTACH NUTS LOOSE.  THIS ALLOWED VIBRATION OF TURBO CAUSING SUPPORT CLAMP TO BREAK AND VIBRATION ON	 MOUNT STUDS.  VIBRATION ON STUDS ALLOWED UPPER STUD ON INTAKE OIL SUMP TO CARRY ALL THE TURBO WEIGHT AND CRACK SUMP.  S	UMP WAS REPLACED.  TT ON ACFT 283 HOURS.  ALL EXHAUST BRACKETS AND SUPPORT NUTS AND BOLTS FOUND LOOSE.  TO PREVENT, CHEC	K TIGHTNESS OF ALL EXHAUST PARTS.  FOUND PROBLEM ON ANNUAL INSPECTION OF ENGINE.			1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1998102300398	19981023	00398	CE  	1998	10	23	98ZZZX3885       	1	19980911	G	7714	22A667	TACH GENERATOR  			CESSNA	414   	414A        	2075907	CE  										LEFT ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	5614C		1497 		477088	414A0203				THE LT ENGINE RPM GAUGE FAILED ON RUN-UP. DISCOVERED THE TACHOMETER GENERATOR P/N 22A667 DRIVE SHAFT HAD SHEARED.  THE T	ACHOMETER GENERATOR WAS REPLACED AND AIRPLANE RETURNED TO SERVICE.  THE TACHOMETER HAD BEEN OVERHAULED AND PUT BACK INTO	 SERVICE 3-29-96.  TOTAL TIME SINCE OVERHAUL 1497.7 HOURS.				1	L	7	2 	3O				A7CE
1998102300399	19981023	00399		1998	10	23	98ZZZX3886       	1	19981002	G	2560	2700771	STRAP           																	CABIN	DELAMINATING    	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03										VELCRO FASTENERS ARE DELAMINATING FROM HEADLINER ASSY.  FASTENERS ARE NECESSARY FOR USE OF OXYGEN MASK.
1998102300400	19981023	00400	CE  	1998	10	23	98ZZZX3887       	1	19980918	G	2720	07136285	BRACKET         			CESSNA	182   	R182        	2072734	CE  										RUDDER PEDAL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	9039C	8692 				R18200378				RUDDER PEDAL BRACKET ON PILOTS AND COPILOTS INBOARD SIDE CRACKED.  FOUND ON REMOVAL OF RUDDER PEDALS FOR FIREWALL REPAIR	.  INSPECTION WOULD NOT BE POSSIBLE WITHOUT REMOVING RUDDER PEDALS.					1	H	7	1 	3O			RT	3A13
1998102300401	19981023	00401	EA  	1998	10	23	98ZZZX3888       	2	19980901	G	8530		EXHAUST VALVE   			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					NR 4 CYLINDER	STUCK           	H				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	40NR	613  				243330	L263555V			CYLINDER NR 4 EXHAUST VALVE STUCK OPEN ON TAKEOFF.  AIRCRAFT RETURNED TO AIRPORT, MADE SAFE LANDING.  UPON INSPECTION, C	YLINDER NR 4 EXHAUST ROTATER CAP WAS FOUND IN THE BOTTOM OF THE ROCKER BOX.  INSPECTED VALVE PER LYC SB 388B.  CLEARANCE	 FOUND TO BE SATISFACTORY.  REMOVED CYLINDER FOR INSPECTION AT OVERHAUL FACILITY.  GUIDE WAS REAMED, SEAT WAS GROUND.  R	EINSTALLED CYLINDER ASSY.  SUBMITTER STATED POSSIBLE CAUSE:  CARBON LEAD DEPOSITS STUCK VALVE OPEN.			1	L	7	1 	3O	3	O		2A3     	1E10
1998102300402	19981023	00402	CE  	1998	10	23	98ZZZX3889       	1	19981007	G	7931	070009937	LINE            			CESSNA	182   	R182        	2072734	CE  										OIL SYSTEM	CORRODED        	B			HX1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2666C	2754 				R18200202				THE ALUMINUM LINE WAS AN OIL PRESSURE LINE RUNNING FROM THE FIREWALL TO THE OIL PRESSURE GAUGE.  IT IS LOCATED BEHIND TH	E INSTRUMENT PANEL IN A VERY HARD TO SEE AREA AND FOUND CORRODED AND DEEPLY PITTED.  DISCOVERED DURING  ANNUAL INSPECTIO	N.  SUBMITTER STATED CAUSE OF CORROSION WAS A DEFROSTER DUCT DIRECTLY ABOVE THE LINE AND TOUCHING IT.  THE DEFROSTER DUC	T WAS THE OLD STYLE SCAT TYPE DUCTING THAT WAS MADE OF COTTON MATERIAL AND IRON FORMING WIRE.  OVER THE YEARS, COTTON DE	TERIORATED AND IRON WIRE RUSTED FROM MOISTURE AND BEGAN TO POKE THROUGH THE COTTON ALLOWING RUSTED WIRE TO CONTACT ALUM 	LINE CAUSING A DISSIMILAR METAL SITUATION AND CORROSION.	1	H	7	1 	3O			RT	3A13
1998102300403	19981023	00403	SO  	1998	10	23	98ZZZX3890       	1	19980928	G	3230	4198301	DOWNLOCK        			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	FAILED          	B			EDER	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SO	15	54313	3664 				317405439				AIRCRAFT LANDED WITH NO RT GEAR DOWN LIGHT.  FOUND RT GEAR DOWNLOCK NOT LATCHED COMPLETELY.  FOUND DOWNLOCK HAD DIRT AND	 EXHAUST DEBRIS AND WAS STIFF.  CLEANED AND LUBED DOWNLOCKS.  PERFORMED RETRACTION TEST.  AIRCRAFT HAS CABLE KIT 764-958	, NOT SPRING CAPSULES.  INSTALLED NEW DOWNLOCK SRINGS, P/N 41952-00.				1	L	7	2 	3O				A20SO
1998102300404	19981023	00404	SO  	1998	10	23	98ZZZX3891       	1	19980817	G	2720	400407	TORQUE TUBE     		5109400     	PIPER 	PA31T 	PA31T1      	7103126	SO  										RUDDER	CORRODED        	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	817CT	2706 				31T1104010				DURING A PHASE INSPECTION, THE RUDDER TORQUE TUBE WAS FOUND CORRODED.  THE RUDDER WAS REMOVED.  THE TURQUE TUBE WAS VERY	 HEAVILY CORRODED AND NOT FIT FOR SERVICE.  IT WAS REMOVED AND REPLACED WITH A NEW PART.  THE BOTTOM RIB WAS ALSO REPLAC	ED DUE TO CORROSION.  WHEN THE SKIN WAS REMOVED FROM THE RUDDER, RESIDUE OF PAINT STRIPPER FOUND.  ACFT RECORDS SHOWED A	CFT WAS PAINTED IN 10-93.  THE NEW TORQUE TUBE, SUPPLIED BY MFG, WAS CORRODED.  THIS WAS PAINT STRIPPED AND TREATED BEFO	RE FITTING.  THE RESIDUE OF PAINT STRIPPER, DISSIMILAR METALS OF THE TORQUE TUBE, AND RIB, NO DRAINIAGE HOLE IN THE BOTT	OM RIB ALL ADDED TO THE ACCELERATION OF THE CORROSION.  THIS AREA OF THE ACFT REQUIRES A REGULAR DETAILED INSPECTION.	1	L	7	2 	3T				A8EA
1998103000046	19981030	00046	EU  	1998	10	30	98ZZZX3924       	1	19980923	G	2434	0120488269	ALTERNATOR      	BOSCH       		GROB  	G115  	G115C       	1660303	EU  										ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	115FN	180  				82061C1				DURING ROUTINE INSPECTION, THE ALTERNATOR HOUSING WAS FOUND CRACKED AT THE MOUNT POINT.						1	L	7	1 	3O			NT	A57EU
1998103000047	19981030	00047	SO  	1998	10	30	98ZZZX3925       	1	19980906	G	3340	D7080A	BEACON          	GRIMES      	33188D      	PIPER 	PA24  	PA24250     	7102404	SO  										FUSELAGE	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11										MOTOR JAMMED AND STOPPED TURNING, BUT LIGHT CONTINUED TO BURN.  THE HEAT FROM THE LAMPS BECAME HOT ENOUGH TO BLISTER AND	 DISCOLOR THE AIRCRAFT PAINT JUST ADJACENT TO THE LENS.  ROTATING BEACON SHOULD BE MANUFACTURED SO THAT THE LAMPS WILL N	OT OPERATE IF THE MOTOR DOES NOT OPERATE.  SHOULD BE FUSED SO THAT IF MOTOR BINDS, IT WILL SHUT DOWN COMPLETE UNIT.  SUB	MITTER STATED STILL NEED A BEACON EVEN THOUGH MOTOR MALFUNCTIONS.  RECOMMENDED A LOWER WATTAGE BULB.			1	L	7	1 	3O				1A15
1998103000048	19981030	00048	SW  	1998	10	30	98ZZZX3926       	1	19981013	G	2434	ALY8420	ALTERNATOR      			MOONEY	M20   	M20F        	5870214	SW  										ENGINE	FAILED          	B				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			SO	01	5000F	283  			65000030	221363				PILOT LOST ALL ELECTRICAL POWER.  ON INSPECTION, THE ALTERNATOR FAN WAS FOUND DESTROYED AND LODGED IN THE ALTERNATOR BRA	CKET AND ENGINE BAFFELS.  SUBMITTER STATED POSSIBLE CAUSE SEEMS TO BE FRAME CRACKS OR DAMAGE DONE PREVIOUSLY TO CAUSE A 	FAN SEPARATION UNDER ROTATIONAL FORCE.  SUBMITTER RECOMMENDED CHECKING THE FAN EVERY 100 HOURS OR EVERY ANNUAL.  FOR CRA	CKS OR DEFECTS OR AS IN AD 72-15-02.			1	L	7	1 	3O				2A3
1998103000049	19981030	00049	SO  	1998	10	30	98ZZZX3927       	1	19980527	G	3710		PUMP            	AIRBORNE    		PIPER 	PA32  	PA32301T    	7103209	SO  										ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	81573	65   			10AN3711	328024004				SECOND VAC PUMP FAILURE IN 253 HOURS OPERATION.  FIRST PUMP FAILED AT 188 HOURS.  SECOND PUMP FAILED AFTER 65 HOURS.						1	L	7	1 	3O				A3SO
1998103000050	19981030	00050	EA  	1998	10	30	98ZZZX3928       	2	19980529	G	8520	13B17166	CRANKSHAFT      			MOONEY	M20   	M20F        	5870214	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	6414Q	4547 	1273 			640493	L120251A			ENGINE VIBRATED 5-10 SECONDS BEFORE SEIZING, NO OTHER INDICATIONS OF PENDING FAILURE WERE NOTED.  AT ENGINE TEARDOWN, TH	E CRANKSHAFT WAS FOUND BROKEN AT THE FORWARD END OF THE NR 4 CONNECTING ROD JOURNAL.  MAINTENANCE RECORDS ONLY WENT BACK	 TO LAST OVERHAUL AND NO RECORD OF PREVIOUS PROPELLER STRIKES OR SUDDEN ENGINE STOPPAGE COULD BE FOUND.				1	L	7	1 	3O	3	O		2A3     	1E10
1998103000051	19981030	00051	SO  	1998	10	30	98ZZZX3929       	1	19980929	G	3250	AN422A	BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										NLG STEERING	BENT            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	62762	4400 				277754004				DURING THE ANNUAL INSPECTION AND FOLLOW-UP ON A NOSE WHEEL SHIMMY SQUAWK.  BOTH NOSE GEAR STEERING (ROLLER) BOLTS P.M. A	N 4-22A WERE FOUND SEVERELY BENT.  AR SHIMMING INSTRUCTIONS IN THE SERVICE MANUAL DO NOT ADDRESS THE POTENTIAL HARDWARE 	PROBLEM.  SUBMITTER RECOMMENDED WHENEVER SHIMMING THE STEERING COLLAR, REPLACE ROLLER HARDWARE AND INSPECT REMAINDER OF 	STEERING LINKAGE TO SPOT HIDDEN DAMAGE.			1	L	7	2 	3O				1A10
1998103000052	19981030	00052	CE  	1998	10	30	98ZZZX3930       	1	19981006	G	5751	502100212	HINGE           			CESSNA	421   	421         	2076010	CE  										WS 229	LOOSE           	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	62DW	3582 				4210188				RIGHT AND LEFT OUTBOARD AILERON HINGE AS ATTACHED TO SPAR.  RIVETS THAT PASS THROUGH HINGE, SPAR, AND LAST RIB HAVE SHEA	RED LEAVING LAST RIB UNSUPPORTED CRACKING SKIN IN ONE PLACE; AS WELL AS OUTER MOST PART OF REAR SPAR NOT BEING SUPPORTED	 WHEN AIR LOADS ARE BEING PLACED ON THE AILERON WHICH COULD LEAD TO PREMATURE SPAR FAILURE IF LEFT UNATTENDED OR DETECTE	D.			1	L	7	2 	3O			RT	A7CE
1998103000053	19981030	00053	CE  	1998	10	30	98ZZZX3931       	1	19981006	G	5751	502100213	HINGE           			CESSNA	421   	421         	2076010	CE  										WS 229	LOOSE           	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	62DW	3582 				4210188				RIGHT AND LEFT OUTBOARD AILERON HINGE AS ATTACHED TO SPAR.  RIVETS THAT PASS THROUGH HINGE, SPAR, AND LAST RIB HAVE SHEA	RED LEAVING LAST RIB UNSUPPORTED CRACKING SKIN IN ONE PLACE; AS WELL AS OUTER MOST PART OF REAR SPAR NOT BEING SUPPORTED	 WHEN AIR LOADS ARE BEING PLACED ON THE AILERON WHICH COULD LEAD TO PREMATURE SPAR FAILURE IF LEFT UNATTENDED OR DETECTE	D.			1	L	7	2 	3O			RT	A7CE
1998103000056	19981030	00056	SO  	1998	10	30	98ZZZX3934       	1	19980827	G	3222	9572305	STOP            			PIPER 	PA34  	PA34200T    	7103406	SO  										STRUT	DAMAGED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2190K	3843 				347970096				DURING AIRCRAFT INSPECTION, NOSE LANDING GEAR WAS FOUND BADLY DAMAGED DUE TO OVERSTEERING WHEN TOWING.  PARTS HAD TO BE 	REPLACED.  SUBMITTER SUGGESTED MFG INSTALL TOW LIMIT MARKING TO AID IN PREVENTING EXCEEDING TOW LIMITS.  ALSO, FOUND P/ 	N 7853500 TILLER ARM BOLT AND ROLLER ASSY LOOSE.  FOUND UNAPPROVED REPAIR ON TILLER ARM.  REPLACED ARM.  THIS ARM CENTER	S NLG WHEN RETRACTED.  PART FAILURE COULD CAUSE NLG TO JAM IN UP POSITION OR OTHER NLG FAILURE.			1	L	7	2 	3O				A7SO
1998103000057	19981030	00057	CE  	1998	10	30	98ZZZX3935       	1	19980810	G	7810	9695000257	EXHAUST STACK   			BEECH 	58    	58          	1152740	CE  										RT ENGINE	CRACKED         	G	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	500GD					TH197				UPON PERFORMING OTHER MAINTENANCE, A CRACK WAS DISCOVERED IN THE EXHAUST STACK/RISER ASSY UNDER THE CLAMP POSITIONED APP	ROXIMATELY 12 INCHES FROM END OF EXHAUST.  SUBMITTER SUSPECTS HEAT, VIBRATION, AND FATIGUE CAUSED ROLE IN PART FAILURE. 	 SUGGEST AREA BE INSPECTED CAREFULLY TO PREVENT RECURRENCE.  AIRCRAFT HOUR METER 5,964.0.				1	L	7	2 	3O				3A16
1998103000058	19981030	00058	SO  	1998	10	30	98ZZZX3936       	1	19980827	G	7620	236405	VALVE           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					RT ENGINE	FAILED          	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2190K	3843 			13487	347970096				DURING AIRCRAFT INSPECTION, INSPECTORS FOUND NEITHER ENGINE FUEL SHUT-OFF VALVE WOULD SHUT OFF FUEL TO ENGINES.  TEAR DO	WN INSPECTION REVEALED O-RINGS IN VALVES IN SHREADS.  INSTALLED NEW SEAL MODIFICATION KITS AND REINSTALLED VALVES.  OPS 	CHECK OK.  SUBMITTER STATED VALVES NEED TO BE OPS CHECKED EVERY INSPECTION PER PIPER FACTORY CHECKLIST FOR AIRCRAFT INSP	ECTION.  IN AN EMERGENCY SUCH AS FIRE, COULD BE SAFETY PROBLEM.			1	L	7	2 	3O	3	O		A7SO    	E9CE
1998103000059	19981030	00059	SO  	1998	10	30	98ZZZX3937       	1	19980827	G	7620	236405	VALVE           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					LT YENGINE	FAILED          	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2190K	3843 			13450	347970096				DURING AIRCRAFT INSPECTION, INSPECTORS FOUND NEITHER ENGINE FUEL SHUT-OFF VALVE WOULD SHUT OFF FUEL TO ENGINES.  TEAR DO	WN INSPECTION REVEALED O-RINGS IN VALVES IN SHREADS.  INSTALLED NEW SEAL MODIFICATION KITS AND REINSTALLED VALVES.  OPS 	CHECK OK.  SUBMITTER STATED VALVES NEED TO BE OPS CHECKED EVERY INSPECTION PER PIPER FACTORY CHECKLIST FOR AIRCRAFT INSP	ECTION.  IN AN EMERGENCY SUCH AS FIRE, COULD BE SAFETY PROBLEM.			1	L	7	2 	3O	3	O		A7SO    	E9CE
1998103000060	19981030	00060	SO  	1998	10	30	98ZZZX3938       	1	19980827	G	5341	6864400	ANGLE           			PIPER 	PA34  	PA34200T    	7103406	SO  										LT WING	CORRODED        	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2190K	3843 				347970096				WHILE C/W SB 977, CORROSION WAS FOUND ON TOP OF LEFT, AFT WING ATTACH AND LOWER CABIN DOOR POST ATTACH.  SUSPECT WATER L	EAKING IN AFT CABIN DOOR AT SOME PREVIOUS TIME.  LEFT CABIN INTERIOR WAS REMOVED FOR AVIONICS INSTALL AND PROVIDED ACCES	S FOR BETTER INSPECTION THAN CALLED OUT IN SB.  IN THIS AREA, STEEL SPAR PLATE HOOKS TO ALUMINUM STRUCTURE.  MAINTENANCE	 WAS ABLE TO CLEAN CORROSION AND EPOXY PRIMER WITHOUT REPLACING PARTS.  SUBMITTER SUGGESTED INSPECTION OF AREA WHEN C/W 	S977 (PIPER).		1	L	7	2 	3O				A7SO
1998103000062	19981030	00062	CE  	1998	10	30	98ZZZX3940       	1	19980909	G	3230	60820091	GEAR            			BEECH 	60    	B60         	1153605	CE  										NLG	SHEARED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	4646M	3346 				P464				GROUND PERSONNEL NOTICED PIECE MISSING FROM DRAG BRACE TO NOSE GEAR ATTACH BOLT.  BOLT WITH INTEGRAL PIN SERVES AS UPLOC	K FOR NOSE GEAR.  INSPECTION REVEALED P/N 60-820091 PIN SHEARED AT LEFT DRAG BRACE AND CORRODED IN NOSE GEAR.  FAILURE M	AY HAVE BEEN CAUSED BY TENSION TOO HIGH ON UPLOCK AND FATIGUE.  PIN IN NOSE GEAR IS THROUGH HOLE IN MAGNESIUM HOUSING SE	TTING UP CORROSION.  PM SHOWS P/N 105740X-6B2305 BUSHING INSTALLED IN HOUSING.  BUSHING WAS INSTALLED AT TIME OF REPAIR.	  SUBMITTER RECOMMENDED C/W 2,000 HOUR OVERHAUL TIME PER MANUFACTURER.		1	L	7	2 	3O				A12CE
1998103000063	19981030	00063	CE  	1998	10	30	98ZZZX3941       	1	19980819	G	2434	643704	ROTOR           		649304      	BEECH 	36    	A36         	1151604	CE  										ALTERNATOR	FAILED          	B			TVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	971PC				52594010	E2123				OPEN CIRCUIT IN ROTOR FIELD WINDING.						1	L	7	1 	3O				3A15
1998103000064	19981030	00064	SO  	1998	10	30	98ZZZX3942       	1	19981007	G	2150	AZ1006762K0230	HOSE            			PIPER 	PA31T 	PA31T       	7103124	SO  										COMPRESSOR	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	78TW	20   				31T7920092				REMOVED AIR CONDITIONING LOW PRESSURE HOSE FROM COMPRESSOR TO FIRE WALL AFTER FINDING A LEAK AT THE FIRE WALL CONNECTION	.  UPON INSPECTION OF THE HOSE, THE TECHNICIAN WAS ABLE TO UNSCREW THE HOSE FROM THE FITTING BY HAND DETERMINING THE HOS	E WAS ONLY ONE-QUARTER OF THE WAY INTO THE FITTING.				1	L	7	2 	3T				A8EA
1998103000065	19981030	00065	SO  	1998	10	30	98ZZZX3943       	1	19981013	G	2810	461713	FUEL CELL       			PIPER 	PA31  	PA31350     	7103110	SO  										FUSELAGE	DETERIORATED    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	4093W	2161 			A1277	318152176				AIRCRAFT HAD NOTICEABLE FUEL ODOR IN CABIN AFTER SITTING OVERNIGHT WITH FULL FUEL IN TANKS.  THERE WERE NO VISIBLE FUEL 	STAINS ON WINGS, FUEL PUMPS, LINES, OR GAUGES.  LEFT MAIN FUEL TANK WAS FOUND DETERIORATED ON THE UPPER SURFACE AND LEAK	ING THROUGH THE FABRIC.  TANK WAS MFG 2-97, AND REMOVED FROM SERVICE 9-98.				1	L	7	2 	3O				A20SO
1998103000066	19981030	00066	EU  	1998	10	30	98ZZZX3944       	1	19980922	G	2930	51088	SWITCH          			ISRAEL	1125  	ASTRASPX    	4500205	EU  										HYDRAULIC SYSTEM	FAILED          	G				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			EA	07										THE AUXILIARY PRESSURE SWITCH, PN 51088, FAILED ON A LOCAL MISSION RESULTING IN LOSS OF THE AUXILIARY HYDRAULIC SYSTEM A	ND AN IN-FLIGHT EMERGENCY.  THE DIAPHRAGM INSIDE THE PRESSURE SWITCH FAILED RESULTING IN FLUID LOSS.  THE SWITCH SHOULD 	BE PROVIDED FOR SELF-CONTANTAINMENT IF FAILURE OCCURS.				2	L	7	2 	4F			RT	A16NM
1998103000067	19981030	00067	SO  	1998	10	30	98ZZZX3945       	1	19981007	G	3242	5403009501	LINE            			GULSTM	AA5   	AA5B        	3960105	SO  										CABIN	CORRODED        	B		A	HX1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	711AP	1258 				AA5B1314				THE LINE IS LOCATED BEHIND THE INSTRUMENT PANEL AND SIDE PANEL IN A VERY HARD TO SEE AREA.  IT WAS FOUND CORRODED AND DE	EPLY PITTED AND LEAKING HYDRAULIC FLUID DURING AN AVIONICS INSTALLATION.  THE CAUSE OF THE CORROSION WAS DETERMINED TO B	E A DEFROSTER DUCT DIRECTLY ABOVE THE LINE AND TOUCHING IT.  THE DEFROSTER DUCT WAS THE OLD STYLE SCAT TYPE DUCTING THAT	 WAS MADE OF COTTON MATERIAL AND IRON FORMING WIRE.  OVER THE YEARS, THE COTTON DETERIORATED AND THE IRON WIRE RUSTED FR	OM MOISTURE AND BEGAN TO POKE THROUGH THE COTTON ALLOWING THE RUSTED WIRE TO CONTACT THE ALUMINUM LINE CAUSING A DISSIMI	LAR METAL SITUATION AND CORROSION.	1	L	7	1 	3O				A16EA
1998103000068	19981030	00068	CE  	1998	10	30	98ZZZX3946       	1	19980827	G	3222	5082020445	BRACE           			BEECH 	100   	B100        	1152919	CE  										NLG	CORRODED        	B			R2JR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	988JR	3277 				BE46				CUSTOMER COMPLAINED OF HARD TO STEER AIRCRAFT AND NLG FAILING TO TURN WHEN O.A.T. WAS VERY LOW.   ON TEAR DOWN, INSPECTO	RS FOUND MASSIVE CORROSION IN NLG BRACE ASSY.  BRACE HAD TO BE REPLACED WITH NEW PART.  CAUSE OF FAILURE FELT TO BE LACK	 OF PROPER LUBBING PER MM LUBE CHART AT EVERY INSPECTION.  REFER TO ATA 12 FOR PROPER GREASE TYPE AND LUBE INTERVALS.				1	L	7	2 	4T				A14CE
1998103000069	19981030	00069	CE  	1998	10	30	98ZZZX3947       	1	19980827	G	5513	1156200219	HINGE FITTING   			BEECH 	100   	B100        	1152919	CE  										HORIZONTAL STAB	HOLES ELONGATED 	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	988JR	3277 				BE46				DURING INSPECTION. LT ELEVATOR OUTBOARD HINGE FOUND LOOSE.  FOUND HOLES ELONGATED IN 115-620021-9 HINGE ASSEMBLY AND SUR	ROUNDING STRUCTURE.  BOLTS CALLED OUT FOR IN BEECH MSB 2132-R1 AND AD NOTE 87-03-06 HAD BEEN P/C/W.  AD NOTE STATES THE 	RECURRING INSPECTION MAY BE TERMINATED AFTER THE RIVETS ARE REPLACED WITH NAS BOLTS AS THIS ACFT HAD BEEN.  SUBMITTER SU	GGESTED INSPECTION CALLED OUT IN PARA (A) STILL BE C/W EACH 100-150 HOURS.  SKIN PARTIALLY REMOVED TO REPLACE DAMAGED PA	RTS ALONG WITH HINGE ASSEMBLY.		1	L	7	2 	4T				A14CE
1998103000070	19981030	00070	NE  	1998	10	30	98ZZZX3948       	2	19980825	G	7261		ENGINE          			AIRBUS	300   	A300B4622R  		EU  	PWA   	4158  	PW4158      		NE  					NR 2 NACELLE	LEAKING         	B				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	88881					743	724877			CI-151 NGO-TPE.  AIRCRACFT AIR TURN BACK DUE TO NR 2 ENGINE OIL LOSS.  NR 2 ENGINE REPLACED IN NGO BY AOG TEAM.  S/N OFF	 724877.  S/N ON 728513.  ENGINE TSO:  8,766:48 HOURS.  ENGINE TC:  3,785.					2	L	7	2 	4F	4	F	RT	A35EU   	E24NE
1998103000071	19981030	00071		1998	10	30	98ZZZX3949       	4	19980901	G	2211	501113202	COMPUTER        	JET         	MT101       	LEAR  	35    	35LEAR      	5170600	CE  										CABIN	DAMAGED         	E				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			DE	DESCENT        	1			SW	99	600DT				1642	35017				WHILE DESCENDING FROM FL 240 TO FL 180, THE AIRCRAFT PITCHED UP AND CLIMBED BACK TO FL 240.  THE PILOT DECLARED AN EMERG	ENCY, SWITCHED TO MANUAL TRIM AND DESCENDED BACK TO FL 180.  THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.  MAINTENANCE 	FOUND THE MACH TRIM COMPUTER INOPERATIVE.  THERE WAS A HOLE DRILLED THROUGH THE UNIT INTO A CIRCUIT BOARD.  THE MACH TIM	E COMPUTER IS MOUNTED ON THE BACK SIDE OF THE CABIN FLOORBOARD.  THE CARPET WAS REPLACED THE DAY BEFORE THIS FLIGHT, AND	 A FASTENER WAS INSTALLED THROUGH THE UNIT.  SUBMITER RECOMMENDED BEFORE DRILLING HOLES IN AN AIRCRAFT, KNOW WHAT IS UND	ER THE SURFACE.	2	L	7	2 	4F				A10CE
1998103000072	19981030	00072	SO  	1998	10	30	98ZZZX3950       	1	19980928	G	2150	20392541	COOLING TURBINE 			GULSTM	G1159 	G1159       	3953505	SO  										CABIN AIR	CONTAMINATED    	B			EW7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	518JT		223  		61492	135				FOUND WATER IN OIL DURING ROUTINE SERVICING.  SUSPECT BAD SEALS.  OVERHAUL COMPLETED ON 9-30-97.  CYCLES:  158.						2	L	7	2 	4F			RT	A12EA
1998103000073	19981030	00073	SO  	1998	10	30	98ZZZX3951       	1	19980928	G	2150	20392541	COOLING TURBINE 			GULSTM	G1159 	G1159       	3953505	SO  										CABIN AIR	CONTAMINATED    	B			EW7R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	518JT		111  		44307	135				FOUND WATER IN OIL DURING ROUTINE SERVICING.  SUBMITTER SUSPECTS BAD SEALS.  OVERHAUL COMPLETED ON 6-8-98.  CYCLES:  99.						2	L	7	2 	4F			RT	A12EA
1998103000074	19981030	00074	CE  	1998	10	30	98ZZZX3952       	1	19980928	G	3230	12838002117	RELEASE CABLE   			BEECH 	MU300 	400A        	1155402	CE  										RT MLG	BROKEN          	B	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	60SM	1997 				RK60				RIGHT MAIN GEAR STRUT EMERGENCY RELEASE CABLE MANUALLY DISENGAGES STRUT UPLOCKS SHOULD A HYDRAULIC FAILURE OCCUR.  THIS 	CABLE WAS FOUND WITH 75 PERCENT OF STRANDS BROKEN AT SWAGE END WHERE IT ATTACHES TO UPLOCK MECHANISM WITH A CLEVIS PIN. 	 THIS FACILITY HAS FILED A PREVIOUS M OR D REPORT FOR THIS CONDITION.  COMPLETE FAILURE OF THIS CABLE WOULD CREATE A CON	DITION WHERE THE NOSE AND LEFT MAIN STRUT WOULD EXTEND AND THE RIGHT MAIN WOULD REMAIN LOCKED IN THE WHEEL WELL.  THIS C	ONDITION WAS DISCOVERED DURING A FACTORY A INSPECTION (200 HOUR REQUIREMENT).  IT IS IMPERATIVE THAT RAYTHEON ENGINEERS 	SOLVE THIS RECURRING PROBLEM BEFORE SOMEONE GETS HURT.	2	H	7	2 	4F			RT	A16SW
1998103000075	19981030	00075	NE  	1998	10	30	98ZZZX3953       	2	19980504	G	8530		CYLINDER        			DOUG  	DC3   	DC3         	3021401	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 2 ENG NR 1CYL	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			NR	NOT REPORTED   	1			AL	01	305SF		1098 			6208	CP354320			NR 1 CYLINDER ON NR 2 ENGINE FAILED.  SHUT DOWN NR 2 ENGINE AND FEATHERED.  RETURNED TO ANCHORAGE.						2	L	7	2 	4R	4	R		A669    	5E4
1998110600524	19981106	00524	NE  	1998	11	6	98ZZZX3970       	1	19981002	G	7312	320115	VALVE           			BOEING	727   	727251      	138408H	NM  	PWA   	JT8   	JT8D7A      	52053	NE  					NR 3 ENGINE	MALFUNCTIONED   	G				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			O			OTHER                     			NR	NOT REPORTED   	1			SO	11	286US					21325				FUEL HEAT VALVE, WHITTAKER CONTROLS P/N 320115, VALVE INSTALLED ON THE NR 3 ENGINE.  FUEL HEAT VALVE PREVIOUSLY PLACED O	N MEL, VALVE VIBRATED PARTIALLY OPEN, OIL TEMP HIGH, CREW MADE PRECAUTIONARY ENGINE SHUT DOWN.  AIRCRAFT DIVERTED TO ATL	ANTA.  REMOVED AND REPLACED NR 3 ENGINE FUEL HEAT VALVE.				2	L	7	3 	4F	4	F		A3WE    	E2EA
1998110600632	19981106	00632	CE  	1998	11	6	98ZZZX3993       	1	19980824	G	8120	47090811	VALVE           	GARRTT      		CESSNA	210   	210L        	2073448	CE  										WASTEGATE	MISSING         	H		A		C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SO	14	218SG				IOR0150	21061225				A NORMAL FLIGHT WAS COMPLETED.  THE NEXT TAKEOFF RESULTED IN ONLY A 26.50 INCH MANIFOLD PRESSURE (NORMAL RED LINE 32.50 	INCHES).  AFTER TROUBLESHOOTING THE PRE SSURE RELIEF VALVE AND TURBO CONTROL VALVE, THE TAILPIPE WAS REMOVED AND DISCOVE	RED THE WASTEGATE BUTTERFLY VALVE WAS MISSING AND HAD ENTERED THE ACFT THROUGH THE TAILPIPE.  SUBMITTER STATED THE MOST 	OBVIOUS CAUSE IS EXCESS TIME IN USE.  T IME SINCE OVERHAUL 1,482 HRS (1,400 TBO) JUST UNDER 13 YEARS.			1	H	7	1 	3O				3A21
1998110600633	19981106	00633		1998	11	6	98ZZZX3994       	2	19980826	G	7322	778912	PUMP            																	FUEL CONTROL	MISMANUFACTURED 	B			CY4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03										THE LEATHER PORTION OF THE P/N 194-605 IS NOT DEEP ENOUGH TO COVER THE EXPANDER SPRING WHICH WILL ALLOW THE EXPANDER SPR	ING TO RUB ON THE ACCELERATOR PUMP WELL.
1998110600634	19981106	00634		1998	11	6	98ZZZX3995       	2	19980825	G	7322	194605	PUMP            	PRECISION   																FUEL CONTROL	MISMANUFACTURED 	B			CY4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03										THE LEATHER PORTION OF THE P/N 194-605 IS NOT DEEP ENOUGH TO COVER THE EXPANDER SPRING WHICH WILL ALLOW THE EXPANDER SPR	ING TO RUB ON THE ACCELERATOR PUMP WELL.
1998110600635	19981106	00635	SO  	1998	11	6	98ZZZX3996       	2	19980722	G	8520	6541194	CRANKCASE       		E199803R    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					ENGINE	MISMANUFACTURED 	D				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	745CA		8    			421C1043	227868R			APPROXIMATELY 8.0 HOURS TIS AFTER INSTALLATION, OIL OPERATING PRESSURES FELL BELOW ALLOWABLE LIMITS, ENGINE WAS REMOVED 	AND FOUND TO HAVE INSUFFICIENT MATERIAL THICKNESS BETWEEN AN OIL PICK-UP CAVITY AND AN OIL PUMP HOUSING STUD BOSS.  THIS	 CONDITION CREATED A WEAKNESS IN THE ENGINE OIL PRESSURE SYSTEM WHICH FAILED AFTER CONTINUED INTRODUCTION OF OIL PRESSUR	E.  AS A RESULT, OIL BEGAN TO BYPASS AT THIS POINT AND THE OIL SYSTEM COULD NOT MAINTAIN NORMAL OPERATING PRESSURES.			1	L	7	2 	3O	3	O		A7CE    	E7CE
1998110600636	19981106	00636	NE  	1998	11	6	98ZZZX3997       	2	19980916	G	7230	0292252970	MANIFOLD        		70BM035410  	SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					GAS GENERATOR	FAILED          	B		A	R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6084W	1265 	63   		0080XG	2672	9245			MECHANIC WAS PERFORMING A DAILY INSPECTION AFTER A FLIGHT AND FOUND THE COMPRESSOR WOULD NOT ROTATE, THE ENGINE WAS SEIZ	ED.  AFTER THE ENGINE COOLED, COMPRESSOR TURNED FREELY, BUT THE REPAIR IS TO CHANGE THE GAS GENERATOR AND THE COMPRESSOR	 AS AN ASSY.  SUBMITTER SUGGESTED CAUSE AS COKING OF THE FUEL INJECTION WHEEL.  REF:  TURBOMECA SL 1617/94/ARRIEL/17.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1998110600638	19981106	00638	GL  	1998	11	6	98ZZZX3999       	2	19980119	G	7250	23031899	TURBINE         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	FAILED          	H				A	R			UNSCHED LANDING         	AUTOROTATION            			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SW	99	8WH	6409 	5179 			45318	CAE860198			DURING CRUISE FLIGHT, ENGINE CHIP LIGHT ILLUMINATED.  ONE MINUTE LATER, PILOT EXPERIENCED ENGINE FAILURE.  PILOT THEN PR	OCEEDED TO AUTO-ROTATE TO SAFE LANDING.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998111800029	19981118	00029	EU  	1998	11	18	98ZZZX4000       	1	19980930	G	3340	G62504	LIGHT           	GRIMES      		AGUSTA	A109  	A109K2      	0260502	EU  										FUSELAGE	FAILED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	129AL	97   				10029				THE RELAYS THAT CONTROL EXTENTION, RETRACTION, AND ROTATION (AIM) ARC, AND THE POINTS EITHER MELT (FUSE) TOGETHER OR IN 	SOME CASES, HAVE TOTALLY VAPORIZED.  THE LIGHT CANNOT BE AIMED ONCE THIS OCCURS.  THE EMS NIGHT SCENE FLIGHTS.  WHEN THE	 LIGHT FAILS THE DANGER OF CONTACT WITH OBSTACLES INCREASES.  IN 5 YEARS, THIS P/N LIGHT HAS FAILED 13 TIMES.  THE MANUF	ACTURER HAS BEEN UNABLE TO CORRECT THE PROBLEM.			1	G	7	2 	3U			RT	H7EU
1998110600639	19981106	00639	WP  	1998	11	6	98ZZZX4001       	1	19980908	G	3320	BR9707001	BALLAST         	BRUCE       		DOUG  	DC9   	DC932       	3022066	WP  										CABIN	SHORTED         	B	P	A	ASMF	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	1003P					48150				TWO POWER LAMPHOLDER ASSEMBLIES (BALLAST) WERE BURNED BY ARCING WITH THE ELECTRIC WIRE CONNECTOR WHICH WAS FABRICATED AN	D ASSEMBLED BY BRUCE INDUSTRIES (FAA PMA 400-067), AND DELIVERED TO AEROMEXICO FOR INTERIOR MODIFICATION OF DC9'S.  THIS	 AIRCRAFT WAS MODIFIED ON 3-10-98; HENCE, THE PARTS WERE ALMOST NEW (6 MONTHS OF USE SINCE INSTALLED).  SUBMITTER STATED	, APPARENTLY, THE PLASTIC COVER AT THE CONNECTION WAS MELTED BY OVERHEAT AND THEN THERE WAS A SHORT CIRCUIT THAT BURNED 	THE BALLAST.		2	L	7	2 	4F			 	A6WE
1998110600640	19981106	00640	EU  	1998	11	6	98ZZZX4002       	1	19980811	G	3250		PIN             			ISRAEL	1121  	1121B       	0142010	EU  										COCKPIT	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	372Q					112				NOSE STEERING KNOB ROTATING ON SHAFT DUE TO ROLL PIN BACKED OUT.  INSTALLED ROLL PIN AND SAFETIED WITH .032 INCH SAFETY 	WIRE.  HYDRAULIC SYSTEM CHECKED AND WAS FOUND FULLY SERVICED.					2	M	7	2 	4J				A2SW
1998110600641	19981106	00641	SO  	1998	11	6	98ZZZX4003       	1	19981007	G	7931	55000091	LINE            			GULSTM	AA5   	AA5B        	3960105	SO  										OIL INDICATOR	CORRODED        	B			HX1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	711AP	1258 				AA5B1314				THE ALUMINUMN LINE REFERENCED ABOVE WAS AN OIL PRESSURE LINE FOR THE OIL PRESSURE GAUGE.  IT IS LOCATED BEHIND THE INSTR	UMENT PANEL IN A VERY HARD TO SEE AREA.  IT WAS FOUND CORRODED AND DEEPLY PITTED AND LEAKING OIL DURING AN AVIONICS INST	ALLATION.  THE CAUSE OF THE CORROSION WAS DETERMINED TO BE A DEFROSTER DUCT DIRECTLY ABOVE THE LINE AND TOUCHING IT.  TH	E DEFROSTER DUCT WAS THE OLD STYLE SCAT TYPE DUCTING THAT WAS MADE OF COTTON MATERIAL AND IRON FORMING WIRE.  OVER THE Y	EARS THE COTTON DETERIORATED AND THE IRON WIRE RUSTED FROM MOISTURE AND BEGAN TO POKE THROUGH THE COTTON ALLOWING THE RU	STED WIRE TO CONTACT THE ALUMINUM LINE CAUSING A DISSIMILAR METAL SITUATION AND CORROSION.	1	L	7	1 	3O				A16EA
1998110600642	19981106	00642	EU  	1998	11	6	98ZZZX4004       	1	19980921	G	2731		SPLINES         		258CT29116A 	BRAERO	DH125 	BAE125800A  	1500285	EU  										ELEVATOR TAB	CORRODED        	D	L	A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	23	204JC	3437 				258175				AUTOPILOT SYSTEM WOULD SWITCH FROM LAFCS TO RAFCS WHEN ACFT APPROACHED SPEEDS WITHIN 15 KNOTS OF REDLINE.  AT ALL TIMES 	THE FAULT CODES PULLED UP BY THE TECH WOULD SHOW EXCESSIVE FRICTION IN THE ELEV TRIM SYS.  EXTENSIVE T/S SHOWED NO PROBL	EM WITH THE STATIC FRICTION IN CABLE RUNS.  TRIM SERVOS CHANGED OUT.  CABLE TENSIONS CHECKED AND ADJUSTED.  ELEV TRIM JA	CKS DISASSEMBLED PARTIALLY TO CHECK FOR BURRS AND WARPAGE ON THE SCREWJACK.  PROBLEM STILL EXISTED.  DURING MM INSPECTIO	N, JACKS WERE DISASSEMBLED AND DRIVE SPLINES INSPECTED.  PITTING CORROSION FOUND ON BOTH LT AND RT JACK SPLINES.  BOTH J	ACKS REPLACED WITH NEW.  ACFT HAS FLOWN FOR OVER 50 HRS WITH NO PROBLEM.	2	L	7	2 	4F			RT	A3EU
1998110600643	19981106	00643	CE  	1998	11	6	98ZZZX4005       	1	19980903	G	3231	08411066	BELLCRANK       			CESSNA	421   	421B        	2076014	CE  										RT MLG	BROKEN          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	421FM	4977 				421B0841				RIGHT MAIN GEAR DOOR WAS FOUND HANGING OPEN UPON POST-FLIGHT INSPECTION.  THE DOOR BELLCRANK WAS FOUND BROKEN ON THE DOO	R ACTUATOR ARM AND ALLOWED THE DOOR TO OPEN AND NOT OPERATE WITH THE MAIN GEAR LEG.					1	L	7	2 	3O				A7CE
1998110600644	19981106	00644	EU  	1998	11	6	98ZZZX4006       	1	19980922	G	3230	200497614	SPRING CARRIER  		200498005   	FOKKER	F28   	F28MK4000   	4990810	EU  										MLG	BROKEN          	B				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			EA	21	477AU				DRG467877	11226				ON GEAR RETRACTION AFTER TAKEOFF, THE GEAR INTRANSIT LIGHT WOULD NOT GO OUT.  SHORTLY THEREAFTER, THE LOW HYDRAULIC FLUI	D QUANTITY LIGHT CAME ON.  ON GEAR EXTENSION, THE DOWN AND LOCKED INDICATOR LIGHT DID NOT COME ON.  OPERATOR:  HORIZON A	IRLINES.  CYCLES:  9,031.				2	L	7	2 	4F			RT	A20EU
1998110600648	19981106	00648	EU  	1998	11	6	98ZZZX4010       	1	19980921	G	2150	20388022	COOLING TURBINE 			HWKSLY	DH125 	BH125400A   	4230138	EU  										BEARINGS	FAILED          	D				A				UNSCHED LANDING         				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		CL	CLIMB          	1			GL	07	900WG				59331	NA757				AIRCRAFT TOTAL TIME 6,992.5 HOURS.  AIRCRAFT WAS IN CLIMB TO 10,000 FEET WHEN VIBRATIONS AND ODOR WERE NOTICED IN COCKPI	T AND CABIN.  RETURNED TO AIRPORT AND FOUND MAIN BEARINGS HAD FAILED ON COOLING TURBINE.  MANUFACTURER HAS NO OVERHAUL P	ERIOD FOR THIS UNIT.  SUBMITTER SUGGESTED A TBO BE SET.				2	L	7	2 	4J				A3EU
1998110600649	19981106	00649	NE  	1998	11	6	98ZZZX4011       	3	19980924	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9284 	4636 		2178NR			HJ271		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INOBARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  FIVE CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998110600650	19981106	00650	WP  	1998	11	6	98ZZZX4012       	1	19980924	G	7830		FAN FRAME       			DOUG  	DC10  	DC1030      	3023501	WP  	GE    	CF6   	CF650C2     	30018	NE  					NR 1 ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	14079					46927	517553			THE NR 1 ENGINE REVERSER SEAL SUPPORT RING, LEFT, WAS FOUND CRACKED AT ALL FIVE FORWARD ATTACH POINTS.  THE FLANGE SECTI	ONS HAD BROKEN COMPLETELY AWAY FROM THE TWO BOLT ATTACHMENTS IN AN ARC THE CRACK PASSING THROUGH THE TOP ROW OF TWO ATTA	CHMENT RIVETS OF A SUPPORT DOUBLER BRACKET.  NO CAUSE HAS BEEN DETERMINED AT THIS TIME.  FURTHER INVESTIGATION IS BEING 	MADE.  NO PERIPHERAL DAMAGE IS EVIDENT ON THE RING OR ON THE ADJACENT STRUCTURE.  FOUND ON A ROUTINE C-CHECK.  ENGINE TT	:  64,235 HOURS.		2	L	7	3 	4F	4	F		A22WE   	E23EA
1998110600651	19981106	00651	WP  	1998	11	6	98ZZZX4013       	2	19980917	G	7250	31037131	NUT             			SWRNGN	SA226 	SA226TB     	8780406	SW  	GARRTT	TPE331	TPE33110U   	01514	WP  					TURBINE	BROKE           	B			UO2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	193CS	1810 				T300	P35063			TURBINE NUT FAILED ON ENGINE RUN-UP.  ROTATING GROUP BECAME UNSTACKED RESULTING IN SHUTDOWN OF ENGINE.  REPAIRED IAW TPE	331 MM.  C/W SB 72-0935, IMPROVED TURBINE NUT.  FAILED NUT HAD BEEN INSTALLED PER SB 72-0592 AT ENGINE OVERHAUL.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
1998110600652	19981106	00652	EU  	1998	11	6	98ZZZX4014       	1	19980913	G	2121		MOTOR           		TBL25       	BRAERO	DH125 	BAE125800A  	1500285	EU  										COCKPIT	FAILED          	H	L	A		A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			SW	01	309G	4755 				NA0408				DAL- ACFT DEPARTED AND WITHIN 5 MINUTES CREW NOTICED ACRID ELEC ODOR.  CREW EXPERIENCED WATERY EYES AND DIFFICULTY BREAT	HING.  CREW DONNED OXY MASKS AND RETURNED TO BASE.  ACFT LANDED WITH NO FURTHER INCIDENT.  PASSENGERS DID NOT REQUIRE OX	YGEN, NOTICED ACRID ODOR.  MAINT FOUND INST PANEL BLOWER LOCATED IN CENTER PEDESTAL TO BE CAUSE OF ODOR.  BLOWER MOTOR I	S BRAILSFORD, MODEL TBL2-5.  MAINT REPLACED BLOWER MOTOR.  INVEST REVEALED MOTOR POWERED BY C/B NR 41 ON C/B PANEL A.  C	/B IS A 5-AMP BREAKER AND LABELED 'XFER RELAY'.  C/B IS LABELED INCORRECTLY AS 'C/B 21' IN RAYTHEON ARK MOD PRINT.  SUBM	ITTER NOTED THE LT AND RT COCKPIT BLOWER MOTORS ARE BRAILSFORD, MODEL TBL2-5; HOWEVER, THEY ARE PROTECTED BY A 1-AMP C/B	2	L	7	2 	4F			RT	A3EU
1998110600653	19981106	00653	CE  	1998	11	6	98ZZZX4015       	1	19980825	G	2910	124F0016CRO212	HOSE            			LEAR  	25    	25B         	5170511	CE  										LT ENGINE	FAILED          	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	23	49WA	387  				142				THE LEFT ENGINE NR 6 HIGH PRESSURE TEFLON HOSE SPLIT CAUSING AIRCRAFT TO LOSE HYDRAULIC PRESSURE.  SUBMITTER SUGGESTED F	AULTY HOSE AS CAUSE OF FAILURE.					2	L	7	2 	4J				A10CE
1998110600654	19981106	00654	NM  	1998	11	6	98ZZZX4016       	1	19980917	G	2913	40183	PUMP            			ISRAEL	1125  	1125        		NM  										RT ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	705MA		89   		CT25A	011				ON PRE-FLIGHT, FOUND NR 2 HYDRAULIC PUMP LEAKING STATICALLY FROM BETWEEN THE CASE HALVES.  REPLACED LEAKING PUMP.						2	L	7	2 	4F			RT	A16NM
1998110600655	19981106	00655	NM  	1998	11	6	98ZZZX4017       	1	19980917	G	2913	40183	PUMP            			ISRAEL	1125  	1125        		NM  										RT ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	705MA				AH6580A	011				ON PRE-FLIGHT, FOUND NR 2 ENGINE HYDRAULIC PUMP LEAKING STATICALLY FROM CASE HALVES.  REPLACED LEAKING PUMP.						2	L	7	2 	4F			RT	A16NM
1998110600656	19981106	00656	NM  	1998	11	6	98ZZZX4018       	1	19980917	G	2913	40183	PUMP            			ISRAEL	1125  	1125        		NM  										LT ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	705MA					011				DURING ENGINE INSPECTION RUN-UP, FOUND NR 1 HYDRAULIC PUMP OPERATING AT 2,200 PSI (SHOULD BE 3,000).  REMOVED FAILED PUM	P AND INSTALLED REPAIRED UNIT.					2	L	7	2 	4F			RT	A16NM
1998110600657	19981106	00657	EU  	1998	11	6	98ZZZX4019       	1	19980916	G	2920	9850551090	SWITCH          			ISRAEL	1125  	ASTRASPX    	4500205	EU  										HYDRAULIC SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	275RA	113  			0113	098				WITH AUXILIARY HYDRAULIC SYSTEM OPERATING, 'AUX HYD OFF' AND 'AUX HYD LEVEL' LIGHTS CAME ON.  FOUND SWITCH LEAKING AT EL	ECTRICAL CONNECTION.  SWITCH FAILED INTERNALLY.					2	L	7	2 	4F			RT	A16NM
1998110600658	19981106	00658	EU  	1998	11	6	98ZZZX4020       	1	19980916	G	2920	9850551089	SWITCH          			ISRAEL	1125  	ASTRASPX    	4500205	EU  										HYDRAULIC SYSTEM	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	275RA	80   			104	098				AIRCRAFT FOUND LEAKING HYDRAULIC FLUID ON PRE-FLIGHT.  FOUND PRESSURE SWITCH FAILED INTERNALLY, LEAKING AT ELECTRICAL CO	NNECTION.					2	L	7	2 	4F			RT	A16NM
1998110600659	19981106	00659	EU  	1998	11	6	98ZZZX4021       	1	19980916	G	2913	40183	PUMP            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										HYDRAULIC SYSTEM	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			EA	13	275RA	123  			LY68AB	098				PUMP LEAKING STATICALLY FROM THE SHAFT SEAL.						2	L	7	2 	4F			RT	A16NM
1998110600660	19981106	00660	EU  	1998	11	6	98ZZZX4022       	1	19980916	G	2150	32176022	VALVE           			ISRAEL	1125  	ASTRASPX    	4500205	EU  										E/E BAY	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA	80   			1431	098				DURING A/C OPERATION, TEMPERATURE COULD NOT BE CONTROLLED IN AUTO OR MANUAL MODE.  FOUND VALVE FAILED INTERNALLY.						2	L	7	2 	4F			RT	A16NM
1998110600661	19981106	00661	EU  	1998	11	6	98ZZZX4023       	1	19980916	G	2150	32176022	VALVE           			ISRAEL	1125  	ASTRASPX    	4500205	EU  										E/E BAY	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA		10   		1423	098				DURING A/C OPERATION, TEMPERATURE RAN FULL-HOT AND THEN FULL-COLD, COULD NOT BE OVERRIDDEN WITH THE CONTROLLER IN MANUAL	 MODE.  FOUND VALVE FAILED INTERNALLY.					2	L	7	2 	4F			RT	A16NM
1998110600662	19981106	00662	CE  	1998	11	6	98ZZZX4024       	1	19980925	G	2721	101630000155	HINGE           			BEECH 	200   	200BEECH    	1152920	CE  										RUDDER TAB	CORRODED        	B			T4OR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	807SC	6512 	1513 			BB490				SUBMITTER DISCOVERED RUDDER MADE NOISE DURING MOVEMENT.  FOUND RUDDER TRIM TAB BOUND AT HINGE DUE TO LACK OF LUBRICATION	 AND DEEP INTERGRANULAR CORROSION.  PIANO HINGE HAD TO BE CUT OFF TAB IN SMALL PIECES THEN NEW HINGE (FORWARD) RIVETED O	N.  NOTE:  AIRCRAFT WAS PREVIOUSLY LOCATED IN CORROSIVE ENVIRONMENT AND RECENTLY PAINTED.				1	L	7	2 	4T				A24CE
1998110600663	19981106	00663	CE  	1998	11	6	98ZZZX4025       	1	19980921	G	5312		PRESS BULKHEAD  			BEECH 	90    	C90A        	1152911	CE  										BS 177	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	05	4335P					LJ1108				P/N 50-420028-48, BULKHEAD, P/N 50-420028-47, BULKHEAD.  PRESSURE BULKHEADS ARE CRACKED AT FS 177.0 AND WATERLINE 90.0 O	N BOTH LEFT AND RIGHT SIDES OF AIRCRAFT.  RIGHT CRACK HAS ALSO PROCEEDED TO THE OUTSIDE SKIN.  SUBMITTER STATED WILL BE 	REPAIRED PER BEECH ENGINEERING REF KLR/0675-98 9-21-98.				1	L	7	2 	3T			RT	3A20
1998110600664	19981106	00664	NM  	1998	11	6	98ZZZX4026       	1	19980922	G	2752	53181	ACTUATOR        			AMD   	FALC50	FALCON2000  	2730170	NM  										TE FLAP	FAILED          	B		A	CW1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	790L	1747 			157	15				RIGHT INBOARD FLAP DRIVE FAILED CAUSING UNSYMMETRICAL FLAP DEPLOYMENT INDUCING A CONTROLLABLE ROLL MOMENT.  SUBMITTER SU	GGESTED CAUSE AS PREMATURE WEAR.					2	K	7	3 	4F			RT	A50NM
1998110600665	19981106	00665	NM  	1998	11	6	98ZZZX4027       	1	19980922	G	2740	65206866	WHEEL           			BOEING	727   	727225      	1384077	NM  										STABILIZER CNTRL	LOOSE           	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	8892Z				A3193	21861				STABILIZER CONTROL WHEEL SLIPPING IN MANUAL AND TRIM MODES.  REMOVED FORWARD STABILIZER CABLE DRUM.  INTERNAL GEARS WERE	 SEVERELY WORN.  DATE OF DRUM ASSY MFG WAS 1979.  THIS COMPONENT IS NOT A HARD TIME COMPONENT IN SECTION 7 OF MPD.					2	L	7	3 	4F				A3WE
1998110600666	19981106	00666	EU  	1998	11	6	98ZZZX4028       	1	19981001	G	3244	185758	TIRE            			AMD   	FALC10	FALCON10    	2730101	EU  										MLG	MISMANUFACTURED 	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03		150  								AIRCRAFT BLEW OUT 2 RIGHT MAIN TIRES AT V1.  INSP FOUND DEFECT ON 2 MORE TIRES ON A/C.  CRACK STARTS AS A LIGHT CRAZING 	MARK THEN SPLITS TIRES IN TWO.  GOODYEAR FLIGHT EAGLE 18X5.75.8, 190 MPH.					2	L	7	2 	4F				A33EU
1998111800030	19981118	00030	SO  	1998	11	18	98ZZZX4029       	1	19980917	G	2913	1159SCH5053	PUMP            			GULSTM	GV    	GV          		SO  										HYDRAULIC SYSTEM	OVERHEATED      	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	21	158AF				MX573347	506				THE AIRCRAFT WAS IN CRUISE AT 45,000 FEET WHEN THE R1 HYDRAULIC PUMP FAILED.  TEN MINUTES LATER, R2 PUMP FAILED. THERE W	AS NO FLUID LOSS AT THIS POINT.  ON FINAL WHEN THE LANDING GEAR WAS SELECTED DOWN, THE RIGHT HYDRAULIC SYSTEM QUANTITY W	ENT TO ZERO.				2	L	7	2 	4F			RT	A12EA
1998111800031	19981118	00031	SO  	1998	11	18	98ZZZX4030       	1	19980917	G	2913	1159SCH5053	PUMP            			GULSTM	GV    	GV          		SO  										HYDRAULIC SYSTEM	OVERHEATED      	D				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			EA	21	158AF				MX573348	506				THE AIRCRAFT WAS IN CRUISE AT 45,000 FEET WHEN THE R1 HYDRAULIC PUMP FAILED.  TEN MINUTES LATER, R2 PUMP FAILED. THERE W	AS NO FLUID LOSS AT THIS POINT.  ON FINAL WHEN THE LANDING GEAR WAS SELECTED DOWN, THE RIGHT HYDRAULIC SYSTEM QUANTITY W	ENT TO ZERO.				2	L	7	2 	4F			RT	A12EA
1998111800032	19981118	00032	SO  	1998	11	18	98ZZZX4031       	1	19980916	G	2913	1159SCH5053	PUMP            			GULSTM	GV    	GV          		SO  										HYDRAULIC SYSTEM	FAILED          	B			J2BR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	15	777GV	332  			MX573342	508				NR 1 ENGINE HYDRAULIC PUMP L2 OVERHEATED AND FAILED IN-FLIGHT.						2	L	7	2 	4F			RT	A12EA
1998110600667	19981106	00667	SW  	1998	11	6	98ZZZX4032       	1	19980812	G	2820		LINE            			BBAVIA	8     	8GCBC       	1220803	SW  										FUEL CELL	CHAFED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	778AC					38197				BOTH FUEL TANK AFT OUTLET LINES (P/N 7-14761-1 LT, AND P/N 7-1476-3 RT) CHAFED BY FLAP BELLCRANK CABLE GUARD P/N 1-2573 	IN EACH WING ROOT.  THE RT LINE ALSO CHAFED BY THE AILERON CABLE PULLEY P/N 1-10365.					1	H	7	1 	3O				A21CE
1998110600668	19981106	00668		1998	11	6	98ZZZX4033       	1	19980917	G	7712	31030854	TORQUE RING     	GARRTT      							GARRTT	TPE331	TPE3311U    	01514	WP  					ENGINE	FAILED          	B				C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SW	09							P44650			DURING TAKEOFF POWER-UP, TORQUE INDICATION DROPPED TO ZERO.											3	T			E3WE
1998110600669	19981106	00669	WP  	1998	11	6	98ZZZX4034       	2	19980916	G	7261	30748831	LINE            			BRAERO	DH125 	BAE125800A  	1500285	EU  	GARRTT	TFE731	TFE7315R    	01518	WP  					ENGINE	CRACKED         	B			G1FR	E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	13	244JM					NA0428	91389			LOSS OF OIL PRESSURE 2.5 HOURS AFTER REPLACEMENT OF ITT HARNESS.  ENGINE WAS SHUT DOWN AND AIRCRAFT LANDED.  SUBSEQUENT 	INSPECTION FOUND THE NR 6 PRESSURE LINE HAD CRACKED CAUSING THE LOSS OF OIL PRESSURE.  SUBMITTER STATED POSSIBLE CAUSE O	F CRACK COULD BE FROM FATIGUE CAUSED BY STARTER/GENERATOR BEARING FAILURES AT PREVIOUS TIMES.				2	L	7	2 	4F	4	F	RT	A3EU    	E6WE
1998111300248	19981113	00248	SO  	1998	11	13	98ZZZX4035       	1	19980916	G	3320	BC10047003	LAMP HOLDER     	BRUCE       		GULSTM	G1159 	GIV         	3980115	SO  										CABIN	DAMAGED         	B	P	A	VU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	3PG	1482 				1260				DURING COMPLIANCE OF A GULFSTREAM CUSTOMER BULLETIN NR 98 ON BRUCE INDUSTRIES LIGHTING, FOUND THE FLUORESCENT LIGHT LAMP	 HOLDER BURNED AT SOCKET END DUE TO ARCING.					2	L	7	2 	4F			RT	A12EA
1998111300249	19981113	00249	EU  	1998	11	13	98ZZZX4036       	1	19981013	G	3246	AHA1236	WHEEL           	DUNLOP      		STBROS	SD3   	SD360       	8100606	EU  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	124CA		210  		52	SH3652				CAPTAIN AND FIRST OFFICER DID A VISUAL APPROACH TO RUNWAY 31 IN BFD.  AFTER TOUCHDOWN, AIRCRAFT PULLED TO RIGHT AND VIBR	ATION NOTICED INDICATING RT MAIN TIRE FLAT.  BROUGHT AIRCRAFT TO STOP ON RUNWAY AND SHUT DOWN.  ON POST-FLIGHT EXAM, NOT	ICED RT MAIN WHEEL RIM CRACKED AND TIRE FLAT.  THE RUNWAY CLOSED, SO MECHANIC WAS SENT IMMEDIATELY.  RT MAIN WHEEL ASSY 	AND TIRE REMOVED AND REPLACED.  OPS CHECK GOOD.			2	H	7	2 	4T				A41EU
1998111300250	19981113	00250	NM  	1998	11	13	98ZZZX4037       	1	19981013	G	3350	D73402001	BATTERY PACK    			AMD   	FALC50	FALCON2000  	2730170	NM  										CABIN	DISCHARGED      	B			JZBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	25	70KS				121	14				WHILE REPLACING AN EMERGENCY LIGHT BATTERY PACK, AN ECHANGE UNIT WAS PURCHASED FROM FALCON JET (TEB).  THE EXCHANGE UNIT	 WAS DISCHARGED WHEN RECEIVED.  ALL OTHERS IN STOCK WERE ALSO FOUND DISCHARGED.  THE ORIGINAL WAS STILL SERVICEABLE AND 	RE-INSTALLED IN THE AIRCRAFT.				2	K	7	3 	4F			RT	A50NM
1998111300251	19981113	00251	SO  	1998	11	13	98ZZZX4038       	1	19981014	G	3320	5001P02	LIGHT           			GULSTM	G1159 	GIV         	3980115	SO  										CABIN	INOPERATIVE     	B			JZBR	A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			EA	25	250VC	2654 			0209	1231				DURING FLIGHT, NOTICED SLIGHT SMOKE AND PUNGUNT ODOR AT FORWARD RT CABIN COMING FROM LIGHT ASSY.  CREW MADE UNSCHEDULED 	LANDING WITH PASSENGERS ONBOARD AND UNEVENTFUL LANDING.  MAINTENANCE FOUND SHORTED POWER SUPPLY AND SURROUNDING WIRES ON	 PC BOARD.  REPLACED WITH NEW.  OPS OK.				2	L	7	2 	4F			RT	A12EA
1998111300252	19981113	00252	NE  	1998	11	13	98ZZZX4039       	2	19981021	G	7320	MR2725620	COMPUTER        	LUCAS       	FAFC2000    	BOEING	747   	747*        		NM  	RROYCE	RB211 	RB211*      	54555	NE  					ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	BHUD									INTERNAL BOND FAILURE OF INTEL UVAROM DATE CODE 9324 AT 10000 AND FLIGHT HOURS (4 EVENT SAMPLE) LEADS TO A LOSS OF A CON	TROL CHANNEL IN DUAL CHANNEL CONTROL UNIT.  SUBMITTER SUSPECTED BATCH PROBLEM WITH TIME RELATED FAILURE MODE.  800 DEVIC	ES OF SUSPECT DATE CODE, 1275 DEVICES IN BATCH TRACE AT 8 DEVICES PER CONTROL CHANNEL, 16 PER FAFC 2000.  DEVICE OBSOLET	E, NO LONGER MANUFACTURED.  ALTERNATE PART MODIFICATION IN PLACE.  DEVICES TO BE REMOVED AND REPLACED TO A PLANNED PRIOR	ITY BASED ON AIRCRAFT TYPE AND FLIGHT HOURS.		2	L	7	4 	4F	4	F	RT	A20WE   	A12EU
1998111300253	19981113	00253	SO  	1998	11	13	98ZZZX4040       	1	19981007	G	3240	5403009501	LINE            			GULSTM	AA5   	AA5B        	3960105	SO  										COCKPIT	CORRODED        	B			HX1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	25	711AP	1258 				AA5B1314				THE ALUMINUM LINE WAS A BRAKE LINE FOR THE RT BRAKE.  IT IS LOCATED BEHIND INSTRUMENT PANEL AND SIDE PANEL IN A VERY HAR	D TO SEE AREA.  IT WAS FOUND CORRODED AND DEEPLY PITTED AND LEAKING HYD FLUID DURING AVIONIC INSTALL.  SUBMITTER STATED 	CAUSE OF CORROSION WAS DETERMINED TO BE A DEFROSTER DUCT DIRECTLY ABOVE THE LINE AND TOUCHING IT.  THE DEFROSTER DUCT WA	S THE OLD STYLE SCAT TYPE DUCTING THAT WAS MADE OF COTTON MATERIAL AND IRON FORMING WIRE.  OVER THE YEARS, THE COTTON DE	TERIORATED AND THE IRON WIRE RUSTED FROM MOISTURE AND BEGAN TO POKE THROUGH THE COTTON ALLOWING THE RUSTED WIRE TO CONTA	CT THE ALUM LINE CAUSING A DISSIMILAR METAL SITUATION AND CORROSION.	1	L	7	1 	3O				A16EA
1998111300254	19981113	00254	NM  	1998	11	13	98ZZZX4041       	1	19980920	G	2910		VALVE           			BOEING	747   	747123      	1384873	NM  										HYDRAULIC SYSTEM	LEAKING         	B			GK4Y	O				OTHER                   				K			FLUID LOSS                			CR	CRUISE         	1			WP	03	858FT					20109				HNL/NAN - DURING CRUISE, NR 3 SYSTEM HYDRAULIC QUANTITY DECREASED IN-FLIGHT.  ON ARRIVAL NAN, NR 3 SYSTEM FLIGHT CONTROL	 SOV FOUND UNSERVICEABLE.  PART REPLACED AND AIRCRAFT RELEASED TO SERVICE.					2	L	7	4 	4F				A20WE
1998111300255	19981113	00255	CE  	1998	11	13	98ZZZX4042       	1	19981005	G	2752	48C48609	ACTUATOR        			LEAR  	35    	35A         	5170602	CE  										TE FLAP	RUPTURED        	E				A				UNSCHED LANDING         				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	500DS				311	079				FLIGHT CREW REPORTED A LOSS OF HYDRAULIC PRESSURE IN-FLIGHT.  AFTER LANDING, THE MECHANIC INSPECTED THE ACFT AND DETERMI	NED THE LT FLAP ACTUATOR HOUSING HAD RUPTURED CAUSING A LOSS OF HYDRAULIC FLUID.					2	L	7	2 	4F				A10CE
1998111300256	19981113	00256	EU  	1998	11	13	98ZZZX4043       	1	19981020	G	3246	57661	VALVE STEM      	DUNLOP      	AHA1814     	BRAERO	DH125 	BAE125800A  	1500285	EU  										WHEEL	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	204JC					258175				DURING LEAK DOWN CHECK AFTER REBUILD OF WHEEL, DISCOVERED AIR LEAKING FROM VALVE STEM AREA.  REMOVED VALVE STEM FROM WHE	EL AND HAD STEM NTD'D BY LOCAL SHOP.  THEY DISCOVERED A CRACK IN THE SEAL AREA OF THE STEM.  REPLACED VALVE STEM WITH A 	NEW UNIT.  THE DUNLOP OVERHAUL MANUAL DOES NOT SPECIFY NDT OF THE VALVE STEM DURING OVERHAUL PROCEDURES.				2	L	7	2 	4F			RT	A3EU
1998111300257	19981113	00257	CE  	1998	11	13	98ZZZX4044       	1	19981019	G	3241	40955	TRANSDUCER      			CESSNA	500   	550         	2076604	CE  										LT MLG	INOPERABLE      	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NE	01	727C	4530 				5500485				ANTI-SKID SYSTEM INOPERABLE WHICH ALLOWED THE LT WHEEL TO LOCK-UP ON LANDING.  AIRCRAFT SKIDDED THROUGH THE TIRE WHICH W	ENT FLAT.  TROUBLESHOOTING REVEALED LT WHEEL SPEED TRANSDUCER INOPERABLE.  REPLACING TRANSDUCER CORRECTED THE PROBLEM AT	 WHEEL SKID.				1	L	7	2 	4F				A22CE
1998111300259	19981113	00259	NE  	1998	11	13	98ZZZX4046       	1	19981014	G	6120	A1635194	SCREW           			JETAIR	JETSTM	JETSTM4101  	1500501	EU  	GARRTT	TPE331	TPE33114GR  	01514	NE  					CYLINDER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		2659 								EIGHT OF FOURTEEN CYLINDER HOLD-DOWN SCREWS FAILED.  THREE WERE FOUND WITH HEADS SEPARATED FROM THEIR SHANKS.  FIVE OTHE	RS WERE CRACKED IN FIRST THREAD BENEATH THE HEAD.  ALL FAILED UNITS HAVE BEEN FORWARDED TO MCCAULEY FOR ANALYSIS.					2	L	7	2 	4T	4	T	RT	A41NM   	E18NE
1998111300260	19981113	00260	SO  	1998	11	13	98ZZZX4047       	2	19980918	G	8530	401893	STUD            			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					NR 3 CYLINDER	SEPARATED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	8252S					28R8031170	310502			NR 3 CYLINDER ROCKER ARM CAME LOOSE, STUDS PULLED OUT OF CYLINDER.  TACHOMETER:  540.						1	L	7	1 	3O	3	O		2A13    	E9CE
1998111300261	19981113	00261	SO  	1998	11	13	98ZZZX4048       	2	19980915	G	7414	3492205	MAGNETO         	BENDIX      		BEECH 	58    	58P         	1152744	CE  	CONT  	O520  	TSIO520UB   	17040	SO  					ENGINE	FAILED          	H				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			NM	03	121Z	185  			HO69608FR	TJ285	274365R			LEFT MAG FAILED.  RIGHT ENGINE FAILED AT LIFT-OFF.  LEFT MAG REMOVED AND DISASSEMBLED.  FOUND DISTRIBUTOR BLOCK BUSHING 	LOOSE IN BLOCK P/N 10-391586.  REPLACED BLOCK AND GEAR OPS CHECK OK.					1	L	7	2 	3O	3	O		A23CE   	E8CE
1998111300262	19981113	00262	EU  	1998	11	13	98ZZZX4049       	1	19980923	G	2434	0120488269	ALTERNATOR      			GROB  	G115  	G115C       	1660303	EU  										ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	115GR	525  				82033C				DURING ROUTINE INSPECTION, THE ALTERNATOR HOUSING WAS FOUND CRACKED AT THE MOUNT POINT.						1	L	7	1 	3O			NT	A57EU
1998111300263	19981113	00263	EU  	1998	11	13	98ZZZX4050       	1	19980923	G	2731	115C3551	ELEVATOR TRIM   			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR	SEPARATED       	H		A		A				UNSCHED LANDING         				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			WP	23	115FN	587  			82061	82061C1				DURING THE RECOVERY PORTION AT THE BOTTOM OF A 'SLIT 5', THE ELEVATOR TRIM TAB BROKE AWAY FROM ITS PIVOT POINTS.  PILOT 	REPORTED IT WAS A LOUD 'POP' WHICH HE ALSO FELT IN THE CONTROL STICK.  AFTER AIRCRAFT RETURNED TO MAINTENANCE FACILITY, 	FURTHER INSPECTION REVEALED THAT ELEVATOR (LEFT) WAS ALSO DAMAGED AT ATTACH POINTS POSSIBLY DUE TO EXCESSIVE VIBRATION.				1	L	7	1 	3O			NT	A57EU
1998111300264	19981113	00264	SO  	1998	11	13	98ZZZX4051       	1	19981016	G	3243	494083	WASHER          			PIPER 	PA23  	PA23160     	7102304	SO  										MASTER BRAKE CYL	MISMANUFACTURED 	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	05	6918					232038				UNABLE TO BLEED MASTER BRAKE CYLINDER AFTER INSTALLING NEW O-RINGS AND WASHER P/N 494-083 (NR 24 IN ILLUSTRATED PARTS). 	NEW WASHER HAD TOO LARGE ON OUTSIDE DIAMETER PRESENTING SLEEVE (NR 22 IN ILLUSTRATION) FROM SLIDING DOWN OVER IT.  INSTE	AD, THE SLEEVE RESTED UPON SAID WASHER PRESENTING THE FLOW OF RETURN FLUID NECESSARY FOR BLEEDING THE SYSTEM.  SUBMITTER	 SUGGESTED THE WASHER MANUFACTURER BE NOTIFIED THE OUTSIDE DIAMETER OF THE WASHER IS CRITICAL.			1	L	7	2 	3O				1A10
1998111300265	19981113	00265	CE  	1998	11	13	98ZZZX4052       	1	19981023	G	2720	123100111	RUDDER          			CESSNA	182   	182P        	2075816	CE  										TAIL	MISRIGGED       	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	84379					18261866				WHILE PERFORMING A RIGGING CHECK, FOUND THE RUDDER IN FULL RIGHT POSITION, IT WOULD CONTACT THE ELEVATOR.  BOTH CONTROL 	SURFACES WERE RIGGED WITHIN MFG SPECS.  THE RECOMMENDED RUDDER SETTINGS A TOLERANCE MEASURED IN INCHES 8.12 INCHES TO 8.	72 INCHES.  THE RECOMMENDATION WOULD BE TO RIG THE RUDDER TO THE LOWER SETTING.				1	H	7	1 	3O			NT	TA13
1998111300266	19981113	00266		1998	11	13	98ZZZX4053       	4	19981001	G	6122	821002	GOVERNOR        	WOODWARD    																PROPELLER	MISOVERHAULED   	B	L		TQZR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17					2003683					THIS CONSTANT SPEED (PRIMARY PROP) GOVERNOR WAS OVERHAULED BY EMI AIRRAFT ACCESSORIES ON 7-23-98.  ABOUT 1 MONTH AFTER O	VERHAUL, GOVERNOR WAS INSTALLED ON A P & W PT6A-27 TURBINE ENGINE.  WHEN OPERATED, FOLLOWING INSTALLATION, ENGINE EVIDEN	CED ERRATIC SPEED CONTROL OF PROP AND PROP WOULD NOT REVERSE.  GOVERNOR RETURNED TO AIRFORCE TURBINES WHO SENT IT TO INT	'L GOVERNOR SERVICES FOR EVALUATION.  INT'L GOVERNOR DETERMINED THAT EMI HAS INSTALLED INCORRECT PARTS; HAD NOT SET GOVE	RNOR WITHIN CALIBRATION TEST POINTS; AND HAD NOT INCORPORATED SB 33606R1 AS STATED.  THIS IS THE FOURTH GOVERNOR PROBLEM	 IN 4 MONTHS.
1998111300267	19981113	00267	CE  	1998	11	13	98ZZZX4054       	1	19981012	G	3240	2178C30083	HOSE            			CESSNA	182   	182S        	2072701	CE  										LT BRAKE	LEAKING         	B			WIWR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07	789LM	48   				18280043				LEFT BRAKE INOPERABLE.  MASTER CYLINDER EMPTY.  FOUND OUTLET ELBOW LOOSE ALLOWING FLUID TO LEAK OUT.  ALSO, FOUND HOSE A	SSY WITH 90 DEGREE KINK WHERE HOSE CONNECTS TO OUTLET ELBOW.  NUT USED TO SECURE ELBOW (P/N AN924-3D NUT, P/N AN921-3D E	LBOW).  THREE-QUARTER TURN LOOSE, ALLOWING ELBOW TO SWIVEL.				1	H	7	1 	3O			NT	3A13
1998111300268	19981113	00268	CE  	1998	11	13	98ZZZX4055       	1	19981007	G	7930	070009937	LINE            			CESSNA	182   	R182        	2072734	CE  										COCKPIT	CORRODED        	B		A	HX1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	2666C	2754 				R18200202				THE ALUMINUM LINE WAS AN OIL PRESSURE LINE RUNNING FROM THE FIREWALL TO THE OIL PRESS GAUGE.  IT IS LOCATED BEHIND THE I	NSTRUMENT PANEL IN A VERY HARD TO SEE AREA.  IT WAS FOUND CORRODED AND DEEPLY PITTED.  DISCOVERED DURING AN ANNUAL INSPE	CTION.  THE CAUSE OF THE CORROSION WAS DETERMINED TO BE A DEFROSTER DUCT DIRECTLY ABOVE THE LINE AND TOUCHING IT.  THE D	EFROSTER DUCT WAS THE OLD STYLE SCAT TYPE DUCTING MADE OF COTTON MATERIAL AND IRON FORMING WIRE.  OVER THE YEARS, COTTON	 DETERIORATED AND IRON WIRE RUSTED FROM MOISTURE AND BEGAN TO POKE THROUGH THE COTTON ALLOWING THE RUSTED WIRE TO CONTAC	T THE ALUM LINE CAUSING A DISSIMILAR METAL SITUATION AND CORROSION.	1	H	7	1 	3O			RT	3A13
1998111300269	19981113	00269	SO  	1998	11	13	98ZZZX4056       	2	19981001	G	8530	TCM631521	SPRING          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	5HMSW	983  				21063789	294640R			DURING ROUTINE MAINTENANCE, METAL FOUND IN OIL FILTER.  TRACED TO BROKEN INNER VALVE SPRING OF NR 5 CYLINDER.  BROKEN EN	DS HAD STARTED TO EAT INTO CYLINDER HEAD.  SUBMITTER SUGGESTED CAUSE AS METALLURIGICAL FAILURE OF SPRING STEEL. VALVE SP	RINGS ARE A MANDATORY REPLACEMENT ITEM AT OVERHAUL (OR RE-MANUFACTURE).  THEREFORE, THIS PART HAD ONLY ACHIEVED ABOUT HA	LF OF ITS RATED LIFE.  THE OUTER SPRING WAS INTACT.			1	H	7	1 	3O	3	O		3A21    	E5CE
1998111300270	19981113	00270	CE  	1998	11	13	98ZZZX4057       	1	19981001	G	2750		PULLEY BRACKET  			CESSNA	185   	185         	2072802	CE  										TE FLAP	BROKEN          	G	P	A		O				OTHER                   				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			WP	17	23FG					18504035				PILOT SET ONE NOTCH OF FLAPS FOR TAKEOFF AND STARTED DEPARTURE ROLL.  WHEN ACFT LIFTED OFF THE GROUND, IT STARTED A RIGH	T ROLL.  PILOT COUNTERACTED WITH APPROX HALF AILERON DEFLECTION TO THE LEFT AND PUT THE FLAP LEVER TO ZERO FLAP POSITION	 AND ACFT FLEW STRAIGHT.  A NO FLAP LANDING WAS MADE.  INSPECTED FLAP CABLE SYSTEM AND FOUND UNDER FLOOR WHERE THE FLAP 	CABLE SPLITS THE RT PULLEY ATTACH BRACKET (P/N 0512128) HAD BROKEN AWAY FROM THE BULKHEAD.  THIS ALLOWED FOR ABOUT 15 DE	GREES OF FREE PLAY IN THE RT FLAP DUE TO A SLACK CABLE.  INSPECTED THE MOUNTING FLANGES FOR CRACKS ON THIS BRACKET.  CES	SNA: 185,860 HOURS.	1	H	7	1 	3O			NC	3A24
1998111300271	19981113	00271	CE  	1998	11	13	98ZZZX4058       	1	19981015	G	5410	555415017	CHANNEL         			CESSNA	500   	550         	2076604	CE  										ENGINE MOUNT	CHAFED          	B	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		4078 								DURING PHASE INSP, A CHAFED SPOT WAS NOTICED ON THE INBD UPPER ACCESS DOOR ON ENGINE COWL.  INVEST REVEALED IT HAD BEEN 	IN CONTACT WITH ENG MOUNT CHANNEL ON THE FWD SIDE.  FOUND DAMAGE TO BOTH SIDES WHICH NECESSITATED REPLACING BOTH FWD CHA	NNELS.  UPON INSP OF THE OTHER 4 C-550'S, 3 OTHERS HAD SIMILAR DAMAGE REQUIRING CHANNEL REPLACEMENT.  SEVERAL ACFT IN TH	E FLEET MAY HAVE THE SAME CHAFING DAMAGE.  THE MOUNT DAMAGE IS HIDDEN UNDER A FIRESEAL THAT LINES THE PYLON.  INITIALLY,	  DAMAGE ON COWLING DOOR IS ONLY A SHINY SPOT.  AREA IS STAINLESS SHEET THAT IS ATTACHED TO ALUM DOOR.  STAINLESS SHEET 	DOES NOT WEAR LIKE THE CHANNEL, SO A SHINY SPOT CAN ACTUALLY SIGNAL SIGNIFICANT WEAR ON STEEL CHANNEL.	1	L	7	2 	4F				A22CE
1998111300272	19981113	00272	CE  	1998	11	13	98ZZZX4059       	1	19981015	G	5410	555415018	CHANNEL         			CESSNA	500   	550         	2076604	CE  										ENGINE MOUNT	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		7150 								DURING PHASE INSP, A CHAFED SPOT WAS NOTICED ON THE INBD UPPER ACCESS DOOR ON ENGINE COWL.  INVEST REVEALED IT HAD BEEN 	IN CONTACT WITH ENG MOUNT CHANNEL ON THE FWD SIDE.  FOUND DAMAGE TO BOTH SIDES WHICH NECESSITATED REPLACING BOTH FWD CHA	NNELS.  UPON INSP OF THE OTHER 4 C-550'S, 3 OTHERS HAD SIMILAR DAMAGE REQUIRING CHANNEL REPLACEMENT.  SEVERAL ACFT IN TH	E FLEET MAY HAVE THE SAME CHAFING DAMAGE.  THE MOUNT DAMAGE IS HIDDEN UNDER A FIRESEAL THAT LINES THE PYLON.  INITIALLY,	  DAMAGE ON COWLING DOOR IS ONLY A SHINY SPOT.  AREA IS STAINLESS SHEET THAT IS ATTACHED TO ALUM DOOR.  STAINLESS SHEET 	DOES NOT WEAR LIKE THE CHANNEL, SO A SHINY SPOT CAN ACTUALLY SIGNAL SIGNIFICANT WEAR ON STEEL CHANNEL.	1	L	7	2 	4F				A22CE
1998111300273	19981113	00273	SO  	1998	11	13	98ZZZX4060       	1	19980927	G	7160		VALVE           			PIPER 	PA18  	PA18A150    	7101837	SO  										CARBURETOR	SEPARATED       	G	P	A		A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			EA	25	6894B					185087				ENGINE STOPPAGE AND FORCED LANDING OFF AIRPORT OCCURRED WHEN THE BUTTERFLY VALVE IN THE CARBURETOR HEAT AIRBOX SEPARATED	 FROM ITS SHAFT AND BLOCKED OFF AIR FLOW TO CARBURETOR/ENGINE.					1	H	7	1 	3O				1A2
1998111300275	19981113	00275	SO  	1998	11	13	98ZZZX4062       	1	19981009	G	2731	1565710	HINGE           			PIPER 	PA23  	PA23250     	7102308	SO  										LT STABILIZER	WORN            	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	27CY	5106 			27312	277654118				REMOVED TRIM TAB DUE TO WORN HINGE.  INSPECTION FOUND HORN ASSY P/N 28372-02 LOOSE AND SKINS AROUND ATTACHMENT AREA CRAC	KED.  SUBMITTER STATED LEFT UNREPAIRED COULD POSSIBLY SEPARATE IN-FLIGHT.					1	L	7	2 	3O				1A10
1998111300276	19981113	00276	CE  	1998	11	13	98ZZZX4063       	1	19981008	G	5751	0523800	RIVETS          			CESSNA	172   	172B        	2072406	CE  										BALANCE WEIGHT	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	7570X	3710 				17248070				DURING INSPECTION, AILERON BALANCE WEIGHTS WERE OBSERVED TO HAVE SEVERAL RIVET HEADS POPPED.  FURTHER RIVETS COULD BE PO	PPED BY HAND (HEADS POPPING OFF).  THE RIVET CORROSION WAS NOT VISIBLE FROM UNDER/AROUND HEADS.					1	H	7	1 	3O			NT	3A12
1998111300277	19981113	00277	SW  	1998	11	13	98ZZZX4064       	1	19981007	G	5260	S28375	CABLE           			GULSTM	560   	560         	0141402	SW  										STEP ASSY	BROKEN          	B	L		AC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	356WC	465  				560432				THE FWD DOOR CABLE BROKE AS PILOT GOT OFF AIRPLANE.  THIS NEW COMPOSITE STEP HAS 2 SUPPORT CABLES, 1 FWD AND 1 AFT.  THI	S IS 3RD CABLE THAT HAS BROKEN.  THE 1ST CABLE BROKE AT 151.8 HRS; FWD CABLE.  THE 2ND BROKE AT 358.4 HRS; AFT CABLE.  C	ABLES HAVE BEEN BREAKING AT THE BOTTOM END WHERE IT SWAGES TO THE CABLE FITTING. CABLE IS IN A STRAIGHT-LINE PULL WHEN T	HE STEP IS EXTENDED.  CABLES DO BEND WHEN THE STEP IS RETRACTED, BUT THERE IS NO LOAD ON THEM THEN.  THERE HAVE BEEN NO 	INJURIES, BUT SUBMITTER STATED THAT POSSIBILITY EXISTS IF BOTH CABLES BROKE AT ONCE.  A NEW CABLE WAS INSTALLED AND RIGG	ED.	1	H	7	2 	3O			 	6A1
1998111301144	19981113	01144	NE  	1998	11	13	98ZZZX4065       	2	19980723	G	7250	3027102	BLADE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TURBINE	BROKEN          	H	P	A		A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			SW	99	911VR					30998	6B60			IN CRUISE FLIGHT AT 11,500 FEET, ALL NR 1 ENGINE OIL PRESSURE DROPPED FOLLOWED BY A SPLIT IN TORQUE.  OIL PRESSURE LIGHT	 AND NR 2 CHIP LIGHT.  PILOT SHUT NR 1 ENGINE DOWN AND LANDED AT NEAREST AIRPORT (5 MINUTES).  UPON REMOVAL OF NR 1 POWE	R SECTION, FOUND POWER TURBINE FAILURE.  P.T. BLADE SEPARATION.  P.T. FAILURE WAS CONTAINED AND NO DAMAGE TO AIRCRAFT. S	UBMITTER STATED SULPHIDATION IS SUSPECT IN THE FAILURE OF THE TURBINE BLADE.  ENGINE TSO:  3,335.4 HOURS.  TT ON TURBINE	 BLADES UNKNOWN.  (NO TIME LIMITS AT P.T. TURBINE BLADES).		1	G	7	1 	4U	4	U		H4SW    	E22EA
1998111301145	19981113	01145	CE  	1998	11	13	98ZZZX4066       	1	19981007	G	2460	M8353615022	RELAY           			CESSNA	500   	560CESSNA   	2076750	CE  										RT ENGINE	FAILED          	B	L		AC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	356WC	612  				560432				PILOT REPORTED ON START OF RT ENGINE, ROTATION ACHIEVED UP TO 13 PERCENT, BUT ENG WOULD NOT START.  START TERMINATED, AF	TER 2 MINUTES ANOTHER START ATTEMPTED AND ENG STARTED NORMALLY.  MAINT CONSULTED AND AFTER STUDY OF WIRING DIAGRAM, PILO	TS WERE ASKED TO OBSERVE IGNITION AND BOOST PUMP ON LIGHTS.  ENG STARTED NORMALLY ON NEXT 2 STARTS, BUT ON 3RD, ENG DID 	NOT LIGHT OFF, SO PILOT SELECTED IGNITION MANUALLY AND ENG STARTED.  PILOTS NOTICED STATUS OF BOOST PUMP LIGHT.  MAINT P	ERFORMED 2 ENG STARTS.  1ST START NORMAL, BUT 2ND ENG DID NOT START.  AGAIN, IGNITION SELECTED MANUALLY AND ENG STARTED 	AND BOOST PUMP LIGHT ILLUMINATED AND FUEL PRESS LOW LIGHT WAS OUT.   NEW RELAY INSTALLED AND ENG STARTS NORMAL.	2	L	7	2 	4F			RT	A22CE
1998111301146	19981113	01146	SO  	1998	11	13	98ZZZX4067       	1	19980930	G	2750	2634300	FLAP ROLLER     			PIPER 	PA30  	PA30        	7103002	SO  										FLAP TRACK	MISINSTALLED    	D	S			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	7774Y	50   				30860				ACFT HAD NYLON FLAP ROLLERS INSTALLED IN AN ATTEMPT TO PREVENT FLAPS FROM BINDING AND CAUSING AN ASYMMETRICAL FLAP CONDI	TION DURING RETRACTION.  PIPER SL 595 ADDRESSES THIS PROBLEM.  ROLLER INSTALLED APPROX 50 HRS AGO, P/N 26343-00.  BOTH S	TEEL ROLLER P/N 14976-73 AND THE NYLON ROLLER P/N 26343-00 REQUIRE INSTALLATION OF BUSHING P/N 14976-72.  THE NEW NYLON 	ROLLERS WERE INSTALLED WITHOUT THESE BUSHINGS AND THIS CAUSED FLAP ROLLERS TO NOT TURN AND ALLOWED FLAP TO RATTLE IN FLA	P TRACK.		1	L	7	2 	3O				A1EA
1998111301147	19981113	01147	CE  	1998	11	13	98ZZZX4068       	1	19981014	G	5312	9542001713	WEB             		9542001715  	BEECH 	95    	95B55       	1152729	CE  										FUSELAGE	BUCKLED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8493N	2317 				TC1112				DURING ANNUAL INSPECTION, THE FRONT SPAR CARRY-THROUGH STRUCTURE FORWARD WEB WAS FOUND BUCKLED BELOW THE LT WING ATTACH 	FITTING. THE DAMAGE EXTENDED BETWEEN THE LOWER SKIN AND THE FITTING HORIZONTALLY FOR APPROX 12 INCHES. THERE WAS ADDITIO	NAL DEFORMATION INBOARD OF LT LOWER ATTACH FITTING.  GREASE, DIRT, AND DEBRIS HAD TO BE REMOVED TO ADEQUATELY INSPECT TH	E AREA.  AIRCRAFT HAS A PREVIOUS HISTORY OF GEAR-UP LANDING.			1	L	7	2 	3O			RT	3A16
1998111301148	19981113	01148	CE  	1998	11	13	98ZZZX4069       	1	19981005	G	3230	ADNE5323	ROD END         		968200253   	BEECH 	58    	58          	1152740	CE  										NLG	FAILED          	B			DC1R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	07	58WA					TH201				NOSE GEAR COLLAPSED DUE TO ROD END FAILURE.  ROD END BROKE AT GREASE FITTING.  ROD END OF FORWARD GEAR DOWN ROD ASSY ATT	ACHES TO TRUNNION FITTING.					1	L	7	2 	3O				3A16
1998111301150	19981113	01150		1998	11	13	98ZZZX4071       	2	19981012	G	7322	30802	FLOAT           	PRECISION   	MA45AA      															CARB	INTERFERRING    	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05										CARBURETORS THAT ARE USED ON HELICOPTER HAVE A FLOAT HINGE THAT IS RESTING ATO P OF THE ALTITUDE BELLOWS CAUSING FUEL TO	 CUT OFF OR TOO SLOW ENTERING CARBURETOR.  SUBMITTER RECOMMENDED ALERT OR AD BECAUSE THE NEWLY DESIGNED POLYMER FLOAT IN	TERFERES WITH THE ALTITUDE BELLOWS WHICH MAY CAUSE NO START OR SUDDEN STOPPAGE.  NO KNOWN SERVICE BULLETINS EXIST.
1998111301152	19981113	01152	SW  	1998	11	13	98ZZZX4073       	1	19981005	G	2435	MHB6016	STARTER         	ELECTROSYS  		GULSTM	500   	500S        	0141107	SW  										ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9096N	509  			7113353	3076				AFTER SHUT DOWN OF ENGINE, AIRCRAFT WAS GETTING READY TO LEAVE ON ANOTHER FLIGHT AND STARTER WOULD NOT ENGAGE TO START E	NGINE.					1	H	7	2 	3O				6A1
1998111301153	19981113	01153		1998	11	13	98ZZZX4074       	4	19981005	G	3435	MHB6016	STARTER         	ELECTROSYS  		GULSTM	500   	500S        	0141107	SW  										ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99	9096N				8013279	3076				INSTALLED NEW STARTER.  STARTER WOULD NOT ENGAGE.						1	H	7	2 	3O				6A1
1998111301154	19981113	01154	GL  	1998	11	13	98ZZZX4075       	3	19981013	G	6114		HUB             			PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	337EP	4365 	884  			447995064		AV5617		PROPELLER HUB CRACKED IN AREA DICTATED IN AD 98-02-23.  THIS PROPELLER INCURRED SUDDEN STOPPAGE IN 1990.  PROPELLER WAS 	OVERHAULED 10/94.					1	L	7	2 	3O				A19S0   		5	C	P920
1998111301158	19981113	01158	EA  	1998	11	13	98ZZZX4079       	2	19981016	G	8520	LW17060	CRANKSHAFT      			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	OUT OF TOLERANCE	B	L	A	YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09			2001 		V11777		L1728539A			CRANKSHAFT REMOVED FROM ENGINE AT TBO.  JOURNALS REQUIRED GRINDING AND RENITRIDED DUE TO WEAR.  INSPECTION OF GEAR COUNT	ERBORE PER AD 91-14-22 REVEALED DOWL HOLE HAD BEEN FACTORY REPAIRED BY INSTALLATION OF SLEEVE.  TEXTRON LYCOMING SB 475 	HAS NO DATA FOR SLEEVE REPAIRS OR INSPECTION.  DAMAGE TO CRANKSHAFT COUNTERBORE ID AT PREVIOUS GEAR ASSY DUE TO RADIAL P	OSITION OF DOWEL BEING OUT OF TOLERANCE.  THIS REPAIR STATION HAS NOTED SIMILAR PROBLEMS ON TWO OTHER CRANKSHAFTS OF THE	 SAME P/N THIS YEAR. LYC SB 4758 CONTAINS NO DATA FOR RADIAL OR ANGULAR POSITION OF DOWEL HOLE.		1	G	7	1 	3O	3	O		H10WE   	E274
1998111301159	19981113	01159	EU  	1998	11	13	98ZZZX4080       	1	19980729	G	2150	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					A/C BAY	INOPERATIVE     	B			R8RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6095U		14   		SH189RM	2699	9265			AIR CONDITIONING SYSTEM DOES NOT COOL AIRCRAFT.  BLOWS HOT AIR.  FOUND 1 OF 2 CONDENSOR BLOWER MOTOR ASSEMBLIES INOPERAT	IVE.  THE 2-BLOWER MOTOR ASSEMBLIES WERE INSTALLED AT THE SAME TIME.  THEY BOTH HAVE 14.1 HOURS OF USE SINCE OVERHAUL. T	HE REPORTED MOTOR ASSEMBLY HAD ABNORMAL BRUSH WEAR.  RETURNED MOTOR ASSEMBLY TO THE VENDOR FOR WARRANTY.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1998111301160	19981113	01160	SW  	1998	11	13	98ZZZX4081       	1	19981016	G	5302	206033004177	SKIN            			BELL  	206   	206L4       	1182110	SW  										TAIL BOOM	CRACKED         	B			DDZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	2AQ	6212 			52099	52099				SIX INCH CRACK WAS FOUND ON TAIL BOOM SKIN AT THE FORWARD LOWER CUT-OUT AREA FOR THE HORIZONTAL STABILIZER.  SUBMITTER S	TATED BELL HELICOPTER HAS ISSUED AN OPERATION SAFETY NOTICE ON THIS PROBLEM.					1	G	7	1 	3U			NC	H2SW
1998111301161	19981113	01161	SW  	1998	11	13	98ZZZX4082       	1	19981019	G	5302		FITTING         			BELL  	206   	206B        	1181511	SW  										TAIL BOOM	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	158P	14644				1472				UPPER LEFT TAIL BOOM ATTACHMENT FITTING CRACKED.  FITTING CRACKED AT THE LEFT LEG THROUGH AFT MOST TWO RIVET HOLES.						1	G	7	1 	3U				H2SW
1998111301162	19981113	01162	EA  	1998	11	13	98ZZZX4083       	2	19981016	G	8520	LW17060	CRANKSHAFT      			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	OUT OF TOLERANCE	B		A	YECR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09		1993 			V16665		L1480539N			DURING TRAIL ASSY OF NEW 13S19646 GEAR, MARKED 7/89, 27/98, MFR 30620, IN CONJUNCTION WITH FAA AD 91-14-22 INSPECTIONS, 	THE GEAR WOULD NOT START INTO THE CRANKSHAFT COUNTERBORE.  INTERFERENCE WAS FOUND BETWEEN THE CRANKSHAFT COUNTERBORE ID 	AND THE P/N STD-1065 DOWEL DUE TO AN APPARENT OUT-OF-TOLERANCE CONDITION OF THE RADIAL POSITION OF THE DOWEL HOLE IN THE	 CRANKSHAFT AND/OR GEAR.  CRANKSHAFT WAS REPAIRED BY RELOCATING DOWEL HOLE AND INSTALLING OVERSIZE DOWEL.			1	G	7	1 	3O	3	O		H10WE   	E274
1998111301163	19981113	01163	NE  	1998	11	13	98ZZZX4084       	2	19980810	G	7230	0292252970	MANIFOLD        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					GAS GENERATOR	FAILED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6084W	1674 	44   		3157AD	2672	9245			DURING A DAILY INSPECTION, MECHANIC COULD NOT TURN THE COMPRESSOR FREELY.  THIS ACFT JUST RETURNED FROM A FLIGHT.  IT HA	D BEEN SHUT DOWN APPROX 45 MINUTES.  THE ENGINE WAS SEIZED.  THE REPAIR IS THE REPLACEMENT OF THE COMPRESSOR AND THE GAS	 GENERATOR ASSY.  AFTER THE ENGINE COMPLETELY COOLED, COMPRESSOR COULD BE ROTATED FREELY.  SUBMITTER STATED THIS IS A KN	OWN PROBLEM IN THE SOUTHWEST REGION TO TURBOMECA.  REF:  TURBOMECA SL 1617/94/ARRIEL/17.  SUBMITTER SUGGESTED CAUSE AS C	OKING OF THE FUEL INJECTION WHEEL.		1	G	7	1 	3U	3	U		H9EU    	E19EU
1998111301164	19981113	01164	EA  	1998	11	13	98ZZZX4085       	3	19980922	G	6111		BLADE           			CESSNA	172   	172R        	2072401	CE  						MCAULY	IC235	IC235LFA7570	EA  	PROPELLER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	53AF	210  				17280454		RE022		INSPECTION OF PROPELLER INDICATES FLAKING CORROSION ON 3 PLACES ON THE BLADE FACE.  PROPELLER TO BE REPLACED BY MCCAULEY	.					1	H	7	1 	3O			NT	3A12    		5	N	P12EA
1998111301165	19981113	01165	EA  	1998	11	13	98ZZZX4086       	3	19980922	G	6111		BLADE           			CESSNA	172   	172R        	2072401	CE  						MCAULY	IC235	IC235LFA7570	EA  	PROPELLER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	24AF	191  				17280439		RB009		DURING 100-HOUR INPSECTION, SEVERE CORROSION NOTED ON BLADE BACK.  FLAKING TYPE CORROSION INDICATING IMPROPER HEAT TREAT	MENT.  SUBMITTER STATED FIVE TYPE OCCURRENCES COMPANY WIDE.  ALL REQUIRED PROP REPLACEMENT.  PROPELLER TO BE REPLACED BY	 MCCAULEY.				1	H	7	1 	3O			NT	3A12    		5	N	P12EA
1998111301166	19981113	01166	EA  	1998	11	13	98ZZZX4087       	2	19981016	G	8520		CRANKSHAFT      			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	OUT OF TOLERANCE	B		A	YECR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09		1982 			V16476		L1476939A			DURING TRIAL ASSY OF NEW CRANKSHAFT GEAR P/N 13S19646, MARKED 7/89, 27/98, MFR 30620, NOTED THAT GEAR WOULD NOT START IN	TO CRANKSHAFT COUNTERBORE DUE TO INTEFERENCE WITH THE COUNTERBORE ID AND/OR STD-1065 DOWEL.  CRANKSHAFT WOULD BE ASSEMBL	ED WITH EARILIER 61155 GEAR, BUT NOT WITH NEW 13S19646, DUE TO AN APPARENT OUT-OF-TOLERANCE CONDITION OF THE DOWEL HOLE 	IN EITHER THE CRANKSHAFT OR THE GEAR.  CRANKSHAFT DOWEL HOLE WAS RELOCATED WITH OVERSIZE DOWEL TO PERMIT ASSY.			1	G	7	1 	3O	3	O		H10WE   	E274
1998112000005	19981120	00005	SW  	1998	11	20	98ZZZX4089       	1	19980604	G	2140	398522	HOSE            			BBAVIA	8     	8GCBC       	1220803	SW  										ENGINE BAY	MISROUTED       	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	778AC	32   				38197				CARBURETOR THROTTLE ARM HITS REAR CABIN HEAT SCAT HOSE, RESTRICTS FULL TRAVEL.  THE ROUTING OF THE SCAT HOSE CARRYING WA	RM AIR FROM THE MUFFLER HEAT SHROUD TO THE REAR CABIN HEAT VALVE CAUSED THE THROTTLE ARM TO CONTACT IT BEFORE THE THROTT	LE REACHED THE FULL POWER STOP.  IN ORDER FOR THE THROTTLE TO REACH THE FULL POWER POSITION, SUFFICIENT FORCE HAD TO BE 	APPLIED TO DEFORM THE SCAT HOSE.			1	H	7	1 	3O				A21CE
1998112000006	19981120	00006	SW  	1998	11	20	98ZZZX4090       	1	19980904	G	2710		BOLT            			BBAVIA	8     	8GCBC       	1220803	SW  										AILERON	IMPROPER PART   	B			CL4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	778AC	32   				38197				WHILE PERFORMING AN INITIAL INSPECTION ON A NEW AIRCRAFT, DISCOVERED SEVERAL PLACES HAD INCORRECT OR IMPROPERLY INSTALLE	D HARDWARE.  THE FORWARD BOLT ATTACHING THE LOWER CABIN DOOR HINGE HAD BEEN IMPROPERLY DRILLED AND INSTALLED SO THAT IT 	PREVENTED THE DOOR FROM COMPLETELY CLOSING.  THE BOLTS THAT SECURE THE AILERON SPACES TO THE AILERON WERE TOO LONG, EXTE	NDING OUT TO CONTACT THE FABRIC AT THE WING TIPS (OUTBOARD END OF THE AILERON BAY).			1	H	7	1 	3O				A21CE
1998112000007	19981120	00007	SW  	1998	11	20	98ZZZX4091       	1	19980706	G	7800		EXHAUST         			BBAVIA	8     	8GCBC       	1220803	SW  										ENGINE	LEAKING         	B			CL4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	778AC	240  				38197				PILOT REPORTED THE CARBON MONOXIDE DETECTORS TURNED DARK.  (WARM WEATHER OPERATION USING FRESH AIR VENTS INTO THE CABIN)	.  INVESTIGATION BY DELTA AIRCRAFT MAINTENANCE FOUND LEAKS AT THE SLIP JOINTS BETWEEN THE EXHAUST STACK RISERS, P/N 11-0	864, AND THE MUFFLER ASSEMBLY, P/N 7-1553-2.  SUBMITTER STATED DESIGN AND FIT OF THE PARTS DID NOT ALLOW THE LEAKS TO BE	 STOPPED, AND NEW PARTS SUPPLIED BY THE MANUFACTURER FIT WORSE THAN THE ORIGINAL PARTS.  VARIOUS METHODS ARE BEING INVES	TIGATED TO REDUCE THE LEAKS.		1	H	7	1 	3O				A21CE
1998112000008	19981120	00008	SW  	1998	11	20	98ZZZX4092       	1	19980712	G	2140	398522	HOSE            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C1G     	41514	EA  					CABIN	MISINSTALLED    	B			CL4R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	695AC	30   				39498	L3609236A			CARBURETOR THROTTLE ARM HITS REAR CABIN HEAT SCAT HOSE, RESTRICTS FULL TRAVEL.  THE ROUTING OF THE SCAT HOSE CARRYING WA	RM AIR FROM THE MUFFLER HEAT SHROUD TO THE REAR CABIN HEAT CONTROL VALVE CAUSED THE THROTTLE ARM TO CONTACT IT BEFORE TH	E THROTTLE REACHED THE FULL POWER STOP.  IN ORDER FOR THE THROTTLE TO REACH THE FULL POWER POSITION, SUFFICIENT FORCE HA	D TO BE APPLIED TO DEFORM THE SCAT HOSE.			1	H	7	1 	3O	3	O		A21CE   	E286
1998112000009	19981120	00009	EA  	1998	11	20	98ZZZX4093       	2	19980813	G	7322	19995	BOLT            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C1G     	41514	EA  					CARBURETOR	MISINSTALLED    	B			CL4R	O				OTHER                   				W			INADEQUATE Q C            			AP	APPROACH       	1			AL	03	695AC	30   				39498	L3609236A			PILOT REPORTED WHILE IN LANDING PATTERN, WHEN THE CARBURETOR HEAT CONTROL WAS MOVED TO 'COLD' POSITION, THE THROTTLE CON	TROL ADVANCED TO A HIGHER POWER SETTING.  EXAMINATION REVEALED THAT UNDER SOME CIRCUMSTANCES, THE CLEVIS PIN THAT ATTACH	ED THE CARBURETOR HEAT CONTROL CABLE TO THE CONTROL ARM CAN CONTACT THE THROTTLE CONTROL ARM CAUSING THE THROTTLE CONTRO	L TO MOVE IN THE SAME DIRECTION AS THE CARB HEAT CONTROL.  SUBMITTER STATED THIS COULD CAUSE THE THROTTLE SETTING TO CHA	NGE IN EITHER DIRECTION DEPENDING ON WHETHER THE CARB HEAT WAS TURNED ON OR OFF.  CARE MUST BE TAKEN WHEN THE CARBURETOR	 HEAT CONTROL IS MOVED TO INSURE THAT BOTH CONTROLS OPERATE CORRECTLY.	1	H	7	1 	3O	3	O		A21CE   	E286
1998112000010	19981120	00010	SW  	1998	11	20	98ZZZX4094       	1	19980712	G	7800		EXHAUST SYSTEM  			BBAVIA	8     	8GCBC       	1220803	SW  										ENGINE	LEAKING         	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	695AC	30   				39498				PILOT REPORTED EXHAUST LEAKS.  AIRCRAFT HAS LARGE EXHAUST STAINS ON THE COWLING AROUND THE EXHAUST STACK ACROSS THE BOTT	OM OF THE AIRCRAFT AROUND THE LOUVERS ON THE LT SIDE OF THE ENGINE  COWL, AND SPREADING BACK ACROSS THE LT SIDE OF THE A	CFT ACROSS THE CABIN VENT AND UNDER THE WINDOW.  EXAMINATION FOUND THE SLIP JOINTS BETWEEN THE EXHAUST RISERS, P/N 11-08	64, AND THE MUFFLER ASSY, P/N 7-1553-2, WERE LEAKING.  THE DESIGN AND MANUFACTURE OF THE PARTS DOES NOT LEND ITSELF TO A	 TIGHTER FIT.  OPTIONS FOR SEALING THE LEAKS ARE BEING INVESTIGATED.		1	H	7	1 	3O				A21CE
1998112000011	19981120	00011	SW  	1998	11	20	98ZZZX4095       	1	19980707	G	2710		BOLT            			BBAVIA	8     	8GCBC       	1220803	SW  										AILERON	IMPROPER PART   	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	695AC	3    				39498				FORWARD LOWER CABIN DOOR HINGE BOLT IMPROPERLY DRILLED, INSTALLED SO THAT IT CONTACTED THE CABIN DOOR FRAME, KEEPING THE	 DOOR FROM CLOSING PROPERLY.  FACTORY REPRESENTATIVES REPAIRED FIBERGLASS DOOR, REDRILLED, AND REINSTALLED CORRECTLY.  B	OLT ATTACHING LEFT AILERON SPADE TO THE AILERON TOO LONG, CONTACTED FABRIC COVERING THE LEFT AILERON BAY END RIB.  FACTO	RY REP CUT BOLT OFF TO ALLOW CLEARANCE.			1	H	7	1 	3O				A21CE
1998112000012	19981120	00012	SW  	1998	11	20	98ZZZX4096       	1	19980813	G	2820	714763	LINE            			BBAVIA	8     	8GCBC       	1220803	SW  										RT WING	DAMAGED         	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	695AC	30   				39498				BOLT HOLDING THE LOWER CABLE GUARD ON THE RIGHT FLAP BELLCRANK CONTACTS THE FUEL LINE IN THE RIGHT WING ROOT WHEN THE FL	APS ARE ACTUATED.  BOLT HAS CUT APPROX HALF WAY THROUGH THE WALL OF THE FUEL LINE.  INSP OF THE LEFT WING ROOT AREA INDI	CATES THAT CARE IN INSTALLING THE FUEL LINE AND THE BOLTS THROUGH THE FLAP BELLCRANK COULD AVOID THIS PROBLEM.  BOTH THE	 ROUTING OF THE FUEL LINE AND THE DIRECTION OF INSTALLATION OF THE BOLT HOLDING THE CABLE GUARD ARE IMPORTANT TO A SAFE 	INSTALLATION.		1	H	7	1 	3O				A21CE
1998112000013	19981120	00013	SW  	1998	11	20	98ZZZX4097       	1	19980707	G	7160	714755	TUBE            			BBAVIA	8     	8GCBC       	1220803	SW  										AIRBOX	LOOSE           	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	695AC	3    				39498				DURING PRE-BUY INSPECTION OF NEW AIRCRAFT AT THE AMERICAN CHAMPION FACTORY, FOUND THE INDUCTION AIR TUBE BETWEEN THE COW	LING AND THE INDUCTION AIRBOX WAS NOT SECURED TO THE COWLING (SECURED ONLY TO THE INDUCTION AIRBOX).  THE HOSE HAD BEEN 	SUCKED INTO THE FRONT OF THE INDUCTION AIRBOX PARTIALLY OBSTRUCTING THE AIRFLOW INTO CARBURETOR.  THIS AIRCRAFT HAD ONLY	 THE PRODUCTION FLIGHT TEST (2.6 HOURS).  FACTORY REPRESENTATIVES INSTALLED A NEW HOSE (THE ORIGINAL ONE HAD BEEN DEFORM	ED SO THAT IT NO LONGER MADE A TIGHT FIT), AND SECURED IT ON BOTH ENDS.		1	H	7	1 	3O				A21CE
1998112000015	19981120	00015	EU  	1998	11	20	98ZZZX4098       	1	19980611	G	3010	258KFI91A	LINE            			BRAERO	DH125 	BAE125800A  	1500285	EU  										BS 21	CHAFED          	B		A	COZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	27	494AT	3597 				NA0404				DURING AREA INSPECTION BEHIND PANEL F169, NOTED THE TKS MAIN SUPPLY LINE TO THE HORIZONTAL STABILIZER LEADING EDGE WAS R	OUTED BEHIND THE AIR SUPPLY LINE TO THE LEFT ENGINE AIR JET PUMP.  THE TKS LINE WAS UNDER TENSION, WAS MELTED, AND DEFOR	MED TO THE EXTENT THAT 95 PERCENT OF THE LINE WALL THICKNESS WAS MISSING AND THE INTERIOR OF THE PIPE WAS RESTRICTED BY 	OVER 60 PERCENT.  TKS FLUID IS THE ONLY DEICING METHOD FOR THE HORIZONTAL STABILIZER.  RAYTHEON WAS NOTIFIED AND OTHER K	AISER AIR MAINTAINED BAE 125-800'S WILL BE INSPECTED TO DETERMINE THE EXTENT OF THE PROBLEM.		2	L	7	2 	4F			RT	A3EU
1998112000048	19981120	00048	SW  	1998	11	20	98ZZZX4116       	1	19980919	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407AL					53044				DURING 25 HOUR AD, INSPECTED ALL COUPLINGS, FOUND NR 6 COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000049	19981120	00049	SW  	1998	11	20	98ZZZX4117       	1	19980920	G	5302	206031329103S	FITTING         		206031314119	BELL  	206   	206L3       	1182108	SW  										TAIL BOOM	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350AL	6915 	52   			51429				ROUTINE FIGHT, MECHANIC NOTICED AN ABNORMAL TAIL BOOM BOUNCE.  FITTING CRACKED COMPLETELY THROUGH BOTH SIDES AT AFT RIVE	T HOLES.					1	G	7	1 	3U				H2SW
1998112000113	19981120	00113	CE  	1998	11	20	98ZZZX4118       	1	19980916	G	5711	1181000131	SPAR            			BEECH 	1900  	1900C       	1154161	CE  										RT WING	CORRODED        	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5632C	23378				UC81				FOUND MAIN SPAR LOWER CAP SEVERELY CORRODED.  THIS CORROSION WAS FOUND WHERE MAIN SPAR PASSES THROUGH FUSELAGE BENEATH A	IR CONDITIONER LOCATION.  SUSPECT MOISTURE FROM AIR CONDITIONER COLLECTED ON SPAR CAUSING CORROSION.  LOCATION FURTHER I	DENTIFIED AS FS 288.0, FROM WS 0.0 TO RT WS 27.0.				2	L	7	2 	4T			RT	A24CE
1998112000115	19981120	00115	EA  	1998	11	20	98ZZZX4120       	3	19981001	G	6110		BOLT            			PIPER 	PA28  	PA28161     	7102803	SO  						SNSNCH	74D	74DM        	EA  	PROPELLER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	81351	2100 				288016178		A48577		PROPELLER REMOVED TO C/W LYC AD 98-02-08.  AFTER COMPLETING AD, THE PROPELLER WAS TO BE RE-INSTALLED.  THE PROPELLER MOU	NTING BOLTS WERE INSPECTED PRIOR TO INSTALLATION, AND WERE FOUND TO BE STRETCHED.  THE BOLTS WERE REMOVED FROM SERVICE A	ND NEW BOLTS WERE USED TO INSTALL PROPELLER.  SUBMITTER RECOMMENDED DILIGENCE IN ADHERING TO PROPER TORQUE VALVES AND PR	OCEDURES AND INSPECTIONS PRIOR TO RE-INSTALLATION.			1	L	7	1 	3O				2A13    		5	N	P88614
1998112000116	19981120	00116	SO  	1998	11	20	98ZZZX4121       	1	19981022	G	2810	560335	FUEL CELL       			PIPER 	PA42  	PA42720     	7104212	SO  										FUSELAGE	LEAKING         	B			TIMR	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	07	175AA				7944910	428001017				FUEL CELL SENT FOR REPAIR.  RECEIVED FUEL CELL AND INSTALLED.  IT STILL LEAKED.  AFTER TROUBLESHOOTING FOR OVER ONE WEEK	, FOUND TO BE SAME CELL.  REMOVED TANK AND SENT BACK FOR RE-REPAIR.					1	L	7	2 	4T				A23SO
1998112000117	19981120	00117	SO  	1998	11	20	98ZZZX4122       	1	19981022	G	2820	565218	LINE            			PIPER 	PA31  	PA31350     	7103110	SO  										LT WING ROOT	LEAKING         	B			TIMR	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	07	27367	7399 				317252007				FUEL LEAKING INTO CABIN.  STEEL BRAIDED LINE LEAKING INTERNALLY.						1	L	7	2 	3O				A20SO
1998112000118	19981120	00118	CE  	1998	11	20	98ZZZX4123       	1	19980910	G	7820	05540112PTT	MUFFLER         			CESSNA	172   	172R        	2072401	CE  										EXHAUST	CRACKED         	B			EBVD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	992CP	207  				17280284				WHILE PERFORMING THE AIRCRAFT'S FIRST ANNUAL INSPECTION, THE MUFFLER END FLANGE (ONE OF THEM) WAS FOUND TO HAVE A CRACK 	ALONG THE WELD EMANATING ABOUT ONE-THIRD OF THE CIRCUMFERENCE OF THE FLANGE.  THE MUFFLER WAS REPLACED WITH A NEW UNIT. 	 PART ONLY HAD 207 HOURS ON IT.				1	H	7	1 	3O			NT	3A12
1998112000119	19981120	00119	CE  	1998	11	20	98ZZZX4124       	1	19981028	G	7160	05503623	ELBOW           			CESSNA	182   	182S        	2072701	CE  										ENGINE	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	72MR					18280123				ELBOW IS MANUFACTURED FROM THIN FIBERGLASS OVERLAY, AND WAS MANUFACTURED WITH A SEAM IN THE FINISHED PRODUCT.  THIS ELBO	W IS INSTALLED IN THE AIRCRAFT WITH A RUBBER BOOT INSTALLED OVER EACH END.  THE BOOTS ARE ATTACHED WITH WORM-STYLE CLAMP	S.  THE FORWARD CLAMP HAD PREVIOUSLY BEEN OVERTORQUED CAUSING THE ELBOW TO BUCKLE AND CRACK AT THE TOP OF THE ELBOW AND 	CAUSING THE SEAM TO WORK LOOSE AT THE BOTTOM OF THE ELBOW.  PIECES OF THE ELBOW COULD BREAK LOOSE AND BE SUCKED UP INTO 	THE THROTTLE BODY.		1	H	7	1 	3O			NT	3A13
1998112000120	19981120	00120	EA  	1998	11	20	98ZZZX4125       	1	19981024	G	5310	C2FS3281A	STRUT           			DHAV  	DHC2  	DHC2*       	2800108	EA  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	47241	17050				5116819				P/N C2FS3281A AND P/N C2FS3282A STRUT ASSEMBLIES THAT ATTACH TO P/N C2FS3203A TUBULAR FRAME ASSEMBLY WERE DETERMINED UNA	IRWORTHY DUE TO CORROSION.  BECAUSE OF THE LOCATION OF THESE STRUTS (UNDER THE WINDSCREENS), THEY SHOULD BE INSPECTED WH	ENEVER THE WINDSCREENS ARE REMOVED.				1	H	7	1 	3R				A806
1998112000121	19981120	00121	EA  	1998	11	20	98ZZZX4126       	1	19981024	G	3213	C2FS3282A	STRUT           			DHAV  	DHC2  	DHC2*       	2800108	EA  										MLG	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	47241	17050				5116819				P/N C2FS3281A AND P/N C2FS3282A STRUT ASSEMBLIES THAT ATTACH TO P/N C2FS3203A TUBULAR FRAME ASSEMBLY WERE DETERMINED UNA	IRWORTHY DUE TO CORROSION.  BECAUSE OF THE LOCATION OF THESE STRUTS (UNDER THE WINDSCREENS), THEY SHOULD BE INSPECTED WH	ENEVER THE WINDSCREENS ARE REMOVED.				1	H	7	1 	3R				A806
1998112000122	19981120	00122		1998	11	20	98ZZZX4127       	4	19981015	G	3460	7022360901	CDU             	HONEYWELL   	CD815       	RAYTHN	DH125 	HAWKER800XP 		CE  										COCKPIT	FAILED          	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	2G	27   			98030136	258354				FMS CONTROLLED/DISPLAY UNIT TOTALLY DEAD.  TEARDOWN SHOWED BAD POWER SUPPLY, PER HONEYWELL REP.  SIMULTANEOUS FAILURE WI	TH OTHER SIDE.  AIRCRAFT TT:  26.8 HOURS.					2	L	7	2 	4F			RT	A3EU
1998112000123	19981120	00123		1998	11	20	98ZZZX4128       	4	19981018	G	3460	7022360901	CDU             	HONEYWELL   	CD815       	RAYTHN	DH125 	HAWKER800XP 		CE  										COCKPIT	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	26	27   			98030130	258354				FMS WILL NOT ACCEPT ANY KEYPAD ENTRIES.  TEARDOWN SHOWED STUCK KEY.  SUBMITTER STATED KNOWN PROBLEM ACCORDING TO ARNAV, 	THE ACTUAL MANUFACTURER.  SIMULTANEOUS FAILURE WITH OTHER SIDE.  AIRCRAFT TT:  26.8 HOURS.					2	L	7	2 	4F			RT	A3EU
1998112000124	19981120	00124		1998	11	20	98ZZZX4129       	4	19981016	G	3460	7022360901	CDU             	HONEYWELL   	CD815       	RAYTHN	DH125 	HAWKER800XP 		CE  										COCKPIT	FAILED          	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	2G	138  			98050165	258354				FMS CDU FAILED ON POWER-UP.  TOTALLY DEAD.  SUBMITTER STATED THIRD FAILURE OF THIS PART ON THIS AIRPLANE.  AIRCRAFT TT: 	 165.2 HOURS.					2	L	7	2 	4F			RT	A3EU
1998112000125	19981120	00125		1998	11	20	98ZZZX4130       	4	19981016	G	3460	7022360901	CDU             	HONEYWELL   	CD815       	RAYTHN	DH125 	HAWKER800XP 		CE  										COCKPIT	MALFUNCTIONED   	C				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	2G	22   			98070190	258354				CDU TRIPS BREAKER AT POWER-UP.  SUBMITTER STATED FOURTH FAILURE OF THIS AIRCRAFT.  AIRCRAFT TT:  187 HOURS.  SUBMITTER S	TATED SUPPOSED TO BE FIXED BY 'MOD E', BUT HONEYWELL CANNOT SUPPLY THEM.  THESE ALL ARE 'MOD C'.					2	L	7	2 	4F			RT	A3EU
1998112000126	19981120	00126	CE  	1998	11	20	98ZZZX4131       	1	19981020	G	3230	968200125	DRAG BACE       			BEECH 	58    	58          	1152740	CE  										NLG	FAILED          	E	P			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	8140R					TH505				DRAG BRACE BROKE FORWARD OF PIVOT POINT.  PILOT SELECTED LANDING GEAR DOWN, 3 GREEN INDICATED.  NOSE GEAR DID NOT EXTEND	.  SUBMITTER STATED THE BRACE THAT FAILED WAS TUBULAR					1	L	7	2 	3O				3A16
1998112000127	19981120	00127		1998	11	20	98ZZZX4132       	4	19980930	G	3197		WIRE            			BEECH 	200   	B200        	1152922	CE  										MFD	CHAFED          	B	L		VIB4	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	151CF					BB1551				CUSTOMER SAID MFD WAS STAYING A BLUE COLOR IN-FLIGHT.  REMOVED RADIO PANEL, FOUND CHAFED WIRES (4 TWISTED PAIRS) 50FD054	, 50FD055, 50FD062, 50FD063, 50FD066, 50FD067, 50FD120, AND 50FD124.  52AA052 AND 52AC018,  ALSO, FOUND 2 BARE WIRES GOI	NG TO THE FCP-65 A/P PANEL  REMOVED PINS FROM MFD PLUG AND RAN OUT THE WIRING TO THE MPU RACK CONNECTOR TO VERIFY WIRE P	RINTS.  CUT AND CAPPED DEFECTIVE WIRING.  RAN OUT WIRING FROM MPU CONNECTOR TO MFD CONNECTOR.  RE-INSTALLED THE MPU AND 	RACK.  RE-INSTALLED RADIO PANEL AND MFD.  TIED UP AND SECURED RADIO PANEL WIRE HARNESSES.  RAMP TESTED MFD, AUTOPILOT, A	ND RADIO PANEL ASSOCIATED SYSTEMS IAW MFG SPECS.	1	L	7	2 	4T			 	A24CE
1998112000128	19981120	00128	NE  	1998	11	20	98ZZZX4133       	3	19981014	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		9181 	4529 		2205NR			HJ292		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  THREE CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998112000129	19981120	00129	NE  	1998	11	20	98ZZZX4134       	3	19981014	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03			4640 		1809NR			HJ125A		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TWO CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998112000130	19981120	00130	WP  	1998	11	20	98ZZZX4135       	2	19981007	G	7261	30737541	RETAINER        		30770743    	LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					OIL PUMP	FAILED          	B	P		IY2R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	15	431AS	2640 			7P16172	431	P89193			DURING ENGINE DISASSEMBLY, DISCOVERED ONE TANG OF RING, RETAINING HAD SEPARATED FROM RING.  SEPARATED PIECE WAS FOUND LO	DGED IN THE FAN GEARBOX ELEMENT OF OIL PUMP.  RING RETAINING P/N 3073754-1 WAS INSTALLED 2,639.7 HOURS PREVIOUSLY DURING	 INCORPORATION OF SB 72-3498.  FRACTURE OCCURRRED IN FILLET RADIUS.  SUBMITTER STATED CAUSE IS UNKNOWN.  THIS REPAIR STA	TION HAS IMPLEMENTED FLUORESCENT PENETRANT INSPECTION (PFI) OF THE PART ANY TIME ACCESS IS GAINED TO THIS AREA.			2	L	7	2 	4F	4	F		A10CE   	E6WE
1998112000581	19981120	00581	NM  	1998	11	20	98ZZZX4136       	1	19981022	G	5311		FRAME           			BOEING	727   	727231      	1384079	NM  										BS 219	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION WAS NOTED FRAME STA 219, STR 26R.						2	L	7	3 	4F				A3WE
1998112000582	19981120	00582	NM  	1998	11	20	98ZZZX4137       	1	19981022	G	5315		FLOORBEAM       			BOEING	727   	727231      	1384079	NM  										BS 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION WAS NOTED AFT PIT FLOORBEAM 1130 APPROXIMATELY LBL 15, UPPER CHORD LOWER SURFACE.						2	L	7	3 	4F				A3WE
1998112000583	19981120	00583	NM  	1998	11	20	98ZZZX4138       	1	19981022	G	5313		STRINGER        			BOEING	727   	727231      	1384079	NM  										BS 990	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION WAS NOTED ON STR 26R AT FORWARD END FS 990.						2	L	7	3 	4F				A3WE
1998112000584	19981120	00584	NM  	1998	11	20	98ZZZX4139       	1	19981022	G	5320		BRACKET         			BOEING	727   	727231      	1384079	NM  										BS 1030-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION WAS NOTED IN AFT PIT, RT SIDEWALL SMALL ATTACH BRACKETS FS 1030-1050-1070.						2	L	7	3 	4F				A3WE
1998112000585	19981120	00585	NM  	1998	11	20	98ZZZX4140       	1	19981020	G	5320		CLIP            			BOEING	727   	727231      	1384079	NM  										BS 1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION WAS NOTED ON CLIP ATTACHED TO INTERCOSTAL AND FRAME FS 1070 - STR 20R.						2	L	7	3 	4F				A3WE
1998112000586	19981120	00586	NM  	1998	11	20	98ZZZX4141       	1	19981022	G	5320		ANGLE           			BOEING	727   	727231      	1384079	NM  										BS 720	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING C-CHECK, CORROSION WAS NOTED ON AFT FRAME FOR FORWARD ADF LOOP ANTENNA FS 720 AT BL ZERO (APPROXIMATELY).						2	L	7	3 	4F				A3WE
1998112000587	19981120	00587	NM  	1998	11	20	98ZZZX4142       	1	19981022	G	5311		FRAME           			BOEING	727   	727231      	1384079	NM  										BS 770	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING C-CHECK, CORROSION NOTED ON FRAME FORWARD OF BELLY BLOW-OUT DOORS FS 770, APPROXIMATE BL ZERO.						2	L	7	3 	4F				A3WE
1998112000588	19981120	00588	SO  	1998	11	20	98ZZZX4143       	1	19981023	G	5410	12023733001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT/RT NACELLE	CHAFED          	B	P		WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	235AS					120047				ON THE LEFT AND RIGHT ENGINE NACELLE'S, THE LEFT HAND, FORWARD HALF FRAME SHOWS SIGNS OF CHAFING.  THIS CHAFING OCCURRED	 WHERE THE COWLING DOOR MADE CONTACT WITH THE FRAME.  THERE IS NO ANY PROTECTION WHICH PREVENTS THE TWO SURFACES FROM RU	BBING TOGETHER.  THE FRAME IS CHAFED IN SEVEN AREAS WITH THE LARGEST AREA BEING 1.6 FEET IN LENGTH, BY 0.1 INCH WIDE, AN	D .030 INCH DEEP.  TO PREVENT THIS FROM HAPPENING AGAIN, LAYER OF B-HALF PLACED ON THE FRAME SHOULD PROVIDE ENOUGH CUSHI	ON BETWEEN THE DOOR AND THE FRAME TO PROTECT THE TWO SURFACES DURING NORMAL OPERATION.		2	L	7	2 	4T			RT	A31SO
1998112000589	19981120	00589	NM  	1998	11	20	98ZZZX4144       	1	19980929	G	5320		SUPPORT         			BOEING	737   	737242      	1384477	NM  										BS 270-294	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION WAS NOTED ON FLOOR SUPPORT FS 270 - FS 294, LBL 12 APPROXIMATELY.						2	L	7	2 	4F				A16WE
1998112000590	19981120	00590	NM  	1998	11	20	98ZZZX4145       	1	19980929	G	5320		WEB             			BOEING	737   	737242      	1384477	NM  										BS 1016	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION NOTED ON AFT SHEAR WEB AFT OF 1016 FLOORBEAM (ENTIRE LENGTH).						2	L	7	2 	4F				A16WE
1998112000591	19981120	00591	NM  	1998	11	20	98ZZZX4146       	1	19980929	G	5313		STRINGER        			BOEING	737   	737242      	1384477	NM  										BS 947-967	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION WAS NOTED ON AFT PIT BILGE AREA STR 27L, FS 947 - FS 967.						2	L	7	2 	4F				A16WE
1998112000592	19981120	00592	NM  	1998	11	20	98ZZZX4147       	1	19981105	G	5320		CHANNEL         			BOEING	737   	737242      	1384477	NM  										BS 294-315	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION NOTED ON FORWARD LAVATORY AFT WALL SUPPORT FS 294 - FS 312 - LBL 37, APPROXIMATE.						2	L	7	2 	4F				A16WE
1998112000593	19981120	00593	NM  	1998	11	20	98ZZZX4148       	1	19980929	G	5315		FLOORBEAM       			BOEING	737   	737242      	1384477	NM  										BS 294	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION NOTED ON UPPER T-CHORD OF FLOORBEAM 294.5, RBL 25 TO LBL 30.						2	L	7	2 	4F				A16WE
1998112000594	19981120	00594	NM  	1998	11	20	98ZZZX4149       	1	19981026	G	5320		BRACKET         			BOEING	727   	727231      	1384079	NM  										BS 700	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON BRACKET FOR PANEL NR 3346, STA 720C.						2	L	7	3 	4F				A3WE
1998112000595	19981120	00595	NM  	1998	11	20	98ZZZX4150       	1	19981026	G	5240		HINGE           			BOEING	727   	727231      	1384079	NM  										SERVICE DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON EXTERIOR AIRCRAFT GROUND ACCESS DOOR HINGES.						2	L	7	3 	4F				A3WE
1998112000596	19981120	00596	NM  	1998	11	20	98ZZZX4151       	1	19981026	G	5240		SKIN            			BOEING	727   	727231      	1384079	NM  										SERVICE DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON EXTERIOR FUSELAGE AFT LAVATORY SERVICE DOOR, INTERIOR SURFACE.						2	L	7	3 	4F				A3WE
1998112000597	19981120	00597	NM  	1998	11	20	98ZZZX4152       	1	19981026	G	5240		HINGE           			BOEING	727   	727231      	1384079	NM  										SERVICE DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION WAS NOTED ON AFT LAVATORY SERVICE DOOR HINGE PAIRS (UPPER AND LOWER).						2	L	7	3 	4F				A3WE
1998112000598	19981120	00598	NM  	1998	11	20	98ZZZX4153       	1	19981028	G	5311		FRAME           			BOEING	727   	727231      	1384079	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON UPPER LOBE FRAME 1166 AT STR 17R.						2	L	7	3 	4F				A3WE
1998112000599	19981120	00599	NM  	1998	11	20	98ZZZX4154       	1	19981028	G	5347	BAC1520792	SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 1070-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON CABIN FLOOR STRUCTURE, SEAT TRACK FS 1070 - FS 1130 LBL 55 (APPROXIMATE).						2	L	7	3 	4F				A3WE
1998112000600	19981120	00600	NM  	1998	11	20	98ZZZX4155       	1	19981028	G	5320		SUPPORT         			BOEING	727   	727231      	1384079	NM  										BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION WAS NOTED ON FLOORBEAM FS 420, RBL 12 - RBL 24.						2	L	7	3 	4F				A3WE
1998112000601	19981120	00601	NM  	1998	11	20	98ZZZX4156       	1	19981028	G	5315		FLOORBEAM       			BOEING	727   	727231      	1384079	NM  										BS 1130-1148	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION WAS NOTED ON FLOORBOARD SUPPORT STA 1130 - STA 1148 - LBL 12.						2	L	7	3 	4F				A3WE
1998112000602	19981120	00602	NM  	1998	11	20	98ZZZX4157       	1	19981028	G	5320		SUPPORT         			BOEING	727   	727231      	1384079	NM  										BS 1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON FLOOR SUPPORT FS 1070, LBL 45 - LBL 60.						2	L	7	3 	4F				A3WE
1998112000603	19981120	00603	NM  	1998	11	20	98ZZZX4158       	1	19981028	G	5320		SUPPORT         			BOEING	727   	727231      	1384079	NM  										BS 1110-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING C-CHECK, CORROSION NOTED ON FLOOR SUPPORT FS 1110 - FS 1130, LBL 12.						2	L	7	3 	4F				A3WE
1998112000604	19981120	00604	NM  	1998	11	20	98ZZZX4159       	1	19981028	G	5320		SILL            			BOEING	727   	727227      	1384078	NM  										BS 460	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING C-CHECK, CORROSION NOTED AT FLOOR LEVEL MAIN CABIN MOP SILL STA 460 RT.						2	L	7	3 	4F				A3WE
1998112000605	19981120	00605	NM  	1998	11	20	98ZZZX4160       	1	19981028	G	5330		SKIN            			BOEING	727   	727227      	1384078	NM  										BS 680	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING C-CHECK, CORROSION NOTED IN FORWARD PIT BILGE STA 680 STR 28R ON SKIN.						2	L	7	3 	4F				A3WE
1998112000606	19981120	00606	NM  	1998	11	20	98ZZZX4161       	1	19981028	G	5320		SPLICE          			BOEING	727   	727227      	1384078	NM  										BS 680	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING C-CHECK, CORROSION NOTED AT STA 680 ON STR 27R SPLICE FITTING.						2	L	7	3 	4F				A3WE
1998112000607	19981120	00607	NM  	1998	11	20	98ZZZX4162       	1	19981028	G	5320		SUPPORT         			BOEING	727   	727227      	1384078	NM  										BS 520	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING C-CHECK, CORROSION NOTED ON FORWARD BAY PIT FLOOR SUPPORT STA 520, LBL 5.						2	L	7	3 	4F				A3WE
1998112000608	19981120	00608	WP  	1998	11	20	98ZZZX4163       	1	19981021	G	5320	577263833	BEAM            			DOUG  	DC8   	DC861       	3021952	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	841AX	58700				45908				AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED ON THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE AIRCRAFT CENTERLINE.  THE CRACKS A	PPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINS	T THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED	 TO THE J-BEAM.  SUBMITTER RECOMMENDS THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 ACFT WITH FLAT AFT PRESSU	RE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F				4A25
1998112000609	19981120	00609	WP  	1998	11	20	98ZZZX4164       	1	19981021	G	5320	575352215	BEAM            			DOUG  	DC8   	DC861       	3021952	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	841AX	58700				45908				AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE ACFT CENTERLINE.  OPERATING CONDIT	IONS ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED 	THROUGH PULLEYS ATTACHED TO THE J-BEAM.  SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 	ACFT WITH FLAT AFT PRESSURE BULKHEADS, AND,  REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.		2	L	7	4 	4F				4A25
1998112000610	19981120	00610	WP  	1998	11	20	98ZZZX4165       	1	19981021	G	5320	577263835	BEAM            			DOUG  	DC8   	DC863       	302198A	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	964R	62567				46000				AT D-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE AIRCRAFT CENTERLINE.  THE CRACKS A	PPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINS	T THE FRONT FACE OF THE BULKHEAD AND THE TENSION OF THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACH	ED TO THE J-BEAM.  SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS ON DC-8 ACFT WITH FLAT AFT PRESSUR	E BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5, FIG 26.	2	L	7	4 	4F				4A25
1998112000611	19981120	00611	WP  	1998	11	20	98ZZZX4166       	1	19981021	G	5320	577263833	BEAM            			DOUG  	DC8   	DC863       	302198A	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	964R	62567				46000				AT D-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROX 1 INCH EACH SIDE OF THE ACFT CENTERLINE.  THE CRACKS APPEAR TO OC	CUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST THE FRONT	 FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO THE J-B	EAM.  SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 ACFT WITH FLAT AFT PRESSURE BULKHEA	DS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5, FIG 26.	2	L	7	4 	4F				4A25
1998112000612	19981120	00612		1998	11	20	98ZZZX4167       	4	19980928	G	3451	DMN15021	ANTENNA         			BOEING	727   	727224      	1384076	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69736					20665				DURING C-CHECK, CORROSION WAS NOTED, AFT DME ANTENNA.						2	L	7	3 	4F				A3WE
1998112000613	19981120	00613	NM  	1998	11	20	98ZZZX4168       	1	19980928	G	5320		ANGLE           			BOEING	727   	727224      	1384076	NM  										BS 720	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69736					20665				DURING C-CHECK, CORROSION WAS NOTED ON FRAME STRUCTURE AROUND ADF LOOP ANTENNA BL ZERO - FS 720 APPROXIMATE.						2	L	7	3 	4F				A3WE
1998112000614	19981120	00614		1998	11	20	98ZZZX4169       	4	19980928	G	3455	5221827000	ANTENNA         			BOEING	727   	727224      	1384076	NM  										ADF	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69736				9528	20665				DURING C-CHECK, CORROSION NOTED ON FORWARD ADF LOOP ANTENNA.						2	L	7	3 	4F				A3WE
1998112000615	19981120	00615	WP  	1998	11	20	98ZZZX4170       	1	19981021	G	5320	577263835	BEAM            			DOUG  	DC8   	DC871F      	302199D	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	798UP	63378				45898				AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE ACFT CENTERLINE.  THE CRACKS APPEA	R TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST TH	E FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO 	THE J-BEAM.  SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 ACFT WITH FLAT AFT PRESSURE 	BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F			RT	4A25
1998112000616	19981120	00616	WP  	1998	11	20	98ZZZX4171       	1	19981021	G	5320	577263835	BEAM            			DOUG  	DC8   	DC861       	3021952	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	841AX	58700				45908				THE C-CHECK, CrACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS	 ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE ACFT CENTERLINE.  THE CRACKS APPE	AR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLE CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINST T	HE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED TO	 THE J-BEAM.  SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTION  OF ALL DC-8 ACFT WITH FLAT AFT PRESSURE	 BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F				4A25
1998112000617	19981120	00617	WP  	1998	11	20	98ZZZX4172       	1	19981021	G	5320	577263835	BEAM            			DOUG  	DC8   	DC871       	302199A	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8084U	70648				45974				AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY 1 INCH EACH SIDE OF THE AIRCRAFT CENTERLINE.  THE CRACKS A	PPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CABIN PRESSURE AGAINS	T THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUGH PULLEYS ATTACHED	 TO THE J-BEAM.  SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 ACFT WITH FLAT AFT PRESS	URE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F				4A25
1998112000618	19981120	00618	SO  	1998	11	20	98ZZZX4173       	1	19981102	G	7120	MS210426	NUT             			EMB   	120   	EMB120RT    		SO  										LT ENGINE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	130AM					120134				TWO OF THE THREE ATTACHMENT BOLTS FOR THE OUTBOARD TORQUE MOUNT P/N LM-430-SA7 NUTS WERE FOUND CRACKED DURING C-CHECK IN	SPECTION.  SUBMITTER STATED POSSIBLY OVERTORQUED, EXCESSIVE FORCE WAS REQUIRED TO REMOVE THE REMAINING NUT AND RECOMMEND	ED INSPECTION AT EVERY C-CHECK INSPECTION.				2	L	7	2 	4T			RT	A31SO
1998112000619	19981120	00619	SO  	1998	11	20	98ZZZX4174       	1	19981103	G	5320	12015374001	ANGLE           			EMB   	120   	EMB120RT    		SO  										BS 16128	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	130AM					120134				AFT FUSELAGE-TO-FIN CONNECTING ANGLE AT THE BASE OF THE VERTICAL STABILIZER AT FS 16128.0, A CRACK WAS DISCOVERED TRAVEL	ING BETWEEN TWO FASTENERS.  SUBMITTER STATED POSSIBLY CAUSE AS FATIGUE AND RECOMMENDED A DETAILED VISUAL INSPECTION BE C	ALLED OUT DURING C-CHECK INSPECTION.				2	L	7	2 	4T			RT	A31SO
1998112000620	19981120	00620	SO  	1998	11	20	98ZZZX4175       	1	19981029	G	5320	12015374002	ANGLE           			EMB   	120   	EMB120RT    		SO  										BS 16128	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	281AS					120224				AFT FUSELAGE-TO-FIN CONNECTING ANGLE AT THE BASE OF THE VERTICAL STABILIZER AT FS 16128.0, TWO CRACKS .25 INCH LONG TRAV	ELING FORWARD FROM TWO FASTENERS.  THIS PROBLEM WAS DISCOVERED DURING B-CHECK INSPECTION.  RECOMMEND A DETAILED VISUAL I	NSPECTION BE CALLED OUT DURING C-CHECK INSPECTION.				2	L	7	2 	4T			RT	A31SO
1998112000621	19981120	00621	NM  	1998	11	20	98ZZZX4176       	1	19980827	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908-951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	60SW	61002				21812				FOUR FASTENER HOLES CRACKED IN THE FUSELAGE SKIN, STA 908 - STA 951, S10R.  THREE FASTENER HOLES CRACKED IN THE FUSELAGE	 SKIN, STA 908 - STA 951, S10L.  REPAIRED PER DALFORT AEROSPACE XEA X2-53-219, REV 2 DATED 8-25-98 AND BOEING SRM 53-30-	3, FIG 42.  APPROVAL DATA:  FAA FORM 8110-3 DATED 8-24-98.				2	L	7	2 	4F				A16WE
1998112000622	19981120	00622	NM  	1998	11	20	98ZZZX4177       	1	19980827	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908-951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	60SW	61002				21812				SKIN CRACKED AT AFT ENTRANCE DOOR, LOWER HINGE CUTOUT, AT STR 14L BETWEEN STA 908 - STA 951.  SKIN CRACKED AT AFT SERVIC	E DOOR, LOWER HINGE CUTOUT, AT STR 14R BETWEEN STA 908 - STA 951.  REPAIRED PER DALFORT AEROSPACE XEA X2-53-218 DATED 8-	6-98 AND SB 737-53-1074, REV 3.  APPROVAL DATA:  FAA FORM 8110-3 DATED 8-18-98.				2	L	7	2 	4F				A16WE
1998112000623	19981120	00623	NM  	1998	11	20	98ZZZX4178       	1	19980923	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908-951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	61SW	61168				21970				SKIN CRACKED AT HINGE CUTOUTS ALONG STR 10L AND STR 10R, STA 908 - STA 951.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2	-53-220 DATED 9-8-98, AND BOEING 737 SRM 53-30-3, FIG 42.  APPROVAL DATA:  FAA FORM 8110-3 DATED 9-22-98.					2	L	7	2 	4F				A16WE
1998112000624	19981120	00624	NM  	1998	11	20	98ZZZX4179       	1	19980922	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908-951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	61SW	61169				21970				SIXTEEN CRACKED FASTENER HOLES FOUND ALONG STR 14L AT STA 908 - 951.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-221	 DATED 9-8-98, AND BOEING 737 SRM 53-30-3, FIG 42.  APPROVED DATA:  FAA FORM 8110-3 DATED 9-8-98.					2	L	7	2 	4F				A16WE
1998112000625	19981120	00625	NM  	1998	11	20	98ZZZX4180       	1	19980923	G	5330		SKIN            			BOEING	737   	7372H4      	138448C	NM  										BS 908-951	CRACKED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	61SW	61168				21970				TEN CRACKED FASTENER HOLES FOUND ALONG STR 14R AT STA 908 - STA 951.  REPAIRED PER DALFORT AEROSPACE, L.P. XEA X2-53-222	 DATED 9-8-98, AND BOEING 737 SRM 53-30-3, FIG 42.  APPROVAL DATA:  FAA FORM 8110-3 DATED 9-18-98.					2	L	7	2 	4F				A16WE
1998112000626	19981120	00626	EA  	1998	11	20	98ZZZX4181       	1	19981006	G	2160	9795588	VALVE           			CNDAIR	CL600 	CL6002B16   	1900305	EA  										A/C BAY	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	270RA	564  			1065	5337				CABIN TEMPERATURE CONTROL DID NOT WORK ON THE GROUND.  WORKED NORMALLY IN-FLIGHT.  FOUND TEMPERATURE MODULATING AND SHUT	-OFF VALVE CRACKED AT INLET FITTING.  LEAKING.  THIS VALVE WAS INSTALLED AT THE FACTORY.  SUBMITTED SUSPECTED TORQUE NOT	 USED OR RECOMMENDED TORQUE TOO HIGH FOR PART STRENGTH.				2	L	7	2 	4F			RT	A21EA
1998112000627	19981120	00627	SO  	1998	11	20	98ZZZX4182       	1	19981005	G	5320	12044540001	SUPPORT         			EMB   	120   	EMB120RT    		SO  										WINDSCREEN	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	245AS					120075				DURING C-CHECK INSPECTION, WINDSHIELD CENTER POST ATTACH SUPPORT FITTINGS ARE INSPECTED IAW ASA EO-120-53-0021.  THE UPP	ER SUPPORT FITTING WAS FOUND CRACKED ON THE LEFT SUPPORT LEG FROM THE BOLT ATTACHMENT HOLE AFT THROUGH THE LEG.  THIS IS	 A DIFFICULT AREA TO COMPLETE A VISUAL AND/OR DYE PENETRANT INSPECTION.  SUBMITTER RECOMMENDED AN EDDY CURRENT INSPECTIO	N BE COMPLETED ON THE WINDSHIELD CENTER POST FITTINGS.			2	L	7	2 	4T			RT	A31SO
1998112000991	19981120	00991	NM  	1998	11	20	98ZZZX4183       	1	19981021	G	5520	2400093	HORN            			PIPER 	PA60  	PA60601P    	7106012	NM  										ELEVATOR	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	141CA	2993 				601P07117963				ELEVATOR HORN CRACKED ON PLATE .1250 INCH FROM COLLAR RADIATING FROM TRIM CABLE HOLE AROUND COLLAR.  TOTAL CRACK LENGTH 	IS ONE INCH.					1	M	7	2 	3O			RT	A17WE
1998112000992	19981120	00992	EU  	1998	11	20	98ZZZX4184       	1	19980807	G	2910	MY20751736	LINE            			AMD   	FALC20	FALCON20F5  	2730105	EU  										HYDRAULIC SYSTEM	CRACKED         	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	8926B	7084 				379				DURING MAINTENANCE, FOUND DRIP OF HYDRAULIC FLUID ON BEND IN LINE, WHICH WOULD REFORM WHEN WIPED AWAY.  CRACK WAS NOT RE	ADILY VISIBLE UNTIL LINE WAS DISCONNECTED AT AFT END IN ORDER TO SPREAD THE LINE A BIT AT THE BEND RADIUS.  SUBMITTER ST	ATED REPLACED THIS SAME LINE ON ANOTHER FALCON 6-26-96, CRACKED IN SAME LOCATION.				2	L	7	2 	4F			RT	A7EU
1998112000993	19981120	00993	NM  	1998	11	20	98ZZZX4185       	1	19981013	G	3350	D73402001	BATTERY PACK    			AMD   	FALC50	FALCON2000  	2730170	NM  										CABIN	DISDCHARGED     	B			J2BR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15	70KS				121	14				WHILE REPLACING AN EMERGENCY LIGHT BATTERY PACK, AN EXCHANGE UNIT WAS PURCHASED FROM FALCON JET (TEB).  THE EXCHANGE UNI	T WAS DISCHARGED WHEN RECEIVED, ALL OTHERS IN STOCK WERE ALSO FOUND DISCHARGED.  THE ORIGINAL WAS STILL SERVICEABLE AND 	RE-INSTALLED IN THE AIRCRAFT.				2	K	7	3 	4F			RT	A50NM
1998112000994	19981120	00994	CE  	1998	11	20	98ZZZX4186       	1	19981008	G	2730	505244323	BRACKET         			BEECH 	90    	C90         	1152913	CE  										ELEVATOR	CRACKED         	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	973GA					LJ675				WHILE PERFORMING PRE-BUY INSPECTION, ELEVATOR PULLEY BRACKET WAS INSPECTED PER MSB 2150, R1.  BRACKET FOUND CRACKED.  SB	 2150-R1 STATES IF ANY CRACKS ARE FOUND KIT 90-4098-1S, WHICH IS AN IMPROVED HEAVIER BRACKET, IS TO BE INSTALLED.					1	L	7	2 	3T				3A20
1998112000995	19981120	00995	NM  	1998	11	20	98ZZZX4187       	1	19980807	G	3810	7700237501	WATER TANK      			AMD   	FALC50	FALCON2000  	2730170	NM  										POTABLE WATER	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	03	435T	751  			162REVH	09				TANK SPLITS OPEN AND LEAKS WATER INTO BELLY OF AIRCRAFT.  FAILURES OCCUR ON END CAPS AND APPEAR TO BE DUE TO OBVIOUS MAN	UFACTURING DEFECTS.  THIS IS THE THIRD FAILURE OPERATOR HAS EXPERIENCED.					2	K	7	3 	4F			RT	A50NM
1998112000996	19981120	00996	WP  	1998	11	20	98ZZZX4188       	1	19980923	G	2433		TRANSFORMER     			DOUG  	DC10  	DC1030F     	3023504	WP  										E/E BAY	FAILED          	G			M8BB	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			WP	33	10MB	88445			743	47907				DURING MAINTENANCE, AIRCRAFT POWER WAS SELECTED TO GROUND SERVICE OPERATION.  LATER, DISCOVERED SMOKE IN COCKPIT AND SME	LL OF ELECTRICAL BURNING.  UPON TROUBLESHOOTING, FOUND SMELL OF ELECTRICAL BURNING COMING FROM E/E COMPARTMENT LEADING T	O ONE OF THE TRANSFORMER RECTIFIER (TR2B).  DURING ENTIRE TROUBLESHOOTING PROCEDURE TO LOCATE THE SMOKE, NOTICED THERE W	AS NO ABNORMAL INDICATION IN THE COCKPIT INSTRUMENT.  SUBSEQUENTLY, THE UNIT WAS REPLACED AND FOUND TO HAVE INTERNAL DAM	AGE.  SUBMITTER STATED CAUSE OF SMOKE WAS POSSIBLY DUE TO A HIGH TIME UNIT THAT HAD BEEN INSTALLED ON THE AIRCRAFT SINCE	 1974.	2	L	7	3 	4F			RT	A22WE
1998112000997	19981120	00997	WP  	1998	11	20	98ZZZX4189       	2	19980909	G	7250	30727121	BLADE           			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					TURBINE	FAILED          	B			IY2R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			SW	15	28MJ	3513 				224	74651			DURING CRUISE, NR 2 ENGINE EXPERIENCED A RAPID RISE IN INTERSTAGE TURBINE TEMPERATURE (ITT) AND VIBRATION LEVEL.  THRUST	 WAS REDUCED TO IDLE.  A SAFE LANDING WAS MADE AT NEW ORLEANS INTERNATIONAL AIRPORT (MSY).  ENGINE WAS REMOVED FROM AIRC	RAFT FOR INVESTIGATION AND REPAIR.  DISASSEMBLY REVEALED STRESS RUPTURE TO ONE HIGH PRESSURE TURBINE BLADE, P/N 3072712-	1.  SECONDARY DOMESTIC OBJECT DAMAGE WAS CONTAINED.			2	L	7	2 	4F	4	F		A10CE   	E6WE
1998112000998	19981120	00998	CE  	1998	11	20	98ZZZX4190       	1	19980930	G	3222	2342100	BOLT            		AN2430      	LEAR  	35    	35A         	5170602	CE  										NLG	MISINSTALLED    	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	38AM	9213 				174				NOSE GEAR DOOR MECHANISM ROD ATTACH POINT BOLT P/N AN 24-30 TO NOSE STRUT INCORRECTLY INSTALLED ACCORDING TO LEARJET 35A	 IPC CH 32-23-05, FIG 05, ITEM -21, PG 0, AND IS CAUSING GOUGING TO THE SKIN AT FRAME 5, FS 160.77.  GOUGING OCCURS WHEN	 THE BOLT HEAD IS BEING INSTALLED IN THE INBD POSITION AND THREADED PORTION OF THE BOLT IS GOUGING THE FRAME SKIN.  SUBM	ITTER STATED THERE IS NO WRITTEN NOTE/CAUTION IN LEARJET MM TO CORRECT INSTALLATION OF BOLT AND RECOMMENDED THERE BE WRI	TTEN INSTRUCTIONS AND CAUTIONS ON CORRECT INSTALLATION OF BOLT.  THIS IS 7TH ACFT RECORDED WITH THIS TYPE DAMAGE.		2	L	7	2 	4F				A10CE
1998112000999	19981120	00999	EU  	1998	11	20	98ZZZX4191       	1	19981007	G	3260		SWITCH          	MESSIER     	A23709007   	AMD   	FALC20	FALCONE     	2720305	EU  										MLG	INOPERATIVE     	B			XB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	600WD				B101	300				WORN INTERNAL ACTUATING MECHANISM CAUSED SQUAT SWITCH NOT TO OPERATE PROPERLY RESULTING IN NO GEAR UP.  ACFT TT:  7,203 	HOURS.  LANDINGS:  6,165.					2	L	7	2 	4F				A7EU
1998112001000	19981120	01000	SW  	1998	11	20	98ZZZX4192       	1	19980910	G	2150	9770181	ACM             			GULSTM	690TP 	690A        	0141722	SW  										AC BAY	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	112EF				0344	11123				AIR CYCLE MACHINE (ACM) WOULD NOT COOL AIRCRAFT.  REPLACED WITH EXCHANGE UNIT DUE TO BEARING FAILURE.						1	H	7	2 	3T				2A4
1998112001002	19981120	01002	EA  	1998	11	20	98ZZZX4194       	2	19981022	G	7321	32447551614	FUEL CONTROL    			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT ENGINE	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	210SU		9    		A45119	BB420	PCE80207			FUEL CONTROL UNIT WOULD NOT LET THE ENGINE GO BELOW 1,400 POUNDS OF TORQUE ON DESCENT FROM ALTITUDE.  ENGINE WAS SHUT DO	WN.  PROPELLER SECURED TO ALLOW FOR A SAFE LANDING.  SUBMITTER STATED CAUSE OF MALFUNCTION UNKNOWN.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998112001003	19981120	01003	EA  	1998	11	20	98ZZZX4195       	1	19981023	G	3233	600102373	ACTUATOR        			CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT/LT MLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9700X	1849 				5186				FOUND MINOR CORROSION ON LEFT AND RIGHT MLG SIDE STAY ACTUATOR UPPER SHAFT (ACTUATOR ATTACH POINT).  REMOVED AND REPLACE	D LEFT AND RIGHT SHAFTS.					2	L	7	2 	4F			RT	A21EA
1998112001004	19981120	01004	EA  	1998	11	20	98ZZZX4196       	1	19981023	G	3233	90251	EYE BOLT        	ROTOL       	600800185   	CNDAIR	CL600 	CL6002B16   	1900305	EA  										LT MLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9700X	1850 			DCL36795	5186				LEFT MLG SIDE STAY ACTUATOR EYE-BOLT BEARING SOCKET CORRODED BEYOND LIMITS PER CMM.  SUBMITTER STATED TO MAKE SURE GREAS	E FITTINGS ARE NOT CLOGGED AND ARE ABLE TO PASS GREASE.					2	L	7	2 	4F			RT	A21EA
1998112001005	19981120	01005	EA  	1998	11	20	98ZZZX4197       	1	19981023	G	3233	90251	BOLT            	ROTOL       	6008500185  	CNDAIR	CL600 	CL6002B16   	1900305	EA  										LT/RT MLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9700X	1850 				5186				RIGHT MLG SIDE STAY ACTUATOR UPPER AND LOWER EYE BOLT SPHERICAL BEARING SOCKETS FOUND CORRODED DURING SCHEDULED INSPECTI	ON.  SUBMITTER STATED BE SURE THE GREASE FITTINGS ARE NOT CLOGGED.					2	L	7	2 	4F			RT	A21EA
1998112001006	19981120	01006	EA  	1998	11	20	98ZZZX4198       	1	19981023	G	3213	64331	AXLE            	ROTOL       	601850827   	CNDAIR	CL600 	CL6002B16   	1900305	EA  										LT MLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9700X	1850 			DCL25795	5186				LEFT MAIN LANDING GEAR WHEEL AXLE FOUND PITTING (CORROSION) ON FORWARD RADIUS WHERE BEARING RIDES.  FOUND DURING SCHEDUL	ED INSPECTION.					2	L	7	2 	4F			RT	A21EA
1998112001007	19981120	01007	EA  	1998	11	20	98ZZZX4199       	1	19981023	G	3213	64331	AXLE            	ROTOL       	601850827   	CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT MLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9700X	1850 			DCL25395	5186				RIGHT MLG AXLE SHOWS SIGNS OF CORROSION ON THE OTBD SECTION OF THE INNER BEARING RACE.  FOUND DURING SCHEDULED INSPECTIO	N.					2	L	7	2 	4F			RT	A21EA
1998112001008	19981120	01008	EA  	1998	11	20	98ZZZX4200       	1	19981023	G	3222	200811218	AXLE            	ROTOL       		CNDAIR	CL600 	CL6002B16   	1900305	EA  										NLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9700X	1850 			DCL392	5186				DURING SCHEDULED INSPECTION, FOUND CORROSION IN THE NLG AXLE INNER BORE BEYOND ALLOWABLE LIMITS PER CMM.  REPLACED NLG A	XLE FITTING ASSY.					2	L	7	2 	4F			RT	A21EA
1998112001009	19981120	01009	SO  	1998	11	20	98ZZZX4201       	1	19981022	G	5220	1159CE201001	HANDLE          			GULSTM	G1159 	G1159       	3953505	SO  										LT EMERG EXIT	LOOSE           	B			J2BR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	711RL					25				WHILE PERFORMING MAINTENANCE ON AIRCRAFT, FOUND LEFT FORWARD AND AFT EMERGENCY EXIT WINDOW EXTERNAL RELEASE HANDLE DISCO	NNECTED FROM LINKAGE (ATTACHING HARDWARE FOUND IN BAG TIED TO HANDLE).					2	L	7	2 	4F			RT	A12EA
1998112001010	19981120	01010	NM  	1998	11	20	98ZZZX4202       	1	19981021	G	5610	D25W343001010	WINDSHIELD      	SIERRACIN   		ISRAEL	1125  	1125        		NM  										COCKPIT	DAMAGED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	23TJ	672  			610	023				ON 102-21, DISCOVERED SEALANT EXTRUDING OUT OF THE WINDSHIELD.  PRESUMABLY UNCURED SEALANT SQUEEZED OUT UNDER PRESSURIZA	TION.  THIS PORTION OF THE WINDSHIELD IS ASSEMBLED BY THE WINDSHIELD MFG AND IS NOT FIELD SERVICEABLE.  WINDSHIELD ASSY 	REPLACED WITH NEW.  CYCLES, 373.				2	L	7	2 	4F			RT	A16NM
1998112001011	19981120	01011	SW  	1998	11	20	98ZZZX4203       	1	19981105	G	6230		DRIVE COLLAR    			BELL  	206   	206A        	1181508	SW  										SWASHPLATE	FAILED          	G		A		O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	07										'BELL HELICOPTER TEXTRON HAS ISSUED OPERATION SAFETY NOTICE OSN 206-98-34 AND 206L-98-40 DATED 11-2-98.'  BELL HELICOPTE	R HAS LEARNED OF A RECENT HARD-FOULING CONDITION IN THE FLIGHT CONTROL SYSTEM OF A 206L HELICOPTER THAT RESULTED IN A BR	OKEN SWASHPLATE DRIVE COLLAR SET.  INVESTIGATION REVEALED A NON-APPROVED METHOD WAS USED TO ADJUST ROTOR AUTOROTATION RP	M DURING RIGGING.  OSN ISSUED TO STRESS IMPORTANCE FOR OPERATORS TO ADHERE TO THE APPROVED RIGGING PROCEDURE PUBLISHED I	N THE MM'S.  OPERATORS OF 206A/B SERIES ARE ALSO ALERTED BECAUSE OF THE SIMILARITY OF FLIGHT CONTROL SYSTEMS.		1	G	7	1 	3U				H2SW
1998112001012	19981120	01012	SW  	1998	11	20	98ZZZX4204       	1	19981105	G	6230		DRIVE COLLAR    			BELL  	206   	206B        	1181511	SW  										SWASHPLATE	FAILED          	G		A		O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	07										'BELL HELICOPTER TEXTRON HAS ISSUED OPERATION SAFETY NOTICE OSN 206-98-34 AND 206L-98-40 DATED 11-2-98.'  BELL HELICOPTE	R HAS LEARNED OF A RECENT HARD-FOULING CONDITION IN THE FLIGHT CONTROL SYSTEM OF A 206L HELICOPTER THAT RESULTED IN A BR	OKEN SWASHPLATE DRIVE COLLAR SET.  INVESTIGATION REVEALED A NON-APPROVED METHOD WAS USED TO ADJUST ROTOR AUTOROTATION RP	M DURING RIGGING.  OSN ISSUED TO STRESS IMPORTANCE FOR OPERATORS TO ADHERE TO THE APPROVED RIGGING PROCEDURE PUBLISHED I	N THE MM'S.  OPERATORS OF 206A/B SERIES ARE ALSO ALERTED BECAUSE OF THE SIMILARITY OF FLIGHT CONTROL SYSTEMS.		1	G	7	1 	3U				H2SW
1998112001013	19981120	01013	SW  	1998	11	20	98ZZZX4205       	1	19981105	G	6230		DRIVE COLLAR    			BELL  	206   	206L        	1181522	SW  										SWASHPLATE	FAILED          	G		A		O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	07										'BELL HELICOPTER TEXTRON HAS ISSUED OPERATION SAFETY NOTICE OSN 206-98-34 AND 206L-98-40 DATED 11-2-98.'  BELL HELICOPTE	R HAS LEARNED OF A RECENT HARD-FOULING CONDITION IN THE FLIGHT CONTROL SYSTEM OF A 206L HELICOPTER THAT RESULTED IN A BR	OKEN SWASHPLATE DRIVE COLLAR SET.  INVESTIGATION  REVEALED A NON-APPROVED METHOD WAS USED TO ADJUST ROTOR AUTOROTATION R	PM DURING RIGGING.  OSN ISSUED TO STRESS IMPORTANCE FOR OPERATORS TO ADHERE TO THE APPROVED RIGGING PROCEDURE PUBLISHED 	IN THE MM'S.  OPERATORS OF 206A/B SERIES ARE ALSO ALERTED BECAUSE OF THE SIMILARITY OF FLIGHT CONTROL SYSTEMS.		1	G	7	1 	3U				H2SW
1998112001014	19981120	01014	NE  	1998	11	20	98ZZZX4206       	2	19981006	G	7320		P3 LINE         			BRAERO	1000  	BAE1251000  	1500287	EU  	PWA   	305   	PW305       		NE  					NR 1 ENGINE	BROKE           	B			R3RR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	530QS	2588 				259030	PCE105061			PILOTS DISCREPANCY WAS NR 1 ENGINE TEMPORARILY LIMITED ABOVE CRUISE DETENT.  REMOVED THE OUTBOARD INNER BYPASS ACCESS TO	 CHECK BLEED VALVES.  UPON INVESTIGATION, FOUND THE BLEED AIR (P3 LINE) BROKEN AT B-NUT, P/N 3081695.  IT APPEARED THE F	IT OF THE LINE HAD CAUSED FAILURE BECAUSE THE 2 ENDS AT BREAK DID NOT LINE UP.  REPLACED THE LINE WITH NEW.  FIT WAS GOO	D.  RE-ASSEMBLED ENGINE.  GROUND RUN AND FLIGHT CHECK WAS GOOD.			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE
1998112001015	19981120	01015	NM  	1998	11	20	98ZZZX4207       	1	19980722	G	3260	2276500000	HARNESS         			DORNER	DO32  	DO328100    	2996000	NM  										LT MLG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	653PC	3066 			035	3027				INSTALLED S/N 035 AS FACTORY WARRANTY REPLACEMENT PART FOR ONE THAT FAILED.  STARTED HAVING INDICATIONS ON ECIAS AND HYD	RAULIC PAGE OF PROXY FAILURE THEN WOULD GO AWAY.  THIS PROBLEM WOULD SHOW UP ONCE IN A WHILE FIRST, THEN GOT WORSE.  SUB	MITTER SUSPECTED THIS HARNESS AS IT WAS A NO-FAULT FOUND, AND , FAULT BEING (INTERMITTENT OPERATION), INSTALLED NEW UNIT	.  PROBLEM IS GONE.  PART INSTALLED 5-18-98, 2,257 HRS, 3,774 LANDINGS.  REMOVED, 7-20-98, 2,381.4 HOURS, 4,094 LANDINGS	.		2	H	7	2 	4T			RT	A45NM
1998112001016	19981120	01016	CE  	1998	11	20	98ZZZX4208       	1	19980904	G	5620	50420013471	WINDOW RETAINER 			BEECH 	90    	C90A        	1152911	CE  										CABIN	DEBONDED        	B			PAIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	415P					LJ1345				DURING ROUTINE INSPECTION, THE WINDOW FRAME RETAINER WAS FOUND DEBONDED FROM THE AIRCRAFT SKIN.  THE FRAME WAS DEBONDED 	ONE-HALF WAY ROUND.  THIS IS THE SECOND OCCURRENCE OF THIS PROBLEM IN THE LAST 2 MONTHS.  BEECH HAS A REPAIR FOR THIS PR	OBLEM IN THEIR MANUAL.				1	L	7	2 	3T			RT	3A20
1998112001017	19981120	01017	NE  	1998	11	20	98ZZZX4209       	3	19981020	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4607 			2779NR					FORWARD EAR OF PICH CHANGE FOR CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  THREE CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998112001018	19981120	01018	WP  	1998	11	20	98ZZZX4210       	1	19981021	G	5320	577263833	BEAM            			DOUG  	DC8   	DC861       	3021952	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	853AX	52512				46037				AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLT APPROXIMATELY ONE INCH EACH SIDE OF THE AIRCRAFT CENTERLINE.  SUBMITTER S	TATED THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CAB	IN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROUG	H PULLEYS ATTACHED TO THE J-BEAM AND RECOMMENDED THE FOLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 AIRCRAFT WITH F	LAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F				4A25
1998112001019	19981120	01019	WP  	1998	11	20	98ZZZX4211       	1	19981021	G	5320	577263835	BEAM            			DOUG  	DC8   	DC861       	3021952	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	853AX	52512				46037				AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY ONE INCH EACH SIDE OF THE AIRCRAFT CENTERLINE.  SUBMITTER 	STATED THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CA	BIN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROU	GH PULLEYS ATTACHED TO THE J-BEAM AND SUBMITTER RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTIONS OF ALL DC-8 AIR	CRAFT WITH FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F				4A25
1998112001020	19981120	01020	WP  	1998	11	20	98ZZZX4212       	1	19981021	G	5320	577263835	BEAM            			DOUG  	DC8   	DC873F      	302199F	WP  										FUSELAGE	CRACKED         	B			TIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	602AL	86807								AT C-CHECK, CRACKS WERE FOUND IN THE J-BEAM WHICH IS ATTACHED TO THE AFT FACE OF THE AFT PRESSURE BULKHEAD.  THE CRACKS 	ORIGINATE IN THE RADII ADJACENT TO ATTACH BOLTS APPROXIMATELY ONE INCH EACH SIDE OF THE AIRCRAFT CENTERLINE.  SUBMITTER 	STATED THE CRACKS APPEAR TO OCCUR UNDER NORMAL OPERATING CONDITIONS AND ARE POSSIBLY CAUSED BY THE COMBINED FORCES OF CA	BIN PRESSURE AGAINST THE FRONT FACE OF THE BULKHEAD AND TENSION FROM THE 13 FLIGHT CONTROL CABLES WHICH ARE ROUTED THROU	GH PULLEYS ATTACHED TO THE J-BEAM AND RECOMMENDED THE FOLLOWING:  PERFORM PERIODIC INSPECTION OF ALL DC-8 AIRCRAFT WITH 	FLAT AFT PRESSURE BULKHEADS, AND, REPAIR CRACKS PER DC-8 SRM 53-2-5 FIG 26.	2	L	7	4 	4F			RT	4A25
1998112001021	19981120	01021	CE  	1998	11	20	98ZZZX4213       	1	19980928	G	3246	5002460	WHEEL           	GOODYEARAERO		BEECH 	200   	B200        	1152922	CE  										MLG	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	200MJ				8666	BB1012				DURING A ROUTINE TIRE CHANGE OF THE LISTED COMPONENT, VISIBLE SIGNS OF CORROSION THROUGH THE WHEELS PAINT JOB WAS APPARE	NT.  UPON FURTHER INVESTIGATION, THE CORROSION WAS NOTED AS EXCESSIVE AND BEYOND STATED LIMITS NOTED IN THE COMPONENT MM	.   AREAS OF CORROSION, IN SOME CASES, OVER 50 PERCENT OF THE METAL THICKNESS, WERE NOTED IN THE BEAD SEAT, BOLT HOLE, A	ND VALVE STEM AREAS.			1	L	7	2 	4T				A24CE
1998112001022	19981120	01022	CE  	1998	11	20	98ZZZX4214       	1	19981029	G	5620	504001310536	WINDOW          			BEECH 	100   	100BEECH    	1152916	CE  										CABIN	CRACKED         	G		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	03	207SB	8729 				B69				DURING CRUISE AT 14,000 FEET, LT FORWARD CABIN WINDOW BLEW OUT.  UPON INSPECTION OF REMAINING CABIN WINDOWS, ALL EXCEPT 	ONE HAD CRACKS AROUND ENTIRE CIRCUMFERENCE.  THESE CRACKS WERE IN AND PARALLEL TO THE RADIUSED AREA WHERE THE WINDOW IS 	MACHINED TO FIT THE CUT OUT AREA IN THE FUSELAGE.  THESE WINDOWS ARE USED ON VARIOUS MODELS OF THE KING AIR FROM 90 THRO	UGH 350 MODELS.  THE SAME PART NUMBER IS REFERRED TO IN EACH MANUAL FOR THESE DIFFERENT AIRCRAFT.			1	L	7	2 	3T				A14CE
1998112001023	19981120	01023	SW  	1998	11	20	98ZZZX4215       	1	19981104	G	5610	36004311SS	WINDSHIELD      			GULSTM	690TP 	695A        	7630519	SW  										COCKPIT	SHATTERED       	B			JAVR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NE	01	79PH				96012111661	96029				LEFT WINDSHIELD OUTER LAYER SHATTERED AT ALTITUDE.  WINDSHIELD HEAT OPERATED NORMALLY PRIOR TO INCIDENT.  500 HOURS ON W	INDSHIELD.					1	H	7	2 	4T				2A4
1998112001024	19981120	01024	NE  	1998	11	20	98ZZZX4216       	2	19981009	G	7250	783320	LPT SHAFT       								PWA   	JT8   	JT8D217A    	52053	NE  					TURBINE	TWISTED         	B			RA1R	E				ENGINE SHUTDOWN         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	05		9217 	6464 		P99977		P708479			ENGINE WAS REMOVED FROM SERVICE DUE TO AN IN-FLIGHT SHUTDOWN.  DISASSEMBLY OF THE ENGINE REVEALED THE NR 3 BEARING HAD F	AILED AND THE LPT SHAFT TWISTED AT THE HPC CENTER TUBE.  FAILURE INVESTIGATION IS IN PROCESS AT GE ENGINE SERVICES - DAL	LAS.									4	F			E9NE
1998112001025	19981120	01025	CE  	1998	11	20	98ZZZX4217       	1	19981016	G	2810		FUEL CELL       			BEECH 	1900  	1900C       	1154161	CE  										WS 171-183	CONTAMINATED    	B			EBVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	5632C					UC81				THE WING IS CONSTRUCTED IN A WAY THAT TRAPPED WATER CANNOT BE DRAINED FROM THE TRAILING EDGE OF THE FUEL STORAGE AREA BE	TWEEN WS 171.29 AND WS 183.07.  THE SAME PROBLEM IS IN BOTH WINGS.  A DRAIN PATH NEEDS TO BE PROVIDED.					2	L	7	2 	4T			RT	A24CE
1998112001026	19981120	01026	CE  	1998	11	20	98ZZZX4218       	1	19981022	G	3250	50420101	BELLCRANK       			CESSNA	402   	402B        	207590P	CE  										NLG	FAILED          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	87193	9764 				402B1019				DURING A PHASE INSPECTION, DISCOVERED THE NOSE WHEEL STEERING BELLCRANK (P/N 5042010-1) HAD FAILED WITH THE LEFT HALF PU	LLED AFT BY THE STEERING CABLE.  THE PILOT STATED THE RUDDER PEDALS WERE OFFSET DURING TAXI, BUT INLINE DURING FLIGHT. A	 FURTHER INSPECTION OF THE REST OF THE FLEET SHOWED TWO MORE AIRCRAFT HAVE CRACKS IN THE SAME PART, BOTH ARE 'B' MODELS.	  THE 'A' AND 'C' MODELS DID NOT SEEM TO HAVE THIS PROBLEM AS THEY HAVE A DIFFERENT DESIGN OF BELLCRANK.			1	L	7	2 	3O				A7CE
1998112001027	19981120	01027	GL  	1998	11	20	98ZZZX4219       	3	19980911	G	6114		BLADE SOCKET    		D5904C90    	CESSNA	188   	188B        	2073007	CE  						MCAULY	3A32C	D3A32C90    	GL  	HUB	CRACKED         	B			PI4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	07					765861			765861		PROPELLER CAME IN FOR LEAKING CYLINDER GASKET.  REPAIRED AS NECESSARY.  PROPELLER WAS RETURNED IMMEDIATELY FOR DYE LEAKI	NG FROM BLADES.  NDT TESTING REVEALED CRACKS IN ALL THREE BLADE SOCKETS (IN THE 2ND AND 3RD THREADS) AROUND THE BOTTOM H	ALF OF HUB.  CRACKS WERE FROM ONE TO THREE INCHES LONG.  CUSTOMER STATED HE INTENDED TO TAKE THE HUB TO MCCAULEY.  SUBMI	TTER STATED CAUSE UNKNOWN.			1	L	7	1 	3O				A9CE    		5	C	P21EA
1998112001028	19981120	01028	GL  	1998	11	20	98ZZZX4220       	3	19980923	G	6114	C6608C205	HUB             			CESSNA	188   	188B        	2073007	CE  						MCAULY	2A34C	B2A34C205   	GL  	PROPELLER	CRACKED         	B			PI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	07					901493			901493		CRACK ALL THE WAY THROUGH HUB.  LEAKING RED DYE.  SUBMITTER STATED WARNED CUSTOMER IN TIME TO AVOID BLADE SEPARATION.  C	AUSE UNKNOWN.					1	L	7	1 	3O				A9CE    		5	C	P3EA
1998112001029	19981120	01029		1998	11	20	98ZZZX4221       	4	19981006	G	2562	E01	ELT             	ACK         		PIPER 	PA32  	PA32300     	7103212	SO  										EMERG LOCATOR	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	55209	364  			017072	327340105				DURING ANNUAL INSPECTION, PERFORMED ELT INSPECTION IAW FAR 91.207.  UNABLE TO ACTIVATE ELT BY RAPID FORWARD MOVEMENT FOL	LOWED BY A SUDDEN REVERSING MOTION; (TSP C91A UNIT) UNTIL HITTING REAR OF UNIT WITH HAND PRETTY HARD.  G-SWITCH WOULD NO	T ACTIVATE ELT.  AFTER HITTING ELT WITH HAND, ELT WOULD OPERATE PROPERLY.  (MAGNET TO STRONG).				1	L	7	1 	3O				A3SO
1998112001030	19981120	01030	EA  	1998	11	20	98ZZZX4222       	2	19981022	G	7414	ES10391586	BLOCK           	ELECTROSYS  	103493101   	PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					MAGNETO	DAMAGED         	B			SL5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	8390J		416  		5081053	328106083	L2094646A			DURING INVESTIGATION OF UNUSUAL OPERATION OF INSIGHT GRAPHIC ENGINE MONITOR, DISASSEMBLED RIGHT MAGNETO AND FOUND DISTRI	BUTOR GEAR TERMINAL PARTIALLY WORN AWAY AND INSIDE DIAMETER OF DISTRIBUTOR BLOCK SCRAPPED AND GROOVED.  OBTAINED NEW OEM	 BLOCK AND GEAR, OEM DISTRIBUTOR BLOCK WALL THICKNESS IS THINNER THAN ELECTROSYSTEMS DISTRIBUTOR BLOCK WALL THICKNESS. I	NSTALLED NEW PART AND VERIFIED CLEARANCE BETWEEN BLOCK AND DISTRIBUTOR GEAR.			1	L	7	1 	3O	3	O		A3SO    	1E4
1998112600077	19981126	00077	SO  	1998	11	26	98ZZZX4223       	1	19981026	G	3213	6531904	HOUSING         			PIPER 	PA28  	PA28161     	7102803	SO  										RT MLG	CRACKED         	D	P			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	05	405SB	7411 				287919139				CRACK ON BOTTOM TAB TO INSIDE OF STRUT LOCATED ON RIGHT MAIN LANDING GEAR.						1	L	7	1 	3O				2A13
1998112600078	19981126	00078	SO  	1998	11	26	98ZZZX4224       	1	19981106	G	2750	8290503	BELLCRANK       			PIPER 	PA46  	PA46310P    	7104605	SO  										RT FLAP	FAILED          	B		A	MZER	O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	15	9112D	3613 				4608041				ON APPROACH, THE PILOT NOTICED THE RIGHT FLAP DID NOT EXTEND.  THE LEFT FLAP WAS PROMPTLY RETRACTED AND A SAFE LANDING W	AS MADE WITHOUT INCIDENT.  THE INVESTIGATION FOUND THE RIGHT INBOARD FLAP BELLCRANK P/N 82905-03 WAS COMPLETELY BROKEN T	HROUGH THE TUBE PORTION PREVENTING OPERATION OF THE RIGHT FLAP.  SUBMITTER RECOMMENDED BOTH LEFT AND RIGHT BELLCRANKS DE	SERVE SPECIAL ATTENTION DURING INSPECTIONS.			1	L	7	1 	3O			RT	A25SO
1998112600080	19981126	00080	CE  	1998	11	26	98ZZZX4226       	1	19981001	G	2410	643043	BRACKET         			CESSNA	303   	T303        	2073820	CE  										LT ENGINE	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23		1819 								FOUND LEFT ENGINE ALTERNATOR LOWER CASE HALF CRACKED AROUND MOUNTING BOLT BOSS.  FURTHER INSPECTION REVEALED ALTERNATOR 	BOLT AREA WORN AT TOP OUTBOARD ENGINE MOUNT BRACKET.  REMOVAL OF BRACKET FROM ENGINE REVEALED ELONGATED BOLT HOLE.					1	L	7	2 	3O				A34CE
1998112600081	19981126	00081	SO  	1998	11	26	98ZZZX4227       	1	19981009	G	2810	CCA1550	VALVE           			PIPER 	PA28  	PA28140     	7102802	SO  										LT WING	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	41963	10   				287425302				AFTER 10-HOUR SERVICE LIFE, VALVE JAMMED IN THE CLOSED POSITION PREVENTING THE PRE-FLIGHT FUEL SUMP CHECK FOR WATER.						1	L	7	1 	3O				2A13
1998112600082	19981126	00082	CE  	1998	11	26	98ZZZX4228       	1	19980904	G	2410	C6115010102	ALTERNATOR      			CESSNA	182   	182J        	2072722	CE  										ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	3388F	820  			D21580	1825388				CUSTOMER COMPLAINED OF 'NO ALTERNATOR OUTPUT - AMMETER SHOWS DISCHARGE'.  MECHANIC FOUND THE ALTERNATOR IN 3 PIECES.  TH	E DRIVE END WAS STILL ATTACHED TO THE MOUNT AND WAS STILL CAPABLE OF ROTATING.  THE STATOR WAS FOUND IN THE BOTTOM OF TH	E COWL, THE HEAD END WAS STILL ATTACHED TO THE WIRING AND WAS LAYING ON THE INTAKE.  THE THREE SCREWS THAT SECURE THE TW	O HALVES WERE NOT FOUND.  SUBMITTER SUGGESTED PROVISIONS FOR SAFETY WIRE RATHER THAN LOCK WASHERS MIGHT WORK BETTER.			1	H	7	1 	3O			NT	3A13
1998112600083	19981126	00083	CE  	1998	11	26	98ZZZX4229       	1	19980902	G	3260	327	BULB            			CESSNA	501   	501         	2076603	CE  										INSTRUMENT PANEL	FAILED          	B			EHHR	O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			EA	17	106EA	3008 				5010101				WHEN SELECTED DOWN, THE GEAR EXTENDED, BUT NO LEFT MAIN GEAR DOWN LIGHT ILLUMINATED.  THE GEAR WAS BLOWN DOWN.  THE AIRC	RAFT LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED GEAR DOWN LIGHT WAS BURNED OUT.  BULB WAS REPLACED AND GEAR WAS FO	UND TO FUNCTION NORMALLY.				1	L	7	2 	4F				A27CE
1998112600084	19981126	00084	CE  	1998	11	26	98ZZZX4230       	1	19981030	G	5712		WING            			CESSNA	172   	172RG       	2072438	CE  										WS 190 LEFT	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9343D	4197 				172RG1128				LEFT WING RIB WAS FOUND CRACKED AT STA 190.0.  THIS LOCATION IS AT THE OUTBOARD HINGE LOCATION OF THE AILERON.  THIS IS 	WHERE ALL THE BALANCE LEAD IS LOCATED.  SUBMITTER SUGGESTED CAUSE AS FATIGUE DUE TO RIB FLEXING DURING TURBULENCE.  AIRC	RAFT IS USED FOR TRAINING.  CRACK IS .8750 INCH LONG.  REPAIRED BY REPLACMENT OF RIB WITH NEW.				1	H	7	1 	3O				3A17
1998112600085	19981126	00085	EA  	1998	11	26	98ZZZX4231       	2	19981001	G	8530		EXHAUST VALVE   			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	FAILED          	H				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			EA	25	40NR	613  				243330	L263555V			CYLINDER NR 4 EXHAUST VALVE STUCK OPEN ON TAKEOFF.  AIRCRAFT RETURNED TO AIRPORT AND MADE A SAFE LANDING.  UPON INSPECTI	ON, THE CYLINDER'S NR 4 EXHAUST ROTATER CAP WAS FOUND IN THE BOTTOM OF THE ROCKER BOX.  INSPECTED VALVE PER LYC SB 388B.	  CLEARANCE FOUND TO BE SATISFACTORY.  REMOVED CYLINDER FOR INSPECTION AT OVERHAUL FACILITY.  GUIDE WAS REAMED, SEAT WAS	 GROUND.  RE-INSTALLED CYLINDER ASSY.  SUBMITTER SUGGESTED CAUSE AS CARBON 1 LEAD DEPOSITS STUCK VALVE OPEN.			1	L	7	1 	3O	3	O		2A3     	1E10
1998112600086	19981126	00086		1998	11	26	98ZZZX4232       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11		30451			30451					MODE 'C' ERRORS INTERMITTENT ALTITUDE READINGS (ERRONEOUS).
1998112600087	19981126	00087		1998	11	26	98ZZZX4233       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11					58457					MODE 'C' ERRORS INTERMITTENT ALTITUDE READINGS (ERRONEOUS).
1998112600088	19981126	00088		1998	11	26	98ZZZX4234       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11					38098					MODE 'C' ERRORS INTERMITTENT ALTITUDE READINGS (ERRONEOUS).
1998112600089	19981126	00089		1998	11	26	98ZZZX4235       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11					55386					MODE 'C' ERRORS INTERMITTENT ALTITUDE READINGS (ERRONEOUS).
1998112600090	19981126	00090		1998	11	26	98ZZZX4236       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11					28551					INTERMITTENT CODES AT ALL ALTITUDES.
1998112600091	19981126	00091		1998	11	26	98ZZZX4237       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11					47686					INOPERABLE IN AIRCRAFT - INTERMITTENT ALTITUDE READINGS (ERRONEOUS).
1998112600092	19981126	00092		1998	11	26	98ZZZX4238       	4	19981026	G	3416	A30	ENCODER         	ACK         																COCKPIT	MALFUNCTIONED   	B			VM9R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	11					31431					MODE 'C' ERRORS INTERMITTENT ALTITUDE READINGS (ERRONEOUS).
1998112600093	19981126	00093	SW  	1998	11	26	98ZZZX4239       	1	19980812	G	2710		CONTROL CABLE   			BBAVIA	8     	8GCBC       	1220803	SW  										RT WING	TWISTED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	778AC					38197				THE AILERON CABLES IN THE RIGHT WING WERE FOUND WRAPPED AROUND EACH OTHER BETWEEN THE WING ROOT PULLEYS AND THE PULLEY A	T THE OUTBOARD FLAP HINGE ARM.					1	H	7	1 	3O			 	A21CE
1998112600094	19981126	00094	CE  	1998	11	26	98ZZZX4240       	1	19981030	G	7921		OIL COOLER      			CESSNA	421   	421C        	2076016	CE  										ENGINE	LEAKING         	B			YXRR	K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			WP	07	66NC					421C0519				OIL LEAK NOTED BELOW THE OIL COOLER ON A RECENTLY OVERHAULED ENGINE.  OIL COOLER WAS PULLED AND GASKETS REPLACED.  ENGIN	E STILL LEAKED OIL.  OIL COOLER WAS PULLED AND 3 RECENTLY OVERHAULED COOLERS INSTALLED.  ALL LEAKED.  INSPECTION OF OIL 	COOLER MATING SURFACE SHOWED ALL 4 COOLERS TO BE MACHINED CONCAVE TO A DEPTH GREATER THAN THE THICKNESS OF THE GASKET. A	N OIL COOLER WAS INSTALLED.			1	L	7	2 	3O				A7CE
1998112600095	19981126	00095	CE  	1998	11	26	98ZZZX4241       	1	19981001	G	3230	NAS56533	BOLT            		12416185    	CESSNA	210   	P210N       	2073454	CE  										MLG DOWNLOCK	LOOSE           	H		A		O				OTHER                   				O			OTHER                     			LD	LANDING        	1			WP	03	911DS	1455 				P21000787				THE PILOT REPORTED NOISE FROM LANDING GEAR DURING LANDING.  INSPECTION REVEALED THAT BOTH RIGHT AND LEFT MAIN LANDING GE	AR DOWNLOCK SUPPORT BOLTS LOOSE.  SUBMITTER RECOMMENDED INSPECTION AT EACH ANNUAL AND IF BOLTS ARE FOUND LOOSE, RE-TORQU	E USING LOCK-TIGHT IAW CESSNA SM.				1	H	7	1 	3O				3A21
1998112600096	19981126	00096	CE  	1998	11	26	98ZZZX4242       	1	19980923	G	2821	07560052	FUEL STRAINER   			CESSNA	150   	150L        	2071826	CE  										FUEL SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	5258Q	7563 				15073158				DURING SCHEDULED INSPECTION, STRAINER STANDPIPE WAS INSPECTED PER SEB 97-9 AND FAILED INSPECTION - MEASURED 1.758 INCH. 	 A LIGHT TO MODERATE FORCE APPLIED TO STANDPIPE CAUSED IT TO SEPARATE FROM TOP CASTING.  REMOVAL OF CASTING ASSY FROM AC	FT AND INSP SHOWED STANDPIPE HAD BEEN REMOVED, LOOSE, OR FELL OUT IN THE PAST AND OPPOSITE END RE-INSTALLED AS BOTH ENDS	 SHOW INSTALL MARKS.  ACFT RECORDS INDICATE NO MAINT TO ASSY.  SEB 97-9 DOES NOT APPLY BY DATE.  AS SEB 97-9 IN ITSELF W	OULD NOT HAVE APPLIED TO THIS ACFT, SUBMITTER RECOMMENDED ONE-TIME INSP PER PROPOSED AD 97-CE-114 - AD BE ADOPTED REGARD	LESS OF RECORD ENTRIES OR DATES.  NEW ASSY INSTALLED TO CORRECT DEFECT.	1	H	7	1 	3O				3A19
1998112600097	19981126	00097	CE  	1998	11	26	98ZZZX4243       	1	19981027	G	2410	AN644	BOLT            			CESSNA	310   	310G        	2074218	CE  										ALTERNATOR	WORN            	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	88LT	2663 				310G0835				DURING ANNUAL INSPECTION, RIGHT ALTERNATOR BELT WAS FOUND MISSING.  DURING INSTALLATION OF NEW BELT, ALTERNATOR WAS FOUN	D OUT OF ALIGNMENT WITH DRIVE PULLEY DUE TO WORN MOUNTING BOLT.  REPLACED BOLT AND ALIGNMENT OK.					1	L	7	2 	3O				3A10
1998112600098	19981126	00098	CE  	1998	11	26	98ZZZX4244       	1	19981027	G	5280	0851000100	HINGE           			CESSNA	310   	310Q        	2074242	CE  										MLG DOOR	BROKEN          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	88LT	2663 				310Q0835				DURING ANNUAL INSPECTION, OUTBOARD, MAIN GEAR DOOR HINGE HALF (ATTACHED TO WING) HAD ONE SECTION BROKEN OFF.  REPLACED H	INGE HALF.  THIS APPLIES TO BOTH WINGS.					1	L	7	2 	3O				3A10
1998112600099	19981126	00099	CE  	1998	11	26	98ZZZX4245       	1	19981027	G	5713	08220305	STRINGER        		08220441    	CESSNA	310   	310Q        	2074242	CE  										LT WING	CORRODED        	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	88LT	2663 				310Q0835				DURING ANNUAL INSPECTION, STRING IN LEFT WING UPPER SKIN NACELLE AREA STA 80.0L WAS FOUND WITH EXFOLIATION CORROSION.  I	NBOARD 8 INCHES OF STRINGER WAS REPLACED.					1	L	7	2 	3O				3A10
1998112600100	19981126	00100	CE  	1998	11	26	98ZZZX4246       	1	19981027	G	3246	16201700	WHEEL           	CLEVELAND   	4040A       	CESSNA	310   	310Q        	2074242	CE  										RT MLG	DAMAGED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	88LT	2663 				310Q0835				WHILE REPLACING TIRE, RIGHT INBOARD WHEEL HALF BEARING CONE WAS FOUND LOOSE IN HUB.  PERSONS UNKNOWN HAD PREVIOUSLY ATTE	MPTED TO STAKE CONE IN PLACE.  WHEEL HALF WAS REJECTED DUE TO OVERSIZE BORE AND DAMAGE FROM STAKING ATTEMPT.  SUBMITTER 	STATED CAUSE AS IMPROPER  MAINTENANCE REPAIR.  WHEEL HALF WAS REPLACED.				1	L	7	2 	3O				3A10
1998112600101	19981126	00101		1998	11	26	98ZZZX4247       	4	19981028	G	6122	4507032	FLYWEIGHT HEAD  	WOODWARD    	8210263     															GOVERNOR	FAILED          	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03					1997083					BRAZED ON FLYWIEGHT MOUNTING BOSS SEPARATED FROM FLYWEIGHT DRIVE DISC.  SUBSEQUENT ROTATION OF FAILED PARTS CAUSED SUBST	ANTIAL DAMAGE TO FLYWEIGHT CAVITY AND RENDERED THE ENTIRE UNIT UNSERVICEABLE.
1998112600102	19981126	00102	CE  	1998	11	26	98ZZZX4248       	1	19980928	G	3230	20430156	BOLT            			CESSNA	177   	177RG       	2073709	CE  										NLG	BROKEN          	B			EBVD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	35060	2860 				177RG1039				DURING AN ANNUAL INSPECTION, THE NOSE GEAR DRAG BRACE ASSY KNEE JOINT BOLT WAS FOUND SHEARED IN HALF.  THIS BOLT IS DRIL	LED AND ZERKED FOR LUBRICATING.  THE BOLT WAS BROKEN AT THE CENTER HOLE WHERE THE GREASE COMES OUT INSIDE THE BRACE BUSH	INGS.  BOLT WAS REPLACED WITH NEW.  SUBMITTER SUGGESTED REMOVING THIS BOLT AT EVERY INSPECTION AS THERE WAS NO REAL NOTI	CEABLE PROBLEM PRIOR TO REMOVAL.			1	H	7	1 	3O				A20CE
1998112600103	19981126	00103		1998	11	26	98ZZZX4249       	1	19981026	G	3245	2504	TUBE            																	MLG	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05										VALVE STEM REINFORCEMENT PATCH DELAMINATED THE FIRST TIME THE ASSEMBLY WAS AIRED UP AFTER REPLACING THE TUBE.  VISUAL IN	SPECTION REVEALED POOR MANUFACTURING.
1998112600104	19981126	00104		1998	11	26	98ZZZX4250       	1	19981003	G	2560	GA12P0201101	FLOTATION DEVICE	EAAEROMARINE																CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					D38731					FLOTATION DEVICE FAILED MFG RECOMMENDED 2 PSI TEST IAW MANUAL 25-60-13.
1998112600105	19981126	00105		1998	11	26	98ZZZX4251       	1	19981020	G	2560		LIFE VEST       																	CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					71872					FAILED MANUFACTURER'S RECOMMENDED 2 PSI TEST IAW MANUAL  25-60-12.  P/N KSE35L8P0723E105P.
1998112600106	19981126	00106	CE  	1998	11	26	98ZZZX4252       	1	19981030	G	3242	0500118127	LINE            			CESSNA	172   	172R        	2072401	CE  										BRAKE	CHAFED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	385ES	480  				17280103				DURING ANNUAL INSPECTION WHEN THE RT BRAKE FAIRING (P/N 0541124-2) WAS REMOVED, DISCOVERED THE LOWER FAIRING SCREWS (P/N	 5102126-6) HAD CHAFED INTO THE BRAKE LINE ASSY LOWER SIDE.  THE CORRECT LENGTH SCREW WAS INSTALLED PER IPC.  THIS IS AN	 AREA NOT EASILY SEEN UNLESS AN INSPECTION MIRROR IS USED.  CESSNA WAS NOTIFIED.  THE BRAKE LINE WAS REPLACED AND REPOSI	TIONED TO PREVENT RECURRENCE.  SUBMITTER STATED THAT OLDER 172 ACFT HAVE AN ADEL CLAMP HOLDING THE BRAKE LINE AT THE LOW	ER END OF THE STRUT FAIRINGS.  NEWER 172'S DO NOT HAVE THESE CLAMPS.		1	H	7	1 	3O			NT	3A12
1998112600107	19981126	00107	SO  	1998	11	26	98ZZZX4253       	2	19980901	G	8520	653012	CRANKSHAFT      			CESSNA	150   	150K        	2071822	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	6164G					15071664	253226A48			TWO INCH RADIAL CRACK WAS FOUND DURING ENGINE MAJOR OVERHAUL MAGNAFLUX INSPECTION.  CRACKS WERE FOUND BEHIND PROPELLER F	LANGE ON THE CRANKSHAFT.  ENGINE POSSIBLY HAD A PROPELLER STRIKE AND WAS NOT RECORDED.  SUBMITTER STATED ALL PILOTS AND 	OPERATORS NEED TO REPORT THESE INCIDENTS.				1	H	7	1 	3O	3	O		3A19    	E252
1998112600108	19981126	00108	SO  	1998	11	26	98ZZZX4254       	1	19981029	G	5700		LIFT STRUT      			PIPER 	J3    	J3C65       	7100510	SO  										WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	40609					7362				THIS WAS THE FRONT WING LIFT STRUT.  WHILE C/W AD 98-10-06 IAW SB 528D, SKETCH 'A', CORROSION WAS FOUND AT 5 INCH-7 INCH	, AND 10 INCH-12 INCH FROM THE END OF THE STRUT.  AT 12 INCHES, THIS IS 1 INCH OUTSIDE THE INSPECTION AREA PER SKETCH 'A	'.  THE STRUT WAS REPLACED WITH A SERVICEABLE ONE.				1	H	7	1 	3O				A691
1998112600109	19981126	00109		1998	11	26	98ZZZX4255       	2	19981104	G	7322	78A110	WASHER          	PRECISION   	MA4SPA105217															ENGINE	LEAKING         	B			NE2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07			195  		75075511					RECEIVED CARBURETOR FROM CUSTOMER WITH SQUAWK 'CARB SHOOK APART'.  UPON INSPECTION OF THE CARBURETOR, FUEL STAINS WERE N	OTICED ON THE BOWL ASSY AND THROTTLE BODY ASSY.   FURTHER INSPECTION REVEALED THE FOUR SCREWS HOLDING THE THROTTLE BODY 	ASSY TO  THE BOWL ASSY WERE LOOSE.  TWO OF THE FOUR TAB STYLE LOCK WASHERS (WHICH RETAIN THE SCREWS) WERE CRACKED AND HA	D SPREAD IN THE SHAPE OF A 'C'.
1998112600110	19981126	00110	CE  	1998	11	26	98ZZZX4256       	1	19981015	G	2400	72772	CITCUIT BREAKER 	KLIXON      		BEECH 	95    	95B55       	1152729	CE  										COCKPIT	FAILED          	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	111KF					TC633				TECHNICIAN WAS CYCLING CIRCUIT BREAKERS DURING ANNUAL INSPECTION.  TWO CIRCUIT BREAKERS WOULD NOT OPEN.  A 1-AMP AND 3-A	MP BREAKER POWERING AVIONICS AUDIO SYSTEM WERE REPLACED.  AS A PRECAUTION TO PREVENT FIRE HAZARD FROM NOT TRIPPING, 1-AM	P BREAKER DID DISENGAGE WITH MUCH FORCE AND A PAIR OF PLIERS.  ELECTRICALLY, BREAKERS HAD NOT FAILED.  MECHANICAL FAILUR	E POSSIBLY DUE TO AGE.  SUBMITTER SUGGESTED CYCLING BREAKERS PERIODICALLY.			1	L	7	2 	3O			RT	3A16
1998112600111	19981126	00111		1998	11	26	98ZZZX4257       	4	19981004	G	2561	KS9P0101HC2	LIFE VEST       	EAAEROMARINE																CABIN	FAILED          	B			KQ1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07					B70814					LIFE VEST FAILED MFG 2 PSI TEST IAW MANUAL 25-60-1.  VEST MG DATE:  JAN 1981.
1998112600112	19981126	00112	EA  	1998	11	26	98ZZZX4258       	2	19981007	G	7412	90497703B	EXCITER BOX     			GULSTM	560   	560         	0141402	SW  	LYC   	O480  	GSO480B1A6  	41529	EA  					LT ENGINE	FAILED          	B	L		AC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01		622  			NN97076175	560432				PILOT REPORTED LT ENG WOULD NOT LIGHT OFF ON START AND THERE WAS NO AUDIBLE SNAPPING SOUND.  THE BOX HAD 24 VOLTS AND GO	OD GROUND.  ANOTHER EXCITER BOX INSTALLED AND IGNITER CHECKED.  A SNAP FROM INBD IGNITER HEARD AND ENG WAS COWLED UP, EN	G STARTED, AND AIRPLANE RETURNED TO BASE.  ENG HAS 2 EXCITER BOXES AND APPARENTLY BOTH BOXES FAILED.  ACFT HAD UNDERGONE	 A PHASE 3 AND 4 INSPECTIONS 24 HOURS PREVIOUS AT 598 HRS.  IGNITERS WERE CHECKED AND WORKED.  BOXES POSSIBLY DID NOT FA	IL AT SAME TIME AS ENG STARTED ON ONE IGNITER.  OTBD EXCITER CIRCUIT CHECKED.  BOTH WERE GOOD AND 2 EXCHANGE EXCITER BOX	ES INSTALLED.  IGNITERS REMOVED, INSPECTED.  ALL OPS OK.  IGNITER REINSTALLED, ACFT WAS COWLED UP, RETURNED TO SERVICE.	1	H	7	2 	3O	3	O		6A1     	E284
1998112600113	19981126	00113	EA  	1998	11	26	98ZZZX4259       	2	19981007	G	7412	90497703B	EXCITER BOX     			GULSTM	560   	560         	0141402	SW  	LYC   	O480  	GSO480B1A6  	41529	EA  					LT ENGINE	FAILED          	B	L		AC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01		622  			NN97076177	560432				PILOT REPORTED LT ENG WOULD NOT LIGHT OFF ON START AND THERE WAS NO AUDIBLE SNAPPING SOUND.  THE BOX HAD 24 VOLTS AND GO	OD GROUND.  ANOTHER EXCITER BOX INSTALLED AND IGNITER CHECKED.  A SNAP FROM INBD IGNITER HEARD AND ENG WAS COWLED UP, EN	G STARTED, AND AIRPLANE RETURNED TO BASE.  ENG HAS 2 EXCITER BOXES AND APPARENTLY BOTH BOXES FAILED.  ACFT HAD UNDERGONE	 A PHASE 3 AND 4 INSPECTIONS 24 HOURS PREVIOUS AT 598 HRS.  IGNITERS WERE CHECKED AND WORKED.  BOXES POSSIBLY DID NOT FA	IL AT SAME TIME AS ENG STARTED ON ONE IGNITER.  OTBD EXCITER CIRCUIT CHECKED.  BOTH WERE GOOD AND 2 EXCHANGE EXCITER BOX	ES INSTALLED.  IGNITERS REMOVED, INSPECTED.  ALL OPS OK.  IGNITER REINSTALLED, ACFT WAS COWLED UP, RETURNED TO SERVICE.	1	H	7	2 	3O	3	O		6A1     	E284
1998112600114	19981126	00114	CE  	1998	11	26	98ZZZX4260       	1	19980915	G	5720	3A02064001	STRUT FITTING   	WIPLINEINC  	3730        	CESSNA	206   	U206G       	2073356	CE  										LT FUSELAGE	CRACKED         	B	P		NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	70SB	8281 				U20605554				DURING ANNUAL INSPECTION, FOUND THE AFT LEFT UPPER DIAGONAL STRUT FITTING CRACKED IN FIVE SEPARATE AREAS ON BOTH THE UPP	ER AND LOWER SURFACES ALONG THE LONGITUDINAL GRAIN.  IT WAS ALSO NOTED THAT TWO CRACKS WERE LOCATED ALONG AN ORIGINAL MA	CHINING MARK.  THE MARK WAS NOT PRESENT ON THE RIGHT SIDE FITTING.				1	H	7	1 	3O				A4CE
1998112600115	19981126	00115	SO  	1998	11	26	98ZZZX4261       	1	19980911	G	2435	05K213021	STARTER         			PIPER 	PA28  	PA28236     	7102815	SO  										ENGINE	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	2889D	46   			121876	287911227				NEW TEXTRON LYCOMING STARTER MOTOR FAILED 45 HOURS SINCE NEW.  SUBMITTER STATED POSSIBLE CAUSE, INTERNAL ELECTRICAL FAIL	URE.					1	L	7	1 	3O				2A13
1998112600116	19981126	00116	CE  	1998	11	26	98ZZZX4262       	1	19981021	G	3710	21500	AIR PUMP        			CESSNA	150   	152         	2071835	CE  										ENGINE	FAILED          	E				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	49858				7AP2364	15281362				AIR PUMP FAILED AT START UP.  SEE AIRBORNE SL 48.  PUMP STILL TURNS, BUT SHAFT FAILED.						1	H	7	1 	3O			NT	3A19
1998112600117	19981126	00117	CE  	1998	11	26	98ZZZX4263       	1	19981015	G	7160	BA5110	FILTER ASSY     	BRACKETT    		CESSNA	172   	172M        	2072418	CE  										AIR INTAKE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	20109	4000 				17261017				AIR SCREEN CRACKED AROUND ENTIRE OUTSIDE, GOES AROUND THE GREY GLUE INSIDE OF FRAME.  GASKET REMAINS IN VERY GOOD CONDIT	ION.					1	H	7	1 	3O			NT	3A12
1998112600118	19981126	00118	NE  	1998	11	26	98ZZZX4264       	2	19981013	G	8550	212734	SCAVENGE PUMP   			CVAC  	340   	34032       	2422706	WP  	PWA   	R2800 	R280083AM7  	52026	NE  					NR 2 ENGINE	SEIZED          	H				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			EA	23	3427	1311 				90	P37200			AIRCRAFT WAS AT CRUISE ALTITUDE OF 8,000 FEET EN ROUTE FROM HGR TO PTK.  THE NR 2 ENGINE BMCP WENT TO ZERO ALTHOUGH ENGI	NE CONTINUED TO OPERATE.  OIL QUANTITY DECREASED APPROXIMATELY 7 GALLONS IN 30 SECONDS.  ENGINE WAS SHUT DOWN AND AIRCRA	FT DIVERTED TO ERIE, PA, AND LANDED WITHOUT INCIDENT.				2	L	7	2 	4R	4	R		6A6     	5E8
1998112600119	19981126	00119	SO  	1998	11	26	98ZZZX4265       	1	19980923	G	7810	LW16620	EXHAUST PIPE    			PIPER 	PA31  	PA31350     	7103110	SO  										ENGINE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	3525B					317952121				PART HAD EITHER WORN OR WAS IMPROPERLY REWORKED CAUSING THE FLAIR TO GO DEEPER INTO THE PIPE SECTION THAN WAS ORIGINALLY	 INTENDED.  AS A RESULT, FORWARD SECTION SLID TOO FAR INTO THE FLAIR CAUSING THE EXHAUST PIPE SECITON FORWARD OF THIS TO	 SEPARATE.				1	L	7	2 	3O				A20SO
1998112600120	19981126	00120	EA  	1998	11	26	98ZZZX4266       	2	19981020	G	7414	K3822	DIST BLOCK      	SLICK       	4370        	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	TO360E1A6   	41514	EA  					MAGNETO	LOOSE           	B			NX42	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	925ER	479  			97100646	4496012				DURING 500-HOUR INSPECTION, DISTRIBUTOR GEAR ELECTRODE FINGER WAS FOUND LOOSE.						1	L	7	2 	3O	3	O		A19S0   	E26EA
1998112600122	19981126	00122	EA  	1998	11	26	98ZZZX4268       	2	19981016	G	7322		THROTTLE        	FACET       	105217      	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	JAMMED          	B				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			SO	16	147ER		766  		DC21271	2841142	L1106639A			AFTER TAKEOFF, THE PILOT ATTEMPTED TO REDUCE POWER.  THE THROTTLE JAMMED AND WOULD NOT MOVE TO BELOW 2,300 RPM.  THE MIX	TURE WAS PLACED IN ICO FOR LANDING.  THE DISCHARGE TUBE HAD COME LOOSE AND WEDGED IN THE THROTTLE PLATE.  SUBMITTER STAT	ED THEY HAVE A FLEET OF 16 OF THESE AIRCRAFT.  THROTTLE TUBE IS INSPECTED EVERY 100 HOURS.				1	L	7	1 	3O	3	O		2A13    	E274
1998112600123	19981126	00123	NE  	1998	11	26	98ZZZX4269       	1	19980902	G	3230	S4412001	SUPPORT         			CONAER	LA4   	LA4200      	5110310	NE  										NLG	FAILED          	D				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			NM	05	5LY					474				PILOT REPORTED NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF.  INSPECTION OF NOSE LANDING GEAR WHEEL WELL REVEALED B	ROKEN UPPER NOSE L/G SUPPORT ASSEMBLY.  THIS PART IS THE VERY TOP SUPPORT TUBE THAT IS MOUNTED ACROSS THE WHEEL WELL.  I	NSPECTION OF THE BROKEN PART SHOWED VERY LITTLE CORROSION SO CAUSE OF BREAK MAY HAVE BEEN A HARD LANDING.				1	H	7	1 	3O				1A13
1998112600125	19981126	00125	CE  	1998	11	26	98ZZZX4270       	1	19980821	G	3233	8A05116003	ACTUATOR        	WIPLINEINC  	8000A       	CESSNA	208   	208         	2073702	CE  										MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A	1080 			80103	20800225				NOTED DURING PHASE NR 1 'FLOAT' INSPECTION (SBL AAIP 50 HR), THE LT AND RT MAIN LANDING GEAR EXTEND/RETRACT ACTUATOR CYL	INDER (OUTER HOUSING) INDICATED 'CELL CORROSION'.  THIS CORROSION WAS NOTED AT THE MANUFACTURER'S ATTACH POINTS OF THE E	LECTRICAL HARNESS (NYLON TIE WRAPS AND ELECTRICAL HARNESS NON-ENVIRONMENTAL BUTT SPLICE) TO CYLINDER OUTER HOUSING; THUS	, CREATING A LOW OXYGEN REGION WHICH PREVENTED REFORMATION OF PASSIVE FILM BY FOREIGN MATERIAL (NYLON TIE WRAP AND BUTT 	SPLICE WEEPING CORROSION).  REMOVAL OF DETACHED PAINT EXPOSED DEEP CORROSION PITTING BEYOND MFG SPECS.  ACTUATOR CYL ASS	YS REPLACED, ELEC HARNESS ENVIRONMENTALLY SPLICED, REROUTED.	1	H	7	1 	3T			NT	A37CE
1998112600126	19981126	00126	CE  	1998	11	26	98ZZZX4271       	1	19980821	G	3233	8A05116003	ACTUATOR        	WIPLINEINC  	8000A       	CESSNA	208   	208         	2073702	CE  										MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A	1080 			80104	20800225				NOTED DURING PHASE NR 1 'FLOAT' INSPECTION (SBL AAIP 50 HR), THE LT AND RT MAIN LANDING GEAR EXTEND/RETRACT ACTUATOR CYL	INDER (OUTER HOUSING) INDICATED 'CELL CORROSION'.  THIS CORROSION WAS NOTED AT THE MANUFACTURER'S ATTACH POINTS OF THE E	LECTRICAL HARNESS (NYLON TIE WRAPS AND ELECTRICAL HARNESS NON-ENVIRONMENTAL BUTT SPLICE) TO CYLINDER OUTER HOUSING; THUS	, CREATING A LOW OXYGEN REGION WHICH PREVENTED REFORMATION OF PASSIVE FILM BY FOREIGN MATERIAL (NYLON TIE WRAP AND BUTT 	SPLICE WEEPING CORROSION).  REMOVAL OF DETACHED PAINT EXPOSED DEEP CORROSION PITTING BEYOND MFG SPECS.  ACTUATOR CYL ASS	YS REPLACED, ELEC HARNESS ENVIRONMENTALLY SPLICED, REROUTED.	1	H	7	1 	3T			NT	A37CE
1998112600209	19981126	00209	NM  	1998	11	26	98ZZZX4272       	1	19980928	G	5320		PANEL           			BOEING	727   	727224      	1384076	NM  										BS 740	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69736					20665				DURING C-CHECK, CORROSION WAS NOTED ON EXTERIOR GROUND AIR CONNECTION PANEL.						2	L	7	3 	4F				A3WE
1998112600210	19981126	00210	NM  	1998	11	26	98ZZZX4273       	1	19980928	G	2560	65659723	BRACKET         			BOEING	727   	727224      	1384076	NM  										GIRT BAR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	69736					20665				DURING C-CHECK, CORROSION WAS NOTED ON 3 EACH BRACKETS, ON ESCAPE SLIDE GIRT BAR FLOOR BRACKETS.						2	L	7	3 	4F				A3WE
1998112600211	19981126	00211	NM  	1998	11	26	98ZZZX4274       	1	19981105	G	5320		SUPPORT         			BOEING	727   	727227      	1384078	NM  										CABIN	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON TOP AND BOTTOM OF FLOOR SUPPORT R1 DOOR.						2	L	7	3 	4F				A3WE
1998112600212	19981126	00212	NM  	1998	11	26	98ZZZX4275       	1	19981106	G	5720	69144571	BOLT            			BOEING	727   	727227      	1384078	NM  										LT WING	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON LEFT FORWARD WING BODY TERMINAL PIN BEARING LUG BOLT.						2	L	7	3 	4F				A3WE
1998112600213	19981126	00213	NM  	1998	11	26	98ZZZX4276       	1	19981105	G	5320		SUPPORT         			BOEING	727   	727227      	1384078	NM  										CABIN	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON TOP AND BOTTOM OF FLOOR SUPPORT L-1 DOOR.						2	L	7	3 	4F				A3WE
1998112600214	19981126	00214	NM  	1998	11	26	98ZZZX4277       	1	19981105	G	5320	69455551	BRACKET         			BOEING	727   	727227      	1384078	NM  										CARGO BAY	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON FORWARD PIT DOOR FRAME ATTACH BRACKET (STA 580).						2	L	7	3 	4F				A3WE
1998112600215	19981126	00215	NM  	1998	11	26	98ZZZX4278       	1	19981105	G	5347		SEAT TRACK      			BOEING	727   	727227      	1384078	NM  										BS 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK STA 1110RT.						2	L	7	3 	4F				A3WE
1998112600216	19981126	00216	NM  	1998	11	26	98ZZZX4279       	1	19981105	G	5347		SEAT TRACK      			BOEING	727   	727227      	1384078	NM  										BS 1110-1155	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK STA 1110 - STA 1155, LBL 24.5.						2	L	7	3 	4F				A3WE
1998112600217	19981126	00217	NM  	1998	11	26	98ZZZX4280       	1	19981105	G	5741	69139017	BOTTLE PIN      			BOEING	727   	727227      	1384078	NM  										RT WING	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED AT RT REAR SPAR BOTTLE PIN.						2	L	7	3 	4F				A3WE
1998112600218	19981126	00218	NM  	1998	11	26	98ZZZX4281       	1	19981104	G	3230	69443883	LINK            			BOEING	727   	727227      	1384078	NM  										RT MLG	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON RT MLG WALKING BEAM ACTUATOR BEAM SUPPORT LINK SHAFT.						2	L	7	3 	4F				A3WE
1998112600219	19981126	00219	NM  	1998	11	26	98ZZZX4282       	1	19981030	G	5347		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK FS 420 RBL 45.						2	L	7	3 	4F				A3WE
1998112600220	19981126	00220	NM  	1998	11	26	98ZZZX4283       	1	19981030	G	5260		STEP            			BOEING	727   	727231      	1384079	NM  										AFT AIR STAIR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON AFT AIR STAIRS (2ND STEP FROM TOP)						2	L	7	3 	4F				A3WE
1998112600221	19981126	00221	NM  	1998	11	26	98ZZZX4284       	1	19981030	G	5347		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK FS 1030 APPROXIMATELY LBL 55.						2	L	7	3 	4F				A3WE
1998112600222	19981126	00222	NM  	1998	11	26	98ZZZX4285       	1	19981030	G	5313		STRINGER        			BOEING	727   	727231      	1384079	NM  										BS 680-700	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON STR 23R STA 680 - STA 700.						2	L	7	3 	4F				A3WE
1998112600223	19981126	00223	NM  	1998	11	26	98ZZZX4286       	1	19981030	G	5347		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK FS 1030 - FS 1130, LBL 24.						2	L	7	3 	4F				A3WE
1998112600224	19981126	00224	NM  	1998	11	26	98ZZZX4287       	1	19981030	G	5315		FLOOR BEAM      			BOEING	727   	727231      	1384079	NM  										BS 400	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON FLOOR BEAM FS 400, RBL 3, APPROXIMATE.						2	L	7	3 	4F				A3WE
1998112600225	19981126	00225	NM  	1998	11	26	98ZZZX4288       	1	19981030	G	5210		BRACKET         			BOEING	727   	727231      	1384079	NM  										PASSENGER DOOR	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON L-1 DOOR INTERIOR BOTTOM BRACKET FOR DOOR SLIDE.						2	L	7	3 	4F				A3WE
1998112600226	19981126	00226	NM  	1998	11	26	98ZZZX4289       	1	19981030	G	5347		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK STA 420, RBL 24.						2	L	7	3 	4F				A3WE
1998112600227	19981126	00227	NM  	1998	11	26	98ZZZX4290       	1	19981030	G	5320		FLOOR BEAM      			BOEING	727   	727231      	1384079	NM  										BS 344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON FLOOR BEAM UPPER T-CHORD FS 344 LBL 24 - RBL 12.						2	L	7	3 	4F				A3WE
1998112600228	19981126	00228	NM  	1998	11	26	98ZZZX4291       	1	19981030	G	5320		ANGLE           			BOEING	727   	727231      	1384079	NM  										BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON FORWARD END OF SEAT TRACK ON ANGLE FS 420 RBL 55.						2	L	7	3 	4F				A3WE
1998112600229	19981126	00229	NM  	1998	11	26	98ZZZX4292       	1	19981030	G	5347		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 420	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK FS 420, LBL 24.						2	L	7	3 	4F				A3WE
1998112600230	19981126	00230	NM  	1998	11	26	98ZZZX4293       	1	19981105	G	5720	6521658374	WEB             			BOEING	727   	727231      	1384079	NM  										WS 203	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON RIGHT WING WBL:  203, BOTTOM WEB REAR SPAR						2	L	7	3 	4F				A3WE
1998112600231	19981126	00231	NM  	1998	11	26	98ZZZX4294       	1	19981105	G	5330		SKIN            			BOEING	727   	727231      	1384079	NM  										BS 720	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SKIN AT FS 720, STR 23R.						2	L	7	3 	4F				A3WE
1998112600232	19981126	00232	NM  	1998	11	26	98ZZZX4295       	1	19981105	G	5754		SKIN            			BOEING	727   	727231      	1384079	NM  										LE FLAP	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON RT WING NR 4 LE FLAP.  PITTING AROUND BOLT HOLE.						2	L	7	3 	4F				A3WE
1998112600233	19981126	00233	NM  	1998	11	26	98ZZZX4296       	1	19981105	G	5347		SEAT TRACK      			BOEING	727   	727231      	1384079	NM  										BS 1030 - 1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK FS 1030 - FS 1130, LBL 45.						2	L	7	3 	4F				A3WE
1998112600234	19981126	00234	NM  	1998	11	26	98ZZZX4297       	1	19981105	G	5315		FLOOR BEAM      			BOEING	727   	727231      	1384079	NM  										BS 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON TOP OF FLOOR BEAM AT ST 1110, LBL 55.						2	L	7	3 	4F				A3WE
1998112600235	19981126	00235	NM  	1998	11	26	98ZZZX4298       	1	19981105	G	5313		STRINGER        			BOEING	727   	727231      	1384079	NM  										BS 620-640	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON STR 18L STA 620 - STA 640.						2	L	7	3 	4F				A3WE
1998112600236	19981126	00236	NM  	1998	11	26	98ZZZX4299       	1	19981105	G	5311		FRAME           			BOEING	727   	727231      	1384079	NM  										BS 950	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON FRAME 950 ABOVE STR 23R.						2	L	7	3 	4F				A3WE
1998112600237	19981126	00237	NM  	1998	11	26	98ZZZX4300       	1	19981106	G	5311		FRAME           			BOEING	727   	727231      	1384079	NM  										BS 219	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION NOTED ON FRAME AT STA 219 STR 26R.						2	L	7	3 	4F				A3WE
1998112600238	19981126	00238	NM  	1998	11	26	98ZZZX4301       	1	19981030	G	5315		FLOOR BEAM      			BOEING	727   	727231      	1384079	NM  										BS 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK,  CORROSION NOTED ON FLOOR BEAM STA 1110 BL ZERO UPPER CHORD LOWER SURFACE.						2	L	7	3 	4F				A3WE
1998112600239	19981126	00239	NM  	1998	11	26	98ZZZX4302       	1	19981104	G	5330		SKIN            			BOEING	727   	727231      	1384079	NM  										BS 214	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64320					20053				DURING A C-CHECK, CORROSION NOTED AT STA 214R, AFT OF ACCESS DOOR.  THE SKIN IS BULGING AND PULLED RIVET HEADS.						2	L	7	3 	4F				A3WE
1998112600242	19981126	00242	NM  	1998	11	26	98ZZZX4305       	1	19980929	G	5320		CHANNEL         			BOEING	737   	737242      	1384477	NM  										BS 986	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING A C-CHECK, CORROSION NOTED ON AFT LAVATORY FORWARD WALL HAT CHANNEL.  (AFT OF FLOOR BEAM 986.5) LBL 16, APPROXIMA	TE.					2	L	7	2 	4F				A16WE
1998112600243	19981126	00243	NM  	1998	11	26	98ZZZX4306       	1	19980929	G	5315		FLOOR BEAM      			BOEING	737   	737242      	1384477	NM  										BS 1016	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION NOTED FLOOR BEAM AT INTERSECTION OF FRAME 1016 LBL 38.						2	L	7	2 	4F				A16WE
1998112600244	19981126	00244	NM  	1998	11	26	98ZZZX4307       	1	19980929	G	5320		SUPPORT         			BOEING	737   	737242      	1384477	NM  										BS 294-312	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION NOTED ON FLOOR BOARD SUPPORT FS 294 - FS 312, LBL 12, APROXIMATE.						2	L	7	2 	4F				A16WE
1998112600245	19981126	00245	NM  	1998	11	26	98ZZZX4308       	1	19980929	G	5315		FLOOR BEAM      			BOEING	737   	737242      	1384477	NM  										BS 967	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	159PL					21186				DURING MAINTENANCE CHECK, CORROSION NOTED ON UPPER T-CHORD OF FLOOR BEAM 967, LBL 5.						2	L	7	2 	4F				A16WE
1998112600247	19981126	00247		1998	11	26	98ZZZX4310       	1	19981103	G	7603	695525	WIRE            	HAMSTD      	7739004     						LYC   	ALF502	ALF502*     	41580	EA  					POWER LEVER	MISSING         	B			BN4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	05					F10527					REF:  FR40628. THROTTLE JAMMING WHEN ENGINE RUNNING.  SUBMITTER STATED POSSIBLE CAUSE AS MISSING Z-WIRE.											4	F			E6NE
1998112600248	19981126	00248	GL  	1998	11	26	98ZZZX4311       	2	19980818	G	7261	6876689	OIL PUMP        								ALLSN 	250C  	250C20      	03013	GL  					ENGINE	WORN            	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17		8    					CAE845049			ENGINE WAS REPORTED TO HAVE CAUSED SCAVENGE OIL FILTER BYPASS INDICATIONS TWO TIMES SINCE NEW.  UPON DISASSEMLY OF THE O	IL PUMP, FOUND IDLER GEAR, P/N 6875808, HAD WORN AWAY ALMOST HALF THE THICKNESS OF THE GEARSHAFT, P/N 6853346, AND HAD M	OVED ITS LOCATION IN THE PRESSURE PUMP BODY, P/N 6895845, BY WEARING AWAY THE WALL OF THE GEAR POCKET.									3	U			E4CE
1998112600249	19981126	00249	EA  	1998	11	26	98ZZZX4312       	1	19981106	G	2421	721428	IDG             			CNDAIR	CL600 	CL6001A11   	1900302	EA  										RT ENGINE	FAILED          	B			JO1R	O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			EA	25	90UC		6033 		103353	1023				THE NR 2 GENERATOR DROPPED OFF-LINE ON LANDING.  MAINTENNACE FOUND THE INTEGRATED DRIVE GENERATOR (IDG) DIFFERENTIAL IND	ICATORS POPPED AND THE OIL BLACK.  THE OIL-OUT LINE FILTER REVEALED CHUNKS OF METAL.  SUSPECT THE CONSTANT SPEED DRIVE F	AILED (CSD).  SUBMITTER STATED REASON FOR FAILURE UNKNOWN AT THIS TIME.				2	L	7	2 	4F			RT	A21EA
1998112600250	19981126	00250	CE  	1998	11	26	98ZZZX4313       	1	19980924	G	5610	26531820252	WINDSHIELD      			RKWELL	NA265 	NA26565     	7630107	CE  										COCKPIT	CRACKED         	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	05	33TR				82H96492	46547				AIRCRAFT WAS AT FL 390 FOR 2 HOURS. WINDSHIELD DE-ICE WAS OPERATING.  A SMALL AMOUNT OF ARCING ON THE COPILOT WINDSHIELD	 PROBES WAS OBSERVED.  THE WINDSHIELD OUTER PANE CRACKED IN SEVERAL PLACES.  THE COPILOT VIEW WAS NOT OBSCURED.  PRESSUR	IZATION WAS NOT LOST.  A DESCENT AND LANDING FOLLOWED WITH NO FURTHER PROBLEMS.  PROBLEM OCCURRED ON SEPT 24, 1998.  ACF	T TT:  12,667 HOURS.			2	L	7	2 	4J				A2WE
1998112600251	19981126	00251	CE  	1998	11	26	98ZZZX4314       	1	19981102	G	5753	05239012	SKIN            			CESSNA	172   	172R        	2072401	CE  										TE FLAP	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	97100	1032 				17280100				DURING ROUTINE MAINTENANCE, BOTH FLAP LEADING EDGE SKINS WERE FOUND CRACKED.  CRACKS WERE AROUND THE RIVET HOLES WERE P/	N 0523923 26, ATTACHES TO FLAPS ON THE BOTTOM SIDE.  CRACKS WERE .25 INCH - .50 INCH IN LENGTH, AND ALMOST EVERY RIVET H	OLE WAS AFFECTED.  SUBMITTER STATED POSSIBLE CAUSE WAS IMPROPER DEBURRING ON THE FACTORY'S PART.  ALL FLAP RIVETS SHOULD	 BE CHECKED CAREFULLY DURING PRE-FLIGHTS AND ROUTING MAINTENANCE.			1	H	7	1 	3O			NT	3A12
1998112600252	19981126	00252	CE  	1998	11	26	98ZZZX4315       	1	19981102	G	5753	052309511	SKIN            			CESSNA	172   	172R        	2072401	CE  										TE FLAP	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	97100	1032 				17280100				DURING A ROUTINE INSPECTION, NOTED BOTH LT AND RT TRAILING EDGE SKINS IN THE FLAP WELLS HAD MULTIPLE CRACKS RANGING FROM	 .25 INCH TO 2 INCHES EMANATING FROM RIVET HOLES.  MAINTENANCE CHECKED ALL TRAVEL OF THE FLAPS, FLAP TRAVEL WAS WITH SPE	CS AND NOT HITTING THE UNDERSIDE WALL.  UPON DRILLING OUT THE RIVETS, NOTICED NONE OF THE HOLES HAD BEEN DEBURRED PRIOR 	TO DIMPLING AND RIVET SPACING WAS EXCESSIVE FOR THE SIZE OF RIVETS USED.  RIVET SPACING = 2.1250 INCHES FOR A .1250 RIVE	T.		1	H	7	1 	3O			NT	3A12
1998112600253	19981126	00253	CE  	1998	11	26	98ZZZX4316       	1	19981001	G	2720	S100343A	BEARING         			CESSNA	172   	172R        	2072401	CE  										RUDDER PEDAL	MISSING         	B			VDNR	K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			SW	09	857CP					17280518				PILOT REPORTED 'MUSHY' BRAKE RESPONSE FROM COPILOT'S LEFT PEDAL.  INSPECTION REVEALED VERY LOOSE PEDAL.  FOUND BEARING F	OR PEDAL TORQUE TUBE MISSING.  SUBMITTER SUSPECTED BEARING WAS NOT INSTALLED AT FACTORY.  REPLACED BEARING.  OPS CHECK O	K.  AC TT:  146.6 HOURS.				1	H	7	1 	3O			NT	3A12
1998112600254	19981126	00254	NE  	1998	11	26	98ZZZX4317       	3	19981029	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	01			2428 					HJ450		DEBOND ON BLADE S/N 1539 BEYOND LIMITS - DISASSEMBLED PROPELLER.  O/H BLADE S/N 1539.  RE-ASSEMBLED PROPELLER AND STATIC	 BALANCED IAW MFG CMM.															5	C	P10NE
1998112600255	19981126	00255	NE  	1998	11	26	98ZZZX4318       	3	19981029	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	01			2955 					HJ433		EROSION SHIELD DEBONDED UNDER DEICE BOOT, DEBOND BEYOND LIMITS.  DISASSEMBLED PROPELLER - O/H BLADE S/N 2132 - RE-ASSEMB	LED PROPELLER AND STATIC BALANCED IAW MFG CMM.															5	C	P10NE
1998112600256	19981126	00256	NE  	1998	11	26	98ZZZX4319       	3	19981029	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CE	01			793  					HJ551		BLADE S/N 714MA CRACKED AND DEBONDED EROSION SHIELD UNDER DEICE BOOT.  REPAIRED AND INSTALLED NEW DEICE BOOT IAW MFG CMM	.															5	C	P10NE
1998112600258	19981126	00258	CE  	1998	11	26	98ZZZX4321       	1	19981102	G	2842	C6680020301	TRANSMITTER     			CESSNA	150   	152         	2071835	CE  										FUEL CELL	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	4915P	9565 				15284840				SK152-21A KIT WAS INSTALLED DUE TO ERRONEOUS FUEL QUANTITY INDICATIONS.  DURING REMOVAL OF OLD TRANSMITTERS. NOTICED THE	 FLOATS WERE WORN FROM CONTACT WITH THE INSIDE OF THE FUEL TANK AND ALSO AROUND PIVOT HOLE WHERE THEY ATTACH TO TRANSMIT	TERS.  SUBMITTER STATED SHOULD BE ON INSPECTION INTERVAL SUCH AS 500 HOURS OR SO.				1	H	7	1 	3O			NT	3A19
1998112600259	19981126	00259	SO  	1998	11	26	98ZZZX4322       	1	19981110	G	3230		CASTING         			PIPER 	PA28  	PA28140     	7102802	SO  										MLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	13	7582R	4500 				2822149				MAIN LANDING GEAR CASTINGS CRACKED WHERE EARS FOR SCREWS ATTACH.  SUBMITTER SUSPECTS DUE TO ALLOWING WEAR TO LET SCISSOR	 ATTACHMENT GET SLOPPY AND SHIMMY BEATING ON EARS.  RIGHT REQUIRED DYE CHECK TO DETECT, LEFT, OBVIOUS TO NAKED EYE, IF C	LEANED UP.  THIS IS SECOND AIRCRAFT IN THIS AREA IN 3 MONTHS WITH PROBLEM.  SUBMITTER SUGGESTED REGULAR DISASSEMBLY, CLE	AN AND INSPECT BY DYE CHECK, AND CONTROL OF LOOSENESS BY SHIMS.			1	L	7	1 	3O				2A13
1998112600260	19981126	00260	SO  	1998	11	26	98ZZZX4323       	2	19981001	G	8530	646657	CYLINDER        			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520R    	17040	SO  					NR 1-6	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	67VM		300  			P21000568	512174			DURING ANNUAL INSPECTION, FOUND ALL SIX CYLINDERS CRACKED BETWEEN TOP SPARK PLUG BOSS AND FUEL INJECTOR NOZZLE BOSS.						1	H	7	1 	3O	3	O		3A21    	E8CE
1998112600261	19981126	00261	SO  	1998	11	26	98ZZZX4324       	1	19981015	G	5700		LIFT            			PIPER 	PA18  	PA18150     	7101828	SO  										LT REAR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	5767D					185257				UNAIRWORTHY DUE TO CORROSION IN LEFT REAR LIFT STRUT AS INDICATED IN PARAGRAPH 'A'.  AD NOTE 93-10-06.						1	H	7	1 	3O				1A2
1998112600262	19981126	00262	CE  	1998	11	26	98ZZZX4325       	1	19981103	G	3242	16402505	BRAKE DISC      	CLEVELAND   		BEECH 	36    	A36         	1151604	CE  										MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	711SK	1615 			125B730	S877				BRAKE DISC WAS CRACKED AROUND ALL THREE BOLT HOLES AND HAD SOME RADIAL CRACKS ON THE DISC BRAKE SURFACE.  THIS DISC WAS 	INSTALLED ON THE AIRCRAFT ON 4-13-88.  NO APPARENT REASON WAS FOUND FOR THIS FAILURE.					1	L	7	1 	3O				3A15
1998112600263	19981126	00263	SO  	1998	11	26	98ZZZX4326       	1	19981016	G	3213	31768003	HOUSING         			PIPER 	PA23  	PA23250     	7102308	SO  										NLG	CRACKED         	B			FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	153LM	2420 				277754019				DURING INSPECTION OF NOSE GEAR, FOUND NOSE GEAR HOUSING CRACKED AT LOWER FLANGE CLOSE TO STRUT RETENSION SNAP RING.  SUB	MITTER STATED THIS AREA SHOULD BE INSPECTED VERY CLOSE DURING ROUTINE INSPECTIONS.					1	L	7	2 	3O				1A10
1998112600264	19981126	00264	CE  	1998	11	26	98ZZZX4327       	1	19981023	G	2120	8697283	PLENUM ASSEMBLY 			BEECH 	18    	C45H        	1151018	CE  										BLEED AIR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	400WA	3139 			IP3359	AF764				DURING A FUEL NOZZLE TIME CHANGE, FOUND A ONE INCH CRACK IN THE PLENUM BETWEEN THE BLEEED AIR BOSS AND P2 BOSS.  THIS IS	 AN AREA WHERE THE WELDS FOR THE TWO BOSSES TOUCH AT THEIR OUTER EDGES, AND THIS IS WHERE THE CRACK OCCURRED.  THE CRACK	S EXTEND .1250 INCH PAST THE WELDED AREA BOTH FORE AND AFT.  IT IS LIKELY THE CRACKS WOULD HAVE CONTINUED TO EXPAND.  SU	BMITTER STATED POSSIBLE CAUSE IS THAT ONE OR BOTH OF THE BOSSES WERE IMPROPERLY WELDED TO THE PLENUM, THOUGH FROM OUTWAR	D APPEARANCE THE WELDS LOOKED GOOD AND SUGGESTED THIS AREA BE CLOSELY INSPECTED AT ALL REGULAR ENGINE INSPECTIONS.		1	L	7	2 	3R				A765
1998112600265	19981126	00265		1998	11	26	98ZZZX4328       	4	19980706	G	2312	09601D8D0008	RECEIVER        	BENDIX      	KX155       	CESSNA	310   	310R        	2074245	CE  										E/E BAY	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	37242					310R0969				RECEIVER -  PART FAILED AND SMOKED.						1	L	7	2 	3O				3A10
1998112600266	19981126	00266	CE  	1998	11	26	98ZZZX4329       	1	19981013	G	3246	31108819	BUSHING         	WIPLINEINC  	3730        	CESSNA	206   	U206G       	2073356	CE  										LT FLOAT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	94EL				37259	U20604131				DEFECT MAY HAVE BEEN CAUSED BY OVERCENTER NOT GOING TO FULL TRAVEL.						1	H	7	1 	3O				A4CE
1998112600267	19981126	00267	CE  	1998	11	26	98ZZZX4330       	1	19981013	G	3246	31108819	BUSHING         	WIPLINEINC  	3730        	CESSNA	206   	U206G       	2073356	CE  										RT FLOAT	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	94EL				37260	U20604131				DEFECT MAY HAVE BEEN CAUSED BY OVERCENTER NOT GOING TO FULL TRAVEL.						1	H	7	1 	3O				A4CE
1998112600268	19981126	00268		1998	11	26	98ZZZX4331       	4	19981001	G	3451	SW303	SWITCH          	NARCO       	DME890      	CESSNA	150   	150M        	2071830	CE  										COCKPIT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	704HQ	1    			17901	15078627				UNIT DOES NOT TURN OFF.  SUBMITTER SUSPECTS DEFECTIVE ON/OFF SWITCH.  UNIT HAS APPROXIMATELY ONE HOUR TOTAL TIME.  RETUR	NED UNIT TO FACTORY FOR REPAIR.					1	H	7	1 	3O				3A19
1998112600269	19981126	00269	CE  	1998	11	26	98ZZZX4332       	1	19981001	G	2434	MC012	ECU             			CESSNA	172   	172R        	2072401	CE  										E/E BAY	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	419ER					17280251				A BUS 2 FAILURE WAS OBSERVED WHEN THE AUDIO PANEL, NAV/COM 1 AND GPS FAILED WHICH RESULTED IN A LOSS OF COMMUNCIATION. T	HE FAULT WAS LOCATED AT THE JUNCTION OF THE BUS 2 WIRE AND F2 FUSE HOLDER TERMINAL IN THE EPCU.  THE SOLDER JOINT HAD BR	OKEN DUE TO A LACK OF SOLDER.  ARCING HAD RESULTED IN THE MELTING OF THE PLASTIC AROUND THE TERMINAL.  THE EPCU WAS REPL	ACED.  SUBMITTER STATED SUFFICIENT SOLDER AT THE JUNCTION WOULD HAVE PREVENTED THE FAILURE.			1	H	7	1 	3O			NT	3A12
1998112600272	19981126	00272	SO  	1998	11	26	98ZZZX4335       	1	19980925	G	7603	1269304	THROTTLE        			PIPER 	PA28  	PA28140     	7102802	SO  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	5548F	4433 				2824886				THE HOLE AT THE LOWER PANEL INSTRUMENT STRUCTURE WHERE THE THROTTLE CONTROL PASSES THROUGH AND SECURES TO THE PANEL WAS 	FOUND WITH SEVERAL CRACKS RADIATING OUTWARD FROM THE DRILLED HOLE.  THESE CRACKS WERE APPROXIMATELY 1 INCH IN DIAMETER A	ROUND THE .3750 INCH HOLE FOR THE THROTTLE.  SUBMITTER STATED AGE AND/OR A LOOSE THROTTLE MAY HAVE CAUSED THIS CONDITION	.  CLOSE ATTENTION DURING INSPECTIONS SHOULD BE PLACED ON THIS AREA.  THIS IS A VERY SERIOUS CONDITION TO SAFETY AT ADVA	NCING TO FULL THROTTLE.  THE CONTROL COULD BE PUSHED THROUGH THE PANEL.		1	L	7	1 	3O				2A13
1998112600273	19981126	00273	SO  	1998	11	26	98ZZZX4336       	1	19980818	G	3222	752731	RETAINING CAP   			PIPER 	PA31  	PA31350     	7103110	SO  										NLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	515RM	3120 				317405159				DISCOVERED DURING C/W AD 97-07-03 POSSIBLY DUE TO OVERTIGHTENING TENSION BOLT.  SUBMITTER SUGGESTED DESIGN COULD USE SPA	CER BETWEEN PLUGS.					1	L	7	2 	3O				A20SO
1998112600274	19981126	00274	SO  	1998	11	26	98ZZZX4337       	1	19980818	G	2730	7105603	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	09	515RM					317405159				DURING 50-HOUR INSPECTION, 6FEB98 ORDERED PIPER 71056-03 SPRING, ELEVATOR BUNGEE TO C/W SB 626C.  NEW SPRING WAS INSTALL	ED AT 37 POUNDS TENSION WITH CALIBRATED SCALE, BUT EXTENDED TO WITHIN 1.50 INCHES OF LINK END.					1	L	7	2 	3O				A20SO
1998112600275	19981126	00275		1998	11	26	98ZZZX4338       	4	19981026	G	2312	KY195B	VHF             			HUGHES	369   	369D        	4470706	WP  										E/E BAY	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J		218  		5299	900801D				RADIO RECEIVES, BUT DOES NOT TRANSMIT.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998112600276	19981126	00276		1998	11	26	98ZZZX4339       	4	19981027	G	3420	PAI700	MAGNETIC COMPASS			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J				33536	900801D				MAGNETIC COMPASS STUCK ON 15 DEGREES.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998112600277	19981126	00277	WP  	1998	11	26	98ZZZX4340       	1	19981015	G	6230	369A76132	LINK ASSY       			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				LINK ASSEMBLY BEARINGS WORN.						1	G	7	1 	3U				H3WE
1998112600278	19981126	00278	WP  	1998	11	26	98ZZZX4341       	1	19981019	G	6230	369D25100505	TRANSMISSION    			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	LEAKING         	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	369AW	5267 	2267 		0966	470117D				INPUT SHAFT SCORED BY DRIVE BELT PULLEY CAUSING LEAK AT SEAL.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998112600279	19981126	00279	WP  	1998	11	26	98ZZZX4342       	1	19981015	G	6230	369A7607501	LINK ASSY       			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				LINK ASSY BEARINGS WORN.						1	G	7	1 	3U				H3WE
1998112600280	19981126	00280	WP  	1998	11	26	98ZZZX4343       	1	19981015	G	6230	369A7608501	LINK ASSY       			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				LINK ASSY BEARINGS WORN.						1	G	7	1 	3U				H3WE
1998112600281	19981126	00281	WP  	1998	11	26	98ZZZX4344       	1	19981015	G	6230	369A76131	LINK ASSY       			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				LINK ASSY BEARING WORN.						1	G	7	1 	3U				H3WE
1998112600282	19981126	00282	WP  	1998	11	26	98ZZZX4345       	1	19981026	G	2430	A700ZG	RCR             			HUGHES	369   	369D        	4470706	WP  										GEN CONTROL	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P		1744 		1644	611002D				GENERATOR GOES OFF-LINE.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998112600283	19981126	00283	GL  	1998	11	26	98ZZZX4346       	2	19981015	G	7321	104900A5	FUEL CONTROL    			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	49718		3144 		8AFA27	1917				FUEL CONTROL SUSPECTED TO ALLOW AIR INTO FUEL SYSTEM.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998112600284	19981126	00284	NE  	1998	11	26	98ZZZX4347       	1	19981102	G	3240	7025001004101	PIN             			SKRSKY	S76   	S76C        	8143008	NE  										PARKING BRAKE	SEPARATED       	B			JZBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	165ML	74   			04603	760471				ROLL PIN SEPARATED FROM ARM AND IS PART OF THE VALVE ASSY.  THE ROLL PIN ACTUATES A MICROSWITCH THAT OPERATES THE PARKIN	G BRAKE LIGHT.  IF PIN SEPARATES FROM THE ARM, THE PARKING BRAKE INDICATION LIGHT STAYS ILLUMINATED.  SUBMITTER STATED T	HIS IS THE 4TH TIME THIS VALVE HAS BEEN REPLACED FOR THE SAME DISCREPANCY WITHIN 12 MONTHS.				1	G	7	2 	3U			NC	H1NE
1998112600285	19981126	00285	SW  	1998	11	26	98ZZZX4348       	1	19981023	G	2430	CSV115212A	VOLT REGULATOR  			BELL  	204   	UH1H        	1181407	SW  										DC SYSTEM	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG		42   		CR7141A	7221588				VOLTAGE REGULATOR WILL NOT PRODUCE VOLTAGE.						1	G	7	1 	4U				EXPA1G71
1998112600286	19981126	00286	SW  	1998	11	26	98ZZZX4349       	1	19981028	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R DRIVE	LOOSE           	B			BXOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	407MC	651  				53087				FOUR MOUNT BOLT NUTS WERE FOUND LOOSE DURING TORQUE CHECK REQUIRED BY PARAGRAPH B OF AD 97-24-17.  DISC PACK WAS REMOVED	 AND REPLACED WITH NEW DISC PACK.					1	G	7	1 	3U			O	H2SW
1998112600288	19981126	00288	NE  	1998	11	26	98ZZZX4351       	2	19980925	G	7230	0292152880	COVER           			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					COMPRESSOR	CRACKED         	B		A	ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	2127S		2000 			2213	7119			DURING ROUTINE 100 HOUR INSPECTION, THE COMPRESSOR IMPELLER WAS INSPECTED DUE TO THE RECENT PROBLEMS WITH COMPRESSOR COV	ER CRACKING.  THE IMPELLER WAS FOUND UNSERVICEABLE DUE TO THE COMPRESSOR COVER BEING CRACKED AND HAD TO BE REMOVED FROM 	SERVICE.  SUBMITTER STATED FLEET PREVIOUSLY INSPECTED AND WILL CONTINUE TO PERFORM INSPECTIONS AT PERIODIC INTERVALS.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1998112600289	19981126	00289	NE  	1998	11	26	98ZZZX4352       	2	19980915	G	7230	0292152880	COVER           			SNIAS 	350   	AS350B1     	8680811	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					COMPRESSOR	CRACKED         	B		A	ULXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	216LA		2850 			2251	7086			AFTER ROUTINE 100-HOUR INSPECTION, THE SUBSEQUENT GROUND RUN REVEALED AN ODD NOISE COMING FROM THE ENGINE.  A THOROUGH I	NSPECTION WITH BORESCOPE THROUGH THE COMPRESSOR BLEED VALVE OEPNING OF MODULE MO3 REVEALED A PIECE OF THE COMPRESSOR COV	ER IN FRONT OF THE CENTRIFICAL COMPRESSOR IMPELLER HAD BROKEN LOOSE AND WAS INGESTED CAUSING SIGNIFICANT DAMAGE TO THE I	MPELLER.  THE TOTAL TIME OF THE COMPRESSOR COVER IS UNKNOWN AS IT IS AN 'ON CONDITION' PART.  THE COMPRESSOR MODULE MO3 	HAD A TSO OF 2,850 HOURS WITH A TBO OF 3,000 HOURS.  THE IDENTICAL SITUATION OCCURRED ON 8-4-98, WITH A DIFFERENT AIRCRA	FT AND ENGINE.  THIS COMPRESSOR MODULE MO3 HAD A TSO OF 2,634 HOURS.	1	G	7	1 	3U	3	U		H9EU    	E19EU
1998112600290	19981126	00290	SW  	1998	11	26	98ZZZX4353       	1	19981022	G	2842	EA4703587	SENSOR          			BELL  	206   	206B        	1181511	SW  										FUEL CELL	MISMANUFACTURED 	B	S	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	193P					2985				RECEIVED PART FROM BELL HELICOPTER IN REPAIRED CONDITION WITH A FORM 8130 ISSUED BY BF GOODRICH.  PART WAS INSTALLED IN 	AIRCRAFT FOR 23.7 HOURS BEFORE FAILURE.  FOUND FLOAT ARM PIVOT PIN MISSING UPON REMOVAL.  SUBMITTER SUSPECTS PIN WAS IMP	ROPERLY STAKED.  PIN WAS RECOVERED FROM AIRCRAFT FUEL TANK.				1	G	7	1 	3U				H2SW
1998112600291	19981126	00291	SW  	1998	11	26	98ZZZX4354       	1	19981023	G	6220	412010190103	SPLINDLE        		41201015643 	BELL  	412   	412         	1182202	SW  										MAIN ROTOR	FAILED          	D		A		A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			WP	19	411DE	3214 			HM1183	36030				DURING FLIGHT, PILOTS NOTED HELICOPTER HAD SUDDENLY DEVELOPED A VERTICAL AND LATERAL 'SHUFFLE' VIBRATION.  UPON LANDING,	 MAINT INSPECTED ROTOR SYSTEM.  THE MAIN ROTOR SPINDLE LASTOMERIC DAMPER BEARING ASSY ON THE 'RED' BLADE SPINDLE ASSY WA	S FOUND SEPARATED FROM THE INNER BEARING SLEEVE.  A NEW SPINDLE AND DAMPER BEARING ASSY WAS ORDERED FOR THE 'RED' BLADE 	AND THE OPPOSITE SIDE 'BLUE' BLADE POSITION.  COMPONENTS REPLACED AND A MAIN ROTOR SYSTEM TRACK AND BALANCE ACCOMPLISHED	.  HELICOPTER OPER WAS SATISFACTORY DURING TEST FLIGHT.  SUBMITTER RECOMMENDED A 'RETIREMENT TIME' BE ESTABLISHED FOR TH	E DAMPER BEARING ASSY TO PREVENT IN-FLIGHT FAILURES AND POSSIBLY SAFETY OF FLIGHT PROBLEMS ASSOCIATED WITH THE FAILURE.	1	G	7	2 	4U				H4SW
1998112600292	19981126	00292	EU  	1998	11	26	98ZZZX4355       	1	19981016	G	5230		DOOR            			SNIAS 	350   	AS350B      	8680801	EU  										CARGO BAY	UNLATCHED       	C	S	A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	09	350AS	1470 				2338				DURING FLIGHT TRANSITION TO HOVER, LEFT CARGO DOOR UNLATCHED AND CAME OPEN IN-FLIGHT. THERE IS ONLY ONE LOCKING MECHANIS	M ON DOOR.					1	G	7	1 	3U				H9EU
1998112600293	19981126	00293	EU  	1998	11	26	98ZZZX4356       	1	19981016	G	5330		PANEL           			SNIAS 	350   	AS350B      	8680801	EU  										FUSELAGE	SEPARATED       	C		A		B	A			EMER. DESCENT           	UNSCHED LANDING         			D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	09	350AS	1470 				2338				DURING A PASSENGER FLIGHT, AFT BELLY PANEL DEPARTED ACFT AND STRUCK TAIL ROTOR.  THE HELICOPTER MADE AN UNEVENTFUL LANDI	NG IN AN OPEN FIELD.  POST-FLIGHT INSPECTION REVEALED THAT LATCHES ON LEFT SIDE OF AIRCRAFT HAD COME LOOSE ENOUGH TO BRE	AK UP UNDER FLIGHT PRESSURE.  RIGHT SIDE LATCHES WERE COMPLETELY RIPPED FROM THE STRUCTURE THEY WERE MOUNTED ON.  SUBMIT	TER SUSPECTS A PASSENGER MISTOOK BELLY PANEL LATCHES FOR CARGO DOOR AND DID NOT PROPERLY RE-LATCH BELLY PANEL.			1	G	7	1 	3U				H9EU
1998112600294	19981126	00294	SW  	1998	11	26	98ZZZX4357       	1	19981028	G	5302	206033004103A	SKIN            			BELL  	206   	206L1       	1182107	SW  										TAILBOOM	CRACKED         	H	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	119TA	9945 			AOKB00735	45263				ON THE LOOK-OVER INSPECTION, FOUND THE TAILBOOM CRACKED LEFT SIDE OF THE ELEVATOR MOUNT.  CRACK STARTED AT NR 5 BOLT HOL	E FROM TOP.  WENT THROUGH 5 BOLT HOLES AND INTO TAILBOOM.					1	G	7	1 	3U				H2SW
1998120400278	19981204	00278	NE  	1998	12	4	98ZZZX4359       	2	19981027	G	7320	30727491	LINE            	GARRTT      		CESSNA	650   	650         	2076802	CE  	GARRTT	TFE731	TFE7313B    	01518	NE  					OIL SYSTEM	CHAFED          	B				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NM	01	39WP	6620 				6500039	P87218			PILOT NOTED LEFT OIL PRESSURE DROPPING IN-FLIGHT AND THAT IT WOULD FOLLOW THROTTLE MOVEMENT.  PILOT SHUT LEFT ENGINE DOW	N AND LANDED 15 MINUTES LATER NORMALLY.  INVESTIGATION REVEALED NR 6 BEARING PRESSURE OIL LINE CHAFED THROUGH FROM CONTA	CT WITH CESSNA BLEED AIR LINE P/N 6214506-1.  TO FIND AND REPAIR LEAK REQUIRED REMOVAL OF THRUST REVERSER AFTER BODY AND	 REMOVAL OF STAINLESS SHROUD THAT FORMS INSIDE DIAMETER OF BYPASS DUCT.  THIS CONDITION CAN ONLY BE PREVENTED AT ENGINE 	BUILD-UP OR MPI INSPECTION WHERE ADEQUATE QUALITY WORKMANSHIP AND INSPECTION AVOIDS THIS HAPPENING.		2	L	7	2 	4F	4	F		A9NM    	E6WE
1998120400279	19981204	00279	EU  	1998	12	4	98ZZZX4360       	1	19981102	G	5753	F10A124201A1	FLAP TRACK      			AMD   	FALC10	FALCON10    	2730101	EU  										RT TE FLAP	CRACKED         	B	S		ABOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	212FJ	6493 				147				DURING B-INSPECTION OF AIRFRAME, MAINTENANCE DISCOVERED THE CRACK IN THE LOWER CHANNEL OF THE RIGHT INBOARD FLAP, INBOAR	D TRACK.  THE TRACK WAS REMOVED AND REPLACED AND THE ROLLER FOR THAT TRACK WAS REPLACED.  NO BINDING OR ABNORMAL WEAR WA	S DISCOVERED EXCEPT FOR THE CRACK.				2	L	7	2 	4F				A33EU
1998120400280	19981204	00280	NM  	1998	12	4	98ZZZX4361       	1	19981029	G	2740	69778551	SPRING          			BOEING	737   	737*        		NM  										AUXILIARY BRAKE	FAILED          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		18584			KE00438					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  INSTALLED SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400281	19981204	00281	NE  	1998	12	4	98ZZZX4362       	3	19980618	G	6111		BLADE           			EMB   	120   	EMB120ER    	3260203	SO  						HAMSTD	14RF	14RF9       	NE  	PROPELLER	DAMAGED         	B			NQ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	638AS	27102	5622 		849965	120282		9011091873		DISCONTINUITY - NR 2 RIGHT BLADE FILLET FAILED INSPECTION.  DAMAGE TO THE FILLET AREA, BLADE FACE SIDE.  THE BLADE IS SC	RAP.  CUSTOMER:  ATLANTIC SOUTHEAST AIRLINES.					2	L	7	2 	4T			RT	A31SO   		6	C	P11NE
1998120400282	19981204	00282	SO  	1998	12	4	98ZZZX4363       	2	19980929	G	8520	641931981	THRU-BOLT       								CONT  	O520  	IO520A      	17032	SO  					CRANKCASE	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99							112837R			THRU-BOLT IN CRANKCASE FOUND BROKEN.											3	O			E5CE
1998120400283	19981204	00283	EU  	1998	12	4	98ZZZX4364       	1	19981108	G	2520	3410	PASSENGER SEAT  			AIRBUS	320   	A320232     	3930326	EU  										CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	401UA					435				DURING FIRST HEAVY MAINTENANCE VISITS FOR AIRBUS A320-232, MAINTENANCE FOUND VIRTUALLY A 100 PERCENT FAILURE RATE OF THE	 SEAT PANS ON RECARO MODEL 3410, 720 SERIES PASSENGER SEATS.  THE FAILURE ARE CRACKS IN THE SEAT PANS ADJACENT TO THE AT	TACHMENT HOLES AT THE FORWARD EDGE OF THE SEAT PAN.  THESE HOLES ACCEPT SCREWS THAT ATTACH TO THE SEAT PAN TO THE SEAT S	TRUCTURE.  THERE ARE 3 OF THESE ATTACHMENT HOLES, AND ON EACH PAN, A MINIMUM OF ONE HOLE HAS BEEN FOUND WITH CRACKS ADJA	CENT TO IT.  SUBMITTER STATED, IN MOST INSTANCES, 2 OF THE 3 HOLES HAVE BEEN FOUND WITH CRACKED AREAS ADJACENT TO THEM.		2	L	7	2 	4F			RT	A28NM
1998120400284	19981204	00284	NM  	1998	12	4	98ZZZX4365       	1	19981008	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		17844			KE01547					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  INSTALLED SPRINGS, P/N 69-777855-2.						2	L	7	2 	4F			RT	A16WE
1998120400285	19981204	00285	NM  	1998	12	4	98ZZZX4366       	1	19980413	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		1652 			KE01603					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED SPRINGS WITH P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400286	19981204	00286	NM  	1998	12	4	98ZZZX4367       	1	19980427	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		15773			KE01556					FAILED FUNCTIONAL TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400287	19981204	00287	NM  	1998	12	4	98ZZZX4368       	1	19980423	G	2720	69579071	SPRING          		65C254105   	BOEING	737   	737*        		NM  										RUDDER	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					SC921					FRACTURED SPRING DUE TO FATIGUE, STRESS CORROSION.  REPLACED WITH SPRINGS, P/N 69-57907-2.						2	L	7	2 	4F			RT	A16WE
1998120400288	19981204	00288	NM  	1998	12	4	98ZZZX4369       	1	19980422	G	2752	14K311	FAN             	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1988					CRACK INDICATION DUE TO CASTING FLAW.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400289	19981204	00289	NM  	1998	12	4	98ZZZX4370       	1	19980422	G	2740	14K311	FAN             	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		33165	6428 		WN0001					CRACK INDICATION DUE TO CASTING FLAW.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400290	19981204	00290	NM  	1998	12	4	98ZZZX4371       	1	19980422	G	2740	14K311	FAN             	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		35689	6423 		6353					CRACK INDICATION DUE TO CASTING FLAW.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400291	19981204	00291	NM  	1998	12	4	98ZZZX4372       	1	19980422	G	2752	14K311	FAN             	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2898					CRACK INDICATION DUE TO CASTING IN FLAW.  SUBMITTER SUGESTED CLEANING UP EDGES DURING MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400292	19981204	00292	NM  	1998	12	4	98ZZZX4373       	1	19980422	G	2752	14K311	FAN             	TELEFLEX    	79ET100     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					5260					CRACK INDICATION DUE TO CASTING FLAW.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400293	19981204	00293	NM  	1998	12	4	98ZZZX4374       	1	19980422	G	2752	14K311	FAN             	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		15472			7661					CRACK INDICATION DUE TO CASTING FLAW.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400294	19981204	00294	NM  	1998	12	4	98ZZZX4375       	1	19980321	G	3232	119260	GLAND ASSY      	ROTOL       	1U11925     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					454AB					LANDING GEAR ACTUATOR LEAKING DUE TO PITTING.  SUBMITTER SUGGESTED TO ASSEMBLE WITH RTV.						2	L	7	4 	4F			RT	A20WE
1998120400295	19981204	00295	NM  	1998	12	4	98ZZZX4376       	1	19980429	G	2740	69778551	SPRING          		65C3475111  	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KE00638					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  SUBMITTER SUGGESTED REPLACING WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400296	19981204	00296	NM  	1998	12	4	98ZZZX4377       	1	19980428	G	2740	69778551	SPRING          		65C3475111  	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KE00645					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400297	19981204	00297	NM  	1998	12	4	98ZZZX4378       	1	19980505	G	2752	14K311	FAN             	TELEFLEX    	793T1005    	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1988					NDI INDICATION CRACKED DUE TO CASTING FLAW.  SUBMITTER SUGGESTED CLEANING UP DURING THE MANUFACTURING PROCESS.						2	L	7	2 	4F			RT	A16WE
1998120400298	19981204	00298	NM  	1998	12	4	98ZZZX4379       	1	19980522	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		17924			KE01457					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400299	19981204	00299	NM  	1998	12	4	98ZZZX4381       	1	19980519	G	3230	108510	BODY            	ROTOL       	1U1085      	BOEING	727   	727         	1384001	NM  										VALVE	DAMAGED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					345					RIG PIN SLOT IS BROKEN OF DUE TO FATIGUE OR ABUSE.  SUBMITTER SUGGESTED USING A REMOVAL SLOT.						2	L	7	3 	4F				A3WE
1998120400300	19981204	00300	NM  	1998	12	4	98ZZZX4382       	1	19980519	G	2740	69778551	SPRING          		65C3475111  	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		30342	17594		KE00713					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400301	19981204	00301	NM  	1998	12	4	98ZZZX4383       	1	19980507	G	2740	69778551	SPRING          		65C3475111  	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		32103	17764		KE00543					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400302	19981204	00302	NM  	1998	12	4	98ZZZX4384       	1	19981019	G	3240	511531	HOUSING         	PNEUDRAULICS	5059        	BOEING	737   	737*        		NM  										SHUTTLE VALVE	CRACKED         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4208					CRACK IN BOLT HOLE ALONG SEAM OF HOUSING OF SHUTTLE VALVE.						2	L	7	2 	4F			RT	A16WE
1998120400303	19981204	00303	NM  	1998	12	4	98ZZZX4385       	1	19981019	G	3240	511531	HOUSING         	PNEUDRAULICS	50592       	BOEING	737   	737*        		NM  										SHUTTLE VALVE	CRACKED         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					2544A					CRACK IN BOLT HOLE ALONG SEAM OF HOUSING IN SHUTTLE VALVE.						2	L	7	2 	4F			RT	A16WE
1998120400304	19981204	00304	NM  	1998	12	4	98ZZZX4386       	1	19980409	G	2752	14K311	FAN             	TELEFLEX    	79T1007     	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		8856 			4223					CRACK INDICATION DUE TO POOR CASTING.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PHASE.						2	L	7	2 	4F			RT	A16WE
1998120400305	19981204	00305	NM  	1998	12	4	98ZZZX4387       	1	19980409	G	2752	14K311	FAN             	TELEFLEX    	793T1007    	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		6238 			6931					CRACK INDICATION DUE TO POOR CASTING.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PHASE.						2	L	7	2 	4F			RT	A16WE
1998120400306	19981204	00306	NM  	1998	12	4	98ZZZX4388       	1	19980409	G	2752	14K311	FAN             	TELEFLEX    	793T1007    	BOEING	737   	737*        		NM  										TE FLAP	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		6216 			2660					CRACK INDICATION DUE TO POOR CASTING.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PHASE.						2	L	7	2 	4F			RT	A16WE
1998120400307	19981204	00307	NM  	1998	12	4	98ZZZX4389       	1	19980409	G	3232	119362	BARREL          	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					NWA71					DEEP PITS ON EXTERIOR UNDER GLAND NUT POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE.						2	L	7	4 	4F			RT	A20WE
1998020500204	19980205	00204	SO  	1998	2	5	98ZZZX439        	1	19980113	G	2913	268028	PUMP            			PIPER 	PA31  	PA31325     	7103105	SO  										HYDRAULIC	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	101M				OB11552	318112049				INSPECTION FOR FLUID COMING OUT OF PUMP DRAIN.  REMOVED HYDRAULIC PUMP, FOUND SHAFT HAD SEPARATED FROM IMPELLER.  NOTE: 	 SHAFT WAS NOT SHEARED AT SHEAR POINT.  HOBBS:  1,162.8.					1	L	7	2 	3O				A20SO
1998120400308	19981204	00308	NM  	1998	12	4	98ZZZX4390       	1	19980708	G	3232	119383	PISTON          	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					262					LANDING GEAR DOOR ACTUATOR CRACKED.						2	L	7	4 	4F			RT	A20WE
1998120400309	19981204	00309	NM  	1998	12	4	98ZZZX4391       	1	19980408	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAR TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KE01468					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400310	19981204	00310	NM  	1998	12	4	98ZZZX4392       	1	19980408	G	3232	119361	END CAP         	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					350A					PITTING IN END CAP POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400311	19981204	00311		1998	12	4	98ZZZX4393       	1	19980408	G	3232	119360	GLAND ASSY      		1U11935     															ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	747*				350A					PITTING IN GLAND ASSY POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.
1998120400312	19981204	00312	NM  	1998	12	4	98ZZZX4394       	1	19980408	G	3232	119361	END CAP         	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					NWA71					END CAP PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400313	19981204	00313	NM  	1998	12	4	98ZZZX4395       	1	19980408	G	3232	119360	GLAND ASSY      	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					NWA71					GLAND ASSY PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400314	19981204	00314	NM  	1998	12	4	98ZZZX4396       	1	19980408	G	3232	119361	ENG ECAP        	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					262					END CAP PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400315	19981204	00315	NM  	1998	12	4	98ZZZX4397       	1	19980408	G	3232	119360	GLAND ASSY      	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					262					GLAND ASSY PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400316	19981204	00316	NM  	1998	12	4	98ZZZX4398       	1	19980408	G	3232	119361	END CAP         	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					261					END CAP PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400317	19981204	00317	NM  	1998	12	4	98ZZZX4399       	1	19980408	G	3232	119360	GLAND ASSY      	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					261					GLAND ASSY PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998020500205	19980205	00205	SO  	1998	2	5	98ZZZX440        	1	19980105	G	7602	455230	CONTROL CABLE   			PIPER 	PA23  	PA23250     	7102308	SO  										THROTTLE	FAILED          	B			TRKR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	13930					274575				WHILE ATTEMPTING TO START THE ENGINE, THE THROTTLE CABLE WAS STIFF.  UPON PULLING THE THROTTLE BACK TO IDLE, THE CABLE B	ROKE.  AFTER REMOVING THE CABLE, FOUND THE CABLE HAD BEEN BROKEN FOR SOME TIME AND THAT ONE STRAND WAS ALL THAT WAS ALLO	WING THE THROTTLE TO OPERATE.  SUBMITTER STATED CLOSER ATTENTION NEEDS TO BE PAID TO THE CABLES DURING INSPECTION.				1	L	7	2 	3O			 	1A10
1998120400318	19981204	00318	NM  	1998	12	4	98ZZZX4400       	1	19980408	G	3232	119360	GLAND ASSY      	ROTOL       	1U11935     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					00016					GLAND ASSY PITTED POSSIBLY DUE TO MOISTURE. SUBMITTER RECOMMENDED USING RTV TO MINIMIZE CORROSION.						2	L	7	4 	4F			RT	A20WE
1998120400319	19981204	00319	NM  	1998	12	4	98ZZZX4401       	1	19980408	G	2761	33215053	MANIFOLD        	MOOG        	33214807A   	BOEING	757   	757*        		NM  										ACTUATOR	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					506247					MANIFOLD LEAKING WHEN PRESURIZED TO 2,500 PSI AND RETRACTED.  FOUND PIN HOLES.  NOTE:  SUBMITTER STATED SB 3321480-27-06	 HAD NOT BEEN ACCOMPLISHED.					2	L	7	2 	4F			RT	A2NM
1998120400320	19981204	00320	NM  	1998	12	4	98ZZZX4402       	1	19980410	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		13395			KE01483					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED WITH SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400321	19981204	00321	NM  	1998	12	4	98ZZZX4403       	1	19980413	G	2740	69778551	SPRING          		65C347512   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KE00039					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED SPRINGS WITH P/N 69-77855-2 SPRINGS.						2	L	7	2 	4F			RT	A16WE
1998120400322	19981204	00322	NM  	1998	12	4	98ZZZX4404       	1	19980413	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		1652 			KE01603					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  REPLACED SPRINGS WITH P/N 69-77855-2 SPRINGS.						2	L	7	2 	4F			RT	A16WE
1998120400323	19981204	00323	NM  	1998	12	4	98ZZZX4405       	1	19980402	G	3232	119260	GLAND ASSY      	ROTOL       	1U11926     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					765B					GLAND ASSY PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED SEALING WITH RTV.						2	L	7	4 	4F			RT	A20WE
1998120400324	19981204	00324	NM  	1998	12	4	98ZZZX4406       	1	19980402	G	3232	1192113	END CAP         	ROTOL       	1U11926     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					765B					END CAP PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED SEALING WITH RTV.						2	L	7	4 	4F			RT	A20WE
1998120400325	19981204	00325	NM  	1998	12	4	98ZZZX4407       	1	19980409	G	2752	14K311	FAN             	TELEFLEX    	793T1007    	BOEING	737   	737*        		NM  										DRIVE MOTOR	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					5593					CRACK INDICATION DUE TO POOR CASTING.  SUBMITTER SUGGESTED CLEANING UP EDGES DURING MANUFACTURING PHASE.						2	L	7	2 	4F			RT	A16WE
1998120400326	19981204	00326	NM  	1998	12	4	98ZZZX4408       	1	19980730	G	2740	69778551	SPRING          		65C3475111  	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		30845	17931		KE00610					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  INSTALLED P/N 69-77855-2 SPRINGS.						2	L	7	2 	4F			RT	A16WE
1998120400327	19981204	00327	NM  	1998	12	4	98ZZZX4409       	1	19980330	G	3232	1192113	END CAP         	ROTOL       	1U11926     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					533AB					END CAP PART PITTED ON THREADS AND IN TUBE PORTS POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USING RTV DURING ASSEMBL	Y.					2	L	7	4 	4F			RT	A20WE
1998020500206	19980205	00206	SO  	1998	2	5	98ZZZX441        	2	19980114	G	8530		CYLINDER ASSY   			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1835M	137  				18264459	269096R			ENGINE:  137 HOURS SOH (3-20-96).  MODIFIED PER STC SE4985NM.  NEW TCM CYLINDER ASSYS INSTALLED AT OVERHAUL AND MODIFICA	TION.  COMP TEST:  NR 1 - 55/80.  NR 2 - 25/80.  NR 3 - 75/80.  NR 4 - 70/80.  NR 5 - 75/80.  NR 6 - 72/80.  REMOVED ALL	 SIX CYLINDERS.  ALL EXHAUST VALVES LOOSE IN GUIDES.  VISUAL INSPECTION OF INTAKE VALVES AND SEATS SHOWED POOR SEALING O	F INTAKE VALVES ALSO (POOR  VALVE MACHINING BY TEM?).			1	H	7	1 	3O	3	O	NT	TA13    	E273
1998120400328	19981204	00328	NM  	1998	12	4	98ZZZX4410       	1	19980330	G	3232	119260	GLAND ASSY      	ROTOL       	1U11926     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					533AB					GLAND ASSY PART PITTED ON RETRACT PORT PACKING SEALING SURFACE POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED APPLYING R	TV TO FLANGES DURING ASSEMBLY.					2	L	7	4 	4F			RT	A20WE
1998120400329	19981204	00329	NM  	1998	12	4	98ZZZX4411       	1	19980401	G	3232	119269	BARREL          	ROTOL       	1U11925     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					UP01442					BARREL PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USE OF A BETTER SEALANT.						2	L	7	4 	4F			RT	A20WE
1998120400330	19981204	00330	NM  	1998	12	4	98ZZZX4412       	1	19980401	G	3232	119260	GLAND ASSY      	ROTOL       	1U11925     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					UP01442					GLAND ASSY PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTSED USE OF A BETTER SEALANT.						2	L	7	4 	4F			RT	A20WE
1998120400331	19981204	00331	NM  	1998	12	4	98ZZZX4413       	1	19980401	G	3232	1192113	END CAP         	ROTOL       	1U11925     	BOEING	747   	747*        		NM  										ACTUATOR	CORRODED        	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					UP01442					END CAP PITTED POSSIBLY DUE TO MOISTURE.  SUBMITTER SUGGESTED USE OF A BETTER SEALANT.						2	L	7	4 	4F			RT	A20WE
1998120400332	19981204	00332	NM  	1998	12	4	98ZZZX4414       	1	19980331	G	2740	69778551	SPRING          		65C3475111  	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		17791			KE00558					SPRING FAILED FUNCTION TEST.  P/N 69-77855-1 SPRINGS WERE FOUND BROKEN IN PIECES.  REPALCED P/N 69-077855-1 SPRINGS WITH	 P/N 69-77855-2 SPRINGS.					2	L	7	2 	4F			RT	A16WE
1998120400333	19981204	00333	NE  	1998	12	4	98ZZZX4415       	3	19980504	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		8333 	3682 		2135NR			HJ269A		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TWO CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998120400334	19981204	00334	NE  	1998	12	4	98ZZZX4416       	3	19980504	G	6111	57D0495	FORK            			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3I     	NE  	PITCH CHANGE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4643 			2781NR			HJ463		FORWARD EAR OF PTICH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  TWO CRACKS.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998120400335	19981204	00335	NE  	1998	12	4	98ZZZX4417       	2	19980729	G	7230		CARBON SEAL     								LYC   	T53   	T5317A      	41549	NE  					ENGINE	LEAKING         	B	L	A	E6TR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19		3616 	671  				LE81002			ENGINE REMOVED FOR LEAKING NR 2 CARBON SEAL.  FOUND FRONT COMPRESSOR SHAFT HAS GRINDER DAMAGE.  DAMAGE TO COMP BLADES WI	THIN .50 INCH OF BLADE ROOT.  RETAINING BOLT LOCK CUPS NOT DEFORMED SUFFICIENTLY INTO BOLT SLOTS TO SAFELY SECURE BOLTS.	  1ST STAGE GAS PRODUCER.  TURBINE ROTOR ASSY BLADES BURNED AND ERODED.  ACCY DRIVE CARRIER N1 BEVEL GEAR RETAINER NOT L	OCKED.  DRIVE BEVEL DRIVEN GEAR IMPROPERLY SHIMMED.  MAIN OUTPUT GEAR IS SPALLED ON GEAR TEETH AND SHOWS SIGNS OF BEARIN	G SPIN.  2ND STAGE GP NOZZLE ASSY HAS SEVERE BURNING OF OUTER VANE L/E.  1ST STG GP NOZZLE HAS SEVERE BURNING AND WARPIN	G OF T/E AND CRACKS IN OUTER SHROUD.  COMB CHAMBER LINER ASSY BULGING AND CRACKED IN BOTH INNER AND OUTER LINERS.						4	U			E17EA
1998120400336	19981204	00336		1998	12	4	98ZZZX4418       	4	19980714	G	2370	93A10080	CVR             		A100A       	BOEING	737   	73739A      	138447P	NM  										CARGO BAY	INOPERATIVE     	C			A10M	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SO	15	253DV	1778 			52072	23800				CVR FAILED OPERATIONAL TEST DURING ROUTINE SCHEDULED TESTING.  REMOVED AND REPLACED CVR WITH OVERHAULED UNIT, SAME PORT 	NUMBER, SAME MODEL NUMBER.  (TEARDOWN AND BENCH EVALUATION OF FAILED UNIT INDICATED SEVERAL PROBLEMS.  FAILED MOTOR, BEL	T, TAPE, ETC.)  A REVIEW OF THE TEARDOWN OF THE NEWLY OVERHAULED UNIT AND THE FAILED UNIT INDICATES SOME SIMILAR FAILURE	 AND MORE FREQUENT BENCH EVALUATION SHOULD BE SCHEDULED ON THESE UNITS.			2	L	7	2 	4F			RT	A16WE
1998120400337	19981204	00337	NM  	1998	12	4	98ZZZX4419       	1	19980622	G	5311	1506626	STRINGER        			BOEING	737   	73739A      	138447P	NM  										APU BAY	CORRODED        	C			A10M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	253DV	1778 				23800				STIFFENER AND STRINGER FOUND CORRODED IN TORQUE BOX APU BAY.  SUBMITTER SUGGESTED MORE FREQUENT AND MORE DETAILED INSPEC	TIONS OF THE SECTION 48 TORQUE BOX AREA INCORPORATED INTO THE CPCP PROGRAMS. THIS COULD HAVE AFFECTED MORE CRITICAL AREA	S HAD IT NOT BEEN CAUGHT AT SUCH AN EARLY STAGE.  EVEN AT THIS STAGE, THE REPLACMENT OF THESE ITEMS WAS NECESSARY TO ENS	URE A COMPLETE CORRECTIVE ACTION.			2	L	7	2 	4F			RT	A16WE
1998020500207	19980205	00207	CE  	1998	2	5	98ZZZX442        	1	19980120	G	3230	12416307	DOWNLOCK SHELL  			CESSNA	210   	T210L       	2073449	CE  										LT MLG	DEFORMED        	B			CS3R	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			WP	17	29176	1221 				21059828				ON APPROACH, GEAR EXTENDED, LT MAIN GREEN LIGHT FAILED TO ILLUMINATE:  EMERGENCY GEAR EXTENSION USED TO LOCK GEAR.  DURI	NG INSPECTION, FOUND INTERIOR OF DOWNLOCK SHELL LEFT SIDE PEELED BACK INTERFERRING WITH MAIN LEG FULL TRAVEL, THEREFORE,	 PREVENTING OVERCENTER LOCKS FROM BEING ENGAGED.  SUSPECT CAUSE IS RUBBER COMPOSITE INSERT BEING OLD AND BRITTLE WHICH C	REATED DELAMINATION.			1	H	7	1 	3O				3A21
1998121700012	19981217	00012	NM  	1998	12	17	98ZZZX4420       	1	19980622	G	5320	1505100155	STIFFENER       			BOEING	737   	73739A      	138447P	NM  										APU BAY	CORRODED        	C			A10M	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	253DV	1778 				23800				STIFFENER AND STRINGER FOUND CORRODED IN TORQUE BOX APU BAY.  SUBMITTER SUGGESTED MORE FREQUENT AND MORE DETAILED INSPEC	TIONS OF THE SECTION 48 TORQUE BOX AREA INCORPORATED INTO THE CPCP PROGRAMS. THIS COULD HAVE AFFECTED MORE CRITICAL AREA	S HAD IT NOT BEEN CAUGHT AT SUCH AN EARLY STAGE.  EVEN AT THIS STAGE, THE REPLACMENT OF THESE ITEMS WAS NECESSARY TO ENS	URE A COMPLETE CORRECTIVE ACTION.			2	L	7	2 	4F			RT	A16WE
1998120400338	19981204	00338	GL  	1998	12	4	98ZZZX4421       	1	19980928	G	3222	2032200100	FORK ASSY       			DIAMON	DA20  	DA20C1      	2990001	GL  										NLG	FAILED          	B				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			WP	13	228ND	463  				C0010				NOSE GEAR FORK ASSY BROKEN 2 PLACES.  RT AND LT FORK LINK ASSY APPROX 2 INCHES FORWARD OF AXLE.  TOTAL SEPARATION OR NOS	E WHEEL ASSY FROM ACFT - ONLY DAMAGE TO FORK ASSY AND NOSE GEAR TUBE ASSY.  SUBMITTER STATES NOSE GEAR FORK ASSY NOT FAB	RICATED HEAVY ENOUGH TO WITHSTAND TYPICAL FLIGHT TRAINING, LANDINGS, ETC.  PART OBVIOUSLY APPEARS TO BE MANUFACTURED TOO	 LIGHTWEIGHT.  CROSS SECTION IS VERY THIN.			1	L	7	1 	3O			NT	TA4CH
1998020500208	19980205	00208	CE  	1998	2	5	98ZZZX443        	1	19980106	G	3411	S10711	PITOT TUBE      			CESSNA	172   	172P        	2072436	CE  										AIRSPEED	LEAKED          	H		A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	11	54320					17274955				PILOT REPORTED LOW AIRSPEED INDICATION.  PITOT SYSTEM WAS PRESSURE CHECKED AND FOUND TO HAVE A LEAK.  FOUND PITOT HEAT W	IRING CHAFED/MELTED INTO PITOT PRESSURE TUBE APPROXIMATELY 3 INCHES ABOVE CONNECTOR.  REPLACED TUBING AND SYSTEM PITOT H	EAT WIRING SECURED AWAY FROM TUBING.  NOTE:  2 DAYS LATER DURING AN ANNUAL INSPECTION OF ANOTHER 172, FOUND THE SAME PRO	BLEM, EXCEPT IT APPEARED THAT HEAT FROM THE WIRING HAD MELTED THE TUBING HALF-WAY THROUGH.  THE SYSTEM STILL HELD GOOD P	RESSURE.		1	H	7	1 	3O			NT	3A12
1998120400471	19981204	00471	EU  	1998	12	4	98ZZZX4430       	1	19981007	G	6420	350A33200405	SPIDER          			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	STIFF           	D		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	821SP	4804 	81   		M1683	2106				THE TAIL ROTOR SPIDER BECAME STIFF AFTER BEING INSTALLED AT OVERHAUL.  THIS WAS 19 HOURS AFTER OVERHAUL, OVER 80 POUNDS 	IN FORCE WERE REQUIRED TO SLIDE SPIDER  MAXIMUM OF 30 PER MM.  THE SPIDER WAS REPLACED WITH ANOTHER OVERHAULED SPIDER. I	T IS NOW STIFF AND REQUIRES 95 POUNDS OF FORCE.  EUROCOPTER STATES OVERHAUL PROCEDURE CHANGED RECENTLY.  THIS PROBLEM WO	ULD BE IMPOSSIBLE TO DETECT IN-FLIGHT WITH HYDRAULIC POWER ON.  TAIL ROTOR CONTROL WOULD BE VERY DIFFICULT WITH HYDRAULI	C FAILURE.  SUBMITTER STATED WILL CONTINUE 25-HOUR INSPECTION OF FORCE IN THIS AIRCRAFT.		1	G	7	1 	3U			NC	H9EU
1998120400474	19981204	00474	EU  	1998	12	4	98ZZZX4433       	1	19981016	G	5320	150400801	MOUNT           			SNIAS 	350   	AS350B2     	8680813	EU  										FLIR SYSTEM	MISDRILLED      	B			RC0R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17	6103X	81   				2723				HARDWARE IN FLIR INSTALLATION STC NR SH7335SW-D, DRAWING 350A82-1596PG.40F7, COMPONENT P/N 350A82-1147-02 FLIR MOUNT BAS	IC IS DRILLED FOR WAS 1304 BOLT WITH .25 INCH DIAMETER, QD MOUNT TOP PLATE, P/N 15040080-1, IS DRILLED FOR .3125 INCH D.	A. BOLT.  THIS ATTACHMENT HARDWARE NAS1304-18 HAS BEEN TORQUED ON TWO DIFFERENT OCCASIONS, BUT THE QD MOUNT TOP PLATE HA	S BEEN FOUND TO HAVE PLAY.  SUBMITTER RECOMMENDED EITHER THE TOP PLATE BE DRILLED AND BUSHED FOR .25 INCH DIAMETER BOLT 	OR FLIR BASIC MOUNT BE DRILLED TO ACCEPT .3125 INCH DIAMETER BOLT TO TIGHTEN UP THE INSTALLATION.		1	G	7	1 	3U				H9EU
1998120400475	19981204	00475	SW  	1998	12	4	98ZZZX4434       	1	19981026	G	6710	206062721011	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY		234  		0369A	2871				LINEAR ACTUATOR EXTENDS EXCESSIVELY (LOW SIDE OF BEEP).   WORN GEAR MAY BE DISCONNECTED.  SENT FOR REPAIR.						1	G	7	1 	3U				H2SW
1998120400478	19981204	00478	NE  	1998	12	4	98ZZZX4437       	1	19981111	G	6210	7615009000046	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	CRACKED         	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2634				A08600316A	76007				DURING DAILY INSPECTION, FOUND TIP CAP DOUBLER CRACKED.  WHEN TIP CAP WAS REMOVED FOR REPLACEMENT, AFT TIP CAP ANCHOR NU	T SUPPORT CAME UNBONDED.  THIS BLADE HAD 720.4 HOURS ON IT SINCE IT HAD BEEN TO OVERHAUL FACILITY FOR C-BLOCK MODIFICATI	ON.				1	G	7	2 	3U				H1NE
1998120400479	19981204	00479	SW  	1998	12	4	98ZZZX4438       	1	19980730	G	6320		LINE            			BELL  	206   	206B3       	1181506	SW  										TRANSMISSION OIL	CORRODED        	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	HBXSH					2337				OIL WAS RUNNING OUT OF THE DRAIN HOLE BOTTOM SIDE OF THE HELICOPTER.  FOLLOWING LINES HAD PIN POINT HOLES CAUSED BY CORR	OSION.  P/N 206-070-450-001, TUBE ASSY, TORQUE, ENGINE.  P/N 206-070-446-001, TUBE ASSY, OIL, ENGINE.  OIL PASSING THESE	 HOLES EMANATING THE SYSTEM.  ABOUT 2 LITERS PER 10 MINUTES.  LINE, P/N 206-070-453-001, TUBE ASSY, OIL, TRANSMISSION, A	LSO HAD SIGNS OF CORROSION BUT NO HOLES AND NO OIL ESCAPING FROM SYS.  CORROSION SAME PLACE ON ALL TUBES TOWARDS BOTTOM 	OF ACFT AT STA 74.50.  SUBMITTER SUGGESTED CORROSION CAUSED BY DIRT ACCUMULATED AROUND TUBES AND WATER FROM WASHING HELI	COPTER, RAIN, ETC.  REPLACED LINES, TEST RUN AND FLOWN.  NO OIL LEAKS OBSERVED AFTER EXCHANGE OF TUBES.	1	G	7	1 	3U				H2SW
1998120400480	19981204	00480	NM  	1998	12	4	98ZZZX4439       	1	19980805	G	2750	14K311	IMPELLER        	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										FLAP DRIVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					937					INDICATIONS FOUND DURING DYE PENETRANT INSPECTION DUE TO CASTING FLAWS.  SUBMITTER SUGGESTED CLEANING UP DURING MANUFACT	URING.					2	L	7	2 	4F			RT	A16WE
1998120400481	19981204	00481	NM  	1998	12	4	98ZZZX4440       	1	19980805	G	2750	14K311	IMPELLER        	TELEFLEX    	793T100     	BOEING	737   	737*        		NM  										FLAP DRIVE	CRACKED         	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		52199			5209					INDICATIONS FOUND DURING DYE PENETRANT INSPECTION DUE TO CASTING FLAWS.  SUBMITTER SUGGESTED CLEANING UP DURING MANUFACT	URING.					2	L	7	2 	4F			RT	A16WE
1998120400482	19981204	00482	NM  	1998	12	4	98ZZZX4441       	1	19980805	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		17750			KE01555					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  INSTALLED SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998120400483	19981204	00483	NM  	1998	12	4	98ZZZX4442       	1	19980921	G	2782	1103044	BODY ASSY       	ROTOL       	1U11032     	BOEING	737   	737*        		NM  										SLAT ACTUATOR	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			619  		10358					CRACKED AND FLAKING CHROME.						2	L	7	2 	4F			RT	A16WE
1998120400484	19981204	00484	NM  	1998	12	4	98ZZZX4443       	1	19980925	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		23845			KE01117					FAILED AUXILIARY BRAKE TEST DUE TO BROKEN SPRINGS.  INSTALLED SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998121100001	19981211	00001	EA  	1998	12	11	98ZZZX4444       	2	19981001	G	7310	1072903	LINE            			PIPER 	PA18  	PA18A       	7101804	SO  	LYC   	O290  	O290D2      	41506	EA  					FUEL SYSTEM	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1388C					182649				ALUMINUM FUEL LINE CORRODED.  MANUFACTURER WRAPS FRICTION TAPE ON TUBING FORMING CORROSION TRAP.  SUBMITTER SUGGESTED RE	PLACEMENT WITH CORROSION PROOFED TUBING AND ELIMINATION OF FRICTION TAPE.					1	H	7	1 	3O	3	O		1A2     	E229
1998121100002	19981211	00002	EA  	1998	12	11	98ZZZX4445       	2	19981001	G	7310	8237104	LINE            			PIPER 	PA18  	PA18A       	7101804	SO  	LYC   	O290  	O290D2      	41506	EA  					FUEL SYSTEM	DETERIORATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	1388C					182649				FUEL HOSE INTERNAL DETERIORATION RESULTING IN DECREASED FUEL FLOW TO CARBURETOR.  SUBMITTER SUSPECTS AUTOFUEL AND/OR OLD	 AGE, INADEQUATE INSPECTION AND RECOMMENDED FUEL FLOW CHECK AT ANNUAL INSPECTION.					1	H	7	1 	3O	3	O		1A2     	E229
1998121100003	19981211	00003	SO  	1998	12	11	98ZZZX4446       	2	19981026	G	8530		CYLINDER HEAD   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  					ENGINE	CRACKED         	B			ISOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	13LM					347870075	306232			DURING INSPECTION FOR AN OIL LEAK, FOUND THE ENGINE CYLINDER HEAD CRACKED BEHIND THE ROCKER COVER AREA AND EXTENDING BEH	IND THE INTAKE VALVE SPRING.  ONE DAY BEFORE FOUND, SIMILAR CRACK AND DIFFERENT AIRPLANE WITH SAME MODEL ENGINE.  AFTER 	CLOSE INSPECTION, UNABLE TO DETERMINE REASON.  FIRST ACFT, CESSNA R172K, ENGINE IO-360-K, S/N 355310.  SECOND ACFT, PIPE	R PA34200T, ENGINE LTSIO-360-E, S/N 306232.			1	L	7	2 	3O	3	O		A7SO    	E9CE
1998121100004	19981211	00004		1998	12	11	98ZZZX4447       	2	19981108	G	7421	REM40E	SPARK PLUG      	CHAMPION    																ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05										SPARK PLUGS WILL NOT FIRE (TESTED IN AIRCRAFT AND PLUG TESTER).  SOME ARE INTERMITTENT, BREAKING DOWN UNDER PRESSURE.  O	UT OF 40 PLUGS PURCHASED, 24 WERE REPLACED WITH ANOTHER BRAND IN ONE AIRCRAFT WITH PERFECT RUNNING ENGINE AFTER INSTALLA	TION.  THE OTHER AIRCRAFT WAS REFITTED WITH ITS SERVICEABLE USED PLUGS AND NO PROBLEM WITH PERFORMANCE.  SUBMITTER DOES 	NOT KNOW THE CAUSE FOR THIS PROBLEM AS IT HAS BEEN ON-GOING FOR A LITTLE WHILE.  THEY WERE HANDLED WITH EXTREME CARE WHE	N OPENED AND INSTALLED.
1998121100005	19981211	00005		1998	12	11	98ZZZX4448       	2	19981108	G	7421	RHM40E	SPARK PLUG      	CHAMPION    																ENGINE	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	05										SPARK PLUGS WILL NOT FIRE (TESTED IN AIRCRAFT AND PLUG TESTER).  SOME ARE INTERMITTENT, BREAKING DOWN UNDER PRESSURE.  O	UT OF 40 PLUGS PURCHASED, 24 WERE REPLACED WITH ANOTHER BRAND IN ONE AIRCRAFT WITH PERFECT RUNNING ENGINE AFTER INSTALLA	TION.  THE OTHER AIRCRAFT WAS REFITTED WITH ITS SERVICEABLE USED PLUGS AND NO PROBLEM WITH PERFORMANCE.  SUBMITTER DOES 	NOT KNOW THE CAUSE FOR THIS PROBLEM AS IT HAS BEEN ON-GOING FOR A LITTLE WHILE.  THEY WERE HANDLED WITH EXTREME CARE WHE	N OPENED AND INSTALLED.
1998121100010	19981211	00010	SO  	1998	12	11	98ZZZX4453       	2	19980513	G	8520	649478	CAMSHAFT        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE	SCORED          	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC		780  			18263638	269416R			THE INTERNAL TACHOMETER DRIVE SEIZED UP AND SHEARED THE TACH DRIVE PIN.  REMOVAL OF THE TACH DRIVE COVER REVEALED METAL 	HAD PASSED THROUGH THE OIL PUMP.  FURTHER INVESTIGATION REVEALED THE NR 5 CYLINDER VALVE LIFTER AND CAM LOBE WERE BREAKI	NG UP AND SCOURED.  THE ENGINE WAS REMOVED FOR SERVICE.  SUBMITTER SUGGESTS POSSIBLE CAUSE AS DEFECTIVE PARTS INSTALLED 	IN THE ENGINE AT REMANUFACTURE.			1	H	7	1 	3O	3	O	NT	TA13    	E273
1998121100013	19981211	00013	SO  	1998	12	11	98ZZZX4456       	2	19980701	G	8530	654650A4	CYLINDER HEAD   			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	MISMANUFACTURED 	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC	103  				18263638	470757			DURING A ROUTINE COMPRESSION CHECK, AIR WAS FOUND LEAKING THROUGH A POROUS CASTING IN THE CYLINDER HEADS ON THE NR 2 AND	 NR 6 CYLINDERS.  BOTH CYLINDERS WERE REPLACED.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE CYINDER HEADS INSTALLED	 ON CYLINDERS AT MANUFACTURE OF THE ENGINE.				1	H	7	1 	3O	3	O	NT	TA13    	E273
1998121100021	19981211	00021	SO  	1998	12	11	98ZZZX4464       	2	19980814	G	8530	646283	INTAKE VALVE    			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC	278  				18265290	813337R			DURING AN INSPECTION REQUIRED BY TCM CSB98-1B, TITLED INTAKE AND EXHAUST VALVE INSPECTION, THE INTAKE VALVE TIPS ON THE 	NR'S 2, 4, AND 6 CYLINDERS WERE FOUND EXCESSIVELY WORN.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS INSTALLED	 INTO THE ENGINE AT REMANUFACTURE.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1998121100023	19981211	00023	SO  	1998	12	11	98ZZZX4466       	2	19980929	G	7311	652661	OIL COOLER      			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	CRACKED         	B			MK5R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	23	954CC		390  		A27985476	18265290	813337R			DURING A ROUTINE INSPECTION, A CRACK WAS FOUND ON THE OIL COOLER NEAR THE AFT, LOWER SUPPORT, STRUT ATTACH POINT (WELD).	  SUBMITTER SUGGESTED POSSIBLE CAUSE AS IMPROPER WELDING DURING MANUFACTURE OR REMANUFACTURE.					1	H	7	1 	3O	3	O	NT	3A13    	E273
1998121100026	19981211	00026	SO  	1998	12	11	98ZZZX4469       	2	19980220	G	8520	642522A1	CRANKCASE       			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	CRACKED         	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC		25   			18265290	813337R			DURING A ROUTINE OIL CHANGE, A CRACK WAS FOUND IN THE CRANKCASE THAT RADIATES ABOUT ONE INCH TOWARDS THE CENTER OF THE E	NGINE STARTING FROM THE FORWARD UPPER HOLD DOWN STUD ON THE NR 5 CYLINDER.  THE ENGINE WAS RETURNED TO THE FACTORY FOR A	 CRANKCASE REPLACEMENT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS. (CRANKCASE) INSTALLED IN THE ENGINE AT R	EMANUFACTURE.			1	H	7	1 	3O	3	O	NT	3A13    	E273
1998121100028	19981211	00028	SO  	1998	12	11	98ZZZX4471       	2	19980327	G	8530	653443	VALVE GUIDE     			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					ENGINE EXHAUST	WORN            	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	953CC	916  				18264109	269396R			DURING A ROUTINE COMPRESSION CHECK, LEAKAGE WAS FOUND PAST THE EXHAUST VALVE ON THE NR 2 CYLINDER.  THE REMOVED CYLINDER	, EXHAUST VALVE AND GUIDE WERE FOUND WORN OUT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PART AND/OR ASSEMBLY PRO	CESS FROM THE FACTORY.				1	H	7	1 	3O	3	O	NT	TA13    	E273
1998121100033	19981211	00033	SO  	1998	12	11	98ZZZX4476       	2	19981015	G	8530	SA629690	PISTON PIN      	SUPAIRPART  		CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					NR 4 CYLINDER	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	736VN	109  				R1722823	355899			ENGINE DISASSEMBLED PER AD 98-19-02.  FOUND NR 4 PISTON PIN BROKEN INTO TWO PIECES.  REBUSHED NR 4 CONNECTING ROD, INSTA	LLED NEW PISTON AND RINGS.  REPLACED ALL PISTON PINS WITH NEW.					1	H	7	1 	3O	3	O		3A17    	E1CE
1998121100034	19981211	00034	SO  	1998	12	11	98ZZZX4477       	1	19981029	G	5542	2072916	SKIN            			PIPER 	PA24  	PA24250     	7102404	SO  										RUDDER	CRACKED         	B	S		TIMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	6079P	3474 				24117				RUDDER CRACKED AT TRAILING EDGE ON BOTH SIDES.  CRACK WAS MIDWAY FROM TOP TO BOTTOM.  NO INTERNAL DAMAGE FOUND.  RUDDER 	REMOVED AND SENT OUT FOR RESKIN.					1	L	7	1 	3O				1A15
1998121100035	19981211	00035	SO  	1998	12	11	98ZZZX4478       	2	19980922	G	8520	646683	CRANKSHAFT      			CESSNA	210   	P210R       	2073455	CE  	CONT  	O520  	TSIO520CE   	17040	SO  					ENGINE	SHEARED         	G				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			GL	15	5245A	1080 				P21000839	530002			JUST AFTER TAKEOFF, THE ENGINE STARTED TO RUN ROUGH AND LOST POWER.  PILOT RETRACTED GEAR AND LANDED IN FIELD.  INVESTIG	ATION REVEALED THE CRANKSHAFT FAILED BETWEEN NR 2 AND NR 3 CYLINDERS NTSB NR CHI98LA360.  THE ENGINE IS STILL INSTALLED 	ON AIRCRAFT AWAITING OWNER DECISION TO REPAIR OR REPLACE AIRCRAFT.				1	H	7	1 	3O	3	O	RT	3A21    	E8CE
1998121100036	19981211	00036	CE  	1998	12	11	98ZZZX4479       	1	19981101	G	2410	ALV9510	ALTERNATOR      	PRESTOLITE  		CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  					ENGINE	FAILED          	D				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			EA	03	4DM	900  			4H000722	340A0719	R514243			ALTERNATOR HAD IN-FLIGHT FAILURE RESULTING IN CLUTCH FAILURE.  METAL FROM CLUTCH WENT INTO THE INTERNAL ENGINE AND CLOGG	ED OIL PUMP INLET SCREEN RESULTING IN ZERO OIL PRESSURE AND ENGINE SHUT DOWN.  INSPECTION OF ALTERNATOR SHOWED DRIVESHAF	T SEIZED FROM LACK OF LUBRICATION.				1	L	7	2 	3O	3	O		3A25    	E8CE
1998121100038	19981211	00038	NE  	1998	12	11	98ZZZX4481       	3	19981001	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			219  							REPAIRED EROSION SHIELD ON NR 3 BLADE IAW MFG CMM DUE TO DEBOND.																5	C	P10NE
1998121100039	19981211	00039	NE  	1998	12	11	98ZZZX4482       	3	19981007	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			681  					HJ140A		REPLACED EROSION SHIELD ON NR 3 BLADE IAW MFG CMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998121100040	19981211	00040	NE  	1998	12	11	98ZZZX4483       	3	19981001	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2040 					HJ869		REPLACED BLADE S/N 2943 DUE TO EROSION SHIELD BEING LOST IN-FLIGHT.  BLADE HAS BEEN SENT TO HARTZELL FOR EVALUATION.  MR	R HAS BEEN FILED BY AIRLINE REGARDING INCIDENT.															5	C	P10NE
1998121100041	19981211	00041	NE  	1998	12	11	98ZZZX4484       	3	19981023	G	6111		PROPELLER       													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1390 					HJ526		REPLACED EROSION SHIELD ON NR 2 BLADE DUE TO DEBOND BEYOND LIMITS.  BLADE S/N 1150.																5	C	P10NE
1998121100042	19981211	00042	NE  	1998	12	11	98ZZZX4485       	3	19981001	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3977 					HJ725		REPLACED EROSION SHIELDS ON NR 2 AND NR 3 BLADES IAW MFG CMM DUE TO DEBOND BEYOND LIMITS.																5	C	P10NE
1998121100043	19981211	00043	NE  	1998	12	11	98ZZZX4486       	3	19981001	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1957 					HJ460		REPAIRED EROSION SHIELD IAW HARTZELL MANUAL 135F.																5	C	P10NE
1998121100099	19981211	00099	CE  	1998	12	11	98ZZZX4488       	1	19981019	G	3710	AJ101	VACUUM FILTER   	AIRBORNE    		CESSNA	172   	172M        	2072418	CE  										VACUUM SYSTEM	CLOGGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	61571	2898 				17264648				DIRECTIONAL GYRO FAILED DURING REPAIR.  INSPECTED ALL VACUUM FILTERS FOR CONDTION.  B3-54 FILTER BROWN IN COLOR AND 1J10	-1 FILTER WAS ORIGINAL FILTER FROM DAY OF MANUFACTURE OF AIRCRAFT.  DATE CODE FOUND ON FILTER 2Q74.  REPLACED BOTH FILTE	RS.  SUBMITTER STATED MOST LIKELY CAUSE OF DG FAILURE IS CLOGGED FILTER.  NEED AD OR MSB TO INSPECT AND CHANGE OLD FILTE	RS.			1	H	7	1 	3O			NT	3A12
1998121700001	19981217	00001	CE  	1998	12	17	98ZZZX4489       	1	19980901	G	1100		PLACARD         			CESSNA	441   	441         	2076020	CE  										PASSENGER DOOR	MISINSTALLED    	B			WTXR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	07										PLACARD FOR UPPER CABIN DOOR HANDLE READS OPEN CLOSED.  PLACARD SHOULD READ CLOSED OPEN.						1	L	7	2 	3T			RT	A28CE
1998121100100	19981211	00100	CE  	1998	12	11	98ZZZX4490       	1	19981001	G	3242	47606	BRAKE DISK      	CLEVELAND   		CESSNA	185   	A185F       	2072821	CE  										MLG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	CGSPL									SUBJECT BRAKE DISK INSTALLED ON EDO 3500 AMPHIBIOUS FLOATS.  FLANGE FAILURE AT EACH OF THREE MOUNTING HOLES TO WHEEL RES	ULTING IN LOCKED BRAKE.  DISK IS EXCESSIVELY LOADED IN THIS INSTALLATION DUE TO GROSS WINDS OF AIRCRAFT, SPEEDS, AND NEC	ESSITY OF OVERUSE OF BRAKES IN CROSSWIND TAXIING.				1	H	7	1 	3O				3A24
1998121100101	19981211	00101		1998	12	11	98ZZZX4491       	2	19981030	G	7414	M3068	MAGNETO         	SLICK       	4330        															MAGNETO	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11		250  			97061307					NEW MAGNETO, 250 HOURS SINCE NEW.  PAWLS WORN AT RIVET ATTACHMENT SEVERELY.  SUBMITTER STATED CAUSE AS POSSIBLE SOFT MET	AL.
1998121100102	19981211	00102		1998	12	11	98ZZZX4492       	1	19981104	G	2622		NOZZLE          		1600        															CABIN	MISMANUFACTURED 	B			R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21					A591954					RECEIVED NEW HALON 1211, 2-1/2 POUND PORTABLE FIRE EXTINGHUISHER CLASS 1-A-5B-C FROM AVIATION PARTS SUPPLY HOUSE.  REPAI	R STATION INCOMING INSPECTION REVEALED NOZZLE MISSING FROM FIRING HEAD.  SUPPLIER WAS NOTIFIED AND THEIR ENTIRE STOCK OF	 THESE EXTINGHISHERS WERE MISSING NOZZLES.  A NEW NOZZLE WAS ORDERED AND OBTAINED BEFORE BOTTLE INSTALLED.  SUBMITTER SU	GGESTED ANYONE WHO HAS PURCHASED BOTTLES RECENTLY - RE-INSPECT FOR NOZZLE INSTALLATION.
1998121100103	19981211	00103	SO  	1998	12	11	98ZZZX4493       	2	19980128	G	8520	649478	LIFTERS         			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	PITTED          	B			MK5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC	875  				18265290	809905R			DURING A ROUTINE COMPRESSION CHECK, THE NR 2 CYLINDER EXHAUST VALVE WAS FOUND LEAKING.  AFTER THE CYLINDER WAS REMOVED, 	ALL CAM LIFTERS FOUND PITTED AND THE NR 5 CYLINDER INTAKE CAM LOBE FOUND SCOURED.  THE ENGINE REMOVED FROM SERVICE.  SUB	MITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS AND/OR ASSEMBLY PROCESS FROM THE FACTORY.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1998121100104	19981211	00104	SO  	1998	12	11	98ZZZX4494       	1	19981003	G	2720	634510U	SUPPORT ASSY    			PIPER 	PA28  	PA28140     	7102802	SO  										COCKPIT	CRACKED         	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	5978U	7109 				2826865				RIGHT RUDDER PEDAL ON PASSENGER SIDE OF AIRCRAFT HAD EXCESSIVE TRAVEL BEFORE NOSE WHEEL STEERING CAME INTO EFFECT.  FURT	HER INSPECTION REVEALED THE CENTER RUDDER BAR SUPPORT CRACKED AT ALL FOUR MOUNTING HOLES AND SUPPORT WAS BADLY BENT.  PA	RT REPLACED.				1	L	7	1 	3O				2A13
1998121100105	19981211	00105	SO  	1998	12	11	98ZZZX4495       	1	19981103	G	2823	3138400	CONTROL CABLE   			PIPER 	PA23  	PA23250     	7102308	SO  										FUEL SELECTOR	BROKEN          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	40599	9628 				277405345				PILOT SWITCHED RIGHT FUEL SELECTOR PRIOR TO LANDING.  ENGINE BEGAN TO LOSE POWER.  PILOT THOUGHT FUEL SELECTOR CABLE MIG	HT HAVE BROKEN DUE TO THE FACT IT MOVED VERY EASY.  CROSS-FEED WAS SELECTED WHICH RESTORED POWER.  PILOT MADE NORMAL LAN	DING.  CABLE WAS FOUND BROKEN INSIDE HOUSING WHERE IT CANNOT BE INSPECTED.				1	L	7	2 	3O			 	1A10
1998121100106	19981211	00106	EA  	1998	12	11	98ZZZX4496       	2	19981105	G	7310	U70322020	FLEX LINE       			PIPER 	PA12  	PA12        	7101202	SO  	LYC   	O235  	O235C       	41505	EA  					FUEL SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	4437M					123388				REPLACED HOSE AT FUEL TANK BECAUSE OF AGB.  REPLACED HOSE WAS MADE UP OF MIL-H-6000, DATED 12-95.  EIGHTEEN MONTHS AFTER	 INSTALLATION, HOSE BECAME SOFT, DETERIORATED AND FAILED.  SUBMITTER STATED THIS IS SECOND HOSE OF .3750 INCH SIZE TO FA	IL IN THIS AREA OR LOCALITY IN 18 MONTHS TO 2 YEARS AFTER INSTALLATION.  THIS AIRCRAFT HAS AUTOGAS S.T.C.  THE OTHER HAS	 NEVER USED AUTO FUEL.  HOSE IS AVAILABLE FOR FURTHER INVESTIGATION.  MFG P/N IS UNIVAIR NUMBER.			1	H	7	1 	3O	3	O		A780    	E223
1998121100107	19981211	00107	GL  	1998	12	11	98ZZZX4497       	1	19981027	G	3233		ARM             			NAMER 	NA260 	T28A        	6402504	GL  										LT MLG	BROKEN          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	300AF					491513				OWNER INDICATED THE LEFT MAIN GEAR WOULD NOT RETRACT.  THE AIRCRAFT WAS THEN BROUGHT TO MAINTENANCE.  AIRCRAFT WAS JACKE	D AND AN ATTEMPT TO SWING THE GEAR WAS MADE, THE LEFT WOULD NOT MOVE.  OPENED LEFT MAIN GEAR ACTUATOR CYLINDER PANEL.  F	OUND LEFT MAIN GEAR ACTUATING ARM BROKEN.  BOTH EARS FAILED WHERE ROD END FROM ACTUATING CYLINDER ATTACHES.  ACTUATING A	RM REMOVED WAS CAST ALUMINUM.  REPLACEMENT ARM IS STEEL.  ALSO, FOUND CYLINDER ROD END BOLT IN THE WRONG DIRECTION AND W	AS CONTACTING THE AIRFRAME STRUCTURE, BOLT HEAD SHOULD BE AFT.		1	L	7	1 	4R				EXPA1L71
1998121100108	19981211	00108	SO  	1998	12	11	98ZZZX4498       	1	19981117	G	3213	6531904	STRUT           			PIPER 	PA28  	PA28140     	7102802	SO  										MLG	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	1839T	3158 				287125262				THE TWO LUGS THAT ARE CAST AS AN INTEGRAL PART OF THE LANDING GEAR CYLINDER TO WHICH THE UPPER END OF THE LANDING GEAR T	ORQUE LINK ATTACHES, FAILED ALLOWING THE LANDING GEAR TO BE ABLE TO SWIVEL.  THERE WAS NO OBVIOUS SIGN OF AN IMPENDING P	ROBLEM AT ANY PREVIOUS INSPECTIONS.				1	L	7	1 	3O				2A13
1998121100109	19981211	00109	CE  	1998	12	11	98ZZZX4499       	1	19981105	G	7820	MFR8W928	MUFFLER         			CESSNA	172   	172R        	2072401	CE  										EXHAUST	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	724HG				713790554011	17280409				CRACK FOUND AROUND HEAT SHROUD SUPPORT COLLAR.  TT ON MUFFLER, 98.2 HOURS.						1	H	7	1 	3O			NT	3A12
1998020500217	19980205	00217	CE  	1998	2	5	98ZZZX450        	1	19980103	G	3230	115380025	MOTOR           			BEECH 	200   	200BEECH    	1152920	CE  										MLG	FAILED          	B			BXSR	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	09	200BE		2136 		1037	BB832				PILOT COULD NOT EXTEND THE GEAR WITH THE NORMAL SYSTEM.  FOUND THE MOTOR DEFECTIVE.  MOTOR INSPECTION WAS NOT DUE UNTIL 	7/98.					1	L	7	2 	4T				A24CE
1998121100110	19981211	00110	CE  	1998	12	11	98ZZZX4500       	1	19981105	G	7820	MFR8W928	MUFFLER         			CESSNA	172   	172R        	2072401	CE  										EXHAUST	CRACKED         	G	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	723HG				713790554011	17280408				CRACK FOUND AROUND HEAT SHROUD SUPPORT COLLAR.  TT ON MUFFLER, 100.0 HOURS.						1	H	7	1 	3O			NT	3A12
1998121100113	19981211	00113	SW  	1998	12	11	98ZZZX4503       	1	19981109	G	6120	660226009	CABLE           			MOONEY	M20   	M20K        	5870220	SW  										PROP CONTROL	CHAFED          	B			EA6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	252WG					251031				THE PROPELLER GOVERNOR CONTROL WAS CHAFED INTO CABLE THROUGH CONDUIT AT BRACKET ATTACHMENT JUST AFT OF GOVERNOR.						1	L	7	1 	3O			 	2A3
1998121100114	19981211	00114	EU  	1998	12	11	98ZZZX4504       	1	19981101	G	2730	486314	INDICATOR       			AMD   	FALC20	FALCON      	2720302	EU  										ELEVATOR CONTROL	MISMANUFACTURED 	B			QY5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	01	20NY				325	61				UNIT MANUFACTURED IN 1982 AND STILL IN SEALED PACKAGE WHEN RECEIVED.  STABILIZER TRIM GAVE REVERSE INDICATION WHEN INSTA	LLED.  ACTUAL TAIL PLANE POSITION 38 DEGREES/ZERO INDICATION.  UNIT EXCHANGED FOR S/N 329 NEW INDICATOR (ALSO MFG 1982) 	WHICH OPERATED PROPERLY.				2	L	7	2 	4F				A7EU
1998121100115	19981211	00115	CE  	1998	12	11	98ZZZX4505       	1	19981101	G	7120	646057	MOUNT           			CESSNA	303   	T303        	2073820	CE  										LT/RT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	303ET	1819 				T30300036				DURING ANNUAL INSPECTION, FOUND LOWER LT MOUNTING BRACKET OF BOTH LT AND RT ENGINES CRACKED.  CRACKS FOUND JUST FORWARD 	OF AFT ALTERNATOR MOUNTING BOSS.  LEFT ENGINE WAS ABVIOUS, BUT RIGHT ENGINE MOUNT BRACKET HAD TO BE DYE PENETRANT.  REMO	VED AND REPLACED BOTH MOUNTING BRACKETS WITH NEW.				1	L	7	2 	3O				A34CE
1998121100116	19981211	00116	CE  	1998	12	11	98ZZZX4506       	1	19980908	G	5210	26171041	BELLCRANK       			CESSNA	208   	208B        	2073701	CE  										CREW DOOR	LOOSE           	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	727FX	1545 				208B0468				PILOT REPORTED CREW DOOR WOULD NOT UNLOCK.  INSPECTION REVEALED THE PIN ON BELLCRANK DISENGAGED FROM THE CAM ASSY AND BA	CK PIN WHEN KNOB WAS PULLED OUT TO ITS FULL EXTEND.  SUBMITTER RECOMMENDED INSTALLING LONGER PIN ON BELLCRANK ASSY OR A 	STOP-TO-LIMIT TRAVEL WHEN THE KNOB IS PULLED.				1	H	7	1 	3T				A37CE
1998121100117	19981211	00117	SO  	1998	12	11	98ZZZX4507       	2	19981110	G	8520	642133	CASE            			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	CRACKED         	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	421UP	2327 	857  			421B0142	600984			CASE CRACKED BELOW NR 3 CYLINDER TOP STUD SECOND FROM THE FRONT.  FOUND DURING CYLINDER REMOVAL TO REPLACE BASE SEAL.  C	RACK ABOUT .50 INCH LONG.					1	L	7	2 	3O	3	O		A7CE    	E7CE
1998121100118	19981211	00118	CE  	1998	12	11	98ZZZX4508       	1	19981106	G	3252	1693800297	SHIMMY DAMPENER 			BEECH 	23    	C23         	1151242	CE  										NLG	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	6639D	30   				M2223				AIRCRAFT EXPERIENCED NOSE WHEEL SHIMMY.  A NEW SHIMMY DAMPENER INSTALLED.  THE USUAL PRECAUTIONS AND TROUBLESHOOTING PRO	CEDURES WERE UTILIZED TO DETERMINE SHIMMY DAMPENER.   WITHIN A FEW HOURS, ACFT REPORTED WITH SAME PROBLEM.  INSTALLED NE	W SHIMMY DAMPENER MFG BY COMMERCIAL ACFT PRODUCTS (CAP P/N C100016-1A) AND THIS FLIGHT REPORTED NO SHIMMY.  S/N 638 MFG 	7-97.  ANOTHER UNIT, S/N 574 MFG 1/95 FAILED IN LESS THAN 2 YEARS AS WITH S/N 596 MFG 4-96.			1	L	7	1 	3O				A1CE
1998121100119	19981211	00119	CE  	1998	12	11	98ZZZX4509       	1	19981102	G	3243	0541144	ROD             			CESSNA	172   	172N        	2072434	CE  										MASTER CYLINDER	BROKEN          	H	S			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	03	738ZC					17270357				PILOT'S RIGHT MASTER CYLINDER ROD IN CYLINDER BROKE (3) IN 200 HOURS AT AREA OF MACHINED THREADS.  SUBMITTER SUSPECTED M	ANUFACTURING DEFECT.					1	H	7	1 	3O			NT	3A12
1998020500218	19980205	00218	EU  	1998	2	5	98ZZZX451        	1	19980115	G	5320	F9EX511111	U CHANNEL       			AMD   	FALC50	FALCON900   	2700160	EU  										FRAME 12 RT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	330MC					21				AILERON BELLCRANK WAS HITTING FLOOR SPLICE U-CHANNEL.  THE U-CHANNEL WAS NOT CUT AWAY PER BLUEPRINT TO ALLOW CLEARANCE F	OR BELLCRANK.  THE BLUEPRINT HAS BEEN REVISED TO PREVENT THIS FROM HAPPENING AGAIN.					2	L	7	3 	4F			RT	A46EU
1998121100121	19981211	00121	SO  	1998	12	11	98ZZZX4511       	1	19981019	G	7820	1443402	MUFFLER         			PIPER 	PA18  	PA18150     	7101828	SO  										ENGINE	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	63803	1137 				187809147				MUFFLER ASSY BAIL HAS CORRODED AWAY DUE TO 180 HP PER STC NR SA92NW AND LACK OF INSPECTION OF AD 68-05-01 AND OPERATOR C	OMPLIANCE.  SUBMITTER RECOMMENDED EVERY 1,000 TIS, THE MUFFLER ASSY SHOULD BE REPLACED WITH A NEW ASSY, NOT OVERHAULED.					1	H	7	1 	3O				1A2
1998121100122	19981211	00122	EA  	1998	12	11	98ZZZX4512       	2	19981019	G	7311	5A92NW	OIL COOLER      			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O360  	O360*       	41514	EA  					ENGINE	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	63803	93   				187809147	L3558236A			PILOT STATES THAT OIL TEMPERATURE DOES NOT GO ABOVE 140 DEGREES FAHRENHEIT IN-FLIGHT OPS.  LYCOMING REQUIRES 170 DEGREES	 PLUS PER OPERATOR'S MANUAL.  SUBMITTER FOUND SOME SILVER DUCK TAPE WITH A STRING COVERING AIR INTAKE TO REGULATE.  AIR 	FLOW OVER COOLER TO ADJUST OIL TEMPERATURE.				1	H	7	1 	3O	3	O		1A2     	E286
1998121100123	19981211	00123	CE  	1998	12	11	98ZZZX4513       	1	19981101	G	5520		HINGE           			CESSNA	180   	180         	2072602	CE  										ELEVATOR	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2244C					30544				UPON INSPECTION OF RUDDER AND LT ELEVATOR, FOUND EXCESSIVE PLAY AT RUDDER AND ELEVATOR TIP WHEN MOVING CENTRAL SURFACE F	ROM STOP-TO-STOP.  OPENED UP ELEVATOR AND FOUND BROKEN RIVET AT OUTBOARD HINGE POINT.  REPLACED RIVET AND CLOSED UP SKIN	.  MOVEMENT GONE.				1	H	7	1 	3O			NC	5A6
1998121100124	19981211	00124	CE  	1998	12	11	98ZZZX4514       	1	19981101	G	7820	05501570	SEAL            	HANLON      		CESSNA	172   	172A        	2072404	CE  										MUFFLER	MISSING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	7459T	4774 				47059				EACH MUFFLER REQUIRED 3 SEALS, 0550157-29-30 AND -31 WHICH PROTECTS THE HEATER PINS FROM DAMAGING THE WALL OF THE MUFFLE	R FROM FRACTURING RESULTING IN OXYGEN ENTERING THE CABIN.  THERE WAS ONLY ONE SEAL TOTAL IN THE 2 UNITS.  REP ADVISED 6 	SEALS ARE REQURIED TO ENSURE AIRWORTHINESS.  THE LAST ANNUAL INSPECTION THAT C/W WITH THE MANUFACTURER'S REQUIRED FORMAT	 WAS JULY, 1985.  SUBSEQUENT INSPECTIONS MADE NO REFERENCE IN MAINTENANCE RECORDS OF C/W MUFFLER INSPECTIONS.			1	H	7	1 	3O				3A12
1998121100125	19981211	00125	EA  	1998	12	11	98ZZZX4515       	2	19981106	G	7322		VENT TUBE       			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					CARBURETOR	LOOSE           	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	147ER		1773 		15004705	2841142	L1106639A			THE PILOT REPORTED THE THROTTLE WAS STUCK AT FULL THROTTLE.  WHEN PILOT LANDED, IT CAME UNSTUCK.  UPON INSPECTION, FOUND	 ACCELERATOR INJECTOR TUBE BENT AND LAYING IN AIRBOX.  COMPONENT P/N PAEC1510N105217.					1	L	7	1 	3O	3	O		2A13    	E274
1998121100126	19981211	00126	CE  	1998	12	11	98ZZZX4516       	1	19981021	G	7160	16500196	AIR DOOR        			CESSNA	177   	177RG       	2073709	CE  										AIRBOX	LOOSE           	B			E96R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	122WR					177RG0744				OWNER OF AIRCRAFT SAID FUEL FLOW WAS LOW.  RAN UP, OPS CHECKED FUEL FLOW AT 14 PSI AT FULL POWER.  INSPECTED ACFT AND FO	UND TWO BOLTS MISSING FROM THROTTLE CABLE MOUNT ON BOTTOM OF ENGINE AND ALTERNATE AIR DOOR LAYING IN THE AIRBOX ASSY.  I	NSTALLED TWO NEW BOLTS IN THROTTLE CABLE MOUNT AND INSTALLED NEW ALTERNATE AIR DOOR AND HINGE AND SPRING IN AIR BOX ASSY	.  (ACFT HAS 10 HRS FROM LAST ANNUAL INSPECTION).  NEEDS INSPECTION OF AIR BOX ASSY AND ALTERNATE AIR DOOR ASSY  (VISUAL	 INSPECTION).		1	H	7	1 	3O				A20CE
1998121100128	19981211	00128	SO  	1998	12	11	98ZZZX4518       	2	19980216	G	7314	6462121	PUMP            			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	962CC		202  			21064986	294785R			FUEL PRESSURES ARE UNSTABLE AND FLUCTUATING.  THE ENGINE DRIVEN FUEL PUMP AND FUEL CONTROLLER ARE REPLACED AND THE PROBL	EM SOLVED.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSEMBLY PROCESS OF THE PUMP AND FUEL CONTROLLER AT	 RE-MANUFACTURE OF THE ENGINE.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE
1998121100129	19981211	00129	SO  	1998	12	11	98ZZZX4519       	2	19980216	G	7322	6297032	FCU             			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	962CC		202  			21064986	294785R			FUEL PRESSURES ARE UNSTABLE AND FLUCTUATING.  THE ENGINE DRIVEN FUEL PUMP AND FUEL CONTROLLER ARE REPLACED AND THE PROBL	EM SOLVED.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSEMBLY PROCESS OF THE PUMP AND FUEL CONTROLLER AT	 RE-MANUFACTURE OF THE ENGINE.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE
1998020500219	19980205	00219	EU  	1998	2	5	98ZZZX452        	1	19980115	G	5320	F9EX511111	U CHANNEL       			AMD   	FALC50	FALCON900   	2700160	EU  										FRAME 12 RT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	11	331MC					22				AILERON BELLCRANK WAS HITTING FLOOR SPLICE U-CHANNEL.  THE U-CHANNEL WAS NOT CUT AWAY PER BLUEPRINT TO ALLOW CLEARANCE F	OR BELLCRANK.  THE BLUEPRINT HAS BEEN REVISED TO PREVENT THIS FROM HAPPENING AGAIN.					2	L	7	3 	4F			RT	A46EU
1998121100130	19981211	00130	SO  	1998	12	11	98ZZZX4520       	2	19980416	G	8540	643259A8	STARTER ADAPTER 			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	962CC		698  			21064986	294563R			THE ENGINE WOULD NOT CRANK OVER.  INVESTIGATION REVEALED THE STARTER MOTOR WAS TURNING.  INSPECTION OF THE STARTER ADAPT	ER, INTERNALLY, INDICATES EXCESSIVE CLEARANCES.  REPLACEMENT OF THE UNIT RESOLVES PROBLEM.  SUBMITTER SUGGESTED POSSIBLE	 CAUSE AS DEFECTIVE PARTS AND/OR IMPROPER ASSY PROCESS FROM THE FACTORY.				1	H	7	1 	3O	3	O	RT	3A21    	E5CE
1998121100133	19981211	00133	CE  	1998	12	11	98ZZZX4523       	1	19981101	G	2820		LINE            		05503641    	CESSNA	172   	172R        	2072401	CE  	CONT  	O360  	IO360C      	17025	SO  					FUEL SYSTEM	CLOGGED         	B			N3XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	500ER	193  				17280653	L2782851A			PERFORMED FUEL LEAK CHECK AND NOTICED FUEL WAS NOT OVERFLOWING FROM INDICATION ELBOW FUEL DRAIN LINE.  REMOVED INDUCTION	 ELBOW FUEL DRAIN LINE.  REMOVED INDUCTION AIR FILTER AND FOUND INDUCTION ELBOW FULL OF 100LL.  REMOVED INDUCTION ELBOW 	FUEL DRAIN LINE AND FOUND CORK AND TOP IN LINE.  REMOVED CORK, FUEL LEAK CHECK WAS NORMAL.				1	H	7	1 	3O	3	O	NT	3A12    	E1CE
1998121100134	19981211	00134	SO  	1998	12	11	98ZZZX4524       	1	19981026	G	2810		NIPPLE          	GOODYEAR    	2F16419145RH	PIPER 	PA42  	PA42        	7104202	SO  										FUEL CELL	CRACKED         	B			TIMR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	175AA				8011868	428001017				RUBBER NIPPLE AT OUTBOARD END OF TANK FROM TIP TANK CRACKED AND ALLOWED FUEL TO LEAK FROM WING.  DEFECT WAS FOUND AFTER 	REPLACING FORWARD FUEL CELL AND FILLING WING WITH FUEL TO LEAK CHECK.  SUBMITTER SUGGESTED POSSIBLE CAUSE OF FAILURE, AG	E OF FUEL CELL CAUSING RUBBER TO BECOME CRACKED AND MOVEMENT OF FUEL CELL WHILE INSTALLATION OF FOWARD FUEL CELL.				1	L	7	2 	4T				A23SO
1998121100135	19981211	00135	CE  	1998	12	11	98ZZZX4525       	1	19981112	G	7160	2250111	SUPPORT         			CESSNA	182   	R182        	2072734	CE  										AIR BOX	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	124HK	1644 				R18207621				DUIRNG ROUTINE ANNUAL INSPECTION, FOUND CARBURETOR HEAT/ENGINE INDUCTION AIR BOX, LOWER SUPPORT BROKEN.  SUBMITTER STATE	D DAMAGE POSSIBLY CAUSED BY TWO OF THE FOUR MOUNTING BOLTS MISSING.  REMOVED AND REPLACED LOWER SUPPORT WITH NEW.					1	H	7	1 	3O			RT	3A13
1998121100136	19981211	00136	SO  	1998	12	11	98ZZZX4526       	1	19981028	G	5320	77844002	BRACKET         			PIPER 	PA38  	PA38112     	7103812	SO  										BS 134	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2322K	4133 				3879A0574				DURING ANNUAL INSPECTION, THE PULLEY CLUSTER LOCATED AT STA 134.0, WAS FOUND BROKEN OFF ITS BRACKETS AND SITTING ON BOTT	OM OF FUSELAGE.  RUDDER, ELEVATOR, AND ELEVATOR TRIM CABLES PASS UNDER THIS PULLEY CLUSTER.  THE CABLES RUBBED AGAINST T	HE BULKHEAD AT STA 134.0, BUT DID NOT APPEAR DAMAGED.  BRACKETS 77844-003 AND 77844-002 BROKE WHERE THE PULLEY CLUSTER B	OLT 401-367 PASSES THROUGH.  BOLT WAS ALSO SLIGHTLY BENT.  SUBMITTER STATED COULD NOT DETERMINE AT THIS POINT WHAT CAUSE	D BRACKET FAILURE.  POSSIBLY FATIGUE, CABLE OVERTENSION, OR MECHANICS KNEE, ETC.  SUGGEST CLOSE INSPECTION OF THIS AREA 	DURING ANNUAL OR 100-HOUR.	1	L	7	1 	3O				A18SO
1998121100137	19981211	00137	SO  	1998	12	11	98ZZZX4527       	1	19981028	G	5320	77844003	BRACKET         			PIPER 	PA38  	PA38112     	7103812	SO  										BS 134	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	2322K	4133 				3879A0574				DURING ANNUAL INSPECTION, THE PULLEY CLUSTER LOCATED AT STA 134.0, WAS FOUND BROKEN OFF ITS BRACKETS AND SITTING ON BOTT	OM OF FUSELAGE.  RUDDER, ELEVATOR, AND ELEVATOR TRIM CABLES PASS UNDER THIS PULLEY CLUSTER.  THE CABLES RUBBED AGAINST T	HE BULKHEAD AT STA 134.0, BUT DID NOT APPEAR DAMAGED.  BRACKETS 77844-003 AND 77844-002 BROKE WHERE THE PULLEY CLUSTER B	OLT 401-367 PASSES THROUGH.  BOLT WAS ALSO SLIGHTLY BENT.  SUBMITTER STATED COULD NOT DETERMINE AT THIS POINT WHAT CAUSE	D BRACKET FAILURE.  POSSIBLY FATIGUE, CABLE OVERTENSION, OR MECHANICS KNEE, ETC.  SUGGEST CLOSE INSPECTION OF THIS AREA 	DURING ANNUAL OR 100-HOUR.	1	L	7	1 	3O				A18SO
1998121100138	19981211	00138	CE  	1998	12	11	98ZZZX4528       	1	19981106	G	7430		SWITCH          			CESSNA	206   	TU206G      	2073357	CE  	CONT  	O520  	TSIO520M    	17040	SO  					COCKPIT	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	02	232MT	947  				U20606200				DURING ANNUAL, DISCOVERED AD 93-05-06 NOT C/W.  INSPECTED IGNITION SWITCH AND FOUND SIGNS OF MODIFIED STARTER RELAY IAW 	CESSNA SEB 91-5- R1.  NOTE:  AD IS RECURRING EVERY 2,000 HOURS AFTER INITIAL COMPLIANCE.					1	H	7	1 	3O	3	O		A4CE    	E8CE
1998121100139	19981211	00139	CE  	1998	12	11	98ZZZX4529       	1	19981017	G	8011	654565	SPRING          			CESSNA	210   	210J        	2073439	CE  										STARTER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	350TM					21059125				RECEIVED PART ON 10-16-98.  VISUAL INSPECTION OF SPRING REVEALED A CRACK APPROXIMATELY .0625 INCH LONG ON THE FIRST COIL	 AT THE SPRING RETAINER CUT OUT.  SUBMITTER RECOMMENDED A ONE-TIME INSPECTION OF TCM SPRINGS IN STOCK TO PREVENT PREMATU	RE FAILURE.  BROKEN SPRING PARTS COULD BE INTRODUCED INTO GEARBOXES AND CAUSE CATASTROPHIC FAILURE OF CRITICAL ENGINE PA	RTS.			1	H	7	1 	3O				3A21
1998121100141	19981211	00141	SO  	1998	12	11	98ZZZX4531       	1	19981015	G	3222	400159	FORK BOLT       			PIPER 	PA42  	PA421000    	7104225	SO  										LT MLG	FAILED          	B			SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	38AF	4651 				425527029				LEFT MAIN LANDING GEAR WOULD NOT RETRACT.  FORK BOLT WHICH ATTACHES HYDRAULIC ACTUATOR TO FORWARD SIDE BRACES HAD SHEARE	D.  INSTALLED NEW FORK BOLT, OPERATIONAL CHECK SATISFACTORY.  PIPER HAS A 500-HOUR LIFE LIMIT ON THE MLG ACTUATOR ATTACH	 BOLT WHICH SECURES THE ACTUATOR TO THE AIRFRAME, BUT NO LIMIT ON THE FORK BOLT.  SUBMITTER RECOMMENDED REPLACING FORK B	OLT EVERY 500 HOURS.			1	L	7	2 	4T			RT	A23SO
1998121100142	19981211	00142	CE  	1998	12	11	98ZZZX4532       	1	19980819	G	3230	8A05116003	CYLINDER        			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED 2 EACH OUTSID	E CYLINDERS.	1	H	7	1 	3T			NT	A37CE
1998121100143	19981211	00143	CE  	1998	12	11	98ZZZX4533       	1	19980819	G	3230	6A05268001	END CAP         			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED 2 EACH OUTSID	E END CAPS.	1	H	7	1 	3T			NT	A37CE
1998121100144	19981211	00144	CE  	1998	12	11	98ZZZX4534       	1	19980819	G	3230	8A05000010	RAM ASSY        			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED 2 EACH RAM AS	SEMBLIES.	1	H	7	1 	3T			NT	A37CE
1998121100145	19981211	00145	CE  	1998	12	11	98ZZZX4535       	1	19980819	G	3230	6A05181001	RING            			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED RING, CYLINDE	R SUPPORT, 2 EACH.	1	H	7	1 	3T			NT	A37CE
1998121100146	19981211	00146	CE  	1998	12	11	98ZZZX4536       	1	19980819	G	3230	6A05199001	FLANGE          			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED FLANGE, CYLIN	DER END, 2 EACH.	1	H	7	1 	3T			NT	A37CE
1998121100147	19981211	00147	CE  	1998	12	11	98ZZZX4537       	1	19980819	G	3230	MS28735314	O-RINGS         			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED 4 EACH O-RING	S.	1	H	7	1 	3T			NT	A37CE
1998121100148	19981211	00148	CE  	1998	12	11	98ZZZX4538       	1	19980819	G	3230	6A05580002	WIPER FELT      			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED WIPER FELT, 2	 EACH.	1	H	7	1 	3T			NT	A37CE
1998121100149	19981211	00149	CE  	1998	12	11	98ZZZX4539       	1	19980819	G	3230	6A05259002	INSERT          			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED END, SLIDE TU	BE INSERT, 2 EACH.	1	H	7	1 	3T			NT	A37CE
1998121100150	19981211	00150	CE  	1998	12	11	98ZZZX4540       	1	19980819	G	3230	880400U	WIPER           			CESSNA	208   	208         	2073702	CE  										LT MLG	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	248A					20800225				WHILE ACCOMPLISHING A SENSOR REPLACEMENT, DISCOVERED SEVERE CORROSION UNDER WIRING SPLICE TIE-WRAPPED TO THE LT TUBE.  U	PON REMOVING BUBBLED PAINT IN THE AREA, FOUND CORROSION, ALMOST TO WALL THICKNESS, IN THIS AREA.  CHECKED RT SIDE AND FO	UND AN IDENTICAL CONDITION.  AS THIS EXITS ON BOTH SIDES OF ACFT, IT MAY EXIST ON OTHER ACFT OPERATED ON SALT WATER.  TH	E PART WAS IN IMMINENT DANGER OF FAILING, ALTHOUGH THE PAINT WAS ESSENTIALLY IN GOOD CONDITION AND CORROSION WAS NOT EVI	DENT.  THE TUBE AND PROTECTIVE FINISH ARE IN GOOD CONDITION EVERYWHERE OTHER THAN IN THIS AREA.   REPLACED  WIPER, NYLON	, 2 EACH.	1	H	7	1 	3T			NT	A37CE
1998121100151	19981211	00151	CE  	1998	12	11	98ZZZX4541       	1	19981023	G	5312		BULKHEAD        			CESSNA	185   	A185F       	2072821	CE  										BS 90	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	1470Q	9836 				18503483				PARTS ARE THE COMPONENTS OF STA 90.00.  THEY RIVET TOGETHER.  THIS AREA IS WHERE THE FLOAT KIT IS INSTALLED.  RIGHT AND 	LEFT FLOAT ATTACH AREA WAS CRACKED IN MANY PLACES.  THIS AIRCRAFT HAS BEEN ON FLOATS MOST OF ITS LIFE.  SUBMITTER SUGGES	TED INSPECTION OF THIS AREA AFTER SO MANY HOURS OPERATION WITH FLOAT EQUIPPED AIRCRAFT.				1	H	7	1 	3O				3A24
1998121100221	19981211	00221	NM  	1998	12	11	98ZZZX4546       	1	19980921	G	5320		FITTING         			BOEING	727   	72725       	1384006	NM  										BS 870	DAMAGED         	B			EF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	154FE	70702				18287				DURING ACCOMPLISHMENT OF A REPEAT INSPECTION PER SB 737-53-194, HOLE NR 1 WAS FOUND ELONGATED.  LOCATED AT STA 870 STR 9	 AT THE TERMINAL FITTING.  LT HAND SIDE.  REPAIRED PER:  DALFORT AEROSPACE, L.P. XEA X1-53-692 DATED 9-14-98, BOEING SB 	727-53-194, BOEING DWG 69-14462 AND FEDEX SRM 51-30-2.  APPROVAL DATA:  FAA FORM 8110-3 DATED 9-18-98.				2	L	7	3 	4F				A3WE
1998121100225	19981211	00225		1998	12	11	98ZZZX4548       	4	19980919	G	3417	4013241901	ADC             	HONEYWELL   	AZ241       	CESSNA	501   	501         	2076603	CE  										ALTITUDE	MALFUNCTIONED   	B			NZBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	501GS				80011048	5010012				UPON INITIAL 'POWER-UP' OF AIR DATA COMPUTER, ALTIMETER CLIMBS TO 4,000 FEET, AND DROPS VERY SLOWLY.  UPON FLIGHT DESCEN	T, ALTITUDE 'CAPTURE' IS SLOW, AND CAN INDICATE 200 TO 400 FEET IN ERROR.					1	L	7	2 	4F				A27CE
1998121100226	19981211	00226		1998	12	11	98ZZZX4549       	4	19980919	G	3417	4013241901	ADC             	HONEYWELL   	AZ241       	CESSNA	501   	501         	2076603	CE  										COCKPIT	MALFUNCTIONED   	B			NZBR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	501GS				80011070	5010012				UPON INITIAL 'POWER-UP' OF AIR DATA COMPUTER, ALTIMETER FALLS OFF LINE (FLAGS), AND REMAINS OFF LINE UNTIL AIR DATA COMP	UTER IS IN THE OFF POSITION.					1	L	7	2 	4F				A27CE
1998121100239	19981211	00239		1998	12	11	98ZZZX4550       	1	19980923	G	7930	430118501	INDICATOR       								LYC   	LTS101	LTS101650B1 	41560	NE  					COCKPIT	ERRATIC         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			1875 					LE45189EA			(CAN) PILOT NOTED NEEDLE MOVEMENT ON OIL PRESSURE GAUGE.  WET LINE MAINTENANCE CHECK REVEALED FLUCTUATIONS IN EXCESS OF 	5 PSI LIMIT.  UNABLE TO ADJUST OUT PER THE MAINTENANCE MANUAL.										3	U			E5NE
1998121100240	19981211	00240	EA  	1998	12	11	98ZZZX4551       	2	19981121	G	7314	02532310102	PUMP            	PESCO       		PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					ENGINE	FAILED          	D				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			EA	27	155CA				7171	31T782002				ENGINE SHUT DOWN SHORTLY AFTER TAKEOFF.  FOUND ENGINE FUEL PUMP DRIVE COUPLING SHEARED (COUPLING WORN OUT).  REPLACED FU	EL PUMP AND ENGINE FUNCTIONING CHECK OK.  PART TOTAL TIME:  2,009.0 HOURS SMOH.					1	L	7	2 	3T	4	T		A8EA    	E4EA
1998121100241	19981211	00241		1998	12	11	98ZZZX4552       	4	19980101	G	6113	E6178	BACK PLATE      			CESSNA	414   	414A        	2075907	CE  										SPINNER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3216M	200  				414A0826				PROPELLER SPINNER BULKHEAD (2 EACH) CRACKED.						1	L	7	2 	3O				A7CE
1998121100242	19981211	00242		1998	12	11	98ZZZX4553       	4	19981123	G	6113	5506006501	BACK PLATE      			GULSTM	AA5   	AA5         	0631410	SO  										SPINNER	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	5852L	3268 				AA50052				PROPELLER REMOVED TO INSTALL NEW ALTERNATOR BELT.  FOUND SPINNER BACK PLATE CRACKED 320 DEGREES AROUND MOUNTING HOLES, C	OULD NOT BE SEEN UNLESS PROPELLER AND SPACER P/N B4381 REMOVED.  SUBMITTER STATED THIS IS THIRD SPINNER BACK PLATE FOUND	 CRACKED IN SAME AREA.  OTHER 2 WERE C150 AIRCRAFT.  RECOMMEND AD BE ISSUED FOR REMOVAL AND INSPECTION OF BACK PLATE BY 	VISUAL, DYE PENETRANT INSPECTION.  SUBMITTER STATED LOSS OF BACK PLATE IN-FLIGHT COULD CAUSE LOSS OF SPINNER AND POSSIBL	E DAMAGE OR LOSS OF AIRCRAFT.		1	L	7	1 	3O				A16EA
1998121100244	19981211	00244	SW  	1998	12	11	98ZZZX4555       	1	19980918	G	3251	3750055	BUNGEE          			GULSTM	680   	680E        	0141604	SW  										NLG	BENT            	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	50				1666	680E81862				NIGHT CREW HEARD A METALLIC OIL CANNING SOUND IN THE DIRECTION OF AIRCRAFT.  THEY INVESTIGATED AND COULD NOT FIND ANYTHI	NG.  UPON PULLING AIRPLANE OUT, THE NOSE GEAR STARTED TO COLLAPSE.  THE TOW TRACTOR WAS THEN REVERSED TO PREVENT A FULL 	COLLAPSE.  AFTER A THOROUGH INSPECTION, FOUND THE NOSE GEAR BUNGEE SHAFT WAS BENT AND THE AIRFRAME MOUNT CLEVIS BROKEN O	FF.  NO SUBSEQUENT DAMAGE TO THE GEAR OR AIRFRAME WAS DETECTED.  SUBMITTER STATED REASON FOR BUNGEE FAILURE IS UNKNOWN.			1	H	7	2 	3O				2A4
1998121100245	19981211	00245	SO  	1998	12	11	98ZZZX4556       	1	19981110	G	5520	4595106	SPAR ASSY       			PIPER 	PA31T 	PA31T       	7103124	SO  										ELEVATOR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	47CA	3550 				31T7920043				ON THE ELEVATOR CENTER HINGE, FOUND AN3-4A BOLTS LOOSE THROUGH THE SPAR TO P/N 45742-00 RIB AT BL 48.  THIS CAUSED ALL T	HE LOAD TO BE TRANSMITTED INTO THE SPAR FLANGES CRACKING BOTH FLANGES.  CHECKED OTHERS, FOUND BOLT NOT UP TO TORQUE.  SU	BMITTER BELIEVED PAINT DETERIORATION MAY BE THE CAUSE.				1	L	7	2 	3T				A8EA
1998121100246	19981211	00246	SO  	1998	12	11	98ZZZX4557       	1	19980910	G	2710	62701201	BALANCE CABLE   			PIPER 	PA32  	PA32R301    	7103218	SO  										AILERON	BROKEN          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	92208	908  				3213048				DURING AN ANNUAL INSPECTION, DISCOVERED A FLAT SHINEY SPOT ON THE BOTTOM OF THE RIGHT AILERON BALANCE CABLE.  THE LOCATI	ON OF THE CABLE IN QUESTION IS IN THE RIGHT WING ROOT AREA JUST INBD OF THE WHEELWELL.  UPON FURTHER INSPECTION, CABLE W	AS FOUND TO HAVE SEVERAL BROKEN STRANDS.  SUBMITTER STATED POSSIBLE CAUSE IS AN IDLER PULLEY THAT IS TOO SMALL OR MISALI	GNED AND A POSSIBLE SOLUTION IS TO INSTALL A LARGER DIAMETER PULLEY OR MAKE CABLE REPLACEMENT MANDATORY AT 1,000 HOURS T	IS.		1	L	7	1 	3O				A3SO
1998121100247	19981211	00247	EA  	1998	12	11	98ZZZX4558       	2	19981116	G	8520	LW12311	CAMSHAFT        			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LTO360E1A6  	41515	EA  					ENGINE	WORN            	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	41960		646  			347450165	RL18367A			NR 2 CYLINDER EXHAUST LOBE ON CAMSHAFT WORN.						1	L	7	2 	3O	3	O		A7SO    	E26EA
1998121100248	19981211	00248	SO  	1998	12	11	98ZZZX4559       	1	19981120	G	2140	A23D0475	HEATER          	JANITROL    	B4500       	PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	MALFUNCTIONED   	D		A		K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			AL	01	4112K				A98010072	318353006				FUEL WAS OBSERVED RUNNING OUT OF THE FUEL REGULATOR/SHUTOFF VALVE DRAIN CAVITY ON THE FRONT HEATER DURING A ROUTINE HEAT	 OR MAINTENANCE CHECK.  FURTHER INVESTIGATION REVEALED THE VALVE WAS LEAKING FROM THE MATING SURFACE BETWEEN THE VALVE B	ODY AND THE REGULATOR PORTION OF THE VALVE.  SUSPECT A TORN DIAPHRAGM IN THE REGULATOR.  REPLACED VALVE WITH A NEW UNIT.	  HEATER FUNCTIONALLY CHECKED SATISFACTORY.  THIS IS THE FIFTH MALFUNCTION OF THIS VALVE ON THE COMPANY'S ACFT IN RECENT	 MONTHS.		1	L	7	2 	3O				A20SO
1998121100253	19981211	00253	EA  	1998	12	11	98ZZZX4564       	2	19981112	G	8530	LW14995	SPRING          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					NR 3 CYLINDER	BROKEN          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	503MA	1321 				17266089	L4318027A			WHILE TROUBLESHOOTING AN OIL LEAK, FOUND NR 3 CYLINDER PUSH ROD HOUSING RETAINER SPRING BROKEN.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998121100254	19981211	00254	CE  	1998	12	11	98ZZZX4565       	1	19981112	G	2720	0310965	SPRING          			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					RUDDER CONTROL	BROKEN          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	503MA	6071 				17266089	L4318027A			DURING PRE-FLIGHT INSPECTION, NOTED WITH NOSE GEAR TURNED LEFT, THE RUDDER REMAINED FULL RIGHT.  INSPECTION FOUND LEFT R	UDDER RETURN SPRING BROKEN IN LEFT CONSOLE.  SPRING COULD HAVE INTERFERRED WITH RUDDER CONTROL.  REPLACED SPRING.  SUBMI	TTER SUGGESTED LIFE LIMITING RETURN SPRINGS.  BREAK WAS CLEAR WITH NO EVIDENCE OF PREVIOUS DAMAGE.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998121100255	19981211	00255	CE  	1998	12	11	98ZZZX4566       	1	19981116	G	2430	VR600A	VOLTAGE REG     			CESSNA	150   	150         	2071802	CE  										DC SYSTEM	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	16216				8013735	15073549				NEW VOLTAGE REGULATOR VR600A WOULD NOT CONTROL VOLTAGE (OVER VOLTAGE) WITH S-WIRE CONNECTED TO CA2 CIRCUIT BREAKER.  CON	NECTED S-WIRE TO A STANDARD 5-AMP BREAKER AND SYSTEM CHARGED NORMALLY.					1	H	7	1 	3O			NT	3A19
1998121100256	19981211	00256	CE  	1998	12	11	98ZZZX4567       	1	19981101	G	3260	20700171	SWITCH          			CESSNA	177   	177RG       	2073709	CE  										RT MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										ON GEAR RETRACTION, BOTH THE UP AND DOWN LIGHTS WERE ON.  PLACED GEAR SELECTOR IN DOWN POSITION AND GEAR STAYED UP. WHEN	 EMG PUMP GIVEN STROKES, NOSE GEAR STARTED DOWN.  THE PUMP THEN CAME ON AND GEARS STARTED TO EXTEND.  WHEN THE NOSE GEAR	 LOCKED DOWN THE PUMP STOPPED, LEAVING MAINS IN TRAIL POSITION.  CONTINUED TO PUMP EMG PUMP, BOTH MAINS LOCKED DOWN.  ON	 INSPECTION, GEAR DOWN MAGNET FOR RT GEAR WAS WELDED CLOSED, AND LT WAS INTERMITTENT.  REPLACED BOTH SWITCHES AND ALL SY	STEMS OK TO NORMAL.		1	H	7	1 	3O				A20CE
1998121100257	19981211	00257	CE  	1998	12	11	98ZZZX4568       	1	19981101	G	3260	20700174	SWITCH          			CESSNA	177   	177RG       	2073709	CE  										LT MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99										ON GEAR RETRACTION, BOTH THE UP AND DOWN LIGHTS WERE ON.  PLACED GEAR SELECTOR IN DOWN POSITION AND GEAR STAYED UP. WHEN	 EMG PUMP GIVEN STROKES, NOSE GEAR STARTED DOWN.  THE PUMP THEN CAME ON AND GEARS STARTED TO EXTEND.  WHEN THE NOSE GEAR	 LOCKED DOWN THE PUMP STOPPED, LEAVING MAINS IN TRAIL POSITION.  CONTINUED TO PUMP EMG PUMP, BOTH MAINS LOCKED DOWN.  ON	 INSPECTION, GEAR DOWN MAGNET FOR RT GEAR WAS WELDED CLOSED, AND LT WAS INTERMITTENT.  REPLACED BOTH SWITCHES AND ALL SY	STEMS OK TO NORMAL.		1	H	7	1 	3O				A20CE
1998121100258	19981211	00258		1998	12	11	98ZZZX4569       	1	19981117	G	6120	5628322183	PROPELLER CABLE 																	LEFT	MISMANUFACTURED 	B			KZ5R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	15										NEW CABLES BEING USED TO REPLACE OLD LEFT PROPELLER COATED CABLES WHEN ROUTED THROUGH AIRCRAFT FOR INSTALLATION ARE NEXT	 TO BEING LOCKED UP AND VERY HARD TO MOVE.  HOWEVER, WHEN LAID FLAT ON THE FLOOR OR STRAIGHTENED OUT, THEY WORK FINE.
1998020500224	19980205	00224	CE  	1998	2	5	98ZZZX457        	1	19980109	G	2121	MB38A	BLOWER          			CESSNA	500   	550         	2076604	CE  										CABIN	SEIZED          	B			OE5R	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			GL	23	77ND	313  			200	5500005				PILOT REPORTED SMOKE ON LANDING.  FOUND CABIN BLOWER MOTOR TO BE CAUSE.  MOTOR WAS SEIZED.  (MOTOR INSTALLED IN 1991.) T	SOH/TSN:  313.1 HOURS.  INSTALLED NEW BLOWER MOTOR.					1	L	7	2 	4F				A22CE
1998121100259	19981211	00259		1998	12	11	98ZZZX4570       	1	19981027	G	7922	SL53E19600	VERNATHERM      																	ENGINE OIL	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23										THIS PART FROM LOT 503273 DATED 11-2-95, S/N 3743.  NOTICED EXCESS SLIVER OF METAL ON SPRING SUPPORT CONE.  THIS COULD F	ALL OFF IN OIL SYSTEM.  FOUND BEFORE INSTALLATION.
1998121100260	19981211	00260	CE  	1998	12	11	98ZZZX4571       	1	19981115	G	2435	631847	SHAFT GEAR      		643259A16   	CESSNA	421   	421A        	2076012	CE  	CONT  	O520  	GTSIO520D   	17032	SO  					STARTER ADAPTER	BROKEN          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	200CH		130  			421A0102	231474R			GEARS ON SHAFT GEAR BROKEN OFF WHICH CAUSED SHAFT GEAR TO DAMAGE CASE WHERE PILOT BEARING GOES.						1	L	7	2 	3O	3	O		A7CE    	E7CE
1998121100261	19981211	00261	CE  	1998	12	11	98ZZZX4572       	1	19981106	G	5312	05530311	WEB             			CESSNA	172   	172R        	2072401	CE  										FIREWALL	CRACKED         	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	782WW	592  				17280295				DURING A ROUTINE INSPECTION, THE FIREWALL WAS FOUND CRACKED AT THE COWL MOUNT JUST BELOW THE BATTERY BOX.  THE CRACK WAS	 APPROXIMATELY 4 INCHES IN LENGTH.  SUBMITTER STATED POSSIBLE CAUSE AS USE OF A THINNER FIREWALL AND NO LOAD BEARING SUR	FACE FOR THE LORD MOUNT BRACKET WHICH FLEXES AS ENGINE RUNS.				1	H	7	1 	3O			NT	3A12
1998121100262	19981211	00262		1998	12	11	98ZZZX4573       	4	19981114	G	3457	KLN90B	GPS             	BENDIX      		BEECH 	36    	A36         	1151604	CE  										COCKPIT	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	107KC				21778	E2965				IFR FLIGHT PLAN, GPS DIRECT IN IMC - SETTING UP TO SHOOT AN ILS AND WAS GOING TO USE THE GPS FOR SITUATIONAL AWARENESS. 	 WHEN THE LEFT CURSOR BUTTON WAS PRESSED, THE GPS SCREEN DISSOLVED AND WENT BLANK.  WHEN THE SCREEN CAME BACK ON IN ABOU	T 5 SECONDS, THE GPS WENT INTO SELF-TEST MODE.  THE GPS LOST ALL USER-DATA AND COULD NOT LOCATE ITSELF.				1	L	7	1 	3O				3A15
1998121100263	19981211	00263	SO  	1998	12	11	98ZZZX4574       	1	19981101	G	2720	1607000	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  										RUDDER	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	6272Y					273517				AFTER REMOVING LOWER RUDDER SKIN, P/N 16199-02 FOR WIND DAMAGE, FOUND RUDDER TORQUE TUBE CRACKED IN TWO PLACES, BOTH CRA	CKS RADIATING AROUND TUBE JUST BELOW TOP RIB ATTACH FLANGE ON TUBE.  SUBMITTER STATED HAS BEEN CRACKED FOR UNKNOWN PERIO	D OF TIME DUE TO CORROSION FOUND IN CRACKS.  NO COMMENTS AS TO POSSIBLE CAUSE OF ANY SIGN OF DAMAGE TO LOWER SKIN OR BEN	T/CRACKED LOWER RUDDER RIB, P/N 161660-00.  SUBMITTER RECOMMENDED FURTHER INSPECTION OF AREA, ESPECIALLY RUDDER TORQUE T	UBE.		1	L	7	2 	3O				1A10
1998121100264	19981211	00264	SO  	1998	12	11	98ZZZX4575       	1	19981119	G	5543	1705900	RUDDER          			PIPER 	PA23  	PA23        	7102302	SO  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07		6650 								WHILE C/W AD 63-07-03 AND SB 213 WHICH REQUIRES INSPECTION OF THE RUDDER TRIM TAB HORN AND ATTACHMENT AREA SKIN, CRACKS 	WERE DISCOVERED IN SEVERAL RIVET HOLES AS WELL AS A MODERATE AMOUNT OF DISSIMILAR METAL CORROSION AND PITTING.  WHILE RE	PAIRING THE ABOVE DISCREPANCIES, CRACKS WERE ALSO FOUND IN THE RIB AREA.				1	L	7	2 	3O				1A10
1998121100265	19981211	00265	CE  	1998	12	11	98ZZZX4576       	1	19981106	G	2820	50920085259	B-NUT           			BEECH 	90    	C90         	1152913	CE  										FUEL DIST	CRACKED         	B	P		ML2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	690JP	6533 				LJ690				FUEL TRANSFER TUBE B-NUTS FOUND CRACKED.						1	L	7	2 	3T				3A20
1998121100266	19981211	00266	CE  	1998	12	11	98ZZZX4577       	1	19981014	G	5320	9542001711	WEB             		9542001715  	BEECH 	95    	95B55       	1152729	CE  										FUSELAGE	BUCKLED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8493N	2317 				TC1112				DURING ANNUAL INSPECTION, THE FRONT SPAR CARRY-THROUGH STRUCTURE AFT WEB WAS FOUND BUCKLED IN THE LEFT LOWER WING ATTACH	 FITTING AREA.  THE DAMAGE EXTENDED FROM THE LOWER OUTBOARD TO AND THROUGH THE UPPER INBOARD HUCK BOLTS.  IT ALSO EXTEND	ED HORIZONTALLY BELOW FITTING FROM OUTBOARD FORWARD OF END BELOW FITTING INBOARD APPROX 18 INCHES LONG AND .1250 INCH DE	EP.  GREASE, DIRT AND DEBRIS HAD TO BE CLEANED FROM AREA TO ADEQUATELY INSPECT.  AIRCRAFT HAS PREVIOUS HISTORY OF GEAR U	P LANDING.		1	L	7	2 	3O			RT	3A16
1998121100267	19981211	00267	CE  	1998	12	11	98ZZZX4578       	1	19981106	G	7810	70121	MUFFLER         			BEECH 	33    	F33A        	1151425	CE  										ENGINE	BUCKLED         	B	P		ML2R	O				OTHER                   				M			OVER TEMP                 			NR	NOT REPORTED   	1			GL	11	3058S	3674 				CE1099				HEATER DUCT FOUND BURNED THROUGH.  UPON INSPECTION OF HEATER/MUFFLER, FOUND HOLES THROUGH WALL OF MUFFLER INTO HEATER AR	EA.					1	L	7	1 	3O				3A15
1998121100268	19981211	00268	CE  	1998	12	11	98ZZZX4579       	1	19980914	G	3230	3A06031001	FITTING         	WIPLINEINC  	3730        	CESSNA	206   	U206G       	2073356	CE  										FUSELAGE	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05										DURING RECEIVING INSPECTION OF A WIPLINE 3730 NOSE LANDING GEAR PIVOT BLOCK, CORROSION/CASTING FLAWS WERE FOUND ON THE L	OWER FACE SURFACE.  THE PART WAS RED TAGGED AND RETURNED TO WIPAIRE, INC.					1	H	7	1 	3O				A4CE
1998020500225	19980205	00225	CE  	1998	2	5	98ZZZX458        	1	19980115	G	3230	55275341	ACTUATOR        			CESSNA	500   	550         	2076604	CE  										LT MLG UPLOCK	FAILED          	B			AU3R	L	O			ABORTED APPROACH        	OTHER                   			P			NO WARNING INDICATION     			AP	APPROACH       	1			WP	15	789TT	5125 				5500343				AIRCRAFT REPORTED NO DOWNLOCK INDICATION ON LT GEAR AFTER REPEATED CYCLES.  AIRCRAFT MADE LOW PASS.  LT GEAR WAS CONFIRM	ED TO BE UP AND LOCKED.  MANUAL UPLOCK RELEASE DEPLOYED.  LT GEAR STILL LOCKED UP.  EMERGENCY BLOW-DOWN BOTTLE WAS ACTUA	TED AND 3 GREEN INDICATED.  ACFT LANDED UNEVENTFULLY.  ACFT PLACED ON JACKS, FAILURE DUPLICATED.  FOUND UPLOCK LEAKING I	NTERNALLY AND BYPASSING FLUID.  ACTUATOR ALSO ACTS AS SEQUENCE VALVE TO MAIN ACTUATOR.  NEW PART INSTALLED, PROBLEM CORR	ECTED.		1	L	7	2 	4F				A22CE
1998121100269	19981211	00269	CE  	1998	12	11	98ZZZX4580       	1	19980914	G	5720	3A02057001	STRUT FITTING   	WIPLINEINC  	3730        	CESSNA	206   	U206G       	2073356	CE  										FUSELAGE	CORRODED        	B			NZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05										DURING THE RECEIVING INSPECTION OF A WIPLINE 3730 FRONT STRUT JOINING FITTING, PITTING CORROSION WAS FOUND ON THE FRONT 	FACE SURFACE.  THE PART WAS RED TAGGED AND RETURNED TO WIPAIRE, INC.					1	H	7	1 	3O				A4CE
1998121100270	19981211	00270		1998	12	11	98ZZZX4581       	1	19980914	G	3246	3A01156007	COVER           	WIPLINEINC  	3730        	GULSTM														SPREADER BAR	MISIDENTIFIED   	B			NZBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	05										DURING RECEIVING INSPECTION OF A WIPLINE 3730 FLOAT SPREADER BAR COVER REINFORCMENT, FOUND THE PART NUMBER ON THE PART D	ID NOT MATCH THE MANUFACTURER'S CORRESPONDING PAPER WORK.  FURTHER INVESTIGATION REVEALED THAT AN INCORRECT NUMBER, 6A01	156-14, WAS STAMPED ON THE PART.  THE PART WAS GREEN TAGGED AND RETURNED TO WIPAIRE, INC.
1998121100271	19981211	00271	SW  	1998	12	11	98ZZZX4582       	1	19981007	G	7830		STAIN COVER     		99123771    	GULSTM	560   	560         	0141402	SW  										THRUST REVERSER	WORN            	B	L		AC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	356WC	612  				560432				STAIN COVER WORN ON THRUST REVERSER.						1	H	7	2 	3O				6A1
1998121100272	19981211	00272	SO  	1998	12	11	98ZZZX4583       	1	19981029	G	2810		FUEL CELL       			PIPER 	PA34  	PA34200     	7103405	SO  										FUSELAGE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	1039U					347250024				FUEL LEAKING ON SPAR AND ODOR IN COCKPIT.  REMOVED FUEL TANKS AND REPLACED FLEXIBLE FUEL LINES.  TREATED FOR CORROSION P	ER PIPER SB 1006.  THIS SB DOES NOT APPLY TO THE PA-34 SERIES THOUGH AIRCRAFT HAS SAME FUEL TANKS AND FUEL SYSTEM AS THO	SE CALLED OUT IN SB 1006.  SUBMITTER SUGGESTED SB BE CHANGED TO INCLUDE PA-34 SERIES.				1	L	7	2 	3O				A7SO
1998121100273	19981211	00273	CE  	1998	12	11	98ZZZX4584       	1	19980829	G	7160		FILTER          			CESSNA	172   	172R        	2072401	CE  										INDUCTION AIR	SATURATED       	H				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	05	995CP					17280319				PILOT REPORTED LOSS OF POWER DURING LEVEL CRUISE FLIGHT.  WEATHER CONDITIONS PREVAILING WERE 1/8 MILE, MODERATE RAIN.  I	T IS SUSPECTED THE INDUCTION AIR FILTER BECAME SATURATED AND THE ALTERNATE AIR DOORS WERE TOO SLOW IN OPENING.  TWO SIMI	LAR INCIDENTS HAVE BEEN REPORTED LOCALLY.  CESSNA AIRCRAFT HAS BEEN NOTIFIED.				1	H	7	1 	3O			NT	3A12
1998121100274	19981211	00274	CE  	1998	12	11	98ZZZX4585       	1	19980829	G	7160		FILTER          			CESSNA	182   	182S        	2072701	CE  										INDUCTION AIR	SATURATED       	D				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			SO	19	81BR					18280041				PILOT REPORTED LOSS OF POWER DURING CLIMB-OUT AFTER A MISSED APPROACH.  WEATHER CONDITIONS PREVAILING WERE ZERO VISIBILI	TY AND HEAVY RAIN.  IT IS SUSPECTED THE INDUCTION AIR FILTER BECAME SATURATED AND THE ALTERNATE AIR DOORS WERE SLOW IN O	PENING.  TWO OTHER SIMILAR INCIDENTS REPORTED BY TWO OTHER AIRCRAFT.  CESSNA AIRCRAFT NOTIFIED OF THIS PROBLEM.				1	H	7	1 	3O			NT	3A13
1998121100275	19981211	00275		1998	12	11	98ZZZX4586       	1	19981014	G	7160	460632	FILTER          																	AIRBOX	MISMANUFACTURED 	B			BXSR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	09										REFERENCE PIPER SB NR 1022.  WHEN THIS FILTER WAS FIRST INSPECTED IT LOOKED PERFECT, BUT WHEN THE RUBBER EDGE WAS FLEXED	 FIRMLY, RUBBER CHUNKS BROKE OFF EASILY.  THESE CHUNKS WOULD INSTANTLY BE INGESTED INTO THE CARBURETOR IF THEY WERE TO B	REAK OFF ON THEIR OWN.  SUBMITTER STATED A CURSORY INSPECTION WOULD NOT HAVE REVEALED ANY PROBLEM.
1998121100276	19981211	00276	CE  	1998	12	11	98ZZZX4587       	1	19981022	G	3242	070009954	LINE            			CESSNA	182   	182K        	2072724	CE  										MLG	CRACKED         	H	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	2624R	1710 				18258324				THE ALUMINUM BRAKE LINE CRACKED AT THE HOSE CLAMP.  TIME-IN SERVICE ESTIMATED TO BE 31 YEARS.  BRAKE FAILED WHILE LANDIN	G.					1	H	7	1 	3O			NT	3A13
1998121100277	19981211	00277	CE  	1998	12	11	98ZZZX4588       	1	19981019	G	7931		LINE            			BEECH 	P35   	P35         	1151530	CE  										OIL SYSTEM	FAILED          	D				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	01	61JC	3300 				D7021				.1250 INCH ALUMINUM LINE WHICH CONNECTS BETWEEN ENGINE CRANKCASE AND FLEXIBLE LINE GOING TO OIL PRESSURE GAUGE BROKE IN-	FLIGHT CAUSING LOSS OF APPROXIMATELY 5 QUARTS (OUT OF TEN) OF OIL BEFORE AIRCRAFT COULD BE LANDED.   SUBMITTER FEELS AN 	AD REQUIRING REPLACEMENT OF THE METAL LINE WITH A SUITABLE FLEXIBLE LINE SHOULD BE GENERATED.  THIS FAILURE OCCURRED INS	IDE AN ADEL CLAMP MAKING PRE-FLIGHT INSPECTION DIFFICULT.			1	L	7	1 	3O			RT	3A15
1998121100278	19981211	00278	SO  	1998	12	11	98ZZZX4589       	1	19981021	G	3710	215CC	AIR PUMP        			PIPER 	PA28  	PA28RT201   	7102818	SO  										ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	2824Y	52   				28R7918161				FAILED 52 HOURS - OLD DRIVE SHAFT .  PUMP STILL TURNS.  FOUR OF LAST FOUR AIR PUMPS HAVE FAILED.  HOURS TO FAILURE:  NR 	1, ZERO HOURS.  NR 2, 10 MINUTES.  NR 3, 10 HOURS.  NR 4, 52 HOURS.  REF:  PARKER AIRBORNE SL.					1	L	7	1 	3O				2A13
1998020500226	19980205	00226	CE  	1998	2	5	98ZZZX459        	1	19980114	G	3231	1018101267	SWIVEL          		1018101265  	BEECH 	200   	200BEECH    	1152920	CE  										LT INBD MLG DOOR	BROKEN          	B		A	EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	84CC					BB691				LT MLG DOOR SWIVEL FOUND BROKEN ON POST-FLIGHT.  DETERMINED UNIVERSAL ACTION OF AN45 EYEBOLT WITH LINK ASSY WHICH ATTACH	ES MAIN GEAR DOOR, CAN BIND AND BREAK SWIVEL.  KIT PN 101-8013-5 INSTALLS A CORRECTED UNIVERSAL DESIGN TO PREVENT ANY BI	NDING IN THE UNIVERSAL ACTION OCCURRENCE DURING GEAR CYCLE.  SI NR 1114 ADDRESSES THIS IMPROVEMENT.				1	L	7	2 	4T				A24CE
1998121100279	19981211	00279	SO  	1998	12	11	98ZZZX4590       	2	19981020	G	8520	646277	LIFTER          			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520P    	17040	SO  					ENGINE	CHIPPED         	B			ONFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	665SW	393  				P21000588	278724R			UPON REMOVAL OF CYLINDER NR 1, INSPECTION OF LIFTERS OF CAM LOBES REVEALED CYLINDER LIFTER FACE CHIPPED OUT CAUSING SCRA	TCHES ON CAMSHAFT LOBE.  THIS AIRCRAFT DOES NOT HAVE A HISTORY OF PROLONGED PERIODS WITHOUT FLYING.  ENGINE INSTALLED LE	SS THAN 3 YEARS AGO.  THIS WAS A FACTORY RE-BUILT ENGINE.  SUBMITTER STATED IF OPERATION HAD CONTINUED, SEVERE SPALLING 	WITH LIFTER AND LOBE WOULD HAVE DEVELOPED.			1	H	7	1 	3O	3	O		3A21    	E8CE
1998121800001	19981218	00001	CE  	1998	12	18	98ZZZX4591       	1	19981101	G	5320		STIFFENER       			CESSNA	150   	150G        	2071816	CE  										FUSELAGE	CRACKED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	3877J					15065177				STIFFENER, P/N 0412521-3, WAS FOUND CRACKED IN 4 PLACES, .25 INCH TO .3750 INCH LONG.  THIS CONDITION WAS CAUSED BY LOOS	E BOLTS IN PLATE, P/N 0412010-1, FITTINGS, P/N 0432005-1, AND P/N 0432005-2.  BOLTS AND BOLT HOLES WERE WORN EXCESSVIELY	.  THIS CONDITION CAN BE CHECKED BY PLACING FINGERS ON FITTINGS AND PLATES WHILE SHAKING HORIZONTAL STABILIZER.  SUBMITT	ER STATED THIS LOOSE CONDITION HAS BEEN FOUND ON 3 AIRCRAFT IN THE LAST MONTH.  NOTE:  ONLY 1 OF 3 AIRCRAFT HAD STIFFENE	R CRACKED.  ACFT TT:  3,520.0 HOURS.		1	H	7	1 	3O				3A19
1998121800002	19981218	00002	CE  	1998	12	18	98ZZZX4592       	1	19981013	G	7810	991029925	HEADER          			CESSNA	340   	340A        	2076405	CE  										EXHAUST	MISMANUFACTURED 	H	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09					0598					HWS RECEIVED FROM CUSTOMER A NEW TURBOCHARGER EXHAUST HEADER WYE WHICH WAS PURCHASED FROM A CESSNA DISTRIBUTOR RECENTLY 	FOR INSPECTION.  THE CUSTOMER WAS CONCERNED ABOUT THEIR PART BECAUSE ATTEMPTING TO INSTALL CORRESPONDING PARTS IN THEIR 	RESPECTIVE POSITIONS WAS NOT POSSIBLE.  THIS WAS ONE OF SEVERAL IDENTICAL NEW PARTS WHICH THE CUSTOMER HAD RECENTLY RECE	IVED FROM CESSNA AND ALL HAD FAA FORM 8130-3 ACCOMPANYING.			1	L	7	2 	3O				3A25
1998121800003	19981218	00003	CE  	1998	12	18	98ZZZX4593       	1	19981013	G	7810	991029925	HEADER          			CESSNA	414   	414         	2075908	CE  										EXHAUST	MISMANUFACTURED 	H	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99					0598					HWS RECEIVED FROM CUSTOMER A NEW TURBOCHARGER EXHAUST HEADER WYE WHICH WAS PURCHASED FROM A CESSNA DISTRIBUTOR RECENTLY 	FOR INSPECTION.  THE CUSTOMER WAS CONCERNED ABOUT THEIR PART BECAUSE ATTEMPTING TO INSTALL CORRESPONDING PARTS IN THEIR 	RESPECTIVE POSITIONS WAS NOT POSSIBLE.  THIS WAS ONE OF SEVERAL IDENTICAL NEW PARTS WHICH THE CUSTOMER HAD RECENTLY RECE	IVED FROM CESSNA AND ALL HAD FAA FORM 8130-3 ACCOMPANYING.			1	L	7	2 	3O			RT	A7CE
1998121800004	19981218	00004	CE  	1998	12	18	98ZZZX4594       	1	19981106	G	5520	MS210783	NUTPLATE        		05121651    	CESSNA	172   	172R        	2072401	CE  										ELEVATOR	SEPARATED       	B			WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	782WW	790  				17280295				A PRE-FLIGHT REVEALED ELEVATOR WAS NOT HITTING DOWN STOP.  FURTHER INSPECTION REVEALED DOWN STOP BOLT WAS PUSHED IN.  DI	SASSEMBLY REVEALED MS21078-3 NUTPLATE IS A TWO-PIECE PRESSED NUTPLATE THAT CAN BE DISLODGED WITH REPEATED HITTING.  OTHE	R AIRCRAFT OF 172R THAT HAVE BEEN INSPECTED USE THIS NUTPLATE.  THE PROBLEM OF ORDERING NUTPLATES IS THAT MS21078-3 NUTP	LATES ORDERED FROM CESSNA ARE PRESSED IN TYPE.  ANOTHER MS21078-3 NUTPLATE ORDER FROM AIRCRAFT VENDOR IS NOT PRESSED IN 	TYPE.  THE SOLID MS21078-3 WAS INSTALLED AS REPLACEMENT.		1	H	7	1 	3O			NT	3A12
1998121800005	19981218	00005	GL  	1998	12	18	98ZZZX4595       	1	19981016	G	2913	105932B	O-RING          	PRESTOLITE  	195672      	BLANCA	17    	1731ATC     	1220437	GL  										HYD POWER PACK	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	9550E	1409 			AH5945	7531114				THE O-RING THAT SEALS OFF THE MOTOR FROM THE RESERVOIR WAS COMPLETELY WORN OUT ALLOWING OIL TO SEEP INTO THE MOTOR.  IT 	WAS THIS OIL MIXED WITH THE CARBON FROM THE BRUSHES THAT CAUSED GREASE TO BUILD UP AND EVENTUALLY CAUSED THE MOTOR TO FA	IL.  ANY AMOUNT OF OIL OR GREASE IN THIS TYPE OF MOTOR WILL PLAY HAVOC ON HOW IT IS SUPPOSED TO OPERATE.  MOTOR FAILED. 	 ACFT LANDED GEAR UP.  SUBMITTER SUGGESTED CHECKING MOTOR FOR EVIDENCE OF GREASE AND OIL AT ANNUAL INSPECTION.			1	L	7	1 	3O				A18CE
1998121800006	19981218	00006	SO  	1998	12	18	98ZZZX4596       	1	19981030	G	3230	4178900	RETRACTION ARM  			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	FAILED          	D	P	A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	3581C	10000				318052091				PILOT REPORTED THE LANDING GEAR WOULD HAVE INTERMITTENT INCOMPLETE UP CYCLES.  A MAINTENANCE CHECK OF GEAR FOUND THAT WH	EN SLOW CYCLED, RT MAIN GEAR WOULD NOT CATCH UPLOCK.  UPON CLOSER INSPECTION, FOUND THE ACTUATOR ATTACHMENT FORK 'BOLT' 	TO FORWARD DRAG LEG BROKEN.  NOTE:  SUBMITTER STATED IF LANDING GEAR ON UPLOCK AND BOLT HAD COME ALL THE WAY OUT, 'NO WA	Y TO GET GEAR DOWN'.			1	L	7	2 	3O				A20SO
1998121800007	19981218	00007	EA  	1998	12	18	98ZZZX4597       	2	19981019	G	7322	AN500	SCREW           			PIPER 	PA18  	PA18A150    	7101837	SO  	LYC   	O320  	O320A2B     	41508	EA  					CARBURETOR	LOOSE           	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9295D	1364 	374  			186602				ON THE PA-18 APPLICATION, THE AIR BOX IS BOLTED TO THE BASE OF CARBURETOR.  THE AN 500 SCREWS ARE SAFETIED WITH CRES WIR	E.  THESE FASTENERS COME LOOSE AND ALLOW THE FLOAT BOWL TO WORK LOOSE FROM THE THROTTLE BODY CREATING A LEAKING CONDITIO	N, AND A RICH FUEL MIXTURE.  FIX IS TO UPGRADE FASTENERS TO 4 EACH 15-B1P7 SCREWS AND 4 EACH 78-A110 LOCKING TABS.				1	H	7	1 	3O	3	O		1A2     	E274
1998121800008	19981218	00008	SO  	1998	12	18	98ZZZX4598       	2	19981101	G	7322		CARBURETOR      			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  					ENGINE	CONTAMINATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	99155					1778				AIRCRAFT WAS OUTSIDE FOR 3 YEARS NOT RUNNING. UPON INVESTIGATION, NOTED EXCESSIVE WATER IN CARBURETOR.  REMOVED CARBURET	OR FOR REPAIR.					1	L	7	1 	3O	3	O		A718    	E233
1998020500227	19980205	00227	CE  	1998	2	5	98ZZZX460        	1	19980109	G	3230	12416307	DOWNLOCK SHELL  			CESSNA	210   	P210N       	2073454	CE  										LT MLG	DEFORMED        	B			CS3R	O				OTHER                   				P			NO WARNING INDICATION     			AP	APPROACH       	1			WP	17	677PC	814  				P21000677				ON APPROACH WHEN GEAR EXTENDED, LT MAIN GREEN FAILED TO LIGHT.  EMERGENCY GEAR EXTENSION USED TO LOCK GEAR DOWN.  INSPEC	TION REVEALED INTERIOR OF DOWNLOCK SHELL LT SIDE PEELED BACK AND FOLDED OVER PREVENTING FULL TRAVEL OF LEG AND STOPPING 	OVER CENTER LOCK FROM ENGAGING.  SUSPECT CAUSE IS RUBBER COMPOSITE INSERT IS OLD AND BRITTLE CAUSING DELAMINATION.  THIS	 IS SECOND CESSNA 210 SERIES WITH IDENTICAL PROBLEM IN 1 MONTH.			1	H	7	1 	3O				3A21
1998121800011	19981218	00011	EA  	1998	12	18	98ZZZX4601       	1	19981119	G	3320		LIGHT           			CNDAIR	CL600 	CL6002B16   	1900305	EA  										CABIN	OVERTEMP        	B	P	A	VU2R	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			GL	05	5PG					5053				DURING ROUTINE BULB REPLACEMENT, FOUND ONE END OF THE FLUORESCENT TUBE HAD BEEN VERY HOT AND STARTED TO MELT THE TUBE HO	LDER.					2	L	7	2 	4F			RT	A21EA
1998121800012	19981218	00012	NM  	1998	12	18	98ZZZX4602       	1	19980824	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					KE00975					FAILED AUXILIARY BRAKE TEST.  BROKEN SPRINGS.  INSTALLED SPRINGS, P/N 69-77855-2.						2	L	7	2 	4F			RT	A16WE
1998121800013	19981218	00013	NM  	1998	12	18	98ZZZX4603       	1	19980824	G	3240	511531	HOUSING         	PNEUDRAULICS	5059        	BOEING	737   	737*        		NM  										SHUTTLE VALVE	CRACKED         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					4636					SHUTTLE VALVE HOUSING LEAKING DUE TO PIN HOLE CRACK IN SEAM.						2	L	7	2 	4F			RT	A16WE
1998121800014	19981218	00014	NM  	1998	12	18	98ZZZX4604       	1	19980817	G	3230	S6026	HOUSING         	SARGENT     	S60252      	BOEING	727   	727         	1384001	NM  										SELECTOR VALVE	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING CRACKED IN THE THREADS OF THE PORT.						2	L	7	3 	4F				A3WE
1998121800015	19981218	00015	NM  	1998	12	18	98ZZZX4605       	1	19980817	G	3230	S6026	HOUSING         	SARGENT     	S60252      	BOEING	727   	727         	1384001	NM  										SELECTOR VALVE	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										HOUSING CRACKED IN THE THREADS OF THE PORT.						2	L	7	3 	4F				A3WE
1998121800016	19981218	00016	NM  	1998	12	18	98ZZZX4606       	1	19980817	G	3230	S6026	HOUSING         	SARGENT     	S60252      	BOEING	727   	727         	1384001	NM  										SELECTOR VALVE	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1472					HOUSING CRACKED IN THE THREADS OF THE PORT.						2	L	7	3 	4F				A3WE
1998121800017	19981218	00017	NM  	1998	12	18	98ZZZX4607       	1	19980812	G	2740	69778551	SPRING          		65C347513   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		18111	8095 		KE00195					FAILED AUXILIARY BRAKE TEST.  BROKEN SPRINGS.  INSTALLED P/N 69-77855-2 SPRING.						2	L	7	2 	4F			RT	A16WE
1998121800018	19981218	00018	NM  	1998	12	18	98ZZZX4608       	1	19980811	G	2930	122510	HOUSING         	ROTOL       	1U1225      	BOEING	727   	727         	1384001	NM  										VALVE	LEAKING         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01			51946		1229					LEAKING AT SEAM INSIDE BOLT HOLE.  CASTING WEAKNESS AT SEAM.						2	L	7	3 	4F				A3WE
1998121800019	19981218	00019	NM  	1998	12	18	98ZZZX4609       	1	19980804	G	2740	69778551	SPRINGS         		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		30179	17768		KE00800					FAILED AUXILIARY BRAKE TEST.  BROKEN SPRINGS.  INSTALLED P/N 69-77855-2 SPRINGS.						2	L	7	2 	4F			RT	A16WE
1998020500228	19980205	00228	GL  	1998	2	5	98ZZZX461        	2	19980121	G	7210	23005749	BEARING         								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE GEARBOX	MAKING METAL    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23					MP18982		CAE830981			ENGINE GEARBOX BEARING RETAINER HAD FALLEN OFF DURING OPERATION AND STARTED MAKING METAL.											3	U			E4CE
1998121800020	19981218	00020	NM  	1998	12	18	98ZZZX4610       	1	19980923	G	2930	113610	HOUSING         	ROTOL       	1U1136      	BOEING	737   	737*        		NM  										VALVE	CRACKED         	B	S		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		48916			1673					HOUSING LEAKING.  HAIRLINE CRACK ON SEAM OF HOUSING ON PORT NR 1.						2	L	7	2 	4F			RT	A16WE
1998121800023	19981218	00023	EU  	1998	12	18	98ZZZX4613       	1	19981120	G	2520		SEAT PAN        			AIRBUS	320   	A320232     	3930326	EU  										CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	404UA					450				DURING FIRST HEAVY MAINTENANCE VISIT FOR THIS AIRBUS, A-320-232, 100 PERCENT OF THE SEAT PANS WERE FOUND CRACKED ON THE 	RECARO MODEL 3410, 720 SERIES PASSENGER SEATS USED IN THE COACH CLASS CABIN.  THESE SEAT PANS ARE CRACKED ADJACENT TO TH	E SCREW HOLES ON THE FORWARD EDGE OF THE PAN.  THESE ARE THE HOLES USED TO ATTACH THE SEAT PAN TO THE SEAT FRAME.				2	L	7	2 	4F			RT	A28NM
1998121800024	19981218	00024	EA  	1998	12	18	98ZZZX4614       	2	19981118	G	7414	M3819	MAGNETO         	SLICK       	4370        	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	172WE	488  			95050027	17265192	RL5061427A			FOUND DISTRIBUTOR BLOCK CRACKED DURING A 500-HOUR INSPECTION.  CRACK RADIATES FROM BEARING OUTWARD APPROXIMATELY .25 INC	H.  APPEARS TO COME FROM STRESS, IN THAT AREA.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998121800025	19981218	00025		1998	12	18	98ZZZX4615       	2	19981119	G	7322	78A110	WASHER          	PRECISION   	MA4SP105217 															CARBURETOR	CRACKED         	B			NE2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07			896  		75071112					RECEIVED CARBURETOR FROM CUSTOMER WITH SQUAWK 'CARB IS LEAKING AND LOOSE AT THE BOWL".  UPON INPSECTION OF THE CARBURETO	R, FUEL STAINS WERE NOTICED ON THE BOWL ASSY AND THROTTLE BODY ASSY.  FURTHER INSPECTION REVEALED THE FOUR SCREWS HOLDIN	G THE THROTTLE BODY ASSY WERE LOOSE.  ONE OF THE FOUR TAB STYLE LOCK WASHERS (WHICH RETAIN THE SCREWS) WAS CRACKED AND H	AD SPREAD IN THE SHAPE OF A 'C'.
1998121800026	19981218	00026	WP  	1998	12	18	98ZZZX4616       	2	19981009	G	7250	31021067	TURBINE WHEEL   			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					SECOND STAGE	DAMAGED         	B		A	WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	11MM	1570 			4013456490	4410105	P77105			ENGINE COULD NOT BE TURNED BY HAND ON PRE-FLIGHT.  THIRD ROTOR WAS FOUND TO HAVE PIECES MISSING FROM T-BLADES.  ENGINE T	EAR DOWN REVEALED THAT SEVERAL PLUGGING RIVETS INSTALLED IN HOLES AT THE BLADE ROOTS ON SECOND ROTOR HAD BROKEN.  THE FL	ARED END ON ALL RIVETS WAS CONSIDERABLY SMALLER THAN THOSE ON NEW WHEELS.  RIVETS HAD COME OUT OF SECOND ROTOR AND GONE 	THROUGH BLADES ON THIRD ROTOR.  ALLIED SIGNAL SB TPE33172-2024 RELATES TO THIS PROBLEM.			1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
1998121800029	19981218	00029	NE  	1998	12	18	98ZZZX4617       	3	19981124	G	6111	57D0495	FORK            		3409NR      	BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4530 						HJ714		FORWARD EAR OF PITCH CHANGE FORK CRACKED IN INBOARD RADIUS OF PITCH PIN ENGAGEMENT SLOTS.  ONE CRACK.						2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998121800030	19981218	00030	NE  	1998	12	18	98ZZZX4618       	3	19981124	G	6111	57C0792	BEARING         			BEECH 	1900  	1900D       	1154162	CE  						HARTZL	HCE4A	HCE4A3A     	NE  	NR 4 BLADE	CRACKED         	B			EY2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03		4593 						HJ714		INNER AND OUTER RACE OF NR 4 BLADE BEARING FOUND BROKEN AND SEPARATED INTO NUMEROUS PIECES.  HUB WAS RENDERED SCRAP AS A	 RESULT OF BEARING FAILURE.  SUBMITTER SUGGESTED ENGINEERING REVIEW OF LOADS IMPOSED AT BLADE/HUB INTERFACE.  UNDER LOW 	C.F. LOADING IF THE BLADE IS AT MAX CONDITION (.750), THE BEARINGS MAY BE EXPERIENCING CYCLICAL LOADS NOT PRESENT DURING	 ORIGINAL CERTIFICATION.			2	L	7	2 	4T			RT	A24CE   		5	C	P10NE
1998020500229	19980205	00229	WP  	1998	2	5	98ZZZX462        	1	19980113	G	7714	369H4233	TACH GENERATOR  			HUGHES	369   	369D        	4470706	WP  										ENGINE N1	DEFECTIVE       	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW		1    		524	470117D				PHASING OF ENGINE OUT-SWITCHING ON N1 NOT OPERATING PROPERLY.						1	G	7	1 	3U				H3WE
1998121800032	19981218	00032	NM  	1998	12	18	98ZZZX4620       	1	19981112	G	5347		SEAT TRACK      			BOEING	727   	727227      	1384078	NM  										BS 1040-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION NOTED ON SEAT TRACK INSIDE OF L-1 DOOR STA 1040-1070.						2	L	7	3 	4F				A3WE
1998121800033	19981218	00033	NM  	1998	12	18	98ZZZX4621       	1	19981111	G	5320	NAS110716	BOLT            			BOEING	727   	727227      	1384078	NM  										STA 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORRROSION NOTED ON LT AND RT BULKHEAD ATTACH FITTING STA 1183.						2	L	7	3 	4F				A3WE
1998121800034	19981218	00034	NM  	1998	12	18	98ZZZX4622       	1	19981111	G	5720	69139004	BOTTLE PIN      			BOEING	727   	727227      	1384078	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION WAS NOTED ON RIGHT FRONT SPAR WING TO BODY BOTTLE PIN.						2	L	7	3 	4F				A3WE
1998121800035	19981218	00035	NM  	1998	12	18	98ZZZX4623       	1	19981111	G	5720	69139004	BOTTLE PIN      			BOEING	727   	727227      	1384078	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION WAS NOTED ON LEFT FRONT SPAR WING TO BODY BOTTLE PIN.						2	L	7	3 	4F				A3WE
1998121800037	19981218	00037	EU  	1998	12	18	98ZZZX4625       	1	19981028	G	2432	RG390E	BATTERY         	CONCORDEBATT		BRAERO	DH125 	BAE125800A  	1500285	EU  										BATTERY BOX	DISCHARGED      	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	74NP	377  			297304	NA0440				WILL NOT TAKE CHARGE.  DEAD SHORT IN BATTERY.  290 CYCLES.  8 MONTHS.  377 HOURS.						2	L	7	2 	4F			RT	A3EU
1998121800038	19981218	00038	EU  	1998	12	18	98ZZZX4626       	1	19981014	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										BATTERY BAY	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	75NP	513  			297331	NA0441				BOTH BATTERIES RG390E BLEW HOLE IN THE SIDE.  ENGINE WOULD NOT START.  380 TOTAL LANDINGS.						2	L	7	2 	4F			RT	A3EU
1998121800039	19981218	00039	EU  	1998	12	18	98ZZZX4627       	1	19981014	G	2432	RG390E	BATTERY         			BRAERO	DH125 	BAE125800A  	1500285	EU  										BATTERY BAY	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	05	75NP	513  			297330	NA0441				BOTH BATTERIES RG390E BLEW HOLE IN THE SIDE.  ENGINE WOULD NOT START.  380 TOTAL LANDINGS.						2	L	7	2 	4F			RT	A3EU
1998121800040	19981218	00040	EU  	1998	12	18	98ZZZX4628       	1	19981113	G	3310	LDP505A1002	POWER SUPPLY    			ISRAEL	1125  	ASTRASPX    	4500205	EU  										COCKPIT	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA	184  			LA000657	098				SEVERAL PILOT AND COPILOT INSTRUMENTS HAD NO INSTRUMENT LIGHTING.  REPLACED POWER SUPPLY.  UNIT FAILED INTERNALLY.  VERY	 LOW TIME ON UNIT THAT FAILED.					2	L	7	2 	4F			RT	A16NM
1998121800041	19981218	00041		1998	12	18	98ZZZX4629       	4	19981113	G	3442	6228440003	RADAR           			ISRAEL	1125  	ASTRASPX    	4500205	EU  										RADOME	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	275RA	184  			1911	098				RADAR CIRCUIT BREAKER TRIPS.  WILL NOT RESET.  REPLACED RADAR ANTENNA/RECEIVER/TRANSMITTER.  VERY LOW TIME ON UNIT.						2	L	7	2 	4F			RT	A16NM
1998020500230	19980205	00230	SW  	1998	2	5	98ZZZX463        	1	19980106	G	6710	2060627211	ACTUATOR        	GENDESIGN   		BELL  	206   	206B3       	1181506	SW  										ENGINE	INOPERATIVE     	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	9907K				S151A	2040				LINEAR ACTUATOR, MFG PN 71851, INTERNAL MOTOR SHUT-OFF INOPERABLE.						1	G	7	1 	3U				H2SW
1998121800042	19981218	00042	EU  	1998	12	18	98ZZZX4630       	1	19981113	G	5520		BEARING         			ISRAEL	1125  	ASTRASPX    	4500205	EU  										LT ELEVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA	186  			108	098				TOO MUCH SIDE PLAY.  OUT OF LIMITS.  MANUFACTURER REQUIRES ENTIRE ELEVATOR TO BE CHANGED DUE TO WORN BEARING.  VERY LOW 	TIME ON ITEM.					2	L	7	2 	4F			RT	A16NM
1998121800043	19981218	00043		1998	12	18	98ZZZX4631       	4	19981113	G	3445	6228971120	TCAS            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										CARGO BAY	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA	164  			5243	098				TCAS DOES NOT WORK.  FOUND TCAS TRANSMITTER INOPERATIVE.  REPLACED WITH REPAIRED UNIT.  VERY LOW TIME ON UNIT THAT FAILE	D.					2	L	7	2 	4F			RT	A16NM
1998121800044	19981218	00044	EU  	1998	12	18	98ZZZX4632       	1	19981113	G	3520	5753554503	OXYGEN REGULATOR			ISRAEL	1125  	ASTRASPX    	4500205	EU  										CABIN	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	275RA	186  			2980	098				REGULATOR WAS LEAKING OXYGEN OVERNIGHT.  REPLACED OXYGEN REGULATOR.						2	L	7	2 	4F			RT	A16NM
1998121800045	19981218	00045	EU  	1998	12	18	98ZZZX4633       	1	19981118	G	7332	1103P0956	SWITCH          			ISRAEL	1125  	ASTRASPX    	4500205	EU  										RT ENGINE	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	275RA	216  			0065	098				FUEL PRESSURE WOULD NOT INDICATE A LOW PRESSURE LIGHT WHEN PUMP IS TURNED OFF. REPLACED LOW PRESSURE SWITCH.						2	L	7	2 	4F			RT	A16NM
1998121800046	19981218	00046	EU  	1998	12	18	98ZZZX4634       	1	19981116	G	7830	71757	VALVE           			ISRAEL	1125  	ASTRASPX    	4500205	EU  										THRUST REVERSER	INTERMITTENT    	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	13	273RA	51   			0060	097				LEFT ENGINE THRUST REVERSER LIGHT.  LEFT T/R UNLOCK LIGHT ILLUMINATED.  WILL NOT GO OUT.  REPLACED ISOLATION VALVE WITH 	REPAIRED UNIT.  SWITCH ON ISOLATION VALVE IS INTERMITTENT.  VERY LOW TIME ON UNIT THAT FAILED.					2	L	7	2 	4F			RT	A16NM
1998121800047	19981218	00047		1998	12	18	98ZZZX4635       	4	19981118	G	3416	804710	ALTIMETER       			ISRAEL	1125  	ASTRASPX    	4500205	EU  										COCKPIT ALT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	273RA	82   			9413B	097				INTERGRAL LIGHTING GOES ON AND OFF WHEN BARO KNOB IS SET.  REPLACED WITH REPAIRED UNIT.  VERY LOW TIME ON INSTRUMENT THA	T FAILED.					2	L	7	2 	4F			RT	A16NM
1998121800048	19981218	00048		1998	12	18	98ZZZX4636       	4	19981116	G	3445	6228971120	TCAS            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										CABIN	INOPERATIVE     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	273RA	78   			5269	097				'TTR INOP' MESSAGE (TCAS TRANSMITTER).  REPLACED WITH REPAIRED UNIT.  VERY LOW TIME ON UNIT THAT FAILED.						2	L	7	2 	4F			RT	A16NM
1998121800049	19981218	00049	EU  	1998	12	18	98ZZZX4637       	1	19981116	G	7830	71757	VALVE           			ISRAEL	1125  	ASTRASPX    	4500205	EU  										THRUST REVERSER	INTERMITTENT    	D				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	13	273RA	44   				097				THRUST REVERSER ON BOTH ENGINES 'UNLOCK' LIGHTS UP INTERMITTENTLY.  REPLACED ISOLATION VALVE DUE TO DEFECTIVE SWITCH.  V	ERY LOW TIME ON UNIT THAT FAILED.					2	L	7	2 	4F			RT	A16NM
1998121800050	19981218	00050	NM  	1998	12	18	98ZZZX4638       	1	19981112	G	5315		FLOOR BEAM      			BOEING	727   	727231      	1384079	NM  										BS 1110	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION NOTED ON FLOOR BEAM FS 1110 RBL 24 TO LBL 24.						2	L	7	3 	4F				A3WE
1998121800051	19981218	00051	NM  	1998	12	18	98ZZZX4639       	1	19981112	G	2760	65192221	FITTING         			BOEING	727   	727231      	1384079	NM  										NR 9 SPOILER	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319					20052				DURING A C-CHECK, CORROSION WAS NOTED ON NR 9 GROUND SPOILER MOUNT LUG.						2	L	7	3 	4F				A3WE
1998020500231	19980205	00231	WP  	1998	2	5	98ZZZX464        	1	19980106	G	7931	369H6418	INDICATOR       	INSCO       		HUGHES	369   	369D        	4470706	WP  										OIL PRESSURE	STUCK           	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				OIL PRESSURE INDICATOR, MFG PN 4308-1024, HAS A STUCK NEEDLE.						1	G	7	1 	3U				H3WE
1998121800052	19981218	00052	NM  	1998	12	18	98ZZZX4640       	1	19981117	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 950	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION NOTED AT FS 950D ON STR 29R ON LOWER SURFACE AND ANGLE.						2	L	7	3 	4F				A3WE
1998121800053	19981218	00053	NM  	1998	12	18	98ZZZX4641       	1	19981117	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 400 - 440	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK RBL 50 FS 400 - FS 440.						2	L	7	3 	4F				A3WE
1998121800054	19981218	00054	NM  	1998	12	18	98ZZZX4642       	1	19981117	G	5311	6516338352	FRAME           			BOEING	727   	727259      	138408J	NM  										BS 950	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION NOTED AT STA 950 ON BULKHEAD CHORD (STR 29R TO STR 26R).						2	L	7	3 	4F				A3WE
1998121800055	19981218	00055	NM  	1998	12	18	98ZZZX4643       	1	19981117	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1166 - 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED AT FS 1166 - FS 1183 ON STR 29R.						2	L	7	3 	4F				A3WE
1998121800056	19981218	00056	NM  	1998	12	18	98ZZZX4644       	1	19981117	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1166 - 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED AT FS 1166 - FS 1183 ON STR 25R.						2	L	7	3 	4F				A3WE
1998121800057	19981218	00057	EU  	1998	12	18	98ZZZX4645       	1	19981113	G	5520		BEARING         			ISRAEL	1125  	ASTRASPX    	4500205	EU  										RT ELEVATOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA	186  			108	098				TOO MUCH SIDE PLAY.  OUT OF LIMITS.  MANUFACTURER REQUIRES ENTIRE ELEVATOR TO BE CHANGED DUE TO WORN BEARING.  VERY LOW 	TIME ON ITEM.					2	L	7	2 	4F			RT	A16NM
1998121800792	19981218	00792		1998	12	18	98ZZZX4646       	3	19980903	G	6114		HUB             			AMTR  		AVIDMAGNUM  								WARPDR		T6801       		PROPELLER	CRACKED         	D				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			NM	11	180VL					83M				HOME BUILT AIRCRAFT DEVELOPED SEVERE VIBRATION WHILE AT CRUISE ALTITUDE.  POWER REDUCED AND AN IMMEDIATE LANDING MADE AT	 A CONVENIENT GRASS AIRPORT.  DISCOVERED ONE BLADE OF THE THREE BLADE PROPELLER WAS OUT OF TRACK 2 INCHES TO THE REAR. F	URTHER INVESTIGATION REVEALED THE REAR MOUNTING PLATE CRACKED ACROSS BOTH INBOARD BLADE MOUNT HOLES.  BOLTS WERE LOOSENE	D AND TIGHTENED SEVERAL TIMES GETTING PITCH CORRECT FOR PROPER ENGINE LOADING.  TT ON ACFT 55 HOURS.						0
1998121800793	19981218	00793	GL  	1998	12	18	98ZZZX4647       	3	19981103	G	6110	C56481	BETA ROD        			BEECH 	200   	200BEECH    	1152920	CE  						MCAULY	4JFR34	4JFR34C758  	GL  	PROPELLER	BROKEN          	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	17		520  						961832		PROPELLER RECEIVED LEAKING OIL FROM BETA ROD.  UPON FURTHER INSPECTION, BETA ROD WAS FOUND BROKEN IN HALF AT THE START O	F THE THREADED PORTION OF ROD.  SUBMITTER STATED CAUSE UNKNOWN.					1	L	7	2 	4T				A24CE   		5	C	P3NE
1998121800794	19981218	00794	NE  	1998	12	18	98ZZZX4648       	2	19981006	G	7530		LINE            			BRAERO	1000  	BAE1251000A 	1500104	EU  	PWA   	305   	PW305       		NE  					NR 1 ENGINE	BROKEN          	B			XA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	530QS	2588 				259030	PCE305061			PILOT'S DISCREPANCY WAS NR 1 ENIGNE IS TEMP LIMITED ABOVE CRUISE DETENT.  REMOVED THE OUTER AND INNER BYPASS ACCESS TO C	HECK BLEED VALVES.  UPON INVESTIGATION, FOUND THE BLEED AIR (P3 LINE) BROKEN AT B-NUT, P/N 3081695.  IT APPEARED THE FIT	 OF THE LINE HAD CAUSED FAILURE BECAUSE THE 2 ENDS AT BREAK DID NOT LINE UP.  REPLACED THE LINE WITH NEW.  FIT WAS GOOD.	  RE-ASSEMBLED ENGINE.  GROUND RUN AND FLIGHT CHECK WAS GOOD.			2	L	7	2 	4F	4	F	RT	A3EU    	E35NE
1998121800795	19981218	00795		1998	12	18	98ZZZX4649       	4	19981110	G	6122	6851007	COIL            	WOODWARD    	8974108     															PROP GOVERNOR	DETACHED        	B			IG0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										SYNCROPHASE COIL CAME LOOSE GRINDING METAL TO METAL AGAINST FLYWEIGHT ASSEMBLY.  UNIT RECEIVED WITHOUT DATAPLATE.
1998020500232	19980205	00232	WP  	1998	2	5	98ZZZX465        	1	19980106	G	2841	369H641751	GAUGE           			HUGHES	369   	369D        	4470706	WP  										FUEL QUANTITY	FLUCTUATION     	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC				6457740	290456D				FUEL GAUGE FLUCTUATES.						1	G	7	1 	3U				H3WE
1998121800796	19981218	00796	SW  	1998	12	18	98ZZZX4650       	1	19980626	G	5280	NAS464P4A10	BOLT            		55421028    	GULSTM	560   	560         	0141402	SW  										NLG DOOR	BROKEN          	D				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	11	30PC	5223 				5600090				TORQUE TUBE, NLG DOORS, ATTACH BOLT, RT SIDE, BROKE IN-FLIGHT CAUSING NLG DOORS TO OPEN.  CREW DIVERTED TO VALDOSTA, GA.	  EITHER BOLT IS TOO LONG OR NO WASHER WAS INSTALLED AT FACTORY.  SUBMITTER RECOMMENDED CHECK P/N ON BOLT AND INSURE WAS	HER IS PRESENT.  BOLT APPEARED TO BE CRACKED BEFORE IT BROKE.  RUST WAS NOTICED AT BRAKE.				1	H	7	2 	3O				6A1
1998121800797	19981218	00797	SO  	1998	12	18	98ZZZX4651       	1	19981204	G	7160	434134	GROMMET         			PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4144K	86   				2843145				DURING A SCHEDULED INSPECTION OF THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  TH	IS IS A RECURRING PROBLEM ON FLEET OF ARCHER 111'S.  THESE BUSHINGS AND GROMMETS HAVE TO BE REPLACED EVERY 50 TO 100 HOU	RS OF OPERATION.  SUBMITTER STATED IT IS POSSIBLE THAT PARTS OF THE GROMMET AND BUSHING MATERIAL COULD BE INJESTED BY TH	E ENGINE.			1	L	7	1 	3O				2A13
1998121800798	19981218	00798	SO  	1998	12	18	98ZZZX4652       	1	19981204	G	7160	453491	BUSHING         			PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4144K	86   				2843145				DURING A SCHEDULED INSPECTION OF THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  TH	IS IS A RECURRING PROBLEM ON FLEET OF ARCHER 111'S.  THESE BUSHINGS AND GROMMETS HAVE TO BE REPLACED EVERY 50 TO 100 HOU	RS OF OPERATION.  SUBMITTER STATED IT IS POSSIBLE THAT PARTS OF THE GROMMET AND BUSHING MATERIAL COULD BE INJESTED BY TH	E ENGINE.			1	L	7	1 	3O				2A13
1998121800799	19981218	00799	SO  	1998	12	18	98ZZZX4653       	1	19981101	G	2822	1656	PUMP            			PIPER 	PA32  	PA32300     	7103212	SO  										FUSELAGE	INTERMITTENT    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	4215R	4403 			1N17	3240580				PIPER P/N 481-701.  ELECTRIC FUEL PUMP REPORTED INTERMITTENT.  REMOVED PUMP AND REMOVED REAR COVER TO INSPECT BRUSHES AN	D FOUND THE ELECTRIC MOTOR FULL OF FUEL.  UNIT IS BEING SENT FOR OVERHAUL.  SUBMITTER STATED THE MOTOR SHAFT BEARING HAS	 ALLOWED FUEL PAST IT.				1	L	7	1 	3O				A3SO
1998121800801	19981218	00801	SO  	1998	12	18	98ZZZX4655       	2	19980820	G	7414	1051676F	CONDENSER       		S6RN25      						CONT  	O520  	IO520F      	17032	SO  					ENGINE	FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		124  			J189126DR		1682257F			CONDENSER FAILED 124 HOURS AFTER OVERHAUL.  THIS CAUSED THE POINTS TO BURN RESULTING IN EXCESSIVE MAGNETO DROP.  DATE CO	DE:  84-47.										3	O			E5CE
1998121800802	19981218	00802	SO  	1998	12	18	98ZZZX4656       	2	19981101	G	7414	1051676F	CONDENSER       		S6RN25      	CESSNA	206   	U206        	2073306	CE  	CONT  	O520  	IO520F      	17032	SO  					MAGNETO	FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		20   								CONDENSER FAILED 20.0 HOURS AFTER OVERHAUL.  THIS CAUSED THE POINTS TO BURN RESULTING IN EXCESSIVE MAGNETO DROP.  DATE C	ODE:  96-47.					1	H	7	1 	3O	3	O		A4CE    	E5CE
1998121800803	19981218	00803	SO  	1998	12	18	98ZZZX4657       	2	19981101	G	7414	1051676H	CONDENSER       		S6RN25      						CONT  	O520  	IO520F      	17032	SO  					MAGNETO	FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		200  								CONDENSER FAILED 200 HOURS AFTER OVERHAUL.  THIS CAUSED THE POINTS TO BURN RESULTING IN EXCESSIVE MAGNETO DROP.  DATE CO	DE:  97-31.										3	O			E5CE
1998121800804	19981218	00804	SO  	1998	12	18	98ZZZX4658       	2	19980926	G	7414	1051676H	CONDENSER       		S6RN25      						CONT  	O520  	IO520F      	17032	SO  					MAGNETO	FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		120  			178918DR					CONDENSER FAILED 120 HOURS AFTER OVERHAUL.  THIS CAUSED THE POINTS TO BURN RESULTING IN EXCESSIVE MAGNETO DROP.											3	O			E5CE
1998121800805	19981218	00805	SO  	1998	12	18	98ZZZX4659       	2	19980926	G	7414	1051676H	CONDENSER       		S6RN25      						CONT  	O520  	IO520F      	17032	SO  					MAGNETO	FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		128  			DO78726DR					CONDENSER FAILED 128 HOURS AFTER OVERHAUL.  THIS CAUSED THE POINTS TO BURN RESULTING IN EXCESSIVE MAGNETO DROP.											3	O			E5CE
1998121800806	19981218	00806	SO  	1998	12	18	98ZZZX4660       	2	19981101	G	7414	10561676H	CONDENSER       		S6RN25      						CONT  	O520  	IO520F      	17032	SO  					MAGNETO	FAILED          	B			CY4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03		35   			A188806DR					CONDENSER FAILED 35 HOURS AFTER OVERHAUL.  THIS CAUSED THE POINTS TO BURN RESULTING IN EXCESSIVE MAGNETO DROP.											3	O			E5CE
1998121800807	19981218	00807	SO  	1998	12	18	98ZZZX4661       	2	19981130	G	8530	SA631496	GUIDE           								CONT  	O520  	IO520K      	17032	SO  					ENGINE	INCOMPATIBLE    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17			133  							EXHAUST VALVE STICKING AND MATERIAL TRANSFER DUE TO MATERIAL INCOMPATIBILITY.  EXHAUST VALVE (P/N SA643873), STEM IS CHR	OME PLATED AND VALVE GUIDE (P/N SA631496), IS ALUMINUM BRONZE AND THE 2 MATERIALS ARE NOT COMPATIBLE.  NI-RESIST VALVE G	UIDE (P/N 643767) SHOULD BE USED IAW TCM SB M85-18.  ALL CYLINDERS REPAIRED BY USING (P/N 652956) EXHAUST VALVE AND (P/N	 643767) EXHAUST GUIDE.								3	O			E5CE
1998121800808	19981218	00808	SO  	1998	12	18	98ZZZX4662       	2	19981130	G	8530	SA643873	VALVE           								CONT  	O520  	IO520K      	17032	SO  					ENGINE	INCOMPATIBLE    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17			133  							EXHAUST VALVE STICKING AND MATERIAL TRANSFER DUE TO MATERIAL INCOMPATIBILITY.  EXHAUST VALVE (P/N SA643873), STEM IS CHR	OME PLATED AND VALVE GUIDE (P/N SA631496), IS ALUMINUM BRONZE AND THE 2 MATERIALS ARE NOT COMPATIBLE.  NI-RESIST VALVE G	UIDE (P/N 643767) SHOULD BE USED IAW TCM SB M85-18.  ALL CYLINDERS REPAIRED BY USING (P/N 652956) EXHAUST VALVE AND (P/N	 643767) EXHAUST GUIDE.								3	O			E5CE
1998121800809	19981218	00809	CE  	1998	12	18	98ZZZX4663       	1	19980109	G	3233	S24266	BEARING         			CESSNA	177   	177RG       	2073709	CE  										MLG	FAILED          	B			B1TR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	52823					177RG1279				MAIN LANDING GEAR ACTUATOR ROD-END FAILED DURING FLIGHT.  LANDING GEAR COULD NOT BE LOWERED AND LOCKED DOWN.  PILOT MADE	 A LANDING WITH GEAR UP.  THE AIRCRAFT AND THE PARTICULAR PART IN QUESTION WERE INSPECTED 5 HOURS PRIOR WITH NO VISIBLE 	DISCREPANCY.				1	H	7	1 	3O				A20CE
1998121800810	19981218	00810	NE  	1998	12	18	98ZZZX4664       	3	19981123	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2866 					HJ203A		EROSION SHIELD DEBONDED ON NR 2 AND NR 3 BLADES.  DISASSEMBLED PROPELLER, REPLACED EROSION SHIELDS AND O/H BLADE S/N'S 9	32 AND 965.  REASSEMBLED PROPELLER IAW MFG COMM.															5	C	P10NE
1998121800811	19981218	00811	NE  	1998	12	18	98ZZZX4665       	3	19981123	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1603 					HJ39A		EROSION SHIELD IS CRACKED ON NR 3 AND NR 4 BLADES.  DISASSEMBLED, INSPECTED NR 3 BLADE (S/N 1917).  REMOVED AND REPLACED	 EROSION SHIELD WITH NEW SHIELD.  OVERHAULED BLADE S/N 1917.  BLADE NR 4 (S/N 1925) IS WITHIN AIRWORTHY LIMITS.  ASSEMBL	ED PROPELLER AND STATIC BALANCED IAW MFG COMM.														5	C	P10NE
1998121800812	19981218	00812	NE  	1998	12	18	98ZZZX4666       	3	19981119	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3209 					HJ717		EROSION SHIELD DEBONDED ON NR 3 BLADE.  DEBONDED IN DEICE BOOT AREA FROM EDGE OF EROSION SHIELD TO 3 INCH OUTBOARD.  REP	AIRED AND INSTALLED NEW DEICE BOOT IAW MFG COMM.															5	C	P10NE
1998121800813	19981218	00813	NE  	1998	12	18	98ZZZX4667       	3	19981123	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1274 					HJ249		EROSION SHIELD DEBONDED ON NR 4 BLADE UNDER DE-ICE BOOT.  REPAIRED AND INSTALLED NEW DE-ICE BOOT IAW HARTZELL MANUAL 135	F.															5	C	P10NE
1998121800814	19981218	00814	NE  	1998	12	18	98ZZZX4668       	3	19981123	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2976 					HJ834		EROSION SHIELD DEBONDED ON NR 3 BLADE.  DISASSEMBLED PROPELLER.  OVERHAULED BLADE NR 3.  REASSEMBLED PROPELLER.  SET BLA	DE ANGLES FEATHER AT 79.0 DEGREES, LOW PITCH AT 18.6 DEGREES, REV AT 14.5 DEGREES.  BALANCED PROPELLER IAW MFG COMM.															5	C	P10NE
1998020500234	19980205	00234		1998	2	5	98ZZZX467        	4	19980106	G	3421	500DC	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										HORIZON REF	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	206BY				906	2871				HORIZON REFERENCE INDICATOR INOPERABLE.  WILL NOT HOLD ATTITUDE.						1	G	7	1 	3U				H2SW
1998121800816	19981218	00816		1998	12	18	98ZZZX4670       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T				3488	318152089				AUTOPILOT WILL NOT ENGAGE.						1	L	7	2 	3O				A20SO
1998121800817	19981218	00817		1998	12	18	98ZZZX4671       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4082T				3483	318152089				AUTOPILOT WILL NOT TEST UP, ALWAYS TESTS DOWN.						1	L	7	2 	3O				A20SO
1998121800818	19981218	00818		1998	12	18	98ZZZX4672       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T				3425	318152089				AUTOPILOT WILL NOT ENGAGE.						1	L	7	2 	3O				A20SO
1998121800819	19981218	00819		1998	12	18	98ZZZX4673       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T	197  			3477	318152089				AUTOPILOT WILL NOT ENGAGE.						1	L	7	2 	3O				A20SO
1998121800820	19981218	00820		1998	12	18	98ZZZX4674       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4082T	364  			3482	318152089				AUTOPILOT WILL NOT TEST UP OR DOWN.						1	L	7	2 	3O				A20SO
1998121800821	19981218	00821		1998	12	18	98ZZZX4675       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T	197  			3463	318152089				AUTOPILOT KICKS OFF IN SMOOTH AIR.						1	L	7	2 	3O				A20SO
1998121800822	19981218	00822		1998	12	18	98ZZZX4676       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	4082T				3485	318152089				AUTOPILOT KICKS OFF IN SMOOTH AIR.						1	L	7	2 	3O				A20SO
1998121800823	19981218	00823		1998	12	18	98ZZZX4677       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4082T				3486	318152089				AUTOPILOT WILL NOT TEST DOWN, ALWAYS TESTS UP.						1	L	7	2 	3O				A20SO
1998121800824	19981218	00824		1998	12	18	98ZZZX4678       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4082T	2    			3475	318152089				SUCCESSFULLY TEST UP ONLY INTERMITTENTLY; AFTER SUCCESSFUL DOWN TEST, WILL NOT TEST UP UNTIL TEST SWITCH HAS REPEATEDLLY	 BEEN PLACED IN UP POSITION.  WHEN AUTOPILOT ENGAGED AND ENGINES ARE BROUGHT UP TO HIGH RPM, THE FOLLOWING OCCURS.  AP A	NNUNCIATOR LAMP BRIGHTENESS DIMS SLIGHTLY.  AP ANNUNCIATOR LAMP INTENSITY CONTINUOUSLY VARIES FROM BRIGHTNESS NOTED ABOV	E TO HALF.  ROLL AND PITCH SERVOS WILL NOT DRIVE.  COMMAND BARS FUNCTION PROPERLY.  UNIT REMOVED AND BENCH TESTED.  MALF	UNCTION DUPLICATED ON BENCH.		1	L	7	2 	3O				A20SO
1998121800825	19981218	00825		1998	12	18	98ZZZX4679       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4082T	48   			3480	318152089				AUTOPILOT INTERMITTENLY KICKS OFF IN SMOOTH AIR.  WILL NOT TEST UP OR DOWN.  REMOVED UNIT AND BENCH TESTED; DUPLICATED M	ALFUNCTION.					1	L	7	2 	3O				A20SO
1998020500235	19980205	00235	EA  	1998	2	5	98ZZZX468        	1	19980112	G	6310	107DS2131	SPRAG CLUTCH    		107D2003515 	BOEING	107   	1072        	9420604	EA  										NR 2 IDLER ASSY	UNDERSIZED      	B			CHIR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	09	194CH	39   			XBW1614	404				NR 2 CLUTCH DISENGAGED DURING FLIGHT.  FOUND CLUTCH SPRAGS MAY BE UNDERSIZED.  ALL OTHER PARTS CHECKED GOOD ON DIMENSION	AL INSPECTION.					2	G	7	2 	4U				1H16
1998121800826	19981218	00826		1998	12	18	98ZZZX4680       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	INTERMITTENT    	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	4082T	103  			3478	318152089				AUTOPILOT INTERMITTENTLY WILL SUCCESSFULLY TEST.  AUTOPILOT INTERMITTENTLY WILL NOT ENGAGE.						1	L	7	2 	3O				A20SO
1998121800827	19981218	00827		1998	12	18	98ZZZX4681       	4	19981125	G	2210	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AUTOPILOT	MALFUNCTIONED   	B				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	01	7164D				3293	318052013				AUTOPILOT WILL NOT TEST DOWN, ALWAYS TESTS UP.  UNIT REMOVED AND BENCH TESTED, MALFUNCTION DUPLICATED ON BENCH.						1	L	7	2 	3O				A20SO
1998121800828	19981218	00828	CE  	1998	12	18	98ZZZX4682       	1	19981017	G	2820	3040637	LINE            			BEECH 	1900  	1900C       	1154161	CE  										LT ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	05	207CJ					UC107				THIS FUEL LINE GOES FROM THE FCU TO THE FUEL FLOW TRANSMITTER.  THE DUCT FROM THE COWL TO THE STARTER/GENERATOR RUBS ON 	THIS LINE.  THIS IS ONLY ON THE LEFT ENGINE.  THIS DUCT RUBBED A HOLE IN THIS HIGH PRESSURE FUEL LINE.  SUBMITTER STATED	 THEY HAVE CHANGED 2 OF THESE LINES IN THE PAST 9 MONTHS ON 2 DIFFERENT AIRCRAFT.				2	L	7	2 	4T			RT	A24CE
1998121800829	19981218	00829	EU  	1998	12	18	98ZZZX4683       	1	19981113	G	2917	A24518001	REGULATOR       			AMD   	FALC50	FALCON50MYST	2730106	EU  										E/E BAY	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	955E	870  			173	14				PRESSURE REGULATOR HOUSING CRACKED WITH TOTAL LOSS OF NR 1 HYDRAULIC RESERVOIR.  UNIT IS A KNOWN PROBLEM WITH MANUFACTUR	ER AND FALCON HAS AN NDT SCHEDULE OR ORIGINAL DASH NUMBER COMPONENT.  PART FAILED AT APPROXIMATELY 870 HOURS TT.  NDT SC	HEDUED EVERY 1,200 HOURS.  SUBMITTER RECOMMENDED TO DECREASE TIME BETWEEN NDT CHECKS AND/OR RE-DESIGN WITH STRONGER HOUS	ING.			2	L	7	3 	4F				A46EU
1998121800831	19981218	00831	CE  	1998	12	18	98ZZZX4685       	1	19981120	G	2435	23048018	START/GEN       	LEARSIEGLER 	23048018    	BEECH 	99    	99A         	1154003	CE  										RT ENGINE	FAILED          	B			WD4R	A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			SO	17	491BB		385  		7432	U97				ON TAKEOFF ROTATION, THE PILOT NOTICED THE LEFT GENERATOR OFF LIGHT CAME ON AND THEN A COMPLETE LOSS OF ELECTRICAL POWER	 ON THE RIGHT SIDE WITH LOSS OF COMMUNICATION AND VARIOUS LIGHTS AND INSTRUMENTS.  THE AIRCRAFT LANDED SAFELY WITH THE A	ID OF LIGHTS FROM THE TOWER.  UPON INSPECTION, FOUND THE RIGHT STARTER GENERATOR FAN BLADES BROKE OFF AND WEDGED IN THE 	BRUSHES AND SHORTED THE GENERATOR OUT WHICH CAUSED A MAJOR OVERVOLTAGE CONDITION.  THIS FRIED MANY LIGHTS, INSTRUMENTS A	ND RADIOS.		1	L	7	2 	3T				A14CE
1998121800832	19981218	00832	CE  	1998	12	18	98ZZZX4686       	1	19981110	G	2121	99141292	FAN             			CESSNA	650   	650         	2076802	CE  										AIR DISTRIBUTION	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	38WP		797  		0135	650032				POST-FLIGHT INSPECTION REVEALED STREAKING ON AFT FUSELAGE HYDRAULIC FAN AFT EXHAUST DUCT AREA.  REPLACED HYDRAULIC FAN A	SSEMBLY.					2	L	7	2 	4F				A9NM
1998121800833	19981218	00833	CE  	1998	12	18	98ZZZX4687       	1	19981110	G	2710	678001	ACTUATOR        			CESSNA	650   	650         	2076802	CE  										AILERON	LEAKING         	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	38WP	6165 			0046	650032				EXTERNAL LEAKAGE INTO WING TRAILING EDGE CAVITY.  REPLACED ACTUATOR.						2	L	7	2 	4F				A9NM
1998121800834	19981218	00834	CE  	1998	12	18	98ZZZX4688       	1	19981124	G	3231	50810094	ROLLER          			BEECH 	90    	C90         	1152913	CE  										RT MLG DOOR	DAMAGED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	01	6656D	5208 				LJ879				DURING GEAR RETRACTION IT WAS NOTED THE RT MLG DOORS DID NOT CLOSE.  UPON FURTHER INVESTIGATION, FOUND THE GEAR DOOR ROL	LER ASSEMBLY HAD BEEN BROKEN OFF CAUSING THE GEAR DOORS TO STAY OPEN.  REPLACED PART AND HAD NO FURTHER PROBLEMS.  SUBMI	TTER SUGGESTED CLOSER INSPECTION OF ROLLER ASSEMBLY.				1	L	7	2 	3T				3A20
1998121800835	19981218	00835	CE  	1998	12	18	98ZZZX4689       	1	19981120	G	5630	010A31870011	WINDOW          			MTSBSI	MU2   	MU2B35      	5780411	CE  										PASSENGER DOOR	CRACKED         	E	S			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	17	375CA	7856 				643				DURING FLIGHT, MAIN CABIN DOOR WIDOW CRACKED.  CRACK STARTED ALONG EDGE OF PAIN PARALLEL TO OPENING JUST UNDER SEAL.						1	H	7	2 	3T			RT	A10SW
1998020500236	19980205	00236	CE  	1998	2	5	98ZZZX469        	1	19980116	G	2434	315	ALTERNATOR      			CESSNA	185   	A185F       	2072821	CE  										DC SYSTEM	MALFUNCTION     	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	86109		211  		6013283	18503153				ALTERNATOR CAUSING STATIC IN RADIOS.  REPLACED, NOISE GONE.						1	H	7	1 	3O				3A24
1998121800836	19981218	00836	NE  	1998	12	18	98ZZZX4690       	3	19981130	G	6111	7826853	PIN             	HAMSTD      		EMB   	120   	EMB120      	3260201	SO  						HAMSTD	14RF	14RF9       	NE  	PROPELLER BLADE	MISSING         	B			BN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05		17161	2108 		864776					REFERENCE:  FW 08706.  REASON FOR REMOVAL:  NICKEL SHEATH DE-BONDED.  POSSIBLE CAUSE:  TBD.  SUBMITTER RECOMMENDED BLADE	 BE SENT TO HAMILTON STANDARD FOR METALLURGICAL EVALUATION.  CUSTOMER:  FLIGHT WEST.					2	L	7	2 	4T			RT	A31SO   		6	C	P11NE
1998121800838	19981218	00838	CE  	1998	12	18	98ZZZX4692       	1	19981116	G	5520	25315354	BOLT            			LEAR  	25    	25D         	5170514	CE  										ELEVATOR	WORN            	B			DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	531CW	8529 				231				REMOVED ELEVATOR DOWN SPRING TO FACILITATE OTHER MAINTENANCE.  DISCOVERED THE ELEVATOR DOWN SPRING DRAW BOLT EXCESSIVELY	 WORN NEAR FORWARD MOUNT BOLT.  TO PREVENT MISSING THIS ITEM DURING THE B6 INSPECTION, THE INSPECTION ITEM SHOULD READ: 	 CHECK ELEVATOR DOWN SPRING DRAW BAR FOR WEAR, PAYING PARTICULAR ATTENTION NEAR THE FORWARD ATTACH POINT.  FAILURE OF TH	IS PART COULD CAUSE DAMAGE TO EQUIPMENT OF FAILURE OF THE ELEVATOR FLIGHT CONTROLS.			2	L	7	2 	4J				A10CE
1998121800839	19981218	00839	NM  	1998	12	18	98ZZZX4693       	1	19981112	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	675  			AH6587A	064				HYDRAULIC PUMP DRIVE SHAFT SEAL FAILED AND WAS DRIPPING SKYDROL FROM OVERBOARD DRAIN ON RT ENGINE.  TIS:  675 HOURS.  LA	NDINGS:  445.  AIRCRAFT TT:  2,156.3 HOURS.  LANDINGS, 1,437.  DATE:  8-10-98.					2	L	7	2 	4F			RT	A16NM
1998121800840	19981218	00840	NM  	1998	12	18	98ZZZX4694       	1	19980911	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	1374 			AH6534A	064				HYDRAULIC PUMP DRIVE SHAFT SEAL FAILED AND WAS DRIPPING SKYDROL FROM OVERBOARD DRAIN ON LEFT ENGINE.  TIS:  1,374 HOURS.	  LANDINGS:  897.  AIRCRAFT TT:  2,206.0. LANDINGS:  1,468.  DATE:  9-11-98.					2	L	7	2 	4F			RT	A16NM
1998121800841	19981218	00841	NM  	1998	12	18	98ZZZX4695       	1	19980917	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	61   			EP68A	064				HYDRAULIC PUMP DRIVE SHAFT SEAL FAILED AND WAS DRIPPING SKYDROL FROM OVERBOARD DRAIN ON RT ENGINE.  TIS:  60.7 HOURS.  L	ANDINGS: 38.  AIRCRAFT TT:  2,217.0 HOURS.  LANDINGS:  1,475.  DATE: 9-17-98.					2	L	7	2 	4F			RT	A16NM
1999010100057	19990101	00057	NM  	1999	1	1	98ZZZX4696       	1	19980925	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	9    			CT30A	064				HYDRAULIC PUMP DRIVE SEAL FAILED AND WAS LEAKING SKYDROL FROM OVERBOARD DRAIN ON RT ENGINE.  TIS:  8.9 HOURS.  LANDINGS:	  8.  INSTALLED PUMP 40183 S/N RAL63AB FROM LT ENGINE TO RT ENGINE.  ACFT TT:  2,228.3 HOURS.  LANDINGS:  1,485.  DATE: 	9-25-98.				2	L	7	2 	4F			RT	A16NM
1999010100058	19990101	00058	NM  	1999	1	1	98ZZZX4697       	1	19980917	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	2    			AH6587A	064				HYDRAULIC PUMP DRIVE SEAL FAILED AND WAS DRIPPING SKYDROL FROM OVERBOARD DRAIN ON RT ENGINE.  TIS:  2.4 HOURS.  LANDINGS	:  2.  AIRCRAFT TT:  2,219.4 HOURS.  LANDINGS:  1,477.  DATE:  9-17-98.					2	L	7	2 	4F			RT	A16NM
1999010100059	19990101	00059	NM  	1999	1	1	98ZZZX4698       	1	19981107	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	41   			LH50A	064				HYDRAULIC PUMP DRIVE SEAL FAILED AND WAS LEAKING FROM OVERBOARD DRAIN ON LT ENGINE.  TIS:  40.5 HOURS.  LANDINGS:  32. A	IRCRAFT TT:  2,268.8 HOURS.  LANDINGS:  1,517.  DATE:  11-7-98.					2	L	7	2 	4F			RT	A16NM
1999010100060	19990101	00060	NM  	1999	1	1	98ZZZX4699       	1	19981107	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	4    			CT25A	064				HYDRAUILC PUMP DRIVE SEAL FAILED AND WAS LEAKING SKYDROL FROM OVERBOARD DRAIN ON LT ENGINE.  TIS:  3.6 HOURS.  LANDINGS:	  6.  AIRCRAFT TT:  2,272.4 HOURS.  LANDINGS:  1,523.  DATE:  11-7-98.					2	L	7	2 	4F			RT	A16NM
1998020500237	19980205	00237	EA  	1998	2	5	98ZZZX470        	2	19980122	G	7414	1081806	BEARING         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENG RT MAGNETO	FAILED          	B			CKYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	437FL	2400 				287125224				PILOT REPORTED WHINE IN ENGINE WHEN MAGNETO CHECK ACCOMPLISHED.  FOUND RT MAGNETO DEAD.  REMOVED MAGNETO, DISASSEMBLED, 	FOUND BEARING FAILED.  MAGNETO OVERDUE OVERHAUL.  NO RECORD OF MAGNETO EVER BEEN TAKEN APART.  SUBMITTER STATED MAGNETOS	 SHOULD NOT RUN OVER TBO BEFORE OVERHAUL.				1	L	7	1 	3O	3	O		2A13    	E274
1999010100061	19990101	00061	NM  	1999	1	1	98ZZZX4700       	1	19981109	G	2913		SEAL            	ABEX        	40183       	ISRAEL	1125  	1125        		NM  										HYDRAULIC PUMP	FAILED          	G				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	650GE	3    			AH6587A	064				HYDRAULIC PUMP DRIVE SEAL FAILED AND WAS LEAKING SYDROL FROM OVERBOARD DRAIN ON LT ENGINE.  TIS: 2.6 HOURS.  LANDINGS: 2	.  AIRCRAFT TT:  2,275.0 HOURS.  LANDINGS:  1,525.  DATE:  11-9-98.					2	L	7	2 	4F			RT	A16NM
1999010100062	19990101	00062	EU  	1999	1	1	98ZZZX4701       	1	19981013	G	7722	54287068010	INDICATOR       			AMD   	FALC20	FALCON20D5  	2730003	EU  										COCKPIT	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	520TJ	6    			782	198				NEW PART INSTALLED DURING F20 RETROFIT.  FAILED AFTER APPROXIMATELY 3.5 HOURS OF GROUND TEST AND 2.5 HOURS OF FLIGHT TIM	E.  DIGITAL DISPLAY SHOWED TEST PATTERN.  ALL SEGMENTS LIGHTED.					2	L	7	2 	4F			RT	A7EU
1999010100063	19990101	00063	SO  	1999	1	1	98ZZZX4702       	1	19981118	G	5411		FRAME           			EMB   	120   	EMB120RT    		SO  										LT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	286AS					120268				FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN LEFT ENGINE FORWARD NACELLE NR 1 FRAME.  SEEMS TO BE A REPETITIVE D	ISPREPANCY AS PREVIOUSLY DETAILED AND REPORTED.  SUBMITTER STATED CAUSE REMAINS UNDETERMINED.  WOULD SUSPECT ENGINE TORQ	UE AND VIBRATION TO BE POSSIBLE CONTRIBUTING FACTORS AND SUGGEST TIMED INTERVALS FOR REPETITIVE INSPECTION OF AREA.				2	L	7	2 	4T			RT	A31SO
1999010100064	19990101	00064	SO  	1999	1	1	98ZZZX4703       	1	19981118	G	5411		FRAME           			EMB   	120   	EMB120RT    		SO  										RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	286AS					120268				FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN RT ENGINE FORWARD NACELLE NR 1 FRAME.  SEEMS TO BE A REPETITIVE DIS	CREPANCY AS PREVIOUSLY DETAILED AND REPORTED.  SUBMITTER STATED POSSIBLE CAUSE IS STILL UNDETERMINED.  WOULD SUSPECT ENG	INE TORQUE AND VIBRATION TO BE POSSIBLE CONTRIBUTING FACTORS AND WOULD SUGGEST TIMED INTERVALS AND REPETITIVE INSPECTION	 OF AREA.			2	L	7	2 	4T			RT	A31SO
1999010100065	19990101	00065	SO  	1999	1	1	98ZZZX4704       	1	19981116	G	5411	12D03851001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	127AM					120103				FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN LT ENGINE FORWARD NACELLE NR 1 FRAME.  SEEMS TO BE A REPETITIVE DIS	CREPANCY AS PREVIOUSLY DETAILED AND REPORTED.  SUBMITTER STATED CAUSE IS STILL UNDETERMINED.  WOULD SUSPECT ENGINE TORQU	E AND VIBRATION TO BE POSSIBLE CONTRIBUTING FACTORS AND SUGGEST TIMED INTERVALS FOR REPETITIVE INSPECTION OF AREA.				2	L	7	2 	4T			RT	A31SO
1999010100066	19990101	00066	SO  	1999	1	1	98ZZZX4705       	1	19981116	G	5320	12015374002	ANGLE           			EMB   	120   	EMB120RT    		SO  										VERTICAL STAB	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	127AM					120103				RIGHT VERTICAL STABILIZER CHINE ANGLE IS CRACKED .250 INCH BY .010 INCH AND HAS WORKING RIVETS.  SUBMITTER SUGGESTED POS	SIBLE CAUSE AS FATIGUE/VIBRATION AND RECOMMENDED A DETAILED INSPECTION BE CALLED OUT DURING C-CHECK INSPECTION.					2	L	7	2 	4T			RT	A31SO
1999010100067	19990101	00067	SO  	1999	1	1	98ZZZX4706       	1	19981116	G	5320	12015374001	ANGLE           			EMB   	120   	EMB120RT    		SO  										VERTICAL STAB	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	127AM					120103				LEFT VERTICAL STABILIZER CHINE ANGLE IS CRACKED .250 INCH BY .010 AND HAS WORKING RIVETS.  SUBMITTER SUGGESTED CAUSE AS 	FATIGUE/VIBRATION AND RECOMMENDED A DETAILED INSPECTION BE CALLED OUT DURING C-CHECK INSPECTION.					2	L	7	2 	4T			RT	A31SO
1999010100068	19990101	00068	SO  	1999	1	1	98ZZZX4707       	1	19981116	G	5320	12009789001	ANGLE           			EMB   	120   	EMB120RT    		SO  										BS 4214-4992	CORRODED        	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	127AM					120103				DURING C-CHECK INSPECTION, CORROSION WAS DISCOVERED BETWEEN FUSELAGE FRAMES 13A AND 15A, FS 4214.0 TO FS 4992.0 ON LOWER	 PASSENGER/CREW ENTRANCE DOOR SURROUNDING STRUCTURE ANGLE.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS MOISTURE PENETRATION.					2	L	7	2 	4T			RT	A31SO
1999010100069	19990101	00069	SO  	1999	1	1	98ZZZX4708       	1	19981116	G	5411	1203851002	FRAME           			EMB   	120   	EMB120RT    		SO  										RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	127AM					120103				FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN RT ENGINE FORWARD NACELLE NR 1 FRAME.  SUBMITTER STATED SEEMED TO B	E A REPETITIVE DISCREPANCY AS PREVIOUSLY DETAILED AND REPORTED AND POSSIBLE CAUSE IS STILL UNDETERMINED.  WOULD SUSPECT 	ENGINE TORQUE AND VIBRATION AS POSSIBLE CONTRIBUTING FACTORS.  WOULD SUGGEST TIMED INTERVALS FOR REPETITIVE INSPECTION O	F AREA.			2	L	7	2 	4T			RT	A31SO
1998020500238	19980205	00238	SO  	1998	2	5	98ZZZX471        	2	19980105	G	8550	CH48104	OIL FILTER      	CHAMPION    		CESSNA	320   	320A        	2074506	CE  	CONT  	O470  	TSIO470B    	17026	SO  					AUXILIARY OIL	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	27	3020R	73   			F083061	320A0020	993572			FOUND FILTER PLEATS POPPED OUTWARD ALLOWING OIL TO PASS THROUGH UNFILTERED.  FOUND AUXILIARY OIL FILTER INSTALLATION HOS	ES CROSSED REVERSING THE OIL FLOW THROUGH THE FILTER.  RECOMMEND ONE-TIME INSPECTION OF HOSE ROUTING ON SAME TYPE INSTAL	LATIONS.				1	L	7	2 	3O	3	O		3A25    	3E3
1999010100071	19990101	00071	CE  	1999	1	1	98ZZZX4710       	1	19981103	G	3233	993880001	ACTUATOR        			BEECH 	99    	99A         	1154003	CE  										MLG	FAILED          	B			TIMR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	955AA					U128				ON POST-FLIGHT INSPECTION, PILOT REPORTED HYDRAULIC FLUID ON LOWER FUSELAGE AND TAIL.  MECHANICS WERE NOTIFIED AND CLOSE	R INSPECTION REVEALED FLUID LEAKING FROM LOWER SHAFT SEAL.  AIRCRAFT WAS JACKED AND GEAR SWUNG TO VERIFY SOURCE OF LEAKA	GE.  PROBLEM DUPLICATED WITH GEAR IN UP POSITION.  REPLACED ACTUATOR.  SUBMITTER STATED SMALL DIVIT IN SHAFT COULD HAVE 	CONTRIBUTED TO DEFECTIVE SHAFT SEAL.			1	L	7	2 	3T				A14CE
1999010100072	19990101	00072	WP  	1999	1	1	98ZZZX4711       	2	19981215	G	7321	30708008	FCU             			LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE	MALFUNCTIONED   	D				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CE	09	35NW				A5110CT	069	P74282			ABOVE 30,000 FEET, ENGINE, S/N P-74282, WOULD BEGIN TO SURGE IN ALL ENGINE PARAMETERS.  AS THE AIRCRAFT INCREASED ALTITU	DE, THE SURGING WOULD BECOME MORE INTENSE.  AT THIS POINT (APPROXIMATELY 39K), THE PILOT BROUGHT THE POWER LEVER TO IDLE	 AND THE ENGINE SHUT DOWN.  DUNCAN AVIATION DETERMINED THE FUEL CONTROL UNIT WAS AT FAULT.  THE FUEL CONTROL WAS REPLACE	D AND TEST FLOWN WITHOUT INCIDENT.  TO PREVENT RECURRENCE, PILOT SHOULD SWITCH ENGINE TO MANUAL MODE WHEN ENGINE STARTS 	TO SURGE.		2	L	7	2 	4F	4	F		A10CE   	E6WE
1999010100073	19990101	00073	CE  	1999	1	1	98ZZZX4712       	1	19981208	G	5713	10112002011	STRINGER        			BEECH 	B300  	B300        	1159232	CE  										RT/LT WS 50-93	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	305RL					FL10				DURING A ROUTINE PHASE II INSPECTION, A CRACK WAS FOUND ON THE UPPER SURFACE OF THE RT WING AT WS 93.00.  FURTHER INSPEC	TION REVEALED THE RIB UNDER THE SKIN (P/N 101-12W20-35) HAD CRACKED ALSO.  A SPLICE STRINGER REPAIR AND A PATCH ON THE U	PPER SURFACE WAS MADE AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER INSPECTION WAS COMPLETED.				2	L	7	2 	4T			RT	A24CE
1999010100074	19990101	00074	CE  	1999	1	1	98ZZZX4713       	1	19981208	G	5713	10112002035	STRINGER        			BEECH 	B300  	B300        	1159232	CE  										RT/LT WS 50-93	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	616CK					FL114				DURING A PHASE III INSPECTION, WORKING RIVETS WERE NOTED AT THE LT WING STATIONS 93.00, 85.00 AND 75.50 RIBS.  FURTHER I	NSPECTION REVEALED CRACKS IN THE STRINGER AT THESE LOCATIONS.  ON THE RIGHT WING, A CRACK WAS NOTED AT WS 93.00 ALSO.  (	THERE WERE NO SURFACE SKIN FLAWS ON THIS AIRCRAFT).  ACCEPTABLE REPAIRS WERE MADE ON THIS AIRCRAFT.  SUBMITTER STATED CA	USE UNKNOWN.  NO RECOMMENDATION TO PREVENT RECURRENCE, BUT RECOMMEND ADDITIONAL INSPECTION INTERNALLY FOR THIS AREA.			2	L	7	2 	4T			RT	A24CE
1999010100075	19990101	00075		1999	1	1	98ZZZX4714       	4	19981124	G	3442	6225132109	RECEIVER        	COLLINS     		BOEING	757   	75723A      	1384967	NM  										E/E BAY	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	987AN	27383	845  		4517	25494				BUE/BOG - FLT 088 - AIR TURN BACK WXR FAIL DISPLAYED ON HSI.  TEST OK ON GROUND AND IN-FLIGHT.  REPLACED RADAR TRANSCEIV	ER.  ACCOMPLISHED OPERATIONAL TEST.  RADAR WORKED OK.					2	L	7	2 	4F			RT	A2NM
1999010100076	19990101	00076	NM  	1999	1	1	98ZZZX4715       	1	19981114	G	2933		LINE            	VICKERS     	PV32402F    	BOEING	767   	767383      	1385214	NM  										RT PYLON	FAILED          	B			CW7R	O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			GL	25	984AN	17   	5    		MX521967	24357				SKBO/KJFK - FLT 020 - DURING FLIGHT, RT HYDRAULIC SYSTEM WAS LOST.  PILOTS REPORTED:  'RT HYD QTY READS ZERO.  HYD QTY L	IGHT ILLUMINATED AND EICAS MESSAGE DISPLAYED RT HYD QTY'.  FOUND EDP PRESSURE LINE IN RT PYLON BROKEN.  REPLACED PRESSUR	E LINE.  ALSO CHANGED EDP ACCORDING AMM 29-11-05.				2	L	7	2 	4F			RT	A1NM
1999010100077	19990101	00077	CE  	1999	1	1	98ZZZX4716       	1	19981123	G	3030	72705712	SWITCH          			BEECH 	100   	B100        	1152919	CE  										PITOT HEAT	FAILED          	B			CW7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	241CW					BE54				STALL WARNING HEAT AND RIGHT HEAT SWITCHES DROP OFF-LINE.  INSPECTED SWITCHES AND FOUND LOOSE CONNECTION ON STALL WARNIN	G HEAT SWITCH AND DEFECTIVE PITOT HEAT SWITCH.  REPLACED PITOT SWITCH, RE-SECURED CONNECTION ON STALL WARNING SWITCH.  A	IRCRAFT TT:  7,189.9 HOURS.				1	L	7	2 	4T				A14CE
1999010100078	19990101	00078		1999	1	1	98ZZZX4717       	4	19981113	G	3454	3137LB63C	RMI             	AERONETICS  		MTSBSI	MU2   	MU2B60      	5780460	CE  										COCKPIT	MALFUNCTIONED   	B		A	RG4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	429WM				2081	1520SA				WITH LOSS OF 26VAC VOR POWER SOURCE, RMI INDICATED 180 DEGREES OUT.  HOOKED UP ANOTHER RMI OF SAME TYPE AND HAD SAME RES	ULTS.  NO FLAGS OR OTHER INDICATIONS WERE PRESENT.  SUBMITTER STATED WITH THIS PROBLEM, IF THE PILOT WERE RELYING ON THE	 RMI FOR NAVIGATION, THE PILOT WOULD NOT KNOW WHETHER THE RMI WAS FAULTY OR ANOTHER INSTRUMENT, AND COULD END UP DANGERO	USLY OFF-COURSE.			1	H	7	2 	3T			RT	A10SW
1999010100079	19990101	00079	CE  	1999	1	1	98ZZZX4718       	1	19981029	G	2810	5038903514	FUEL CELL       			BEECH 	99    	99          	1154002	CE  										RT WING	LEAKING         	B			TIMR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	07	4381Y					U71				ON INSPECTION, MECHANICS NOTICED FUEL DRIPPING FROM AREA ON LOWER RIGHT-HAND WING NOT IN VICINITY OF SUMP DRAIN.  A CHEC	K WAS MADE TO VERIFY SECURITY OF ALL TANK CONNECTIONS.  CONNECTIONS ALL OK.  REPLACED CELL WITH SERVICEABLE CELL.  MECHA	NICS INDICATED UPON REMOVAL OF FUEL CELL, NUMEROUS DRILL OUT RIVET BUCKED HEAD WITH SHARP POINTS.  THIS MAY HAVE CONTRIB	UTED TO THE LEAK.			1	L	7	2 	3T				A14CE
1999010100080	19990101	00080	EU  	1999	1	1	98ZZZX4719       	1	19981113	G	2520	3410	SEAT            			AIRBUS	320   	A320232     	3930326	EU  										CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	402UA					439				DURING THE FIRST HEAVY MAINTENANCE VISIT, VIRTUALLY 100 PERCENT OF THE SEAT PANS ON THE RECARO MODEL 3410, 720 SERIES CO	ACH SEATS WERE FOUND CRACKED AT THE FORWARD EDGE OF THE SEAT PAN.  THE CRACKS ARE AT THE MOUNTING HOLES WHERE THE SEAT P	AN MOUNTS TO THE SEAT FRAME.  THE PAN IS IDENTIFIED BY THE MANUFACTURER OF THE SEAT AS PRIMARY STRUCTURE.  A MINIMUM OF 	ONE CRACK PER SEAT PAN HAS BEEN FOUND WITH THE NORM BEING 2 CRACKS PER PAN.  AN AD IS NEEDED FOR REPETITIVE INSPECTIONS 	OF THESE SEAT PANS TO INSURE THEIR INTEGRITY.  NOTE:  THERE ARE 132 OF THESE SEAT PANS ON THE AIRCRAFT.		2	L	7	2 	4F			RT	A28NM
1998020500239	19980205	00239	CE  	1998	2	5	98ZZZX472        	1	19980101	G	2810	S21062	DRAIN VALVE     			CESSNA	172   	172P        	2072436	CE  										RT FUEL TANK	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	15	97919					17276239				FUEL DRAIN VALVE HAS DEFECTIVE O-RING ON SEAT CAUSING SEVERE LEAK.						1	H	7	1 	3O			NT	3A12
1999010100081	19990101	00081	CE  	1999	1	1	98ZZZX4720       	1	19981110	G	2130	99120789	VALVE           			CESSNA	500   	550         	2076604	CE  										ACM	FAILED          	B	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	37201					5500655				AIRCRAFT UNDERGOING IN-FLIGHT PRESS TEST AND IT FAILED CABIN LEAKAGE RATE CHECK WHEN PRESSURE SOURCES WERE SHUT OFF.  WH	EN PRESSURIZED ON THE GROUND, AIR FLOW WAS HEARD INTO THE CABIN ACM.  DUCT FROM ACM TO REAR PRESS BULKHEAD REMOVED AND F	LAPPER TYPE CHECK VALVE FOUND AS CAUSE OF LEAKAGE.  CHK VALVE FLAPPERS HAVE A THIN PIECE OF SILICON RUBBER ADHERED TO TH	EM WITH AN RTV TYPE ADHESIVE.  ONE OF THE RUBBER PIECES WAS LOOSE AND HAD FOLDED UNDER FLAPPER PREVENTING IT FROM SEALIN	G.  THIS CONDITION WOULD NOT BE DETECTED NORMALLY, ONLY APPEAR DURING A HIGH ALTITUDE LEAKAGE TEST.  THIS COULD CAUSE A 	PROBLEM AT HIGH ALTITUDE CRUISE IF A SITUATION REQUIRED SHUT DOWN OF CABIN BLEED AIR.  CABIN ALT WOULD ASCEND RAPIDLY.	1	L	7	2 	4F				A22CE
1999010100082	19990101	00082	SO  	1999	1	1	98ZZZX4721       	1	19981109	G	5330	12019230003	SKIN            			EMB   	120   	EMB120RT    		SO  										BS 7257	CORRODED        	B	S		WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	130AM					120134				AT STA 7257.6 UNDERNEATH FRAME 22 IN BETWEEN STR 21L AND STR 20R, CORROSION DETECTED WHICH EXCEEDED THE MANUFACTURER'S R	ECOMMENDATION FOR ALLOWABLE DAMAGE.  THE AREA OF CORROSION WAS EXTENSIVE ENOUGH THAT THE MECHANIC HAD TO CUT A 9.25 INCH	 BY 1.52 INCH SECTION OF SKIN OUT.  SUBMITTER STATED CAUSE OF CORROSION IS A COMBINATION OF MOISTURE AND DISSIMILAR META	LS WHICH ARE IN CONTACT WITH ONE ANOTHER.  A TITANIUM STRIP RUNS BETWEEN THE FUSELAGE SKIN AND FRAME 22.  THIS COUPLED W	ITH FLUIDS AND OTHER CONTAMINANTS WHICH ACCUMULATE ON THE BELLY OF THE PLANE HAVE A DETRIMENTAL AFFECT ON THE CONDITION 	OF THE METALS IN THAT AREA.	2	L	7	2 	4T			RT	A31SO
1999010100083	19990101	00083	NE  	1999	1	1	98ZZZX4722       	3	19981110	G	6110	7826691	BOLT            			EMB   	120   	EMB120RT    		SO  						HAMSTD	14RF	14RF9       	NE  	RT PROPELLER	SHEARED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	130AM					120134		333		DURING INSTALLATION OF PROPELLER ASSEMBLY ON THE RIGHT ENGINE OF S/N 120134, ONE ATTACHMENT BOLT SHEARED PRIOR TO REACHI	NG TORQUE OF 140 FEET/POUNDS.					2	L	7	2 	4T			RT	A31SO   		6	C	P11NE
1999010100084	19990101	00084	EU  	1999	1	1	98ZZZX4723       	1	19981029	G	3241	ACM22742	VALVE           			BRAERO	DH125 	BAE125800A  	1500285	EU  										RT MLG	CONTAMINATED    	H	L			O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	12F	2199 				258182				BRAKES LOCK UP AFTER PARK BRAKE IS RELEASED.  SECOND OCCURRENCE OF THIS PROBLEM.  FIRST OCCURENCE, BRAKE CONTROL VALVE R	EPLACED PER ACFT MFG.  SECOND OCCURRENCE, FOUND INTERNAL SEAL BROKEN ON RT OTBD BRAKE SHUTTLE VALVE AND FOUND RT MODULAT	OR VALVE CONTAMINATED WITH SMALL PIECES OF O-RING.  REPLACED MODULATOR VALVE.				2	L	7	2 	4F			RT	A3EU
1999010100085	19990101	00085	EU  	1999	1	1	98ZZZX4724       	1	19981029	G	3241	195187	VALVE           			BRAERO	DH125 	BAE125800A  	1500285	EU  										RT MLG	CONTAMINATED    	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	07	12F	2199 				258182				BRAKES LOCK UP AFTER PARK BRAKE IS RELEASED.  SECOND OCCURRENCE OF THIS PROBLEM.  FIRST OCCURENCE, BRAKE CONTROL VALVE R	EPLACED PER ACFT MFG.  SECOND OCCURRENCE, FOUND INTERNAL SEAL BROKEN ON RT OTBD BRAKE SHUTTLE VALVE AND FOUND RT MODULAT	OR VALVE CONTAMINATED WITH SMALL PIECES OF O-RING.  REPLACED MODULATOR VALVE.				2	L	7	2 	4F			RT	A3EU
1999010100086	19990101	00086	NM  	1999	1	1	98ZZZX4725       	1	19981102	G	5522	183T30017	SKIN            			BOEING	767   	767         	1385102	NM  										ELEVATOR	DELAMINATED     	B	S		HN6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					000618					ELEVATOR RECEIVED FOR WORK.  UPON PRELIMINARY WORK, DISCOVERED THAT A PORTION OF THE UPPER SKIN IN THE INBOARD END AT TH	E SPAR WAS DELAMINATED EXPOSING THE PEEL PLY STILL ATTACHED.  DISPOSTION PENDING.					2	L	7	2 	4F				EXPA2L72
1999010100087	19990101	00087	EU  	1999	1	1	98ZZZX4726       	1	19981113	G	2917	A24518001	REGULATOR       			AMD   	FALC50	FALCON50MYST	2730106	EU  										E/E BAY	CRACKED         	D		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	955E	870  			173	14				PRESSURE REGULATOR HOUSING CRACKED WITH TOTAL LOSS OF NR 1 HYDRAULIC RESERVOIR.  PART FAILED AT APPROXIMATELY 870 TT.  N	DT SCHEDULED EVERY 1,200 HOURS.  SUBMITTER RECOMMENDED DECREASING TIME BETWEEN NDT CHECKS AND/OR RE-DESIGN WITH STRONGER	 HOUSING.				2	L	7	3 	4F				A46EU
1999010100088	19990101	00088	WP  	1999	1	1	98ZZZX4727       	1	19981106	G	6220	3691A76131	LINK            			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				BEARINGS WORN.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100089	19990101	00089		1999	1	1	98ZZZX4728       	4	19981106	G	2312	KY195B	TRANSCEIVER     			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J		36   		9543	900801D				TRANSCEIVER WILL NOT RECEIVE.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100090	19990101	00090	WP  	1999	1	1	98ZZZX4729       	1	19981106	G	6220	369A76132	LINK            			HUGHES	369   	369D        	4470706	WP  										MAIN ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC					290456D				BEARINGS WORN.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998020500240	19980205	00240	SO  	1998	2	5	98ZZZX473        	1	19980121	G	2701		YOKE            			PIPER 	PA30  	PA30        	7103002	SO  										COCKPIT	CRACKED         	B			NUTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7045Y					3048				UPON REMOVAL OF BOTH CONTROL YOKES, FOUND CRACKS RUNNING FROM HOLDING PIN TO BACK OF CONTROL YOKE.  LOCATION OF CRACKS A	RE SIMILAR IN LOCATION AS TO PIPER PA-28 AD 64-06-06 AND PIPER SL 396, SKETCH B.  SUSPECT CAUSE IS AGING.  SUBMITTER STA	TED AD SHOULD BE ISSUED TO INCLUDE THIS MODEL.				1	L	7	2 	3O				A1EA
1999010100091	19990101	00091	EU  	1999	1	1	98ZZZX4730       	1	19981129	G	3213	350A4110161263	SKID TUBE       			SNIAS 	350   	AS350B2     	8680813	EU  										RT AND LT	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	996PT	1007 				2865				BOTH SKID TUBES WERE FOUND TO HAVE CRACKS ON THE BOTTOM UNDER SKID SHOE.  THE CRACKS APPEAR TO HAVE STARTED FROM SMALL A	REAS OF CORROSION.  ALL THE PAINT HAD TO BE REMOVED TO DETECT CRACKS.					1	G	7	1 	3U				H9EU
1999010100092	19990101	00092	EU  	1999	1	1	98ZZZX4731       	1	19981129	G	3213	350A4110161363	SKID TUBE       			SNIAS 	350   	AS350B2     	8680813	EU  										RT AND LT	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	996PT	1007 				2865				BOTH SKID TUBES WERE FOUND TO HAVE CRACKS ON THE BOTTOM UNDER SKID SHOE.  THE CRACKS APPEAR TO HAVE STARTED FROM SMALL A	REAS OF CORROSION.  ALL THE PAINT HAD TO BE REMOVED TO DETECT CRACKS.					1	G	7	1 	3U				H9EU
1999010100093	19990101	00093		1999	1	1	98ZZZX4732       	4	19981111	G	3457	0110004200	GPS             			HUGHES	369   	369D        	4470706	WP  										E/E BAY	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5027P					611002D				ANTENNA WOULD NOT LOCK ON SATELLITES.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100094	19990101	00094		1999	1	1	98ZZZX4733       	4	19981111	G	3457	GPS150	GPS             			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P		1305 		81506744	611002D				CALL-UPS NEED BACK UP BATTERY SERVICE.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100095	19990101	00095	SW  	1999	1	1	98ZZZX4734       	1	19981113	G	7722	12444412	GAUGE           			BELL  	206   	206B        	1181511	SW  										TOT	STICKING        	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX				8080973	2872				ERRATIC GAUGE STICKS, DOES NOT GIVE ACCURATE POWER CHECK.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1999010100096	19990101	00096	SW  	1999	1	1	98ZZZX4735       	1	19981130	G	6720	20690705105	LINK            			BELL  	206   	206B        	1181511	SW  										TAIL ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BX					2872				BEARING WORN.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1999010100097	19990101	00097	WP  	1999	1	1	98ZZZX4736       	1	19981111	G	7810	369A8230503	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	62   				900801D				LEFT EXHAUST STACK CRACKED.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100098	19990101	00098	SW  	1999	1	1	98ZZZX4737       	1	19981207	G	6240	2060702657	INDICATOR       			BELL  	206   	206B        	1181511	SW  										DUAL TACHOMETER	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322		1250 			1736				ROTOR NEEDLE DROPS TO ZERO DURING FLIGHT.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1999010100099	19990101	00099	GL  	1999	1	1	98ZZZX4738       	2	19981205	G	7532	23053176	VALVE           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322		347  		FF14714	1736				VALVE DOES NOT CLOSE COMPLETELY.  REMOVED AND REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1999010100103	19990101	00103		1999	1	1	98ZZZX4742       	4	19981102	G	8300	6893672	GEAR            		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	547AL	963  			NN76749	53243	CAE847258			ENGINE MADE CHIP LIGHT.  UPON DISASSSEMBLY AND INSPECTION OF PARTS, FOUND EXCESSIVE GALLING ON PINION GEAR AND T/M GEAR.	  PINION GEAR HAS EXCESSIVE GALLING ON GEAR TEETH, POSSIBLY DUE TO IMPROPER MESHING OF T/M AND PINION GEARS.  SECONDARY 	DAMAGE:  T/M GEAR P/N 6893673 S/N NN144782.  TT:  963.3 HOURS.  GALLING ON GEAR TEETH.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999010100108	19990101	00108	EA  	1999	1	1	98ZZZX4747       	2	19981124	G	8520	13B17060	CRANKSHAFT      			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	OUT OF TOLERANCE	B		A	YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09		1512 					L1668239A			WHILE INSPECTING CRANKSHAFT, S/N V21384, PER TEXTRON LYC MSB 475B AND FAA AD 91-14-22, NOTICED CRANKSHAFT COUNTERBORE HA	D BEEN FACTORY REPAIRED BY CHROME PLATING PER MSB 475B; CRANK FLANGE MARKED 'L-21884-1', HOWEVER, NEW 13S19646 GEAR MARK	ED 7189, 29/98, MFR30620, WOULD NOT START INTO CRANKSHAFT COUNTERBORE DUE TO A DISCREPANCY BETWEEN THE RADIAL POSITION O	F THE DOWEL IN THE CRANKSHAFT AND THE DOWEL HOLE IN THE GEAR.  CRANKSHAFT WAS REPAIRED BY RELOCATING THE DOWEL HOLE .004	5 INCH CLOSER TO AXIS AND INSTALLATION OF .010 INCH OVERSIZE DOWEL.  SUBMITTER STATED THIS IS THE 7TH EXAMPLE OF THIS PR	OBLEM NOTED BY THIS REPAIR STATION THIS YEAR.	1	G	7	1 	3O	3	O		H10WE   	E274
1999010100109	19990101	00109	NE  	1999	1	1	98ZZZX4748       	1	19981124	G	5410	7630307600012	COWL            			SKRSKY	S76   	S76C        	8143008	NE  										AFT ENGINE	DAMAGED         	B		A	JZBR	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			EA	25	803S	506  				760377				ENGINE WAS RUN WITH AFT ENGINE COWL OPEN DAMAGING PAINT (BURNT) ON TAILBOOM. THERE ARE NO PRECAUTIONS IN THE FLIGHT MANU	AL.  THE ONLY PRECAUTION IN THE MM IS AT THE END OF 71-01-00 (ENGINE R & R).  IT STATES 'OPERATION OF ENGINE WITH COWL O	PEN OR UNLATCHED IS PROHIBITED'.  THERE ARE MANY FUNCTIONS, LEAK CHECKS, ETC., THAT WOULD NORMALLY BE DONE WITH THE COWL	 OPEN.  SUBMITTER RECOMMENDS WARNING PLACARDS ON COWL.			1	G	7	2 	3U			NC	H1NE
1999010100110	19990101	00110		1999	1	1	98ZZZX4749       	4	19981130	G	2312	AA34100	VHF COMM        			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	B			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	369AW				1402	470117D				FM RADIO BROKEN WHEN TRANSMITTING AND RECEIVING.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100112	19990101	00112	SW  	1999	1	1	98ZZZX4751       	1	19981121	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	WORN            	B			BXOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	98VG				RNFS7827	53171				EXCESSIVE SPREAD BETWEEN DISCS WAS DISCOVERED IN THE COURSE OF COMPLYING WITH PARAGRAPH A(1) OF AD 97-24-17, DISC PACK R	EMOVED AND REPLACED WITH NEW ZERO TIME DISC PACK.					1	G	7	1 	3U			O	H2SW
1999010100115	19990101	00115	SW  	1999	1	1	98ZZZX4754       	1	19981106	G	5347	206072903104	RELEASE CABLE   			BELL  	206   	206L4       	1182110	SW  										CARGO HOOK	MALFUNCTIONED   	B		A	GJQR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	404W	2970 				52055				CARGO HOOK MANUAL RELEASE CABLE TOO SHORT.  APPLIES TO ALL BELL 206L SERIES HELICOPTERS UTILIZING ONBOARD SYSTEMS E-72 E	LECTRONIC LOAD WEIGH SYSTEM.  WITH THE LOAD CELL INSTALLED BETWEEN THE CARGO HOOK AND LOAD TROLLEY, FULL TRAVEL CANNOT B	E OBTAINED WITH THE BELL CARGO HOOK MANUAL RELEASE CABLE INSTALLED (P/N 206-072-903-104).  AS THE FERTILIZER BUCKET SWUN	G TO  FULL RIGHT STOP ON CARGO HOOK TROLLEY, IT PULLED THE RELEASE CABLE TIGHT CAUSING IT TO BREAK THE FITTING WHERE IT 	CONNECTS TO THE HOOK.  ONCE THE FITTING BROKE IT ACTIVATED THE MANUAL RELEASE MECH RELEASING CARGO FROM THE HOOK.  ONBOA	RD SYS OFFERS A LONGER MANUAL RELEASE CABLE FOR THEIR (E-72) KIT (P/N 268-011-00) WHICH WILL EILIMINATE THIS PROBLEM.	1	G	7	1 	3U			NC	H2SW
1999010100116	19990101	00116	SW  	1999	1	1	98ZZZX4755       	1	19981020	G	5311	206032308103	FRAME           		206032308115	BELL  	206   	206L4       	1182110	SW  										BS 31	DAMAGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	173AL	6110 				52066				REMOVAL OF FRAME TO REPLACE WORKING RIVETS ON UPPER FITTING.  LOWER LT AND RT ATTACHMENT CASTINGS CHAFING FRAME IN RADIU	S.					1	G	7	1 	3U			NC	H2SW
1999010100120	19990101	00120	WP  	1999	1	1	98ZZZX4759       	1	19981130	G	3310	22455	SWITCH          			HUGHES	369   	369D        	4470706	WP  										COCKPIT	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW	3203 			1689M	470117D				INSTRUMENT LIGHTS WILL NOT ILLUMINATE.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1998021100007	19980211	00007		1998	2	11	98ZZZX476        	4	19980128	G	3425	329B7A	FLIGHT DIRECTOR 	COLLINS     		SWRNGN	SA226 	SA226AT     	8780405	SW  										PITCH SYNCHRO	FAILED          	B	L	A	EI4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	59TP				2490	T26161				WHEN RECEIVED, THE FLIGHT DIRECTOR PRESENTATION WAS SHOWING AN ATTITUDE OF 70 DEGREES UP WHEN ENERGIZED.  IT SHOULD HAVE	 BEEN SHOWING ZERO ATTITUDE.  THE PROBLEM WAS TRACED TO THE PITCH SYNCHRO.  THIS SYNCHRO HAD LOCKED UP DUE TO THE LAMINA	TION  IMPREGNATING MATERIAL GETTING INTO THE VERY SMALL AIR GAP BETWEEN THE ROTOR AND STATOR OF THE SYNCHRO.  ONLY ONE S	ET SCREW WAS USED TO HOLD THE SYNCHRO DRIVE GEAR ON THE SYNCHRO SHAFT; WHEN SYNCHRO LOCKED UP, THE GEAR SLIPPED ON THE S	HAFT ALLOWING SYNCHRO TO GIVE THE WRONG INFO TO THE PRESENTATION.  AFTER ELIMINATING CONTAMINATION PROBLEM IN THE SYNCRH	O, A FLAT WAS MACHINED ON THE SYNCHRO SHAFT.  TWO SET SCREWS WERE USED TO SECURE THE SYNCHRO DRIVE GEAR.	2	L	7	2 	4T			RT	A5SW
1999010100121	19990101	00121	EU  	1999	1	1	98ZZZX4760       	1	19981027	G	2431		WIRE            			SNIAS 	350   	AS350B2     	8680813	EU  										E/E BAY	CHAFED          	B				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			NM	03	97LG	816  				2917				BATTERY TEMPERATURE WARNING LIGHTS WIRE CHAFED AT UPPER BATTERY TRAY.  LOWER TRAY HAD RUBBER CHAFE PROTECTOR IN SIMILAR 	AREA.  UPPER TRAY DID NOT CAUSING BOTH TEMPERATURE LIGHTS TO COME ON.					1	G	7	1 	3U			 	H9EU
1999010100122	19990101	00122		1999	1	1	98ZZZX4761       	4	19981106	G	3452	K776A	TRANSPONDER     			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	500DC		881  		114114	290456D				TRANSPONDER DOES NOT TURN ON.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010100233	19990101	00233	CE  	1999	1	1	98ZZZX4762       	1	19980330	G	7930	070009937	LINE            			CESSNA	182   	R182        	2072734	CE  										ENGINE BAY	CORRODED        	B			HX1R	A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			EA	25	321Q	2600 				R18200438				AFTER TAKEOFF, PILOT NOTICED A FLICKER OF OIL PRESS GAUGE.  CONTROL TOWER WAS ADVISED, ACFT STARTED TO RETURN TO BASE. O	IL PRESS DROPPED TO ZERO AND ON 2-MILE FINAL, ENG QUIT.  DEAD STICK LANDING WAS MADE WITH NO DAMAGE TO AIRFRAME.  UPON I	NVEST A HOLE WAS FOUND, PUNCHED IN THE UPPER CASE.  THE OIL SUMP WAS EMPTY.  OIL WAS RUNNING OUT DRAIN HOLES IN BELLY AN	D OUT THE RT SIDE CABIN VENT.  INVEST BEHIND INST PANEL REVEALED OIL PRESS LINE (P/N 0700099-37) FROM FIREWALL TO GAUGE 	HAD FRACTURED ALLOWING OIL TO RUN DOWN THE FIREWALL.  CORROSION FOUND TO BE CAUSE OF FAILURE.  ORIG EQUIP AVIONIC COOLIN	G HOSE WAS ROUTED OVER THE LINE AND IT HAD NUMEROUS HOLES.  THE FORMING WIRE INSIDE COOLING HOSE WAS ALL CORRODED AWAY.	1	H	7	1 	3O			RT	3A13
1999010100234	19990101	00234	EA  	1999	1	1	98ZZZX4763       	2	19981112	G	8520	LW11750	ROD             			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					CYLINDER	BROKEN          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	8554C	9532 	1937 			32R7680122	L1390548A			CONNECTION ROD BROKE .1250 INCH ABOVE WHERE BOLT GOES THROUGH TO CONNECT ROD CAP.						1	L	7	1 	3O	3	O		A3SO    	1E4
1999010100235	19990101	00235		1999	1	1	98ZZZX4764       	4	19981125	G	2200	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AFCS	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	3527U	198  			3458	317952141				SWITCH INTERMITTENT, WILL TEST SUCCESSFULLY.  REMOVED UNIT AND BENCH TESTED.  DUPLICATED MALFUNCTION ON BENCH, BUT ONLY 	AFTER SUBJECTING UNIT TO A TEMPERATURE OF MINUS 12 DEGREES FAHRENHEIT FOR 3.75 HOURS.					1	L	7	2 	3O				A20SO
1999010100236	19990101	00236		1999	1	1	98ZZZX4765       	4	19981125	G	2200	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AFCS	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	7164D	1188 			3429	318052013				KICKS AUTOPILOT OFF IN SMOOTH AIR.  WILL NOT TEST UP OR DOWN.  UNIT REMOVED AND BENCH TESTED:  DUPLICATED MALFUNCTION 2 	ABOVE ON BENCH.					1	L	7	2 	3O				A20SO
1999010100237	19990101	00237		1999	1	1	98ZZZX4766       	4	19981125	G	2200	KA132	SWITCH          	KING        	KFC200      	PIPER 	PA31  	PA31350     	7103110	SO  										AFCS	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	01	3527U	393  			3474	317952141				WILL NOT TEST UP OR DOWN.  AUTOPILOT WILL NOT ENGAGE.						1	L	7	2 	3O				A20SO
1999010100238	19990101	00238	CE  	1999	1	1	98ZZZX4767       	1	19981015	G	7820	12540178PTT	MUFFLER         			CESSNA	182   	182S        	2072701	CE  										EXHAUST	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9512L	91   				18280237				PERFORMED MUFFLER INSPECTION PER AD 98-13-10.  NO CRACKS FOUND.  PERFORMED PRESSURE TEST PER CESSNA SB 98-78-02 AND FOUN	D 1 INCH CRACK ALONG EDGE OF WELD ATTACHING FLANGE TO FORWARD END PLATES.  CRACK CANNOT BE VISUALLY SEEN UNLESS MUFFLER 	IS REMOVED AND HELD IN BRIGHT LIGHT.  AD DOESN'T REQUIRE PRESSURE TEST, BUT SB DOES.  AD HAD BEEN C/W 14.7 HRS PREVIOUSL	Y AND NO DEFECTS WERE NOTED.			1	H	7	1 	3O			NT	3A13
1999010100239	19990101	00239	EA  	1999	1	1	98ZZZX4768       	2	19981120	G	7261		DIPSTICK        			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O360  	AEIO360H1A  	41514	EA  					ENGINE	LOOSE           	H				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		AB	AEROBATIC      	1			SW	09	118AC	544  				67292	RL2291151A			DIPSTICK VIBRATED LOOSE DURING SUSTAINED INVERTED FLIGHT AND 4 QUARTS OF OIL WERE LOST.  ENGINE HAD OPERATED NORMALLY FO	R 30 MINUTES OF AEROBATIC FLIGHT AND 30 MINUTES OF NORMAL FLIGHT BEFORE LOOSENING.  ENGINE MANUFACTURER AND AIRCRAFT BUI	LDER DO NOT PROVIDE INFORMATION AS TO PROPER TIGHTENING OF THIS PORT IN OPERATOR'S MANUELS.				1	H	7	1 	3O	3	O		A21CE   	1E10
1999010100240	19990101	00240	EA  	1999	1	1	98ZZZX4769       	1	19981122	G	3520	17217001	REGULATOR       	PURITANBENET		CNDAIR	CL600 	CL6002B16   	1900305	EA  										OXYGEN BOTTLE	FAILED          	H	L	A		O				OTHER                   				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			GL	03	831CJ	4145 			1111	5050				ON A RECENT TRIP, THE REGULATOR ASSEMBLY ON THE NR 1 PASSENGER OXYGEN BOTTLE FAILED AND A FIRE ENSUED.						2	L	7	2 	4F			RT	A21EA
1998020500425	19980205	00425	CE  	1998	2	5	98ZZZX477        	1	19980112	G	5280	S100316A	BEARING         			CESSNA	500   	560CESSNA   	2076750	CE  										NLG SPADE DOOR	NOT INSTALLED   	B	S	A	AC1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	356WC	179  				5600432				PILOTS REPORTED A RUMBLING NOISE WHILE IN-FLIGHT.  UPON INSPECTION, THE SPADE DOOR ON THE NOSE GEAR WAS FOUND WITH EXCES	S PLAY IN THE HINGE AREA.  ACFT PLACED ON JACKS AND SPADE DOOR REMOVED. THE RT ARM ON THE DOOR HAD THE S1003-16A (ITEM 8	2) BEARING MISSING.  THE 133-3P.250 SPACER WAS INSTALLED, BUT WITHOUT THE BEARING THE JOINT WAS VERY LOOSE.  A GEAR CHEC	K ON A PHASE 2 INSP PERFORMED AT 151.8 HRS AND DID NOT NOTICE DOOR BEING LOOSE.  ALL DOOR RIGGING OKAY AT THAT TIME.  AP	PARENTLY, THE BOLT HAD BEEN TIGHTENED ENOUGH TO KEEP THE DOOR ARM TIGHT, BUT HAD FINALLY WORN ENOUGH TO BECOME LOOSE.  S	1003-16A BEARING INSTALLED WITH A NEW 133-3P.250 SPACER.  DOOR REINSTALLED AND RIGGING CHECKED.  ALL OPERATIONS NORMAL.	2	L	7	2 	4F			RT	A22CE
1999010100241	19990101	00241	EA  	1999	1	1	98ZZZX4770       	1	19981030	G	3510	9007094826	OXYGEN BOTTLE   			DHAV  	DHC7  	DHC7102     	2802708	EA  										CABIN	FAILED          	B				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	07	177RA				907T	85				OXYGEN BOTTLE WAS RECEIVED FROM VENDOR FULLY SERVICED AND WAS INSTALLED ON AIRCRAFT WITHOUT CONNECTING THE SUPPLY LINES.	  OXYGEN BOTTLE SITTING STATICALLY, THE MALE CONNECTION FITTING SEPARATED INTERNALLY CAUSING EXPLOSION LIKE SOUND AND DI	SSIPATING ALL OF THE OXYGEN.  THE OXYGEN BOTTLE WAS REMOVED FROM AIRCRAFT AND RETURNED TO VENDOR.				2	H	7	4 	4T				A20EA
1999010100242	19990101	00242	CE  	1999	1	1	98ZZZX4771       	1	19981202	G	5712	25221403	RIB             			CESSNA	303   	T303        	2073820	CE  										WING	CRACKED         	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	303DT	4410 				T30300067				DURING AN ANNUAL INSPECTION, THE TRAILING EDGE RIBS, P/N 2522140-3, AND 2522140-4 WERE FOUND CRACKED.  THE CRACKS WERE L	OCATED IN THE WEB TO FLANGE RADIUS EMANATING FROM THE CUT-OUT FOR THE STRINGER PROGRESSING APPROXIMATELY .50 INCH ALONG 	THE RADIUS.  SUBMITTER STATED CAUSE AS FATIGUE.				1	L	7	2 	3O				A34CE
1999010100243	19990101	00243	CE  	1999	1	1	98ZZZX4772       	1	19981202	G	5712	25221404	RIB             			CESSNA	303   	T303        	2073820	CE  										WING	CRACKED         	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	303DT	4410 				T30300067				DURING AN ANNUAL INSPECTION, THE TRAILING EDGE RIBS, P/N 2522140-3, AND 2522140-4 WERE FOUND CRACKED.  THE CRACKS WERE L	OCATED IN THE WEB TO FLANGE RADIUS EMANATING FROM THE CUT-OUT FOR THE STRINGER PROGRESSING APPROXIMATELY .50 INCH ALONG 	THE RADIUS.  SUBMITTER STATED CAUSE AS FATIGUE.				1	L	7	2 	3O				A34CE
1999010100244	19990101	00244	CE  	1999	1	1	98ZZZX4773       	1	19981202	G	5712	25221011	RIB             			CESSNA	303   	T303        	2073820	CE  										WS 37	CRACKED         	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	303DT	4410 				T30300067				DURING AN ANNUAL INSPECTION, THE TRAILING EDGE RIBS P/N 2522101-1 AND 2522101-2 WERE FOUND CRACKED.  THE CRACKS WERE LOC	ATED IN THE WEB TO FLANGE RADIUS EMANATING FROM THE CUT-OUT FOR THE STRINGER PROGRESSING APPROXIMATELY .50 INCH ALONG TH	E RADIUS.  SUBMITTER STATED THE CAUSE WAS POSSIBLY FATIGUE.				1	L	7	2 	3O				A34CE
1999010100245	19990101	00245	CE  	1999	1	1	98ZZZX4774       	1	19981202	G	5712	25221012	RIB             			CESSNA	303   	T303        	2073820	CE  										WS 37	CRACKED         	B			MGOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	303DT	4410 				T30300067				DURING AN ANNUAL INSPECTION, THE TRAILING EDGE RIBS P/N 2522101-1 AND 2522101-2 WERE FOUND CRACKED.  THE CRACKS WERE LOC	ATED IN THE WEB TO FLANGE RADIUS EMANATING FROM THE CUT-OUT FOR THE STRINGER PROGRESSING APPROXIMATELY .50 INCH ALONG TH	E RADIUS.  SUBMITTER STATED THE CAUSE WAS POSSIBLY FATIGUE.				1	L	7	2 	3O				A34CE
1999010100246	19990101	00246	NM  	1999	1	1	98ZZZX4775       	1	19981120	G	5711	11121461	SPAR            			UNIVAR	108   	108         	9230402	NM  										WS 10-140	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	8660K	2030 				1081660				AIRCRAFT WAS METALIZED IN 1960'S.  NO INSPECTION PROVISIONS IN WINGS.   FRONT SPAR ON RT WING WAS/IS SEVERELY CORRODED F	ROM STA 40 TO STA 80.  CORROSION IS ON LEADING EDGE SIDE OF SPAR.  FOUR LEADING EDGE FORMERS ALSO SEVERELY CORRODED.					1	H	7	1 	3O				A767
1999010100247	19990101	00247	EA  	1999	1	1	98ZZZX4776       	2	19981116	G	7414	1081806	BEARING         	BENDIX      		CESSNA	177   	177         	2073704	CE  	LYC   	O360  	O360A1A     	41514	EA  					LT MAGNETO	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	3230T	399  			1043261	17700530	L1264636A			PILOT REPORTED NORMAL MAG CHECK PRIOR TO 10-MINUTE FLIGHT.  AFTER LANDING NOTICED OIL DRIPPING FROM COWL.  FOUND LT MAGN	ETO WITH LOWER MOUNTING EAR BROKEN OFF AND MAG PULLED AWAY FROM ACCESSORY CASE.  THE MAGNETO CASE WAS GAPPED OPEN AND ON	LY 2 SCREWS REMAINED HOLDING IT TOGETHER.  REMOVED MOUNTING NUTS AND FOUND A SMALL PIECE BROKEN FROM UPPER MOUNTING EAR.	  LW12706 ADAPTER BROKEN IN SEVERAL PIECES AND LOWER MOUNTING STUD BENT.  MAG DISSASSEMBLY FOUND DRIVE END BEARING DESTR	OYED, SHAFT BENT, AND DISTRIBUTOR GEAR BROKEN.  ELECTROSYSTEMS BELIEVES BEARING FAILURE MAY HAVE BEEN INITIAL CAUSE OF F	AILURE.  COMPONENT P/N S4LN-2110-51360-37.	1	H	7	1 	3O	3	O	NT	A13CE   	E286
1999010100248	19990101	00248	CE  	1999	1	1	98ZZZX4777       	1	19981123	G	5730	052309510	SKIN            			CESSNA	172   	172R        	2072401	CE  										LT WING	CRACKED         	B	P		WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	181MW	956  				17280181				DURING A ROUTINE INSPECTION, THE TRAILING EDGE WING SKIN ON THE RIGHT WING WAS FOUND CRACKED IN SEVERAL PLACES.  CRACKS 	WERE AT THE RIVET HOLES ALONG THE REAR MOST OF THE SKIN.  SUBMITTER STATED THAT IMPROPER DEBURRING OF THE HOLES AND IMPR	OPER RIVET SPACING FOR THE RIVETS AND ALLOWED THE SKIN TO FLEX AND VIBRATE IN-FLIGHT.  RIVETS ARE .1250 INCH AND SPACED 	2.1250 INCHES APART, COUNTERSUNK INTO .016 INCH METAL THAT IS NOT DIMPLED FOR SUCH A LARGE RIVET.			1	H	7	1 	3O			NT	3A12
1999010100249	19990101	00249	GL  	1999	1	1	98ZZZX4778       	3	19981218	G	6114	D5858C406	HUB             													MCAULY	3A32C	3A32C406    	GL  	PROPELLER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								922011		HEAVY CORROSION ON FACE AND INBOARD EDGE OF BLADE SOCKET NR 1.  HUB WAS PLACED IN SERVICE IN 1992 OR 1993.  TSN IS UNKNO	WN.															5	C	P21EA
1999010100250	19990101	00250	SO  	1999	1	1	98ZZZX4779       	2	19981028	G	8530	654961AZ	CYLINDER        			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520B    	17040	SO  					ENGINE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	3758C	896  				4140839	509129			DURING 100-HOUR INSPECTION COMPRESSION CHECK, FOUND NR 3 CYLINDER CRACKED FROM THE EXHAUST VALVE GUIDE TO THE SPARK PLUG	 HOLE.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE
1998020500426	19980205	00426	CE  	1998	2	5	98ZZZX478        	1	19980121	G	2720	45A24073011U	TORQUE TUBE     			MTSBSI	MU300 	MU300       	5780602	CE  										RUDDER	MISALIGNED      	B	S	A	VIB3	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	03	70VT	3023 			A085	A085SA				DURING A AND B  CHECK, AIRCRAFT TECHNICIANS FOUND AIRCRAFT RUDDER DISPLACED TO THE RIGHT APPROXIMATELY 3 INCHES.  THIS C	ONDITION WAS FOUND WITH RUDDER CONTROL SYSTEM RIGGED PER AIRCRAFT MM AND WITH PROPER CABLE TENSION SET.  SYSTEM RIG PINS	 WERE ALSO INSTALLED IN THE FORWARD AND AFT CONTROL SECTIONS.  PROBLEM APPEARS TO BE THE MISALIGNMENT BETWEEN THE LOWER 	MOUNTING FLANGE OF THE RUDDER TORQUE TUBE AND THE AFT RUDDER SECTOR.			2	H	7	2 	4F			RT	A14SW
1999010100251	19990101	00251	CE  	1999	1	1	98ZZZX4780       	1	19981123	G	5312	0553031	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  										ENGINE BAY	CRACKED         	B	P		WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	97100	537  				17280100				DURING A ROUTINE INSPECTION, THE FIREWALL WAS FOUND CRACKED IN 3 PLACES.  THE FIREWALL THICKNESS - .016 INCH WHICH IS TH	INNER THAN OLDER MODELS WHICH ARE BETWEEN .020 INCH AND .024 INCH.  (IT IS DIFFICULT FOR AN ACCURATE MEASUREMENT TO BE T	AKEN WITHOUT DISASSEMBLING ACFT FIREWALL).  THERE IS ALSO NO DOUBLER BEHIND THE COWL MOUNTS TO PREVENT FLEXING OF THE FI	REWALL AT THESE POINTS.			1	H	7	1 	3O			NT	3A12
1999010100252	19990101	00252	CE  	1999	1	1	98ZZZX4781       	1	19981123	G	5312	0553031	BULKHEAD        			CESSNA	172   	172R        	2072401	CE  										ENGINE BAY	CRACKED         	B	P		WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	181MW	956  				17280181				DURING ROUTINE INSPECTION, THE FIREWALL WAS FOUND CRACKED AT THE UPPER PART OF THE LOWER FIREWALL JUST BEHIND THE COWL M	OUNT AND AT THE COWL MOUNT JUST BELOW THE BATTERY BOX.  THIS DEPARTMENT HAS NOTICED THE FIREWALL IS .016 INCH THICK WHIC	H IS THINNER THAN FIREWALLS USED 15 YEARS AGO.  THERE ARE NO DOUBLERS BEHIND THE MOUNTS TO PREVENT FLEXING OF THE FIREWA	LL DURING NORMAL OPERATION.			1	H	7	1 	3O			NT	3A12
1999010100253	19990101	00253	SO  	1999	1	1	98ZZZX4782       	1	19981207	G	5320	706033	ANGLE           			PIPER 	PA42  	PA42        	7104202	SO  										ENGINE BAY	CRACKED         	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	22BD	6907 				428001055				ON A ROUTINE INSPECTION, A 2 INCH CRACK WAS FOUND ON THE RT ENGINE FIREWALL COMING OUT FROM UNDER OUTBOARD LOWER MOUNT F	LANGE.  THE MOUNT BOLT APPEARED TO BE TORQUED CORRECTLY.  WHILE DOING REPAIR TO FIREWALL, FOUND A CRACK IN ANGLE ON AFT 	SIDE OF FIREWALL.  70606-3 WAS INK-STAMPED ON THE ANGLE.				1	L	7	2 	4T				A23SO
1999010100256	19990101	00256	GL  	1999	1	1	98ZZZX4785       	3	19981111	G	6111	V843310	BLADE           			PIPER 	PA23  	PA23250     	7102308	SO  						HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	4528P	5858 	963  			2732		H1552		PROPELLER WAS SUBMITTED FOR C/W AD 97-18-02, SB 217.  BOTH BLADES WERE FOUND CRACKED IN THE RETENTION RADIUS USING EDDY 	CURRENT INSPECTION EQUIPMENT.  CRACKS ARE ESTIMATED AT 50 PERCENT OF CIRCUMFERENCE.					1	L	7	2 	3O				1A10    		5	C	P24EA
1999010100257	19990101	00257	CE  	1999	1	1	98ZZZX4786       	1	19981207	G	3233	98820201	ACTUATOR        			CESSNA	210   	T210N       	2073456	CE  										NLG	FAILED          	B			RC0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	5416U		36   		3012	21064890				UPON REQUEST OF RAYTHEON AEROSPACE IOC TO INSPECTION RECENTLY CHANGED NLG ACTUATOR FOR DOWNLOCK PIN PROTRUSION PER SEB 9	5-20/SK210-155 WHICH SHOWS PROTRUSION TO BE .325 INCH PLUS OR MINUS .005 INCH.  THIS RECENTLY INSTALLED ACTUATOR WAS FOU	ND TO HAVE .280/.291 INCH PROTRUSION OF DOWNLOCK PINS.  SUBMITTER RECOMMENDS ANYONE WHO HAS RECENLY CHANGED NLG ACTUATOR	S OF THIS TYPE, TO INSPECT FOR PROPER PROTRUSION OF NLG DOWNLOCK PINS PER SEB 95-20-SK210-155.			1	H	7	1 	3O				3A21
1999010100258	19990101	00258		1999	1	1	98ZZZX4787       	2	19981124	G	7260	695522722	FAN             		38025611    															ACCY GEARBOX	LEAKING         	B			GV7R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	07					P27436					COWLING FAN STARTED TO LEAK OIL IN OPERATION.  INSPECTION UPON DISSASSSEMBLY REVEALED A CRACKED CARBON SEAL.  SUBMITTER 	SUGGESTED CAUSE OF DEFECT AS IMPROPER INSTALLATION.  ASSEMBLY PROCEDURES HAVE BEEN REVIEWED TO ENSURE PROPER INSTALLATIO	N.
1999010100259	19990101	00259	CE  	1999	1	1	98ZZZX4788       	1	19981015	G	5280	35815055214	DOOR            			BEECH 	58    	58          	1152740	CE  										LT MLG	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	1015E	936  				TH1776				FORWARD HINGE RIVETS SHEARED CAUSING GEAR DOOR TRAILING EDGE TO REST ON TIRE.  UPON TOUCH DOWN, THE TIRE CAUGHT THE DOOR	 CAUSING THE DOOR TO CAUSE DAMAGE TO THE TIRE AND BRAKE LINE.  AIRCRAFT LANDED WITHOUT INCIDENT.					1	L	7	2 	3O				3A16
1999010100260	19990101	00260	CE  	1999	1	1	98ZZZX4789       	1	19981109	G	2730	051050525	CONTROL CABLE   			CESSNA	185   	A185F       	2072821	CE  										BS 140	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	185PW	1964 				18504239				ELEVATOR LOWER CABLE FRAYED AT FS 140.0, RUBBING ON WEAR BLOCK.  INSPECTED ALL CABLES THAT MAKE CONTACT WITH ANOTHER SUR	FACE, PULLEYS, RUB BLOCKS.					1	H	7	1 	3O			 	3A24
1998020500427	19980205	00427	CE  	1998	2	5	98ZZZX479        	1	19980119	G	2912	MS2877422	BACKUP RING     			CESSNA	650   	650         	2076802	CE  										HYD FILTER SEAL	MISMANUFACTURED 	D				K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			NM	01	38WP	522  				650032				ON MAINTENANCE POST-FLIGHT, DISCOVERED RT ENGINE HYDRAULIC MAIN FILTER WET WITH HYDRAULIC FLUID.  INVESTIGATION SHOWED L	EAKAGE FROM FILTER BOWL SEAL AND TEFLON CHEVRON AREA.  INSPECTION OF O-RING SEAL AND BACK-UP TEFLON RINGS SHOWED BEVEL D	EFECT ON BACK-UP RING LETTING O-RING DEFORM.  THE BACK-UP RING SHOWED BEVELS CUT THE SAME ANGLE PREVENTING OVERLAP FOR A	 SMOOTH SURFACE.  REPLACED O-RING AND BACK-UP RINGS THAT CORRECTED THE CONDITION.  RECOMMEND TECHNICIAN'S ATTENTION TO B	ACK-UP RING INSPECTION AT TIME OF INSTALLATION.		2	L	7	2 	4F				A9NM
1999010100261	19990101	00261	CE  	1999	1	1	98ZZZX4790       	1	19981109	G	7810		COLLECTOR       			CESSNA	185   	A185F       	2072821	CE  										ENGINE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	185PW					18504239				NR 6 EXHAUST FLANGE BROKEN OFF EXHAUST COLLECTOR.						1	H	7	1 	3O				3A24
1999010100262	19990101	00262	SO  	1999	1	1	98ZZZX4791       	2	19981208	G	8530	653877K5	LIFTER          			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	761AS	397  				21062107	293829R			SPALLED LIFTER WAS FOUND AFTER NR 1 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION.  SUSPECT MANUFACTURING DEFECT OR OIL FI	LM FAILURE.  ENGINE WAS USING AEROSHELL 15W-50.					1	H	7	1 	3O	3	O		3A21    	E8CE
1999010100263	19990101	00263	EA  	1999	1	1	98ZZZX4792       	2	19981124	G	8530	76428	CRANKSHAFT      								LYC   	O360  	HIO360C1A   	41514	EA  					ENGINE	OUT OF TOLERANCE	B		A	YECR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09							RL957951A			WHILE INSPECTING CRANKSHAFT AND PERFORMING TRIAL ASSEMBLY OF GEAR PER TEXTRON LYC BULLETIN 475B AND FAA AD 91-14-22, NOT	ED THE GEAR WOULD NOT START INTO THE CRANKSHAFT COUNTERBORE DUE TO A DISCREPANCY BETWEEN RADIAL POSITION OF DOWEL IN CRA	NKSHAFT AND DOWEL HOLE IN GEAR.  WHEN DOWEL WAS REMOVED FROM CRANKSHAFT, GEAR FIT WAS OK.  CRANKSHAFT WAS REPAIRED BY RE	LOCATING DOWEL HOLE .002 INCH CLOSER TO AXIS AND INSTALLATION OF OVERSIZE DOWEL.  SUBMITTER STATED THIS IS THE SIXTH EXA	MPLE OF THIS PROBLEM.							3	O			1E10
1999010100264	19990101	00264	SO  	1999	1	1	98ZZZX4793       	1	19981120	G	3246	16101900	WHEEL           	CLEVELAND   	40102       	PIPER 	PA31  	PA31310     	7103103	SO  										RT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	9007Y					3111				AIRCRAFT INSPECTED DUE TO FLAT TIRE AND FOUND INBOARD RIM CRACKED ALONG BEAD ABOUT 10 INCHES.  INSPECTION REVEALED THE C	RACK TO BE A FRESH CRACK.  CHECKED FOR ANY CORROSION, NONE WAS FOUND.  SUBMITTER STATED CAUSE COULD BE FROM HARD LANDING	S OR MISHANDLING DURING TIRE CHANGE.  PART TT UNKNOWN.  AIRCRAFT TT, 6,740.0 HOURS.  THE CRACK WAS ABOUT .2500 INCH WIDE	.			1	L	7	1 	3O			RT	A20SO
1999010100265	19990101	00265	SO  	1999	1	1	98ZZZX4794       	1	19980412	G	3230	3788103	BOLT            		3564455     	PIPER 	PA28  	PA28161     	7102803	SO  										MLG	CRACKED         	D				O				OTHER                   				D			INFLIGHT SEPARATION       			LD	LANDING        	1			GL	09	4385W	6961 				288516002				BOLT (SPECIAL PIPER PART) CRACKED THROUGH THREADS ALLOWING TORQUE LINK TO SERRATE. RT WHEEL DEPARTED AIRCRAFT ON TAKEOFF	.  MINOR DAMAGE TO AIRCRAFT ON LANDING.					1	L	7	1 	3O				2A13
1999010100266	19990101	00266	GL  	1999	1	1	98ZZZX4795       	1	19980918	G	7810	DC001	EXHAUST RISER   			DIAMON	DA20  	DA20C1      	2990001	GL  										ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	311CL	53   				C0011				EXHAUST RISER FOUND CRACKED ON NR 3 CYLINDER ON 50-HOUR OIL CHANGE.  SUBMITTER SUSPECTS CAUSE TO BE EXHAUST SYSTEM TOO R	IGID TO ALLOW FOR HEAT EXPANSION.					1	L	7	1 	3O			NT	TA4CH
1999010100267	19990101	00267	SO  	1999	1	1	98ZZZX4796       	1	19981209	G	3710	211CC	PUMP            	AIRBORNE    		PIPER 	PA24  	PA24250     	7102404	SO  										VACUUM SYSTEM	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	7145P	37   			09AN003366	242310				SHAFT FAILED.  UPON INSPECTING PUMP INTERNALLY, CORE WAS BROKEN IN 3 PIECES.  OCCURRED IN CRUISE FLIGHT.  VACUUM GAUGE H	AD INTERMITTENT FLICKER.					1	L	7	1 	3O				1A15
1999010100268	19990101	00268	EA  	1999	1	1	98ZZZX4797       	2	19981030	G	7414	6351	MAGNETO         	SLICK       		BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  					LT ENGINE	BROKEN          	D				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			SO	21	861VL	7454 	1859 		95020015	2155	L1291640A			DURING RUN-UP, PILOT REPORTED LEFT ENGINE WOULD NOT START.  LEFT MAGNETO REMOVED AND FOUND MAGNETO COUPLING PIN BROKEN A	ND CRANKSHAFT IDLER GEAR ASSY, P/N 71668, BROKEN.  GEAR ASSEMBLY REPLACED.					1	H	7	2 	3O	3	O	RT	A17EU   	E295
1999010100269	19990101	00269	EA  	1999	1	1	98ZZZX4798       	2	19981104	G	7414	6351	MAGNETO         			BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  					RT ENGINE	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	21	902VL	9710 	1632 		8011439	2128	L1458840A			PILOT REPORTED HIGH OIL TEMPERATURE.  OIL FILTER REMOVED AND FOUND METAL PARTICLE CONTAMINATION.  MAGNETOS REMOVED AND F	OUND MAGNETO IMPULSE COUPLING PIN BROKEN.  METAL PARTICLES CONTAMINATED ENGINE.  ENGINE REMOVED TO REPAIR OR OVERHAUL.					1	H	7	2 	3O	3	O	RT	A17EU   	E295
1999010100270	19990101	00270	CE  	1999	1	1	98ZZZX4799       	1	19981101	G	5754	1691600519	RIB             			BEECH 	23    	A23A        	1151208	CE  										LE FLAP	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11	3602Q	3052 				M1034				WHILE ACCOMPLISHING AN ANNUAL INSPECTION, FOUND CORROSION ON THE SMALL AREAS OF THE RIB.  AFTER REMOVING LEADING EDGE OF	 THE FLAP, FOUND SEVERE CORROSION.					1	L	7	1 	3O				A1CE
1998020500428	19980205	00428	EU  	1998	2	5	98ZZZX480        	1	19980113	G	2510	262200	SEAT FRAME      			AMD   	FALC20	FALCON      	2720302	EU  										PILOT	BROKEN          	B		A	QY5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	20NY	7374 			69	61				PILOT'S INBOARD ARM REST WAS NOTICED TO FLEX EXCESSIVELY.  SEAT BACK UPHOLSTERY REMOVED TO INSPECT SEAT FRAME.  FRAME TU	BE FOUND COMPLETELY BROKEN THROUGH APPROXIMATELY 4 INCHES BELOW ARM REST ATTACH POINT.  BREAK APPEARS TO ORIGINATE FROM 	A POP RIVET HOLE WHERE SHEET METAL ATTACHES TO TUBE AND TUBE FLEXES FROM PILOT'S WEIGHT ON ARM REST.  NEW REPLACEMENT PA	RT FROM FALCON CAME WITH ADDITIONAL REINFORCEMENT IN THIS AREA.  RECOMMEND INTERVAL INSPECTION OF OLD STYLE SEAT FRAMES 	IN THIS AREA.		2	L	7	2 	4F				A7EU
1999010100271	19990101	00271	CE  	1999	1	1	98ZZZX4800       	1	19980924	G	3231	316	ROD             		354100772   	BEECH 	35    	V35B        	1151548	CE  										NLG DOOR	WORN            	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	20318					D10173				ACTUATOR ROD WORN IN NLG DOOR.						1	L	7	1 	3O				3A15
1999010100272	19990101	00272	GL  	1999	1	1	98ZZZX4801       	1	19980918	G	7810	DC001	EXHAUST RISER   			DIAMON	DA20  	DA20C1      	2990001	GL  										ENGINE	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	116CL	29   				C0016				EXHAUST RISER FOUND CRACKED ON 25-HOUR INSPECTION.  SUBMITTER SUSPECTED CAUSE TO BE EXHAUST SYSTEM TOO RIGID TO ALLOW FO	R HEAT EXPANSION.					1	L	7	1 	3O			NT	TA4CH
1999010100273	19990101	00273	EU  	1999	1	1	98ZZZX4802       	1	19981102	G	6720	350A33214500	PITCH LINK      			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	410TV	1150 			011707	2408				ON 11-2-98, A DAILY INSPECTION WAS PERFORMED.  A PIECE OF TAPE THAT SEPARATES THE BALL BEARING FROM ITS OUTER RACE ON TH	E T/R P/C LINK HAD FLAKED OUT AND WAS REMOVED (.1250 INCH BY .0625 INCH).  CHAPTER 65.20.00.601 PARA 4.2 OF THE AS350 MM	 WAS CHECKED.  NO MENTION OF THE SEPARATION WAS SHOWN, ONLY CONDITION AND THE RADIAL PLAY CHECK.  THE PART WAS IN TOLERA	NCE.  THE AIRCRAFT WAS RETURNED TO SERVICE.  ON 11-9-98, 76.8 HOURS LATER, THE P/C LINK WAS CHECKED DURING A DAILY INSPE	CTION AND FOUND TO HAVE A RADIAL PLAY OF .023 INCH AND AN AXIAL PLAY OF .068 INCH, WELL BEYOND ALLOWABLE LIMITS.		1	G	7	1 	3U				H9EU
1999010100275	19990101	00275	SW  	1999	1	1	98ZZZX4804       	1	19981209	G	7931	209070262109	INDICATOR       			BELL  	412   	412EP       	1182205	SW  										COCKPIT	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	44454	12   			98030372	36210				OIL PREESSURE INDICATOR REPLACED WITH NEW INDICATOR FROM BELL HELICOPTER.						1	G	7	2 	4U				H4SW
1999010100276	19990101	00276	SW  	1999	1	1	98ZZZX4805       	1	19981201	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										TAIL ROTOR	SPREAD          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	982ST	124  				53200				OIL PRESSURE INDICATOR REPLACED WITH NEW DISC PACK AND INPUT SEAL FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1999010100277	19990101	00277	SW  	1999	1	1	98ZZZX4806       	1	19981201	G	6510	406040453101	SEAL            			BELL  	407   	407         		SW  										TAIL ROTOR	LEAKING         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	982ST	124  				53200				OIL PRESSURE INDICATOR REPLACED WITH NEW DISC PACK AND INPUT SEAL FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1999010100278	19990101	00278	SW  	1999	1	1	98ZZZX4807       	1	19981201	G	6330	206064313101	TUBE            			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CHAFED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	36R	38   				52203				REPLACED TUBE WITH NEW PARTS SUPPLIED BY BELL HELICOPTER.						1	G	7	1 	3U			NC	H2SW
1999010100279	19990101	00279	SW  	1999	1	1	98ZZZX4808       	1	19981201	G	6510	406040340101	DISC PACK       			BELL  	407   	407         		SW  										T/R DRIVE	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407AP	198  			RNFS7900	53020				REPLACED WITH NEW DISC PACK AND ROTOR BRAKE KIT SUPPLIED BY BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1999010100280	19990101	00280	SW  	1999	1	1	98ZZZX4809       	1	19981201	G	6321	B0223KA	BRAKE KIT       			BELL  	407   	407         		SW  										ROTOR BRAKE	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	407AP	198  				53020				REPLACED WITH NEW DISC PACK AND ROTOR BRAKE KIT SUPPLIED BY BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1998020500429	19980205	00429	CE  	1998	2	5	98ZZZX481        	1	19980119	G	3250	171001	LINE            			RKWELL	NA265 	NA26540     	6402608	CE  										NLG STEERING	LEAK            	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	85CC				4CR0134	282108				LINE INSTALLED AT NOSE STEERING ACTUATOR TO SWIVEL JOINT IN NOSE WHEELWELL.  LINE STARTED TO LEAK AT POINT IN LINE WHERE	 LINE BENDS WHEN NLG ACTIVATED.					2	L	7	2 	4J				A2WE
1999010100281	19990101	00281	SW  	1999	1	1	98ZZZX4810       	1	19981201	G	6330	206064313101	TUBE            			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CHAFED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	94PD	13   			5455	52205				REPLACED TUBE AND MOUNT WITH NEW PARTS SUPPLIED BY BELL HELICOPTER.						1	G	7	1 	3U			NC	H2SW
1999010100282	19990101	00282	SW  	1999	1	1	98ZZZX4811       	1	19981201	G	6330	206033542003	MOUNT           			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CHAFED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	94PD	13   			45920	52205				REPLACED TUBE AND MOUNT WITH NEW PARTS SUPPLIED BY BELL HELICOPTER.						1	G	7	1 	3U			NC	H2SW
1999010100283	19990101	00283	SW  	1999	1	1	98ZZZX4812       	1	19981201	G	5510	407023801109	FITTING         			BELL  	407   	407         		SW  										HORIZONTAL STAB	CRACKED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	6376K	10   				543237				REPLACED WITH NEW HORIZONTAL STABILIZER FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1999010100285	19990101	00285	SW  	1999	1	1	98ZZZX4814       	1	19981201	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	720PH	11   			0318	53277				REPLACED WITH NEW INDICATOR FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1999010100286	19990101	00286	EU  	1999	1	1	98ZZZX4815       	1	19981106	G	6210	1090103019	BLADE           			AGUSTA	A109  	A109A2      	0260120	EU  										MAIN ROTOR	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	109SL	1539 			855T	7299				DURING COMPLIANCE OF AGUSTA TB 109-50B PT. 2, 25-HOUR MAIN ROTOR BLADE INSPECTION, A CRACK WAS FOUND STARTING FROM THE T	RAILING EDGE EXTENDING CHORD-WISE FOR APPROXIMATELY 40 MM,  2070 MM FROM THE BLADE ROOT.					1	G	7	2 	3U				H7EU
1999010100288	19990101	00288	CE  	1999	1	1	98ZZZX4817       	1	19981109	G	2730	96610024601	HINGE           			BEECH 	58    	58          	1152740	CE  										ELEVATOR	WRONG PART      	B	L	A	R2JR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	100QD					TH619				DURING MAINT, TECH NOTICED LT OTBD ELEVATOR HINGE BEARING LOOKED SUSPICIOUS.  UPON INVESTIGATION, FOUND WRONG BEARING HA	D BEEN INSTALLED.  A P/N MKSP4A BEARING WAS INSTALLED INSTEAD OF A KSP3L BEARING.  THE WRONG BEARING WAS LARGER AND THE 	HINGE WAS ROUTED OUT TO TAKE THE LARGER BEARING.  BEARING WAS ALSO DAMAGED BY BEING HAMMERED INTO BRACKET.  THE .1875 IN	CH HINGE BOLT WAS OVERTORQUED WITH SPACERS TO FIT THE .25 INCH INSIDE DIAMETER BEARING HOLE.  EDGE DISTANCE ON BRACKET W	AS ALSO MINIMAL.  A NEW P/N 96-610024-601 HINGE ASSY WITH PROPER BEARING, WHICH HAD BEEN FACTORY INSTALLED, WAS INSTALLE	D.  P/N 35-650121-8 ELEV HINGE BRACKET, AND P/N 1309098193 BOLTS WERE INSTALLED AS PRECAUTION.	1	L	7	2 	3O				3A16
1999010100289	19990101	00289	CE  	1999	1	1	98ZZZX4818       	1	19981117	G	7921	10194A	OIL COOLER      			BEECH 	58    	58          	1152740	CE  										OIL SYSTEM	CRACKED         	B	S		EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1061F	616  			D951949859	TH1761				LEFT AND RIGHT OIL COOLERS CRACKED AT MOUNTING FLANGE.  FLANGE ATTACHED TO ENGINE BAFFLES AND SUPPORTS WIRE HARNESS WITH	 90 DEGREE ANGLE AND CLAMP.					1	L	7	2 	3O				3A16
1999010100290	19990101	00290	CE  	1999	1	1	98ZZZX4819       	1	19981117	G	7921	10194A	OIL COOLER      			BEECH 	58    	58          	1152740	CE  										OIL SYSTEM	CRACKED         	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1061F	616  			D951949857	TH1761				LEFT AND RIGHT OIL COOLERS CRACKED AT MOUNTING FLANGE.  FLANGE ATTACHED TO ENGINE BAFFLES AND SUPPORTS WIRE HARNESS WITH	 90 DEGREE ANGLE AND CLAMP.					1	L	7	2 	3O				3A16
1998020500430	19980205	00430	CE  	1998	2	5	98ZZZX482        	1	19980120	G	2810	10192006137	VALVE           			BEECH 	300   	B300C       		CE  										FUEL FILLER	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	80605					FM6				DURING AIRCRAFT REFUELING WHEN THE NOZZLE IS INSERTED INTO THE FUEL FILLER, IT OPENS THE ANTI-SYPHON VALVE FLAPPER DOOR 	(SPRING LOADED) AND EXTENDS INTO THE TANK AREA.  THE AREA OF ANTI-SYPHON VALVE THAT THE FLAPPER DOOR SEALS AGAINST IS CA	LLED THE PAN. THIS PART OF THE ANTI-SYPHON VALVE GETS DAMAGED (BENT) FROM THE NOZZLE.  AFTER THE PAN IS DAMAGED, THE FLA	PPER DOOR CANNOT SEAL AND THE ANTI-SYPHON VALVE BECOMES LESS EFFECTIVE.  SUBMITTER RECOMMENDS CARE BE TAKEN WHEN INSERTI	NG THE NOZZLE INTO THE TANK AND FUELING.		2	L	7	2 	4T			RT	A24CE
1999010100291	19990101	00291	CE  	1999	1	1	98ZZZX4820       	1	19981117	G	7921	10278A	OIL COOLER      			BEECH 	58    	58          	1152740	CE  										OIL SYSTEM	CRACKED         	B	S		EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	207ZA	100  			D97275084	TH1832				LEFT ENGINE OIL COOLER CRACKED AT MOUNTING FLANGE.  FLANGE ATTACHED TO ENGINE BAFFLES AND SUPPORTS WIRE HARNESS WITH 90 	DEGREE ANGLE AND CLAMP.					1	L	7	2 	3O				3A16
1999010100292	19990101	00292	CE  	1999	1	1	98ZZZX4821       	1	19981019	G	2497		WIRE            			CESSNA	500   	560CESSNA   	2076750	CE  										CABIN	FAILED          	B	L		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	330QS	3391 				5600329				SMOKE OBSERVED COMING FROM THE AFT LAVATORY AREA.   BATTERY SWITCH WAS TURNED OFF, AND GROUND POWER UNIT DISCONNECTED FR	OM ACFT.  A CHECK OF CIRCUIT BREAKERS IN THE COCKPIT AND AFT POWER JUNCTION BOXES SHOWED ALL CB' S WERE ENGAGED.  FOUND 	WIRE GOING FROM K55 RELAY TO GND 33 HAD MELTED INSULATION AND BURNED WIRES.  UNABLE TO DETERMINE WHICH WIRES SHORTED TO 	GROUND FIRST, UNABLE TO LOCATE CHAFE OR SHORT TO GROUND DUE TO DAMAGE TO ALL WIRES IN THE AREA.  PERFORMED RESISTANCE CH	ECK OF K55 RELAY.  RELAY CHK GOOD.  ALL DAMAGED WIRING REPLACED.  K55 RELAY REPLACED AS PRECAUTIONARY.  PERFORMED FUNCTI	ONAL CHECK OF THE TEMP CONTROL CIRCUIT AND SYS CHECKED NORMAL.  ACFT APPROVED FOR RETURN TO SERVICE.	2	L	7	2 	4F			RT	A22CE
1999010100294	19990101	00294	CE  	1999	1	1	98ZZZX4823       	1	19980617	G	3230	20810018	GEAR            			CESSNA	177   	177RG       	2073709	CE  										MLG	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	21620					177RG0562				MAIN LANDING GEARS FAILED TO EXTEND.  FROM CHASE PLANE, OBSERVED NOSE GEAR WOULD RETRACT AND EXTEND.  THE MAINS WOULD NO	T MOVE, AND THE AIRCRAFT WAS LANDING WITH BOTH MAINS IN TRAIL.  HOISTING THE AIRCRAFT, FOUND RT MAIN WAS EASILY MOVED TO	 THE DOWN POSITION.  IT TOOK SEVERAL BACK AND FORTH MOVEMENTS TO GET THE LT HAND GEAR DOWN.  ON INSPECTION, FOUND BOTH S	ECTOR GEAR BOLTS SHEARED.  ONE TOOTH FROM THE LT HAND PINION GEAR WAS LYING IN THE BELLY.  SUBMITTER BELIEVES THE SEQUEN	CE OF FAILURE WAS THAT A TOOTH BROKE OFF THE PINION GEAR AND JAMMED THE MAIN GEARS.  ON LANDING, THE SECTOR BOLTS FAILED	 FROM THE WEIGHT OF THE AIRCRAFT FORCING THE GEARS UP.	1	H	7	1 	3O				A20CE
1999010100295	19990101	00295	CE  	1999	1	1	98ZZZX4824       	1	19981130	G	5412		SKIN            			CESSNA	172   	R172K       	2072431	CE  										COWL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	736FC					R1722484				SEVERE CRACKING OF LOWER COWL AT BOTH CORNERS OF THE COWL FLAP CUT-OUT.  CRACKS EXTEND THROUGH DOUBLER P/N 0552145-1.						1	H	7	1 	3O				3A17
1999010100296	19990101	00296	CE  	1999	1	1	98ZZZX4825       	1	19981130	G	5412		SKIN            			CESSNA	172   	R172K       	2072431	CE  										COWL	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	758HC					R1723100				SEVERE CRACKING OF LOWER COWL AT CORNERS OF COWL FLAP CUT-OUT.  CRACKS EXTEND THROUGH DOUBLER P/N 0552145-1.						1	H	7	1 	3O				3A17
1999010100297	19990101	00297	CE  	1999	1	1	98ZZZX4826       	1	19981101	G	3340		CONNECTOR       			CESSNA	310   	310P        	2074238	CE  										STROBE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	5715M					310P0045				NOTED DURING INSPECTION, BELLY STROB MAKING LARGE POPPING SOUND.  INVESTIGATED AREA OF NOISE AND NOTED UNDER PLUG COVER 	BLACK WIRE BROKEN AND BURNED AWAY FROM PIN.  REPLACED ALL PINS IN PLUG.  RE-ATTACHED AND OPERATED.  NOISE GONE AND LIGHT	 OPERATES SATISFACTORY.				1	L	7	2 	3O				3A10
1999010100298	19990101	00298	CE  	1999	1	1	98ZZZX4827       	1	19981014	G	5711	9542001715	SPAR            		354104455   	BEECH 	95    	95B55       	1152729	CE  										WING	BENT            	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8493N	2317 				TC1112				DURING ANNUAL INSPECTION, THE DOUBLER WAS FOUND BENT AND PARTIALLY SEPARATED FROM AFT WEB OF FRONT SPAR CARRY-THROUGH ST	RUCTURE DUE TO PRE-EXISTING DAMAGE TO WEB.  SUBMITTER STATED AIRCRAFT HAS A HISTORY OF PREVIOUS GEAR UP LANDING.					1	L	7	2 	3O			RT	3A16
1999010100299	19990101	00299	CE  	1999	1	1	98ZZZX4828       	1	19981014	G	5711	9542001715	SPAR            		354104456   	BEECH 	95    	95B55       	1152729	CE  										WING	BENT            	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	8493N	2317 				TC1112				DURING ANNUAL INSPECTION, THE DOUBLER WAS FOUND BENT DUE TO PRE-EXISTING DAMAGE TO FORWARD WEB OF FRONT SPAR CARRY-THROU	GH STRUCTURE.  SUBMITTER STATED AIRCRAFT HAS A HISTORY OF GEAR UP LANDING.					1	L	7	2 	3O			RT	3A16
1999010100300	19990101	00300		1999	1	1	98ZZZX4829       	4	19981120	G	6122	B20749	FLYWEIGHT       		C290D3GT18  	PIPER 	PA24  	PA24260     	7102406	SO  										PROP GOVERNOR	FAILED          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	79RG				860366	244399				FLYWEIGHT BASE SEPARATED INTO 2 PIECES CAUSING LOSS OF CONTROL OF GOVERNOR AND PROPELLER.						1	L	7	1 	3O				1A15
1999010100301	19990101	00301	SO  	1999	1	1	98ZZZX4830       	1	19981117	G	7160	MS3548911	GROMMET         			PIPER 	PA28  	PA28181     	7102807	SO  										AIR BOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145A					2843150				FOUND CARBURETOR HEAT PIVOT BUSHING UPPER AND LOWER GROMMETS WORN THROUGH AND ABOUT TO SPLIT APART.  SUBMITTER STATED TH	IS IS A RECURRING PROBLEM ON ALL 16 OF THE ARCHERS IN FLEET.  EVERY 50 TO 100 HOURS OF SERVICE THESE GROMMETS NEED TO BE	 REPLACED.				1	L	7	1 	3O				2A13
1999010100302	19990101	00302	SO  	1999	1	1	98ZZZX4831       	1	19981109	G	5320	12014241001	BRACKET         			EMB   	120   	EMB120RT    		SO  										BS 4825	CORRODED        	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	130AM					120134				AT STA 4825.5, THE LEFT HAND FLOOR SUPPORT BRACKET BETWEEN THE LEFT HAND OMEGA BEAM AND THE FUSELAGE, WAS FOUND SEVERELY	 EXFOLIATED.  THIS AREA IS EXPOSED TO MOISTURE FROM THE PASSENGER DOOR ENTRY WAY, AND ACIDIC SOFT DRINKS FROM THE GALLER	Y.  SUBMITTER RECOMMENDS REMOVING AND REPLACING THE DAMAGED PART AND SEALING THE AREA WITH MASTONOX TO PREVENT RENEWED C	ORROSION.			2	L	7	2 	4T			RT	A31SO
1998020500432	19980205	00432	CE  	1998	2	5	98ZZZX484        	1	19980113	G	3231	08421043	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  										NLG	FAILED          	D				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			EA	05	1545G	7546 				310R1220				PILOT REPORTED NOSE GEAR FAILED TO EXTEND FULLY.  FOUND THE NOSE GEAR INBOARD BELLCRANK TORQUE TUBE ASSIST HAD FAILED AL	ONG THE TOP CASTING MARK AND ALLOWED THE FORK BOLT TO SEPARATE.  ANNUAL INSPECTION WAS 6 MONTHS PRIOR AND LANDING GEAR R	IGGING WAS SET TO LIMITS IN SM.  NO CASE FOUND YET.				1	L	7	2 	3O				3A10
1998020500433	19980205	00433	SW  	1998	2	5	98ZZZX485        	1	19980108	G	5541	442283	SPAR            			GULSTM	112   	114         	7630314	SW  										RUDDER	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	114HP	1427 				14370				DURING ANNUAL INSPECTION, FOUND RUDDER SPAR CRACKED ON EDGE OF ALUMINUM SPACERS MOUNTED UNDER TOP RUDDER HINGE.  CRACK S	EEMS TO ORIGINATE FROM EDGE OF ALUMINUM SPACERS POSSIBLY FROM FLEXING IN THIS AREA. THIS IS A VERY HARD AREA TO SEE WELL	 DURING NORMAL INSPECTION AND MAJORITY OF THE CRACK WAS HIDDEN BY THE EDGE OF THE SPACER.  CRACK WAS DISCOVERED WHEN RUD	DER WAS REMOVED FOR UNRELATED MAINTENANCE.			1	L	7	1 	3O				A12SO
1998021100008	19980211	00008	EU  	1998	2	11	98ZZZX486        	2	19980116	G	8520		ENGINE          			AMTR  	500   	MINI500     	13015HW	GL  	ROTAX 	582   	ROTAX582    	55555	EU  					CRANKSHAFT	SEIZED          	D		A		R				AUTOROTATION            				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			GL	23	120VT					0222				ENGINE SEIZED IN-FLIGHT.  SERVICE CENTER THAT REPAIRED ENGINE SAID COUNTERWEIGHT CAME OFF REAR OF CRANKSHAFT.  SERVICE C	ENTER ALSO SAID THEY BELIEVE THAT COUNTEWEIGHT CAME OFF DUE TO THE WAY REVOLUTION INSTALLS BEARING ON END OF CLUTCH.  IT	 IS HELD STATIONARY WHICH DOES NOT ALLOW END OF CRANKSHAFT TO WOBBLE WHEN IT IS NOT EXACTLY TURNING TRUE.  SUBMITTER HAD	 TO DO AUTOROTATION, NO DAMAGE.			1	G	7	1 	3I	3	I	NC	EXPA1G71	EXPE3I
1998020500434	19980205	00434	CE  	1998	2	5	98ZZZX487        	1	19980112	G	3231	08411065	BELLCRANK       			CESSNA	310   	310R        	2074245	CE  										LT MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			EA	25	1203W					310R2106				FOUND LEFT MAIN GEAR INBOARD GEAR DOOR HANGING DOWN ON POST-FLIGHT,  PILOT REPORTED A LOUD BANG WHEN GEAR SELECTED DOWN.	  FOUND THE MAIN GEAR IDLER BELLCRANK DOOR ARM BROKEN OFF.  THIS IS THE 7TH TIME THIS OCCURRED IN FLEET OF 6 EACH C-310 	AIRCRAFT.  AIRCRAFT TOTAL TIME 5,741.3 HOURS.  LAST INSPECTION, 3 MONTHS PRIOR.				1	L	7	2 	3O				3A10
1998020500435	19980205	00435	CE  	1998	2	5	98ZZZX488        	1	19980114	G	3230	08421022	BELLCRANK       			CESSNA	310   	310Q        	2074242	CE  										NLG IDLER	FAILED          	G				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			EA	25	69622	5234 				310Q0904				LANDING GEAR WAS SELECTED 'UP'.  LOUD BANG WAS HEARD.  UPON INSPECTION, NOSE GEAR IDLER BELLCRANK WAS BROKEN OUT WHERE M	AIN DRIVE TUBE FROM GEAR MOTOR ATTACHES TO IT.  PART IS HARD TO PROPERLY INSPECT. RECOMMEND REMOVAL AND AND TESTING AT A	T ANNUAL INSPECTION.				1	L	7	2 	3O				3A10
1998020500437	19980205	00437	SW  	1998	2	5	98ZZZX490        	1	19980112	G	3213	65412002	AXLE            			GULSTM	560   	560         	0141402	SW  										MLG	CORRODED        	B	S		AC1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	356WC	152  				5600432				WHILE PERFORMING A PHASE 1 AND PHASE 2 ON BOTH MLG AXLES, FOUND CORROSION ON THEM.  THIS SPECIFIC INSPECTION ITEM IS ITE	M CODE NR A324040 IN THE PHASE 2 INSPECTION.  THE AXLE IS TO BE INSPECTED FOR PRESENCE OF PRIMER ON THE AXLE AND AXLE AD	APTER WHERE THE BRAKE AND BRAKE ADAPTER ARE LOCATED.  THE AXLES AND AXLE ADAPTER DID NOT HAVE THE REQUIRED PRIMER.  AS A	 RESULT, LIGHT CORROSION HAD ALREADY STARTED FORMING.  THE CORROSION WAS CLEANED UP AND CORROSION RESISTANT EPOXY PRIMER	 WAS APPLIED PER THE CITATION COMPONENT MM.		1	H	7	2 	3O				6A1
1998021100023	19980211	00023	GL  	1998	2	11	98ZZZX500        	2	19980116	G	7323	23057870	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE PT	MALFUNCTION     	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J		287  		21535	900801D				GOVERNOR DROOPS EXCESSIVELY WHEN POWER IS APPLIED AND IS SLOW TO RESPOND.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998021100024	19980211	00024	GL  	1998	2	11	98ZZZX501        	1	19980122	G	6230		SHAFT           			AMTR  	500   	MINI500     	13015HW	GL  										M/R	MISMANUFACTURED 	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	120VT					0222				BECAUSE OF MANY PROBLEMS WITH VIBRATIONS CRACKING FRAME, FOUND THE MAIN ROTOR SHAFT HAS AN INTERNAL FLAW.  IT WAS MANUFA	CTURED NOT BEING TRUE INSIDE.  THE INSIDE OF ROTOR MAST IS NOT CONCENTRIC WITH OUTSIDE.  THE MAIN CONTROL ASSEMBLY (SWAS	HPLATE) BOLTS TO THE INSIDE OF THIS SHAFT AND NOW HAS A SEVERE WOBBLE BECAUSE OF IT.  SUBMITTER STATED THE PARTS ARE MAN	UFACTURED WITH THIS DEFECT AND THEY STILL CONTINUE TO SELL THSE DEFECTIVE PARTS.			1	G	7	1 	3I			NC	EXPA1G71
1998021100025	19980211	00025	GL  	1998	2	11	98ZZZX502        	1	19980122	G	5310		FRAME           			AMTR  	500   	MINI500     	13015HW	GL  										M/R GEARBOX	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	120VT					0222				MOST ALL MINI-500 AIRFRAMES HAVE CRACKED NEAR THE MAIN ROTOR GEARBOX MOUNT BOLT HOLES.  ALL ARE LOW TIME ANYWHERE FROM 6	 HOURS AND UP.  AIR FRAME TUBE STRUCTURE MAY BE OF TOO THIN MATERIAL.  SUBMITTER BELIEVES CRACKS FORM BECAUSE OF THE INA	BILITY TO TRACK AND BALANCE ROTOR BECAUSE OF A FLAW IN THE MAIN ROTOR MAST.  THE INSIDE OF MAST IS NOT CONCENTRIC WITH T	HE OUTSIDE.  THE LOWER SWASHPLATE ATTACHES TO THE INSIDE OF SHAFT AND NOW HAS A SEVERE WOBBLE SINCE IT IS NOT CONCENTRIC	.  THIS AIRCRAFT, SN 0222, CONTINUES TO CRACK EVEN AFTER APPROVED REPAIRS.		1	G	7	1 	3I			NC	EXPA1G71
1998021100026	19980211	00026	SO  	1998	2	11	98ZZZX503        	2	19980130	G	8530	652956	VALVE           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					CYL 1-2-6	WORN            	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	297DB	101  				421C0826	60446			CYLINDERS REMOVED FROM THE ENGINE DUE TO INCREASED OIL CONSUMPTION REPORTS.  UPON REMOVAL, AN EXCESSIVE AMOUNT OF ROCKER	 ARM TO VALVE CLEARANCE WAS NOTICED ON THE NR 1, NR 2, AND NR 6 CYLINDERS.  CLOSER EXAMINATION REVEALED TIPS OF THE EXHA	UST VALVES HAD EXTREME WEAR.  WHEN COMPARED TO A NEW VALVE, WEAR AS MUCH AS .081 INCH ON ONE OF THE TIPS AND APPROXIMATE	LY .090 INCH AND .095 INCH ON THE OTHER TWO VALVES.  CONSTRUCTION OF THE VALVES INVOLVES A PROCESS WHERE A HARDENED TIP 	IS FRICTION WELDED TO THE VALVE STEM.  SUBMITTER BELIEVES THE HARDENED TIP SEPARATED FROM THE VALVE STEM DURING SERVICE.		1	L	7	2 	3O	3	O		A7CE    	E7CE
1998021100027	19980211	00027	SO  	1998	2	11	98ZZZX504        	2	19980130	G	8530	654654	CYLINDER        								CONT  	O520  	GTSIO520L   	17032	SO  					NR 2	CRACKED         	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19							245870R			FACTORY NEW CYLINDER WITH MANUFACTURE DATE OF 12-1997 WAS REMOVED FROM THE NR 2 POSITION DUE TO OIL LEAKS.  DURING DISAS	SEMBLY OF THE EXHAUST VALVE AND VALVE SPRING ASSEMBLY, A CRACK WAS NOTED BEWEEN THE 1ST AND 2ND FIN.  CLOSER INSPECTION 	REVEALED THE FINS WERE MACHINED TOO DEEP INTO THE CYLINDER HEAD.  SUGGEST A THOROUGH INSPECTION OF THE INTAKE AND EXHAUS	T FIN AREA BE PERFORMED BEFORE CYLINDER ASSEMBLY.  PART T .25 HOUR.								3	O			E7CE
1998021100028	19980211	00028	SO  	1998	2	11	98ZZZX505        	2	19980130	G	8530	65345	CYLINDER        			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					BARREL JOINT	SEPARATION      	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	36989		160  			414A0503	519870			CYLINDER REMOVED DUE TO HEAD SEPARATION FROM THE CLYINDER BARREL.  SUBMITTER NOTES THE CYLINDER WAS RE-MANUFACTURED IN J	ANUARY, 1994 (HEAD STAMP 1-94 AND THE OEM NUMBER IS OF A LATER DESIGN THAN CLYINDER P/N DESCRIBED IN SB M86-7 AND AD 86-	13-04R3 RELATING TO CERTAIN OEM CYLINDERS).  SUBMITTER NOTES CYLINDER WALLS HAD BEEN RECONDITIONED BY CHROME-PLATING AND	 NEW HEAD PARTS HAD BEEN INSTALLED AT THIS TIME OF RECONDITIONING.  SUBMITTER SUGGESTS POSSIBILITY OF AN UNDETECTED CYLI	NDER HEAD CRACK BETWEEN CYLINDER FINS PROGRESSED TO SEPARATION AFTER PROLONGED HEAT AND CYCLE.		1	L	7	2 	3O	3	O		A7CE    	E8CE
1998021100029	19980211	00029	GL  	1998	2	11	98ZZZX506        	2	19980119	G	7412	49522	EXCITER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE IGNITER	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J				16401	900801D				IGNITION EXCITER HAD INTERNAL FAILURE, WOULD NOT EXCITE.  SENT FOR REPAIR.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998021100030	19980211	00030	SW  	1998	2	11	98ZZZX507        	1	19980119	G	7712	206075185001	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										TORQUE	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY				2143	2871				TORQUE INDICATOR GIVES HIGHER TORQUE THAN TESTED.						1	G	7	1 	3U				H2SW
1998021100034	19980211	00034	GL  	1998	2	11	98ZZZX511        	3	19980112	G	6114	C6447C23	HUB             			BEECH 	35    	S35         	1151532	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER	MISDRILLED      	B			EX2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	8835M				778466	D7353		778466		OIL FILLER HOLE ON SIDE OF HUB DRILLED IN WRONG LOCATION.  REF:  MCCAULEY SL1989-5 AND SL1995-14A.						1	L	7	1 	3O				3A15    		5	C	P880
1998021100035	19980211	00035	CE  	1998	2	11	98ZZZX512        	1	19980123	G	2720	086170040	RUDDER PEDAL    			CESSNA	310   	310R        	2074245	CE  										PILOT LT	FAILED          	D		A		K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	05	98904					310R1240				AFTER STARTING ENGINES TO REPOSITION AIRCRAFT, PILOT PUSHED ON LEFT RUDDER PEDAL AND PEDAL BROKE OFF AT BASE WHERE IT IS	 WELDED TO PEDAL ARM ASSY.  AIRCRAFT TOTAL TIME 5,980 HOURS.  PART MAY HAVE BEEN ORIGINAL.  ANNUAL INSPECTION, 6 MONTHS 	PRIOR.  HAVE HEARD OF SAME PROBLEM WITH SIMILAR AIRCRAFT.  SUBMITTER SUGGESTED MORE FREQUENT AND CLOSER INSPECTIONS.				1	L	7	2 	3O				3A10
1998021100036	19980211	00036	CE  	1998	2	11	98ZZZX513        	1	19980120	G	2460	AT30	FUSE CONNECTOR  		MC012       	CESSNA	172   	172R        	2072401	CE  										POWER JUNCT BOX	FAILED          	B	S		WIWR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07	97100	250  				17280100				FOUND COLD SOLDER AT FUSE CONNECTION FOR NR 1 BUS.  WIRE PULLED OUT AFTER TROUBLESHOOTING DEFECTIVE BUS, COLD WIRE WAS N	OT INSTALLED IN RETAINING HOLE, BUT LAID ON TOP AND IMPROPERLY SOLDERED AND COVERED WITH HEAT SHRINK.					1	H	7	1 	3O			NT	3A12
1998021100037	19980211	00037	CE  	1998	2	11	98ZZZX514        	1	19980124	G	7603	S122217	CONTROL CABLE   			CESSNA	150   	150M        	2071830	CE  										THROTTLE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	704AC	2306 				15078450				THROTTLE CABLE PLASTIC OUTER COVER MADE OF PLASTIC BECAME BRITTLE FROM AGE AND HEAT AND FAILED. THE WHOLE ASSEMBLY WAS M	OVING WITH POWER CHANGES.  SUBMITTER STATED THESE ORIGINAL CESSNA SUPPLIED CABLES ARE ALL REACHING THEIR SERVICE LIFE ON	 PLASTIC DETERIORATION.  SUBMITTER HAS NOTICED THIS ON MODEL 172 AND MODEL 150 AIRCRAFT.				1	H	7	1 	3O			 	3A19
1998021100038	19980211	00038	CE  	1998	2	11	98ZZZX515        	1	19980120	G	3213	22411001	FITTING         			CESSNA	172   	172RG       	2072438	CE  										MLG LEG	CRACKED         	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	5510R	6312 				172RG0066				MLG LEG FITTING FOUND CRACKED.  SUBMITTER STATES POSSIBLE CAUSE AS HARD LANDINGS.						1	H	7	1 	3O				3A17
1998021100039	19980211	00039	GL  	1998	2	11	98ZZZX516        	3	19980120	G	6114	D6468C9	HUB             			BEECH 	23    	A24R        	1151252	CE  						MCAULY	2D34C	2D34C9      	GL  	THREADS	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	8015R					MC54		702196		A CRACK WAS FOUND IN THE THREADS OF HUB RENDERING IT UNAIRWORTHY PER AD 91-15-04.  THE DEFECT POSSIBLY COULD HAVE BEEN F	OUND AT AN EARLIER DATE IF COMPLIANCE TIME OF THE AD HAD BEEN ADHERED TO.					1	L	7	1 	3O				A1CE    		5	C	P7EA
1998021100040	19980211	00040	GL  	1998	2	11	98ZZZX517        	3	19980120	G	6111	S78FBM15	BLADE           			BEECH 	23    	A24R        	1151252	CE  						MCAULY	2D34C	2D34C9      	GL  	THREADS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	8015R				K854451YS	MC54		702196		CORROSION WAS FOUND BELOW TTE PITCH LINES OF THE BLADE THREADS CAUSING THE BLADE TO BE UNAIRWORTHY PER MCCAULEY SM NR 72	0415.  SUBMITTER STATED ADHERING TO COMPLIANCE TIMES OF AD 91-15-04 MAY HAVE PREVENTED THIS CONDITION.					1	L	7	1 	3O				A1CE    		5	C	P7EA
1998021100041	19980211	00041	GL  	1998	2	11	98ZZZX518        	3	19980120	G	6111	S78FBM15	BLADE           			BEECH 	23    	A24R        	1151252	CE  						MCAULY	2D34C	2D34C9      	GL  	THREADS	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	8015R				K85459YS	MC54		702196		CORROSION FOUND BELOW THE PTICH LINE IN THE THREADS CAUSING THE BLADE TO BE UNAIRWORTHY PER MCAULEY SM NR 720415.  SUBMI	TTER STATED ADHERING TO PROPER COMPLIANCE TIMES OF AD 91-15-04 MAY HAVE PREVENTED THIS.					1	L	7	1 	3O				A1CE    		5	C	P7EA
1998021100044	19980211	00044	CE  	1998	2	11	98ZZZX521        	1	19980121	G	2810		DRAIN VALVE     			CESSNA	182   	R182        	2072734	CE  										LT WING FUEL	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	1691R					R18200516				LEFT WING FUEL SAMPLE DRAIN VALVE DRIPPING AND THEN REMAINING OPEN.  UPON DISMANTLE, THE O-RING WAS FOUND BROKEN IN 3 PL	ACES AND SEPARATED INTO 2 PIECES.  THE BROKEN O-RING PIECES LODGED IN THE FORWARD FLOW HOLES AND KEPT THE VALVE STEM OPE	N.  UPON MEASUREMENT OF THE VALVE STEM DIAMETER AT THE O-RING POSITION, THE DIAMETER WAS .028 INCH LARGER THAN A VALVE S	TEM REMOVED EARLIER.			1	H	7	1 	3O			RT	3A13
1998021100046	19980211	00046	EA  	1998	2	11	98ZZZX523        	2	19980120	G	8520	LW15861	LIFTER          			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 4 CYL EXHAUST	SPALLED         	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6805L	74   				31P7	RL64562			NR 4 CYLINDER EXHAUST LIFTER SPALLED SEVERELY CAUSING DAMAGE TO THE CAMSHAFT LOBE.  ALL OTHER LIFTERS LOOKED GOOD.  ENGI	NE WAS FACTORY OVERHAULED 7/97.  FOUND METAL IN SCREEN AND FILTER LEADING TO INVESTIGATION WHICH TURNED UP THIS PROBLEM.					1	L	7	2 	3O	3	O		A8EA    	E19EA
1998021100047	19980211	00047	GL  	1998	2	11	98ZZZX524        	3	19980112	G	6114	C6447C23	HUB             			BEECH 	35    	B35         	1151506	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER	MISDRILLED      	B			EK2R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17					768383			768383		OIL FILLER HOLE ON SIDE OF PROPELLER HUB DRILLED IN WRONG LOCATION.  REF:  MCCAULEY SL 1989-5 AND SL 1995-14A.						1	L	7	1 	3O				A777    		5	C	P880
1998021100048	19980211	00048	SO  	1998	2	11	98ZZZX525        	1	19980120	G	3231	1122	ACTUATOR        			PIPER 	PA46  	PA46350P    		SO  										NLG DOOR	LEAKING         	B			RF1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	01	666AS	200  			459	4622186				FOUND NOSE GEAR DOOR ACTUATOR LEAKING INTERNALLY THROUGH AIR ORIFICE.  OVERHAUL KIT NO LONGER AVAILABLE.  REPLACED UNIT 	WITH NEW UNIT FROM PIPER.					1	L	7	1 	3O			RT	A25SO
1998021100050	19980211	00050	CE  	1998	2	11	98ZZZX527        	1	19980113	G	7603	628371	SPRING          			BEECH 	36    	A36         	1151604	CE  										THROTTLE LINK	BROKEN          	B			HUNR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	1066T	292  				E2996				FUEL CONTROL/THROTTLE LINKAGE SPRING BROKEN.  LOW HOURS SINCE NEW.						1	L	7	1 	3O				3A15
1998021100051	19980211	00051	EA  	1998	2	11	98ZZZX528        	2	19980123	G	7414	1059474	IMPULSE COUPLING	BENDIX      	S4LN21      	CESSNA	175   	175A        	2072504	CE  	LYC   	O360  	O360A1A     	41514	EA  					LT MAGNETO	WORN            	B			NG2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	6913E	9    			A129537DR	56413	L571536			PILOT FOUND 250 RPM MAG DROP, LT MAG.  TROUBLESHOT IGNITION SYSTEM.  REMOVED MAG AND FOUND EXCESS PLAY IN IMPULSE COUPLI	NG AND MAG DRIVE.  SENT OUT FOR REPAIR, SPRING WAS BROKEN.  SUSPECT IMPROPER INSTALLATION OR DEFECTIVE METALLURGY PRIOR 	TO INSTALLATION.				1	H	7	1 	3O	3	O		3A17    	E286
1998021100052	19980211	00052	CE  	1998	2	11	98ZZZX529        	1	19980119	G	3221	07436062	FITTING         			CESSNA	182   	182P        	2075816	CE  										NLG ATTACH	CRACKED         	B	S	A	VH3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	7285Q					18260256				FOUND THE LOWER NOSE GEAR FITTING CRACKED AT THE COLLAR.  NOSE GEAR COLLAR WAS SEPARATED FROM THE ATTACH FITTING.  ONLY 	THE UPPER ATTACH FITTING WAS HOLDING THE NOSE GEAR TO THE AIRFRAME.  AFTER THE LOWER ATTACH FITTING WAS REMOVED, A CRACK	 WAS FOUND HALF-WAY ACROSS THE LT REAR ATTACHMENT EAR.  CAUSE OF DEFECT UNKNOWN.				1	H	7	1 	3O			NT	TA13
1998021100053	19980211	00053	CE  	1998	2	11	98ZZZX530        	1	19980120	G	5741	10140261S	BOLT KIT        			BEECH 	200   	A200        	1152921	CE  										WING ATTACH	WRONG PARTS     	B		A	UJJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	01	2MIL					BC15				THE BOLT KIT LISTED IS FOR THE UPPER AND LOWER AFT WING ATTACH FITTINGS FOR A BEECH SERIES 200,  UPON RECEIVING 4 OF THE	SE KITS, NOTICED THE WASHERS INCLUDED IN THE KIT DID NOT HAVE A SMOOTH CONTINUOUS OUTER RADIUS WHICH IS NOTED IN BEECH 2	00 SRM CH 57-17-01 PAGE 212, FIG 207.  SMOOTH OUTER RADIUS IS TO GO AGAINST 'BATHTUB' FITTING SO AS NOT TO SET UP STRESS	.  COULD NOT USE THESE WASHERS AND HAD TO ORDER MORE.  SUBMITTER SUGGESTED BETTER QC ON RAYTHEONS PART COULD PREVENT DEL	AYS SUCH AS THIS.		1	L	7	2 	4T				A24CE
1998021100054	19980211	00054	CE  	1998	2	11	98ZZZX531        	1	19980119	G	5741	10140251S	BOLT KIT        			BEECH 	200   	A200        	1152921	CE  										WING ATTACH	WRONG PARTS     	B			UJJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	01	2MIL					BC15				THE BOLT KIT LISTED IS FOR THE UPPER FORWARD WING BOLTS FOR A BEECH 200.  UPON RECEIVING 2 EACH KITS, NOTED THE WASHERS 	INCLUDED WERE NOT PROPERLY RADIUSED ON THE OUTER EDGE.  THE BEECH 200 SRM CH 57-17-01 P 212 SPECIFICALLY INSTRUCTS TO IN	STALL SMOOTH CONTINUOUS OUTER RADIUS TOWARD 'BATHTUB' FITTING. WASHERS WITH KITS WERE FLAT, AND COULD CAUSE STRESS IF IN	STALLED.  SUBMITTER SUGGESTED BETTER QUALITY CONTROL ON RAYTHEON'S PART MIGHT PREVENT DELAYS AND PROBLEMS LIKE THIS (NOT	E:  REPLACEMENT WASHERS SENT HAD SAME PROBLEM).		1	L	7	2 	4T				A24CE
1998021100056	19980211	00056	EA  	1998	2	11	98ZZZX533        	1	19980122	G	3010	725818	SENSOR          			CNDAIR	CL600 	CL6001A11   	1900302	EA  										WING ANTI-ICE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	19HF	6200 				1081				LEFT AND RIGHT WING ANTI-ICE FAIL LIGHTS CAME ON INTERMITTENTLY ANY TIME WING ANTI-ICE SYSTEM SELECTED.  FOUND THE LEFT 	AND RIGHT WING TEMP SENSORS INSTALLED BACKWARDS FROM THE FACTORY.   INSTALLED NEW SENSORS PER MM.  SYSTEM WORKED NORMALL	Y ON NEXT FLIGHT.				2	L	7	2 	4F			RT	A21EA
1998021100058	19980211	00058	EU  	1998	2	11	98ZZZX535        	2	19980126	G	7210	GD203	DRIVESHAFT      			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					GEARBOX	LOOSE           	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09	2NA		34   			096				THE BOLT SECURING THE FORWARD U-JOINT ONTO THE DRIVESHAFT HAD BACKED ALL THE WAY OUT.  THE BOLT SECURING THE AFT U-JOINT	 TO THE DRIVESHAFT WAS LOOSE EVEN WITH THE LOCKING TAB WASHER INSTALLED.  UPON INVESTIGATION, IT APPEARED THE WRONG LOCK	ING TAB WAS USED DURING OVERHAUL.				2	L	7	2 	4T	4	T		1A17    	E297
1998021100059	19980211	00059	NM  	1998	2	11	98ZZZX536        	1	19980111	G	3244		TIRE            			BOEING	747   	747346      		NM  										RT WING RT FWD	FAILED          	B			JACZ	A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			WP	03	213JL					23068				AIR TURN BACK OF THE FLIGHT ON 1-11-98, BECAUSE THE CONTROL TOWER REPORTED TIRE PIECES ON RUNWAY AFTER TAKEOFF.  ALSO, C	REW FELT SOME SHOCK DURING TAKEOFF.  FOUND RT WING RIGHT FWD TIRE BURST.  CHANGED RT WING RT FWD TIRE AND LT FWD TIRE. A	LSO, FOUND DAMAGE ON RT WING GEAR STRUT DOOR AND NR 6 FLAP MOVEABLE FAIRING AFT SEGMENT.  REMOVED STRUT DOOR AND CANOE T	AIL CONE BY CDL 27-51-3 AND 32-12-1, RESPECTIVELY, AND FERRIED FOR REPAIR.  ALL NECESSARY REPAIRS COMPLETED.			2	L	7	4 	4F			RT	A20WE
1998021100061	19980211	00061	CE  	1998	2	11	98ZZZX538        	1	19980118	G	5741	80691CF1612	BARREL NUT      			BEECH 	200   	A200        	1152921	CE  										WING ATTACH	WRONG PART      	B			UJJR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	01	2MIL					BC15				KIT 101-4024-1S CONTAINS THE FORWARD LOWER WING BOLT, PL WASHER AND BARREL NUT FOR INSTALLATION ON BEECH 200 SERIES ARIC	RAFT.  THE BARREL NUT ASSY PN 80691CF-1612 WAS OF IMPROPER TOLERANCES AND WOULD NOT FIT IN WING 'BATHTUB' FITTING.  FURT	HER INVESTIGATION REVEALED THE LOCKING NUT PORTION WAS INSTALLED IN ASSY SIDEWAYS SO THAT THE OBLONG SHAPE OF NUT WAS CR	OSS WAYS GIVING THE OVERALL DIMENSIONS MORE WIDTH.  SUBMITTER STATED HAVE RECEIVED 2 KITS WITH SAME DISCREPANCY.			1	L	7	2 	4T				A24CE
1998021100065	19980211	00065	SO  	1998	2	11	98ZZZX542        	1	19980115	G	2150	22005402	AIR CYC MACHINE 	AIRESRCH    		EMB   	120   	EMB120RT    		SO  										CABIN AIR	FAILED          	D				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	2FOR		357  							AIR CYCLE MACHINE FAILED TO COOL DUE TO OIL CONTAMINATION IN BLEED AIR CIRCUIT.  ULTIMATELY, THE OIL CONTAMINATION CAUSE	D EXCESS FRICTION IN ROTATING GROUP CAUSING UNIT TO FAIL.					2	L	7	2 	4T			RT	A31SO
1998021100066	19980211	00066	CE  	1998	2	11	98ZZZX543        	1	19980202	G	5711	55221119	CAP STRAP       			CESSNA	500   	500CESSNA   	2076602	CE  										LT WING SPAR	CORRODED        	B			SI6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	293S	6518 				5000193				DURING THE PROCESS OF A NON-SCHEDULED INSPECTION, THE LEFT WING UPPER SPAR CAP STRAP WAS FOUND CORRODED AROUND THE EDGES	.  FURTHER, NDT INSPECTION REVEALED CORROSION BETWEEN THE STRAP AND THE DOUBLER.  CAUSE OF THE CORROSION COULD HAVE BEEN	 IMPROPER SEALING AROUND THE PERIPHERY OF THE STRAP.  SB 500-57-13 WAS PERFORMED TO REPLACE THE STRAP.				1	L	7	2 	4F				A22CE
1998021100068	19980211	00068		1998	2	11	98ZZZX545        	4	19980117	G	3440	560011830	LINE            			CESSNA	310   	310R        	2074245	CE  										ANTI ICE	CRACKED         	H	S			K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	11	6204X	2547 				310R1336				ALCOHOL WINDSHIELD ANTI-ICE LINE COMING OUT OF PUMP CRACKED AT 90 DEGREE BEND ON INSIDE RADIUS.						1	L	7	2 	3O				3A10
1998021100069	19980211	00069	CE  	1998	2	11	98ZZZX546        	1	19980115	G	3222	12434262	TORQUE LINK     			CESSNA	210   	P210N       	2073454	CE  										NLG	FAILED          	H	S	A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			WP	25	323DC	3615 				P21000365				WHILE TAXIING BACK AFTER LANDING ON GRASS STRIP, NOSE WHEEL GAVE SLIGHT SHIMMY AND AIRCRAFT VEERED TO A STOP.  UPPER TOR	QUE LINK WAS BROKEN IN HALF MIDWAY BETWEEN BOLT HOLES.  NO SIGNS OF PRIOR CRACKING.					1	H	7	1 	3O				3A21
1998021100070	19980211	00070		1998	2	11	98ZZZX547        	4	19980122	G	6113	E6178	BULKHEAD        			CESSNA	414   	414A        	2075907	CE  										SPINNER	CRACKED         	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	414VA					414A0442				SPINNER BULKHEAD INSTALLED FOR STC SA7633SW LIQUID COOLED ENGINE INSTALLATION WITH PROPELLER MODEL 3AF365C514-C/G-80VMFA	-2 FOUND CRACKED NUMEROUS TIMES ON OTHER AIRCRAFT WITH SAME MODIFICATION.  APPEARS THE MACHINING OF METAL FOR BULKHEAD M	ATERIAL IS ROUGH CAUSING STRESS AROUND HOLES.				1	L	7	2 	3O				A7CE
1998021100071	19980211	00071	SO  	1998	2	11	98ZZZX548        	2	19980122	G	8530	252501FCC	PISTON RING     								CONT  	O520  	TSIO520NB   	17040	SO  					CYLINDER	MISMARKED       	B		A	VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19										ENGINE COMPONENTS INC., PISTON RING FOR VARIOUS TSIO-520 ENGINE WITH CHROME CYLINDERS.  TOP COMPRESSION PISTON RING P/N 	252501F-CC HAS BEEN FOUND STAMPED WRONG ON AT LEAST A HALF DOZEN RINGS IN THE LAST 6 MONTHS.  IF RING INSTALLED AS MARKE	D, WHICH IS DIFFICULT BUT POSSIBLE, SINCE NORMAL PROCEDURE IS TO INSTALL AS MARKED AND MECHANIC DOES NOT SEE TAPER RING 	LAND TO MATCH RING, THE INSTALLATION WILL FIT EXTREMELY TIGHT AND BREAK AFTER A FEW HOURS.								3	O			E8CE
1998021100074	19980211	00074	CE  	1998	2	11	98ZZZX551        	1	19980119	G	6120	5038901023	CONTROL CABLE   			BEECH 	58    	58          	1152740	CE  										PROP CONTROL	FAILED          	B	S		KZ5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	70DD	200  				TH370				PROPELLER CONTROL CABLE BROKE AT ENGINE END AT THE POINT WHICH THREADED END IS CRIMPED ON TO CABLE END.						1	L	7	2 	3O			 	3A16
1998021100076	19980211	00076	CE  	1998	2	11	98ZZZX553        	1	19980112	G	2434	DOFF10300J	ALTERNATOR      	FORD        		CESSNA	172   	172M        	2072418	CE  										BRUSH	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	73671	342  			6102006	17267605				ALTERNATOR WAS OVERHAULED BY ELECTROSYSTEMS, INC.  AFTER FAILURE, UNIT WAS OPENED AND ONE BRUSH WAS FOUND WORN COMPLETEL	Y DOWN TO WIRE INSERT.  SLIP RING WAS GROOVED DUE TO CONTACT WITH INSERT.  ALTERNATOR HAD ONLY 341.8 HOURS SINCE OVERHAU	L AND ONLY 8 MONTHS.  SECOND BRUSH WAS IN GOOD SHAPE. THERE WERE NO SIGNS OF BRUSH BEING IMPROPERLY INSTALLED OR DAMAGED	, JUST WORE EXTREMELY QUICK.  SUSPECT COMPOSITION OF BRUSH MATERIAL WAS NOT CORRECT.			1	H	7	1 	3O			NT	3A12
1998021100078	19980211	00078	CE  	1998	2	11	98ZZZX555        	1	19980108	G	5520	123262226	CHANNEL         			CESSNA	210   	210         	2073402	CE  										ELEVATOR	CRACKED         	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	15	2306D	3303 				21063828				ELEVATOR CHANNEL HAS 7 LOCATIONS WHERE BUCKING BAR SLIPPED OFF OF RIVET TAIL AND INDENTED STRUCTURE.  CRACKS HAVE FORMED	 AT ALL 7 LOCATIONS.  THIS DEFECT IS ORIGINAL FROM FACTORY.  SUBMITTER STATED THIS IS THE 2ND PART WITH THE SAME DEFECT 	FOUND.				1	H	7	1 	3O			RT	3A21
1998021100079	19980211	00079	CE  	1998	2	11	98ZZZX556        	1	19980109	G	5730		SKIN            			CESSNA	402   	402B        	207590P	CE  										LT/RT WS 57.5	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	400AR	7929 				402B0338				CRACK IN UPPER WING SKIN ABOVE GEAR SUPPORT FOUND DURING 100-HOUR INSPECTION.  SUBMITTER STATED POSSIBLY CAUSED BY A HAR	D LANDING.					1	L	7	2 	3O				A7CE
1998021100081	19980211	00081	CE  	1998	2	11	98ZZZX558        	1	19980115	G	3222	674200605	STRUT           			CESSNA	750   	750         	2076810	CE  										NLG	FROZEN          	G		A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			GL	15	944H	638  	342  			7500011				OPERATOR REPORTED UPON DEPARTURE, ACFT GEAR HANDLE COULD NOT BE PUT UP TO RETRACT GEAR.  ACFT RETURNED AND LANDED SAFELY	.  OUTSIDE AIR TEMPERATURE WAS BELOW ZERO AT DEPARTURE TIME.  WHEN THE ACFT WAS JACKED UP, THE NOSE GEAR STRUT FAILED TO	 EXTEND ALL THE WAY  AFTER 2 HOURS IN A WARM HANGAR, STRUT EXTENDED FULLY ON ITS OWN.  WHEN THE STRUT WAS DISASSEMBLED, 	MECHANICS FOUND ALMOST 2 TABLESPOONS OF WATER TRAPPED IN THE LOWER BARREL BEARING AREA.  THIS SUGGESTED THE WATER FROZE 	INTERRUPTING FULL EXTENSION OF THE STRUT, CESSNA RECOMMENDED SB 750-32-10 BE COMPLETED WHICH INCORPORATES A THREE-PIECE 	LOWER BEARING ASSEMBLY.	2	L	7	2 	4J			RT	T00007WI
1998021100084	19980211	00084	NM  	1998	2	11	98ZZZX561        	1	19980102	G	2740	69778551	SPRING          		654997025   	BOEING	737   	737*        		NM  										STAB TRIM GRBOX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		13748								INSPECTION FOUND STABILIZER TRIM GEARBOX WITH FRACTURED SPRINGS.  SUSPECT IMPROPER HEAT TREATING OR INCORRECT ALLOYS IN 	THE SPRINGS.  SUBMITTER RECOMMENDATIONS:  SPRINGS PN 69-77855-1 SHOULD BE REPLACED WITH PN 69-77855-2 SPRINGS PER BOEING	 TELEX AEO-AUB-94-0195RR.				2	L	7	2 	4F			RT	A16WE
1998021100128	19980211	00128	CE  	1998	2	11	98ZZZX605        	1	19980121	G	5620		WINDOW          			MTSBSI	MU2   	MU2B60      	5780460	CE  										RT FWD CABIN	CRACKED         	B			IZ2R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	15	44MM	8386 			2530	1526SA				DURING CLIMB, AIRCRAFT SLOWLY LOST PRESSURIZATION.  A PASSENGER NOTICED NR 1 RIGHT CABIN WINDOW CRACKED.  AN EMERGENCY W	AS DECLARED AND A LANDING WAS MADE WITHOUT INCIDENT.  DAMAGE FROM WINDOW WAS FOUND ON RIGHT PROPELLER AND RIGHT HORIZONT	AL STABILIZER.  RIGHT PROPELLER SENT TO PROP REPAIR STATION.  RIGHT ENGINE INSPECTED PER ALLIED SIGNAL MM.				1	H	7	2 	3T			RT	A10SW
1998021100129	19980211	00129	NM  	1998	2	11	98ZZZX606        	1	19980121	G	8012	39223411	START VALVE     			BOEING	727   	72761       	1384017	NM  										NR 3 ENGINE	FAILED          	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			SW	99	530KF				P558	19176				1-21-98 AT 0830 HOURS.  AIRCRAFT WAS ON DEPARTURE CLIMBING THROUGH 5,000 FEET AGL WHEN CREW NOTICED NR 3 START VALVE LIG	HT ON.  PILOT DECLARED AN EMERGENCY AND LANDED AIRCRAFT.  MAINTENANCE PERFORMED INSPECTION AND REPLACED NR 3 ENGINE STAR	T VALVE AND PRESSURE SWITCH.  AIRCRAFT RETURNED TO SERVICE AND COMPLETED FLIGHT WITH NO FURTHER INCIDENTS.				2	L	7	3 	4F				A3WE
1998021100130	19980211	00130	SO  	1998	2	11	98ZZZX607        	1	19980116	G	2460	K15	RELAY           			GULSTM	G1159 	G1159A      	3970109	SO  										POWER DIST BOX	FAILED          	D				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			SO	09	843HS		6    			496				DURING CRUISE FLIGHT, THE POWER DISTRIBUTION BOX (PDB) SWITCHED FROM NORMAL-AUTO MODE TO ESSENTIAL BUSS-ON BATTERY-MODE 	WITHOUT NOTICEABLE INDICATION TO THE CREW.  THIS CONDITION RESULTED IN A NEAR-TOTAL ELECTRICAL FAILURE CONDITION CAUSING	 A LOSS OF NAV, COMM, AND TRANSPONDER OPERATION.  AIRCRAFT EN ROUTE FROM MCO TO BHM.  THE CREW SWITCHED TRANSPONDERS TO 	CODE 7700 AS POWER WAS FAILING AND DIVERTED TO  MGM FOR EMERGENCY LANDING USING EMERGENCY BATTERIES FOR NAVIGATION AND M	AGNA STAR PHONE TO COMMUNICATE WITH ATC.  ACFT LANDED AT MGM WITHOUT FURTHER INCIDENT.  SUSPECT K15 RELAY INSIDE THE PDB	 FAILED. COMPONENT P/N 1159SCAV373801	2	L	7	2 	4F				A12EA
1998021100131	19980211	00131	CE  	1998	2	11	98ZZZX608        	1	19980123	G	5522	96610063	SKIN            			BEECH 	55    	D55         	1152730	CE  										LT ELEVATOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	700R					TE633				DURING RAMP INSPECTION, FOUND CRACK IN TOP SKIN JUST OUTBOARD OF OUTBOARD HINGE POINT.  CRACK ALIGNED WITH CRACK IN SKIN	 P/N 96-61006-49.  SUB-SURFACE STRUCTURE SHOWED NO DAMAGE, BUT CRACKED PAINT IN BALANCE WEIGHT ATTACH AREA INDICATES PRE	VIOUS STRESS.  AIRCRAFT TT 4,524 HOURS.				1	L	7	2 	3O				3A16
1998021100132	19980211	00132	CE  	1998	2	11	98ZZZX609        	1	19980123	G	5522	9661000649	SKIN            			BEECH 	55    	D55         	1152730	CE  										LT ELEVATOR	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	7700R					TE633				DURING RAMP INSPECTION, FOUND CRACK IN TOP SKIN JUST OUTBOARD OF OUTBOARD HINGE POINT.  CRACK ALIGNED WITH CRACK IN SKIN	 P/N 96-610006-3.  SUB-SURFACE STRUCTURE SHOWED NO DAMAGE, BUT CRACKED PAINT IN BALANCE WEIGHT ATTACH AREA INDICATES PRE	VIOUS STRESS.  AIRCRAFT TOTAL TIME, 4,524 HOURS.				1	L	7	2 	3O				3A16
1998021100137	19980211	00137	CE  	1998	2	11	98ZZZX614        	1	19980127	G	2430	A876P	RELAY           			CESSNA	500   	550         	2076604	CE  										BAT DISCONNECT	INTERMITTENT    	B			B3OR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2531K				CE40505	5500594				UPON REMOVAL OF THIS RELAY FOR REPLACEMENT, LOOSE HARDWARE WAS HEARD RATTLING AROUND INSIDE.  SUBMITTER STATED THIS IS A	 CONTINUING PROBLEM WITH THIS TYPE AND PART NUMBER RELAY AND HAS BEEN FOUND ON SEVERAL OTHER OCCASIONS.  THE RELAY WOULD	 NOT HAVE FAILED HAD IT NOT BEEN FOR THE LOOSE HARDWARE INSIDE.  THIS RELAY IS THE BATTERY DISCONNECT RELAY AND HANDLES 	LARGE AMOUNTS OF CURRENT (200 AMPS).  WHEN THE RELAY FAILS, IT ALLOWS THE AIRCRAFT BATTERY TO BE DISCHARGED THROUGH THE 	APU!		1	L	7	2 	4F				A22CE
1998021100140	19980211	00140	NE  	1998	2	11	98ZZZX617        	2	19980114	G	7250	31189901	BLADE           								PWA   	PT6   	PT6A67D     		NE  					GAS GENERATOR	DEFECTIVE       	B			MASR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	01										D.T.S. RECEIVED ONE SET OF COMPRESSOR TURBINE BLADES (43 EACH) UNDER SALES ORDER 8891, CUSTOMER ORDER NR S15045.  EXAMIN	ING THE BLADES REVEALED A SURFACE DEFECT ON THE PARENT METALS OF 17 EACH BLADES THAT EXCEEDS THE OVERHAUL LIMITS OF 0.00	3 INCH.  REF:  CHAPTER 72-50-00 PAGE 305B(2)(A) OF OVERHAUL MANUAL 3038337.  THE COMPLETE SET OF BLADES HAVE BEEN RETURN	ED TO VENDOR.								4	T			E26NE
1998021100144	19980211	00144		1998	2	11	98ZZZX621        	4	19980122	G	6113	35323012	BULKHEAD        			PIPER 	PA28  	PA28151     	7102805	SO  										PROP SPINNER	CRACKED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	808RK	605  				287415225				DURING ANNUAL INSPECTION, BOTH SPINNER BULKHEADS FOUND CRACKED.  FORWARD BULKHEAD SEVERELY CRACKED.  CRACKS EMANATED FRO	M BALANCE WEIGHT INSTALLED BY PERSONS UNKNOWN.  COUNTERWEIGHT SHOULD BE MOUNTED TO STARTER RING OR AFT BULKHEAD WHEN POS	SIBLE.  REPLACED BULKHEAD WITH NEW PART.				1	L	7	1 	3O				2A13
1998021100145	19980211	00145	GL  	1998	2	11	98ZZZX622        	3	19980126	G	6111	A47102	COUNTERWEIGHT   		S78FF0      											MCAULY	2A34C	D2AF34C30   	GL  	PROPELLER	FAILED          	B		A	ME4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19					AS567			701837		PROPELLER ASSY COUNTERWEIGHT FAILURE.  COUNTERWEIGHT WAS FLUNG FROM BLADE NR 1 AND HIT BLADE NR 2 DESTROYING BLADE.																5	C	P5EA
1998021100477	19980211	00477	NE  	1998	2	11	98ZZZX625        	2	19980128	G	7313	782299	NOZZLE          								PWA   	JT8   	JT8D9A      	52048	NE  					NR 9	FRACTURED       	B			ANZZ	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	03					PW6665		666868			FUEL NOZZLE FRACTURED DUE TO INCORRECT PART FITTED.  THIS CAUSED DIRECT FLAME TO CONTACT THE BASE OF THE FUEL NOZZLE AND	 THE DIFFUSER CASING.  THE DIFFUSER CASING WAS STARTING TO DEFORM AND OXIDIZE.  POTENTIAL FOR SERIOUS CASE BURN-THROUGH 	AND DUCT FIRE.  CUSTOMER AND FUEL NOZZLE REPAIR STATION HAVE BEEN NOTIFED.									4	F			E2EA
1998021100488	19980211	00488	NM  	1998	2	11	98ZZZX636        	1	19980129	G	3231	400088002	BELLCRANK       			PIPER 	PA60  	PA60602P    	7106015	NM  										RT GEAR DOOR	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	6899L					608365011				PILOT NOTICED THE GEAR REQUIRED CYCLING TWICE BEFORE THE UP AND LOCKED LIGHT WOULD ILLUMINATE.  INSPECTION AFTER LANDING	 FOUND BELCRANK THAT ATTACHES TO INBOARD DOOR LOWER PUSH/PULL TUBE WAS CRACKED ALLOWING DOOR TO FALL OPEN.					1	M	7	2 	3O			RT	A17WE
1998021100490	19980211	00490	CE  	1998	2	11	98ZZZX638        	1	19980113	G	3340		LIGHTS          			BEECH 	23    	C24R        	1151254	CE  										WING BONDING	NOT GROUNDED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	24017					MC478				TT:  2,065.43 HOURS.  THE PILOT REPORTED THAT TURNING ON THE LANDING LIGHTS, NAV LIGHTS, OR PITOT HEAT CAUSED BOTH FUEL 	GAUGES TO PEG ON FULL.  INVESTIGATION DETERMINED THE WING ASSEMBLIES WERE NOT WELL GROUNDED TO THE FUSELAGE.  GROUND WIR	ES WERE ADDED BETWEEN BOTH MAIN WING SPARS AND THE FUSELAGE STRUCTURE TO CORRECT THE PROBLEM.  SUBMITTER RECOMMENDED FUE	L GAUGES BE WATCHED FOR DEFLECTION WHEN ELECTRICAL EQUIPMENT IS TURNED ON.			1	L	7	1 	3O				A1CE
1998021100491	19980211	00491		1998	2	11	98ZZZX639        	4	19980128	G	6113	E6178	BULKHEAD        			CESSNA	414   	414A        	2075907	CE  										PROP SPINNER	CRACKED         	B			VA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	414VA	90   				414A0442				SPINNER BULKHEAD INSTALLED FOR PROPELLER MODEL 3AF36C514-C/G-80VMFA-2 FOUND CRACKED.  SUBMITTER STATED FOUND THIS ON MAN	Y OTHER AIRCRAFT.  THIS SPINNER IS ONLY ON AIRCRAFT MODIFIED PER STC SA 7633SW.  LIQUID COOLED ENGINE INSTALLATION.					1	L	7	2 	3O				A7CE
1998021100492	19980211	00492	SO  	1998	2	11	98ZZZX640        	2	19980121	G	8530	252501FCC	PISTON RING     								CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE CYLINDER	MISMARKED       	B			VA1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	19										ENGINE COMPONENTS INC., PISTON RING FOR TSIO-520 SERIES WITH CHROME CYLINDERS.  RING P/N 252501F-CC, THE PART NUMBER IS 	STAMPED ON BOTTOM OF RING INSTEAD OF TOP OF RING.  IF INSTALLED AS MARKED, IT WILL NOT FIT IN THE PISTON RING LAND - TOP	 RING LAND POSITION.									3	O			E8CE
1998021100493	19980211	00493	CE  	1998	2	11	98ZZZX641        	1	19980119	G	3231	08411066	BELLCRANK       			CESSNA	421   	421B        	2076014	CE  										RT MLG DOOR	CRACKED         	B	S		CM2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	421CP	5549 				421B0015				RIGHT MLG DOOR BELLCRANK CRACK APPEARED TO START AT UPPER FORWARD.  SUBMITTER STATED WAS CRACKED FOR SOME TIME BEFORE FA	ILURE.					1	L	7	2 	3O				A7CE
1998021100495	19980211	00495	SW  	1998	2	11	98ZZZX643        	1	19980109	G	6710	C4264172	RETAINER        	RONSON      		BELL  	206   	206L        	1181522	SW  										M/R SERVO	CORRODED        	B			B6HR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07										SERVO RETAINER CAME BACK FROM NDT WITH CORROSION INDICATION.  RE-CLEANED AND ANODIZED PART.						1	G	7	1 	3U				H2SW
1998021100496	19980211	00496	SO  	1998	2	11	98ZZZX644        	1	19980127	G	7160	638873	FILTER          	FACET       		PIPER 	PA32  	PA32R301    	7103218	SO  										INDUCT AIR	DETERIORATED    	B	S	A	N81R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	581EW	212  				3246070				THE FAA-PMA FACET INDUCTION AIR FILTER WAS FOUND DURING AN INSPECTION WITH THE BLACK RUBBER INTERIOR EDGE DETERIORATING.	  THE FILTER HAD 212.1 HRS SINCE THE AIRCRAFT WAS NEW AND 10 MONTHS SINCE AIRCRAFT WAS ISSUED ITS ORIGINAL AIRWORTHINESS	.  THE DETERIORATION IS ON THE INBOARD SIDE OF FILTER WHERE IT CAN BE INJESTED BY ENGINE.				1	L	7	1 	3O				A3SO
1998021100497	19980211	00497	CE  	1998	2	11	98ZZZX645        	1	19980126	G	2721	MS21251B25	TURNBUCKLE      			CESSNA	340   	340A        	2076405	CE  										RUD TRIM CABLE	SPLIT           	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	6335X	3086 				340A0504				DURING ADJUSTMENT OF RUDDER TRIM CABLES, ONE TURNBUCKLE WAS FOUND SPLIT DOWN THE SIDES.  THE CABLE ENDS WERE NOT BOTTOME	D OUT.  POSSIBLE DEFECT CAUSED FROM OVERTIGHTENING CABLE AT SOME TIME.  SUBMITTER RECOMMENDED CLOSE INSPECTION OF TURNBU	CKLES AT REGULAR INSPECTIONS.				1	L	7	2 	3O				3A25
1998021100873	19980211	00873	SO  	1998	2	11	98ZZZX671        	2	19980208	G	8520	634503M010	BEARING         								CONT  	O520  	GTSIO520*   	17032	SO  					CRANK MAIN	WRONG PART      	D	P			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	11										WHEN PREPARING A GEARED CONTINENTAL ACFT ENGINE   FOR ASSY, MECHANIC NOTICED A MAIN BEARING INSERT APPEARED ABNORMAL.  U	PON CLOSER EXAMINATION, FOUND THE BEARING HAD ONLY ONE OIL HOLE.  NORMALLY, BEARINGS HAVE TWO OIL HOLES.  ONE IS FOR OIL	 SUPPLY TO THE CRANKSHAFT FROM THE OIL SYSTEM AND THE OTHER IS FOR OIL SUPPLY TO THE PISTON COOLING NOZZLE.  IF THE CRAN	KSHAFT OIL SUPPLY IS ABSENT, THE ENGINE WILL FAIL.  THERE HAVE BEEN TWO INSTANCES OF THESE BEARINGS FOUND IN THE SAME WE	EK.  BOTH CAME FROM BEARING SETS PURCHASED DIRECTLY FROM TELEDYNE CONTINENTAL MOTORS.  THE REST OF THE BEARINGS IN THE S	ET WERE NORMAL.  BOTH BEARING SETS WERE FOR GEARED CONTINENTAL GTSIO-520 ENGINES.						3	O			E7CE
1998021100874	19980211	00874	SO  	1998	2	11	98ZZZX672        	1	19980202	G	5743	6704213	MOUNT           			PIPER 	PA32  	PA32R300    	7103213	SO  										MLG RT AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	37RE					32R7780114				ANNUAL INSPECTION OF MLG AREA REVEALED LT FWD MLG TRUNNION MOUNT CRACKED THROUGH 3 OF THE 4 MOUNT BOLT HOLES.  FURTHER I	NSPECTION OF LT AFT AND RT FWD AND AFT.  MAINTENANCE REVEALED 2 ADDITIONAL MOUNTS CRACKED THROUGH BOLT HOLES.  REMOVED M	OUNTS AND INSPECTED SPAR.  STRIPPED AND INSPECTED MLG TRUNNIONS AND FOUND LT TRUNNION CRACKED ABOUT 2 INCHES LONG AT POI	NT OF WEBBING AND BARREL.			1	L	7	1 	3O				A3SO
1998021100875	19980211	00875	SO  	1998	2	11	98ZZZX673        	1	19980202	G	5743	67926030	TRUNNION        			PIPER 	PA32  	PA32R300    	7103213	SO  										LT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	37RE					32R7780114				ANNUAL INSPECTION OF MLG AREA REVEALED LT FWD MLG TRUNNION MOUNT CRACKED THROUGH 3 OF THE 4 MOUNT BOLT HOLES.  FURTHER I	NSPECTION OF LT AFT AND RT FWD AND AFT.  MAINTENANCE REVEALED 2 ADDITIONAL MOUNTS CRACKED THROUGH BOLT HOLES.  REMOVED M	OUNTS AND INSPECTED SPAR.  STRIPPED AND INSPECTED MLG TRUNNIONS AND FOUND LT TRUNNION CRACKED ABOUT 2 INCHES LONG AT POI	NT OF WEBBING AND BARREL.			1	L	7	1 	3O				A3SO
1998021100876	19980211	00876	SO  	1998	2	11	98ZZZX674        	1	19980202	G	5743	6704014	MOUNT           			PIPER 	PA32  	PA32R300    	7103213	SO  										MLG LT AFT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	37RE					32R7780114				ANNUAL INSPECTION OF MLG AREA REVEALED LT FWD MLG TRUNNION MOUNT CRACKED THROUGH 3 OF THE 4 MOUNT BOLT HOLES.  FURTHER I	NSPECTION OF LT AFT AND RT FWD AND AFT.  MAINTENANCE REVEALED 2 ADDITIONAL MOUNTS CRACKED THROUGH BOLT HOLES.  REMOVED M	OUNTS AND INSPECTED SPAR.  STRIPPED AND INSPECTED MLG TRUNNIONS AND FOUND LT TRUNNION CRACKED ABOUT 2 INCHES LONG AT POI	NT OF WEBBING AND BARREL.			1	L	7	1 	3O				A3SO
1998021100877	19980211	00877	SO  	1998	2	11	98ZZZX675        	1	19980202	G	3211	6704014	MOUNT           			PIPER 	PA32  	PA32R300    	7103213	SO  										MLG LT FWD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	37RE					32R7780114				ANNUAL INSPECTION OF MLG AREA REVEALED LT FWD MLG TRUNNION MOUNT CRACKED THROUGH 3 OF THE 4 MOUNT BOLT HOLES.  FURTHER I	NSPECTION OF LT AFT AND RT FWD AND AFT.  MAINTENANCE REVEALED 2 ADDITIONAL MOUNTS CRACKED THROUGH BOLT HOLES.  REMOVED M	OUNTS AND INSPECTED SPAR.  STRIPPED AND INSPECTED MLG TRUNNIONS AND FOUND LT TRUNNION CRACKED ABOUT 2 INCHES LONG AT POI	NT OF WEBBING AND BARREL.			1	L	7	1 	3O				A3SO
1998021900003	19980219	00003	CE  	1998	2	19	98ZZZX690        	1	19980101	G	5512	053200176	SKIN            			CESSNA	172   	172G        	2072420	CE  										HORIZ STAB LE	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4612L	4000 				17254607				FOUND HORIZONTAL STABILIZER LEADING EDGE P/N 0532001-76 CRACKED AT INBOARD RIB P/N 0532001-50.  SUBMITTER STATED CAUSED 	BY GROUND HANDLING.  DAMAGE WAS DIFFICULT TO SEE DUE TO DARK PAINT COLOR AND CRACK WAS CLOSED UNLESS PRESSURE (DOWNWARD)	 WAS PUT ON L.E.				1	H	7	1 	3O			NT	3A12
1998021900004	19980219	00004	EA  	1998	2	19	98ZZZX691        	2	19980107	G	8530	STD587	ROCKER ADJ NUT  			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 3 CYL EXH VLV	LOOSE           	D				K				NONE                    				R	W		PARTIAL RPM/PWR LOSS      	INADEQUATE Q C            		TO	TAKEOFF        	1			WP	07	49100	91   				15283418	L14525615			AIRCRAFT REPORTED SUDDEN LOSS OF POWER ON TAKEOFF.  UPON INSPECTION, FOUND ALL EXHAUST ROCKER VALVE ADJUSTING NUTS HAD I	NSUFFICIENT TORQUE.  NR 3 CYLINDER ADJUSTMENT HAD BACKED OFF COMPLETELY.  ENGINE HAS 90.9 HOURS SINCE OVERHAUL.					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998021900005	19980219	00005	GL  	1998	2	19	98ZZZX692        	3	19980126	G	6110		PROPELLER ASSY  			CESSNA	210   	T210G       	2073432	CE  						MCAULY	3A32C	D3A32C88    	GL  	DOME	RUSTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	6852R		582  			T2100252		880164		PROPELLER WENT TO HIGH PITCH DURING RUN-UP AND WOULD NOT RETURN TO LOW PITCH.  WHEN THE PROPELLER DOME WAS REMOVED, APPR	OXIMATELY 3 CC'S OF RUSTY WATER RAN OUT.  DISASSEMBLY OF THE PROPELLER AT THE PROP SHOP REVEALED SEVERE RUSTING OF INTER	NAL STEEL PARTS.  THIS PROP WAS LAST OVERHAULED 5-2-91.  HOW THE WATER ENTERED THE PROPELLER IS UNKNOWN.				1	H	7	1 	3O				3A21    		5	C	P21EA
1998021900006	19980219	00006	GL  	1998	2	19	98ZZZX693        	3	19980120	G	6111	84334	BLADE           			CESSNA	310   	310D        	2074212	CE  						HARTZL	HCA2X	HCA2XF2     	GL  	SHANK	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6937T				A24805	39237		41034		DURING INSPECTION FOR AD 97-18-02, BOTH PROPELLER BLADES WERE FOUND CRACKED USING PHASE ANALYSIS EDDY CURRENT INSPECTION	 TECHNIQUE.  BOTH BLADES CONTAIN SEVERAL SMALL CRACKS NOT DETECTABLE USING AN ED520 OR SIMILAR METER BASED INSTRUMENTS. 	 SUBMITTER RECOMMENDED PERSONNEL PERFORMING INSPECTIONS CONSIDER UPGRADING TO PHASE SENSITIVE INSTRUMENTATION.				1	L	7	2 	3O				3A10    		5	C	P908
1998021900007	19980219	00007	GL  	1998	2	19	98ZZZX694        	3	19980120	G	6111	84334	BLADE           			CESSNA	310   	310D        	2074212	CE  						HARTZL	HCA2X	HCA2XF2     	GL  	SHANK	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6937T				A25086	39237		41034		DURING INSPECTION FOR AD 97-18-02, BOTH PROPELLER BLADES WERE FOUND CRACKED USING PHASE ANALYSIS EDDY CURRENT INSPECTION	 TECHNIQUE.  BOTH BLADES CONTAIN SEVERAL SMALL CRACKS NOT DETECTABLE USING AN ED520 OR SIMILAR METER BASED INSTRUMENTS. 	 SUBMITTER RECOMMENDED PERSONNEL PERFORMING INSPECTIONS CONSIDER UPGRADING TO PHASE SENSITIVE INSTRUMENTATION.				1	L	7	2 	3O				3A10    		5	C	P908
1998021900010	19980219	00010	CE  	1998	2	19	98ZZZX696        	1	19980202	G	7810	1099500001	EXHAUST STACK   			BEECH 	90    	E90         	1152914	CE  										LT ENG LT EXH	CRACKED         	B			YBJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27	1097B	330  				LJ1452				NORMAL PHASE CHECK.  200 HR LT ENGINE, LT EXHAUST DUCT FOR LIP DEICE SYSTEM.  BROKEN OFF OF TAIL PIPE.  NO DAMAGE TO ENG	INE OR COWLING.  DETERMINED TO BE MATERIAL FAILURE.  SUGGEST MORE FREQUENT INSPECTION OF EXHAUST SYSTEM.  THIS COULD BE 	VERY DANGEROUS.				1	L	7	2 	3T				3A20
1998021900011	19980219	00011	EU  	1998	2	19	98ZZZX697        	1	19980126	G	2823	AV16B1945D	VALVE           			ISRAEL	1124  	1124        	4500102	EU  										FUEL SOV	MALFUNCTIONED   	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	1124F		7    			281				THE FUEL SHUT-OFF VALVE BECAME SLOW TO OPERATE.  CREW STATED IT WAS RELATED TO TEMPERATURE (VALVE IS INTERNAL IN LOWER F	USELAGE FUEL TANK).  REASON IS UNKNOWN.					2	M	7	2 	4F				A2SW
1998021900012	19980219	00012	CE  	1998	2	19	98ZZZX698        	1	19980105	G	2710	626010613	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	150F	6524 				6500150				RIGHT WING AILERON CABLE, OUTBOARD, AFT HAS BROKEN WIRES IN STRAND AT CABLE PULLEY WS 175.63 (PLUS OR MINUS).  FOUND DUR	ING OPERATION 10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.  SUBMITTER RECOMMENDED A MANDATORY 4,800-HOUR CABLE CHANGE,	 ALL PRIMARY CONTROL SURFACES.				2	L	7	2 	4F			 	A9NM
1998021900013	19980219	00013	CE  	1998	2	19	98ZZZX699        	1	19980105	G	2710	626010616	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	150F	6524 				6500150				RIGHT AILERON CABLE (INBOARD FOWARD) AT CABLE PULLEYS WS 88.00.  BROKEN WIRES IN THREE STRANDS.  FOUND DURING OPERATION 	10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.  SUBMITTER RECOMMENDED A MANDATORY 4,800 HOUR CABLE CHANGE, ALL PRIMARY S	URFACES.				2	L	7	2 	4F			 	A9NM
1998021900014	19980219	00014	CE  	1998	2	19	98ZZZX700        	1	19980105	G	2710	626010625	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	150F	63524				6500150				RIGHT AILERON CABLE, (OUTBOARD FORWARD) AT CABLE PULLEYS WS 175.63 (PLUS OR MINUS) HAS BROKEN WIRES IN STRAND.  FOUND DU	RING OPERATION 10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.  SUBMITTER RECOMMENDED A MANDATORY 4,800-HR CABLE CHANGE, 	ALL PRIMARY CONTROL SURFACES.				2	L	7	2 	4F			 	A9NM
1998021900015	19980219	00015	CE  	1998	2	19	98ZZZX701        	1	19980105	G	2710	626010613	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	175J	5697 				6500168				RIGHT WING AILERON CABLE, (OUTBOARD, AFT) HAS BROKEN WIRES IN STRAND AT CABLE PULLEY WS 175.63 (PLUS OR MINUS).  FOUND D	URING OPERATION 10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.  SUBMITTER RECOMMENDED A MANDATORY 4,800-HOUR CABLE CHANG	E, ALL PRIMARY CONTROL SURFACES.				2	L	7	2 	4F			 	A9NM
1998021900016	19980219	00016	CE  	1998	2	19	98ZZZX702        	1	19980105	G	2710	626010625	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	175J	5697 				6500168				RIGHT WING AILERON CABLE, (OUTBOARD, FORWARD), HAS BROKEN WIRES IN STRAND AT CABLE PULLEY WS 175.63 (PLUS OR MINUS).  FO	UND DURING OPERATION 10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.   SUBMITTER RECOMMENDED A MANDATORY 4,800-HOUR CABLE	 CHANGE, ALL PRIMARY CONTROL SURFACES.				2	L	7	2 	4F			 	A9NM
1998021900017	19980219	00017	CE  	1998	2	19	98ZZZX703        	1	19980105	G	2710	626010616	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	175J	5976 				6500168				RIGHT WING AILERON CABLE (INBOARD FORWARD), HAS BROKEN WIRES IN ONE STRAND AT CABLE PULLEYS WS 88.00.  FOUND DURING OPER	ATION 10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.  SUBMITTER RECOMMENDED A MANDATORY 4,800-HOUR CABLE CHANGE, ALL PRI	MARY CONTROL SURFACES.				2	L	7	2 	4F			 	A9NM
1998021900018	19980219	00018	CE  	1998	2	19	98ZZZX704        	1	19980105	G	2710	626010616	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT AILERON	FRAYED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	650Z					6500108				RIGHT WING AILERON CABLE, (INBOARD, FORWARD) HAS BROKEN WIRES IN SEVERAL STRANDS AT CABLE PULLEYS WS 88.00.  FOUND DURIN	G OPERATION 10, CONTINUOUS INSPECTION PROGRAM NR SMP650-1.  SUBMITTER RECOMMENDED A MANDATORY 4,800-HOUR CABLE HCANGE, A	LL PRIMARY CONTROL SURFACES.				2	L	7	2 	4F			 	A9NM
1998021900019	19980219	00019	CE  	1998	2	19	98ZZZX705        	1	19980105	G	2710	626010613	CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										RT WING	WORN            	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	650Z	6833 				6500108				RIGHT WING AILERON CABLE (OUTBOARD, AFT) WORN THROUGH CLAD.  FOUND DURING OPERATION PROGRAM NR SMP650-1.  SUBMITTER RECO	MMENDED A MANDATORY 4,800-HOUR CABLE CHANGE, ALL PRIMARY CONTROL SURFACES.					2	L	7	2 	4F			 	A9NM
1998021900125	19980219	00125	SO  	1998	2	19	98ZZZX706        	1	19980127	G	2434	ALU9510	ALTERNATOR      	PRESTOLITE  		PIPER 	PA31  	PA31P       	7103120	SO  										DC SYSTEM	FAILED          	B			IL3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	18MC		166  		6081438	31P7300143				OVERHAULED ALTERNATOR FROM ELECTRO SYSTEMS WAS 166.3 HRS SINCE O/H 10-10-96.  NO OUTPUT.  SUBMITTER STATED SHORT SERVICE	 LIFE FROM THESE UNITS.					1	L	7	2 	3O				A8EA
1998021900126	19980219	00126	WP  	1998	2	19	98ZZZX707        	1	19980112	G	2730	40491029	PUSH ROD        			WTHRLY	620   	620         	9630602	WP  										ELEVATOR AFT	LOOSE           	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	197SK	320  				1645				REAR ELEVATOR CONTROL TUBE WAS FOUND TO HAVE MOVEMENT BETWEEN FRONT ATTACH FITTING AND TUBE.  THE CAUSE IS BELIEVED TO B	E A DEFECT WHICH OCCURRED IN MANUFACTURING AND WENT UNDETECTED.  RECOMMEND CLOSE INSPECTION OF THIS AND SIMILAR CONTROLS	 AT REGULAR INSPECTIONS.				1	L	7	1 	3R				A26WE
1998021900127	19980219	00127	NM  	1998	2	19	98ZZZX708        	1	19980115	G	5751	24130007	BRACKET         			CHILD 	S2    	S2BPITTS    	0110304	NM  										LT AIL HINGE	FAILED          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	267SW	810  				5077				AILERON HINGE BRACKET, TUBE BROKE IN CENTER NEXT TO WELD AREA.						1	Q	7	1 	3O				A8SO
1998021900128	19980219	00128	CE  	1998	2	19	98ZZZX709        	1	19980202	G	3230	5045010	TORQUE TUBE     			CESSNA	340   	340CESSNA   	2076404	CE  										RT MLG	FAILED          	G		A		A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			EA	13	500LB					3400006				GOOD BANG HEARD WHEN LANDING GEAR SELECTED UP.  RIGHT GEAR DID NOT RETRACT.  RIGHT GEAR COLLAPSED ON LANDING.  INVESTIGA	TION REVEALED RIGHT TORQUE TUBE RETRACT BELLCRANK BROKEN.					1	L	7	2 	3O				3A25
1998021900129	19980219	00129	CE  	1998	2	19	98ZZZX710        	1	19980130	G	7922	5E19600	VALVE ASSY      			BEECH 	65    	65          	1152802	CE  										THERMO BYPASS	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	5078U	131  				LF32				A NEW OIL TEMP CONTROL VALVE WAS USED FOR ENGINE OVERHAUL PN 5E19600.  ENGINE OIL TEMP FOR FIRST 100 HRS TIS WAS NORMAL.	  THE NEXT 31.2 HRS TIS, OIL TEMP INCREASED TO RED LINE.  PN 5E19600 WAS TESTED AND FOUND DEFECTIVE.					1	L	7	2 	3O				3A20
1998021900130	19980219	00130	SO  	1998	2	19	98ZZZX711        	1	19980128	G	5730	6206200	SKIN            			PIPER 	PA28  	PA28180     	7102808	SO  										WING WALK	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	56619	4800 				287405023				WING WALK SKIN ASSEMBLY CORRIGATED PANEL CRACKED IN SEVERAL PLACES.  CANNOT BE SEEN UNLESS TANKS ARE REMOVED.  THE WING 	WALK IS NOT STRONG ENOUGH TO HOLD TWO ADULTS AT ONCE.					1	L	7	1 	3O				2A13
1998021900131	19980219	00131	SO  	1998	2	19	98ZZZX712        	2	19980205	G	7414	10160894	CAM ASSY        		S6RN25      	CESSNA	175   	175A        	2072504	CE  	CONT  	O470  	O470M       	17026	SO  					ENG MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6981E				A23641	56481	5352671MR			MAGNETO WAS DISASSEMBLED FOR 500-HOUR INSPECTION.  WEAR ON FLYWEIGHT AXLES WAS APPROXIMATELY .020 INCH AND STOP PINS HAD	 GROOVES ABOUT .020 INCH DEEP.  IMPULSE COUPLING SPRING WAS BROKEN.  AIRCRAFT WAS OPERATED 80 HOURS IN PAST 5 YEARS.  NO	T FLOWN AT ALL FOR PAST 4-1/2 YEARS.  INFREQUENT OPERATION AND LACK OF MAGNETO MAINTENANCE LEAD TO A SITUATION THAT COUL	D HAVE CAUSED ENGINE FAILURE.			1	H	7	1 	3O	3	O		3A17    	E273
1998021900132	19980219	00132	SO  	1998	2	19	98ZZZX713        	2	19980129	G	7322	CF30766	FLOAT           		MA3SPA      	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR	MISADJUSTED     	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	704AA					15078448	254842A48			INSPECTION FOUND FLOAT BRASS SLIGHTLY WORN WHERE NEEDLE RIDES AGAINST ADJUSTMENT TAB CAUSING FLOAT LEVEL TO BE ABNORMALL	Y HIGH LEADING TO RICHER MIXTURE.  RESET FLOAT LEVEL.					1	H	7	1 	3O	3	O		3A19    	E252
1998021900133	19980219	00133	CE  	1998	2	19	98ZZZX714        	1	19980116	G	7120	3541534613	MOUNT           			BEECH 	35    	B35         	1151506	CE  										ENG RT SUPPORT	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	8851A	7023 				D2586				CRACK FOUND DURING ANNUAL INSPECTION AT UPPER FRONT ELBOW OF ENGINE MOUNT SUPPORT BRACKET.  PREVIOUS UNRECORDED REPAIR H	AD BEEN MADE, BUT CRACK HAS CONTINUED TO PROGRESS.  CAUSE UNKNOWN.  LEFT SUPPORT SHOWS NO STRESS.					1	L	7	1 	3O				A777
1998021900134	19980219	00134	CE  	1998	2	19	98ZZZX715        	1	19980116	G	2820	35924118	LINE            			BEECH 	35    	B35         	1151506	CE  										RT TANK TO SELTR	LEAKING         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	8851A	7023 				D2586				FUEL LINE, .3750 INCH, SERVING RIGHT WING TANK TO FUEL SELECTOR HAD DEVELOPED PIN HOLE LEAKS DUE TO PITTING CORROSION. L	INE LIES UNDER COCKPIT FLOOR, BUT IN CLOSE PROXIMITY TO UNDERSIDE OF FLOOR.  BELIEVE CORROSION DUE TO YEARS OF MOISTURE 	DRAINING AT THE REAR OF THE FLOORBOARDS AND BEING HELD BY CAPILLARY ACTION BETWEEN FLOORBOARD AND LINE.				1	L	7	1 	3O				A777
1998021900135	19980219	00135	CE  	1998	2	19	98ZZZX716        	1	19980204	G	5210		DOOR TRIM       			CESSNA	500   	560CESSNA   	2076750	CE  										DOOR POST	MISINSTALLED    	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	901RM					5600116				STANDOFFS FOR DOOR TRIM WERE INSTALLED UNDER SUPPORT FOR DOOR CHAIN POKING HOLE IN AFT DOOR POST CAUSING CRACK 1.50 INCH	ES LONG.  SUBMITTER STATED ALL CESSNA CITATION OPERATORS SHOULD INSPECT THIS AREA FOR DAMAGE.					2	L	7	2 	4F			RT	A22CE
1998021900136	19980219	00136	CE  	1998	2	19	98ZZZX717        	1	19980101	G	5210		HINGE           			BEECH 	95    	B95A        	1153406	CE  										DOOR UPPER	FAILED          	C		A		O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SW	99	3113K					TD530				DURING CRUISE FLIGHT, A LOUD BANG WAS HEARD AND SUBSEQUENT LOUD WIND NOISES.  UPPER DOOR HINGE HAD BROKEN ALLOWING DOOR 	TO TILT OUTWARD SINCE IT WAS NOW ONLY HELD BY LOWER HINGE AND REAR LATCH (UPPER LATCH RELEASED WHEN HINGE BROKE).  DOOR 	OPENED APPROXIMATELY 6 INCHES AT TOP AND ACTED AS LARGE AIRSLOOP.  PLANE WAS IMMEDIATELY SLOWED DOWN AND A SAFE LANDING 	WAS EXPECTED.  TTAF 3,510 HOURS.  EXAMINATION SHOWED FAILURE WAS DUE TO INTERGRANULAR CORROSION AND IS ALMOST IMPOSSIBLE	 TO INSPECT.		1	L	7	2 	3O				3A16
1998021900137	19980219	00137		1998	2	19	98ZZZX718        	1	19980112	G	2140	09E472	SWITCH          	JANITROL    																PRESS REGULATOR	FAILED          	B		A	IS4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09										SWITCH HAS CONTINUITY WITH NO AIRPRESSURE ON DIAPHRAGM.  MICROSWITCH MALFUNCTION.  RECOMMEND SWITCH BE CHECKED EVERY YEA	R OR ANNUALLY.  THIS 09E47-2 IS PART OF THE 10E21-X HEATER PACKAGE IN PIPER CHEYENNES.  THIS SWITCH IS NOT COVERED UNDER	 AD NOTE 96-20-07.  PART DESCRIPTION IS:  AIR PRESSURE REGULATOR AND AIR PRESSURE SWITCH.
1998021900138	19980219	00138	CE  	1998	2	19	98ZZZX719        	1	19980113	G	5712	10510001149	RIB             			BEECH 	76    	76          	1153005	CE  										LT WING	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2009X	1627 				ME66				FOLLOWING A WINDSTORM THAT BROKE THE GUSTLOCK, AN INVESTIGATION OF THE FLIGHT CONTROLS REVEALED CRACKS ON BOTH THE INBD 	AND OTBD WING RIBS AT THE AILERON BRACKET RIVETS.					1	L	7	2 	3O				A29CE
1998021900139	19980219	00139	CE  	1998	2	19	98ZZZX720        	1	19980113	G	5712	10510001147	RIB             			BEECH 	76    	76          	1153005	CE  										LT WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	2009X	1627 				ME66				FOLLOWING A WINDSTORM THAT BROKE THE GUSTLOCK, AN INVESTIGATION OF THE FLIGHT CONTROLS REVEALED CRACKS ON BOTH THE INBD 	AND OTBD WING RIBS AT THE AILERON BRACKET RIVETS.					1	L	7	2 	3O				A29CE
1998021900140	19980219	00140	NE  	1998	2	19	98ZZZX721        	2	19980107	G	7250		SHAFT           								GE    	CFM56 	CFM56*      	13802	NE  					TURBINE	MISHEAT TREAT   	B			NM1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	33					FN0128					QUALITY AUDIT FOUND CFM TURBINE SHAFTS WITH A POSSIBLE DEFECT DUE TO HYDROGEN OUTGASSING HEAT TREATMENT HAD BEEN OMITTED	.										4	F			E2GL
1998021900141	19980219	00141	NE  	1998	2	19	98ZZZX722        	2	19980107	G	7250		SHAFT           								GE    	CFM56 	CFM56*      	13802	NE  					TURBINE	MISHEAT TREAT   	B			NM1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	33					FN0524					QUALITY AUDIT FOUND CFM TURBINE SHAFTS WITH A POSSIBLE DEFECT DUE TO HYDROGEN OUTGASSING HEAT TREATMENT HAD BEEN OMITTED	.										4	F			E2GL
1998021900142	19980219	00142	NE  	1998	2	19	98ZZZX723        	2	19980107	G	7250		SHAFT           								GE    	CFM56 	CFM56*      	13802	NE  					TURBINE	MISHEAT TREAT   	B			NM1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	33					FN0907					QUALITY AUDIT FOUND CFM TURBINE SHAFTS WITH A POSSIBLE DEFECT DUE TO HYDROGEN OUTGASSING HEAT TREATMENT HAD BEEN OMITTED	.										4	F			E2GL
1998021900143	19980219	00143	NE  	1998	2	19	98ZZZX724        	2	19980107	G	7250		SHAFT           								GE    	CFM56 	CFM56*      	13802	NE  					TURBINE	MISHEAT TREAT   	B			NM1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	33					FN1006					QUALITY AUDIT FOUND CFM TURBINE SHAFTS WITH A POSSIBLE DEFECT DUE TO HYDROGEN OUTGASSING HEAT TREATMENT HAD BEEN OMITTED	.										4	F			E2GL
1998021900144	19980219	00144	NE  	1998	2	19	98ZZZX725        	2	19980107	G	7250		SHAFT           								GE    	CFM56 	CFM56*      	13802	NE  					TURBINE	MISHEAT TREAT   	B			NM1Y	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	33					F01061					QUALITY AUDIT FOUND CFM TURBINE SHAFTS WITH A POSSIBLE DEFECT DUE TO HYDROGEN OUTGASSING HEAT TREATMENT HAD BEEN OMITTED	.										4	F			E2GL
1998021900145	19980219	00145	GL  	1998	2	19	98ZZZX726        	3	19980202	G	6114	8460	HUB             													HARTZL	HCB3T	HCB3T*      	GL  	PILOT TUBE	DEFECTIVE       	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05					A7553A			BUA19255		TWO HUBS WERE RECEIVED FROM DIAMOND AVIACAO LTDA, BRAZIL.   ON HUB, SN BUA19254, THE NR 1 PILOT TUBE IS EXTENDING TOO FA	R OUTWARD FROM THE END OF THE HUB ARM.  ON HUB, SN BUA19255, THE NR 2 AND NR 3 PILOT TUBES ARE EXTENDING TOO FAR OUTWARD	.  SPECIFIED DIMENSION IS 3.750 INCHES PLUS OR MINUS .0625 INCH FROM THE OTBD END OF THE HUB ARM TO THE OTBD END OF THE 	PILOT TUBE.  ACTUAL DIMENSIONS ARE 3.920 INCHES, 3.845 INCHES, AND 3.875 INCHES RESPECTIVELY.  THE SUSPECTED CAUSE IS IN	 FLIGHT SLIPPAGE CAUSED BY UNDERSIZED PILOT TUBES.												6	C	P15EA
1998021900146	19980219	00146	GL  	1998	2	19	98ZZZX727        	3	19980202	G	6114	8460	HUB             													HARTZL	HCB3T	HCB3T*      	GL  	PILOT TUBE	DEFECTIVE       	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05					A7597A			BUA19255		TWO HUBS WERE RECEIVED FROM DIAMOND AVIACAO LTDA, BRAZIL.   ON HUB, SN BUA19254, THE NR 1 PILOT TUBE IS EXTENDING TOO FA	R OUTWARD FROM THE END OF THE HUB ARM.  ON HUB, SN BUA19255, THE NR 2 AND NR 3 PILOT TUBES ARE EXTENDING TOO FAR OUTWARD	. SPECIFIED DIMENSION IS 3.750 INCHES PLUS OR MINUS .0625 INCH FROM THE OTBD END OF THE HUB ARM TO THE OTBD END OF THE P	ILOT TUBE.  ACTUAL DIMENSIONS ARE 3.920 INCHES, 3.845 INCHES, AND 3.875 INCHES RESPECTIVELY.  THE SUSPECTED CAUSE IS IN 	FLIGHT SLIPPAGE CAUSED BY UNDERSIZED PILOT TUBES.												6	C	P15EA
1998021900147	19980219	00147	GL  	1998	2	19	98ZZZX728        	3	19980206	G	6114	57D220116	HUB             													HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER	CRACKED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		1706 			BCL191			BC491		DURING INSPECTION, HUB WAS FOUND CRACKED IN FILLET AREA.  HUB HAS BEEN SCRAPPED.																5	C	P920
1998021900148	19980219	00148	EU  	1998	2	19	98ZZZX729        	1	19980123	G	3213	25UM403A	SIDE STAY SPRING			BRAERO	DH125 	BAE125800A  	1500285	EU  										MLG UPPER	FAILED          	B	S	A	JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	961JC					258062				COULD NOT OBTAIN CLEARANCE BETWEEN CAM FACE AND ROLLER WHEN MLG SIDE STAY WAS FOLDED.  FOUND SIDE STAY SPRING STRUT WAS 	NOT ALLOWING FULL SLOT TRAVEL.  REMOVED SPRING STRUT, DISASSEMBLED AND FOUND SPRING COIL IN SPRING STRUT HAD CORRODED IN	TO TWO PIECES CAUSING IMPROPER OPERATION OF SPRING STRUT.  SUGGEST THAT SPRING STRUT BE REMOVED, CLEANED,  INSPECTED, LU	BBED, AND REINSTALLED AT A MORE FREQUENT INTERVAL THAN 4,000 LANDINGS.  SUGGEST AN INSPECTION OF 600 HOURS OR 24 MONTHS.	  LANDINGS, 2,150.		2	L	7	2 	4F			RT	A3EU
1998021900149	19980219	00149	SO  	1998	2	19	98ZZZX730        	1	19980121	G	2750	1159SCH2101	VALVE           			GULSTM	G1159 	G1159A      	3970109	SO  										FLAP OVERRIDE	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	843HS	2379 				496				DURING OPERATIONAL CHECKS FOLLOWING MAINTENANCE, THE FLAP MANUAL OVERIDE LEVER COULD NOT BE MOVED.  TROUBLESHOOTING REVE	ALED THAT THE FLAP 4-WAY, 3-POSITION, MANUAL OVERRIDE INPUT SHAFT WAS SEIZED.  REPLACED THE VALVE WITH AN OVERHAULED ASS	EMBLY.  OPERATION OF THE REPLACMENT VALVE WAS FOUND SATISFACTORY.				2	L	7	2 	4F				A12EA
1998021900150	19980219	00150	SO  	1998	2	19	98ZZZX731        	1	19980202	G	3240	1159H40016079	BRAKE LINE      			GULSTM	G1159 	GIV         	3980115	SO  										LT MLG	CRACKED         	C	S	A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	09	1900W	1430 				1124				LEFT MAIN LANDING GEAR BRAKE LINE CRACKED AT THE UPPER FITTING AT THE END OF THE PERMASWAGE CRIMP.  THE LINE WAS CRACKED	 APPROXIMATELY ONE-HALF THE CIRCUMFERENCE.  SUSPECT FROM VIBRATION.  SUBMITTER STATED THE LINE NEEDS ADDITIONAL SECURING	 CLAMPS.  CYCLES, 996.				2	L	7	2 	4F			RT	A12EA
1998021900152	19980219	00152	SW  	1998	2	19	98ZZZX733        	1	19980114	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	DAMAGED         	B			VE3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	1116H	279  				53046				INSPECTING HELICOPTER PER AD 97-22-15 FOUND ONE T/R DRIVE DISK BOLT LOOSE AND DISK PACK BEYOND DAMAGE LIMIT.  REPLACED D	AMAGED PARTS.					1	G	7	1 	3U			O	H2SW
1998021900154	19980219	00154	SW  	1998	2	19	98ZZZX735        	1	19980130	G	6321	209040177101	FLANGE          		412040123103	BELL  	412   	412         	1182202	SW  										ROTOR BRAKE	MISMANUFACTURED 	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	11	411DE					36030				RECEIVED A REPLACEMENT PART FROM BELL HELICOPTER FOR THE ROTOR BRAKE QUILL.  THE REPLACEMENT FLANGE, PN 209-040-177-101,	 DID NOT HAVE THE SAME APPEARANCE IN THE SEAL CONTACT AREA AS THE REMOVED, IDENTICAL PART NUMBER ITEM.  THE 'NEW' FLANGE	 APPEARS TO HAVE BEEN PASSED THROUGH THE FINAL INSPECTION PROCESS AND SHIPPPED WITHOUT ALL THE MACHINING AND POLISHING P	ROCESSES BEING ACCOMPLISHED.  SUBMITTER STATED IT IS VERY IMPORANT TO PERFORM AN ACCEPTANCE INSPECTION ON ALL PARTS BEIN	G INSTALLED REGARDLESS OF THE SUPPLY SOURCE.		1	G	7	2 	4U				H4SW
1998021900156	19980219	00156	NE  	1998	2	19	98ZZZX737        	1	19980126	G	6710	NAS6608D47	BOLT            			SKRSKY	S76   	S76B        	8143007	NE  										PITCH LINK	WORN            	B			CW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	780P					760359				UPPER BOLT IN UPPER PITCH CHANGE LINK SEVERELY WORN.  SUSPECT BOLT TORQUE DOES NOT ALWAYS COMPRESS YOKE HOLDING SPHERICA	L ROD END.					1	G	7	2 	4U				H1NE
1998043000241	19980430	00241	SO  	1998	4	30	98ZZZX758        	1	19980130	G	3230	4033600	DRAG LINK       			PIPER 	PA31  	PA31350     	7103110	SO  										RT UPPER LEG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	3581C	8994 				318052091				DURING LANDING GEAR CLEANING AND INSPECTION, FOUND THE RT UPPER NOSE LANDING GEAR DRAG LEG CRACKED AT BOSS WHERE THE RET	RACT ACTUATOR LINKAGE ATTACHES.  THIS IS THE SECOND TIME SAME PART FOUND CRACKED ON LIKE AIRCRAFT WITHIN ONE YEAR.  BOTH	 CRACKED IN SAME PLACE!				1	L	7	2 	3O				A20SO
1998043000242	19980430	00242	WP  	1998	4	30	98ZZZX759        	1	19980202	G	5313	PC24000A0	LONGERON        			RHNFLU	EXT300	EXTRA300    	05616CV	WP  										HOR STAB ATTACH	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	328PW	711  				09				DURING ROUTINE SERVICE WITH HORIZONTAL STABILIZER REMOVED, FOUND A CRACK IN THE UPPER LONGERON AT THE HORIZONTAL STABILZ	IER FORWARD ATTACH POINT.  THIS LOCATION CANNOT BE SEEN DURING NORMAL INSPECTION PROCEDURES WITH HORIZONTAL STABILIZER I	NSTALLED.  NO DEFECT WAS FOUND IN THE LOCATION DEPICTED IN SB 300-2-95.  SUBMITTER RECOMMENDED REMOVING HORIZONTAL TO IN	SPECT FOR CRACKS.			1	M	7	1 	3O			NC	EXPA1M71
1998043000243	19980430	00243	SO  	1998	4	30	98ZZZX760        	1	19980122	G	5700	855592	STRUT           			PIPER 	PA22  	PA22150     	7102210	SO  										WING	RUSTED          	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19	6076D	2500 				224730				WING STRUTS WERE INSPECTED IAW AD 93-10-06 AND SB 528D IN DEC '96 AND FOUND OK.  DURING '97 ANNUAL, OWNER HAD ALL FOUR S	TRUTS INSPECTED AND MODIFIED.  STC SA 4635NM WAS DONE TO STRUTS.  OLD FORK BARREL WAS CUT OFF BY TECHNICIANS.  FOUND 2 S	TRUTS RUSTED SEVERELY ON THE INSIDE OF THE STRUT WHERE THE DOOR CATCHES ARE MOUNTED.  TWO NEW STRUTS USED FOR STC COMPLE	TION.  THE OWNER, WHO IS ALSO AN IA, WOULD LIKE TO ADVISE THAT THE AD 93-10-06 DOES NOT SPECIFICALLY ADDRESS THIS AREA O	F STRUTS FOR INSPECTION.  THE AD DIRECTS ONE TO SB 528D.		1	H	7	1 	3O				1A6
1998043000244	19980430	00244	CE  	1998	4	30	98ZZZX761        	1	19980120	G	7160	963890051	AIR FILTER      	DONALDSON   		BEECH 	58    	58          	1152740	CE  										INDUCT AIR	MISMARKED       	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SO	01	827VJ					TH1387				ORDERED PARTS FROM BEECH DISTRIBUTOR FOR INDUCTION AIR FILTER PN 96-38005-1.  TWO BOXES MARKED WITH SAME PART NUMBER, BU	T FILTER PART NUMBER INSIDE IS P/N 35-380035-7.  THIS IS NOW THE 10TH TIME RECEIVED MISMARKED PARTS FROM THE BEECH FACTO	RY AND DISTRIBUTORS.				1	L	7	2 	3O				3A16
1998043000246	19980430	00246	WP  	1998	4	30	98ZZZX763        	1	19980202	G	5313	PC24000A0	LONGERON        			RHNFLU	EXT300	EXTRA300    	05616CV	WP  										HOR STAB ATTACH	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	76PK					15				DURING A MAINTENANCE PROCEDURE INVOLVING THE REMOVAL OF HORIZONTAL STABILIZER AND FUSELAGE FABRIC, FOUND A CRACK IN THE 	UPPER LONGERON AT THE HORIZONTAL STABILIZER FORWARD ATTACH POINT.  THIS LOCATION CANNOT BE SEEN DURING NORMAL INSPECTION	 PROCEDURES.  SB 300-2-95 INSPECTION OF UPPER LONGERON IN FRONT OF HORIZONTAL STABILIZER ATTACHMENT DEPICTS A LOCATION W	HICH NO DEFECT WAS FOUND ON THIS PARTICULAR AIRCRAFT.  SUBMITTER RECOMMENDED REMOVING HORIZONTAL STABILIZER AND INSPECT 	THE AREA BETWEEN THE FORWARD STABILZIER ATTACH BRACKETS.  PARTICULARLY, AT THE WELDS, THIS CRACK WAS LOCATED ON THE AIRC	RAFT'S RIGHT SIDE.	1	M	7	1 	3O			NC	EXPA1M71
1998043000247	19980430	00247	SW  	1998	4	30	98ZZZX764        	1	19980202	G	7921	649479	OIL COOLER      			MOONEY	M20   	M20R        	5870225	SW  										FRONT INBOARD	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	9157M	682  				290009				OIL COOLER INSPECTION FOUND A CRACK FORMED AT THE BASE OF THE FRONT INBOARD STIFFENER, IN WELD AREA. CRACK HAD PENETRATE	D THE WELD.  SUSPECT CAUSE, BAD WELD.					1	L	7	1 	3O			RT	2A3
1998043000248	19980430	00248	SO  	1998	4	30	98ZZZX765        	2	19980210	G	8530		CRANKSHAFT      								CONT  	C145  	C145*       	17012	SO  					CTWT JOURNAL	BROKEN          	G		A		A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NE	03			11   							CRANKSHAFT BROKE AT THE COUNTERWEIGHT JOURNAL AREA IN-FLIGHT.  PART WAS SERVICED BY AIR AGENCY PRIOR TO INSTALLATION DUR	ING OVERHAUL.  PART WILL BE SENT TO CONTINENTAL FOR EVALUATION.										3	O			E253
1998043000249	19980430	00249	EA  	1998	4	30	98ZZZX766        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235*       	41505	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										CRANKSHAFT WAS REMOVED FROM INVENTORY FOR PRECAUTIONARY MPI.  RANK WAS PROCESSED BY AIR AGENCY AND WAS FOUND CRACKED AT 	THE JOURNAL RADII.										3	O			E223
1998043000250	19980430	00250	EA  	1998	4	30	98ZZZX767        	2	19980210	G	8520	75006	CRANKSHAFT      								LYC   	O320  	O320*       	41508	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					121682					PART WAS REMOVED FROM INVENTORY FOR MPI FOLLOWING ADVISORY THAT AIR AGENCY MAY HAVE IMPROPERLY MACHINED CRANKSHAFT.  PAR	T WAS FOUND TO HAVE CRACKS IN THE HOURNAL RADII.  PART IS NOT SERVICEABLE.										3	O			E274
1998043000251	19980430	00251	EA  	1998	4	30	98ZZZX768        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235L2C     	41505	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART WAS REMOVED FROM INVENTORY FOLLOWING ADVISORY THAT CRANKSHAFTS PROCESSED BY AIR AGENCY MAY BE DEFECTIVE.  CRANKSHAF	T WAS MPI AND FOUND TO HAVE CRACKS IN THE JOURNAL RADII.										3	O			E223
1998043000252	19980430	00252	EA  	1998	4	30	98ZZZX769        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235*       	41505	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART WAS REMOVED FROM INVENTORY FOR PRECAUTIONARY MPI.  CRANKSHAFT WAS GROUND AND POLISHED BY AIR AGENCY AND WAS FOUND T	O HAVE CRACKS IN THE JOURNAL AREAS.										3	O			E223
1998043000253	19980430	00253	EA  	1998	4	30	98ZZZX770        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235L2C     	41505	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART WS REMOVED FROM STOCK FOR PRECAUTIONARY MPI.  UNIT WAS GROUND AND POLISHED BY AIR AGENCY AND FOUND TO HAVE CRACKS I	N THE JOURNAL RADII.										3	O			E223
1998043000254	19980430	00254	EA  	1998	4	30	98ZZZX771        	2	19980210	G	8520	LW17031	CRANKSHAFT      								LYC   	O320  	O320D2J     	41508	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART WAS REMOVED FROM INVENTORY AND PRECAUTIONARY MPI PERFORMED.  CRACKS IN JOURNAL RADII WERE APPARENT.  THIS UNIT WAS 	PREVIOUSLY GROUND AND POLLISHED BY AIR AGENCY.  PART IS SCRAP.										3	O			E274
1998043000256	19980430	00256	EA  	1998	4	30	98ZZZX773        	2	19980124	G	8520	LW10842	CRANKSHAFT      			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					NR 2 JOURNAL	FAILED          	D				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CL	CLIMB          	1			NE	03	TGWOW	882  	8    			61P068379633	L1959748A			PILOT (OWNER) DEPARTING FROM AIRPORT AND CLIMBING THROUGH 4,000 FEET NOTED LOUD BANG AND SEVERE VIBRATION FROM LT ENGINE	.  ENGINE SHUT DOWN AND SECURED AND SAFE LANDING MADE.  DISASSEMBLY OF ENGINE REVEALED CRANKSHAFT BROKEN.  BREAK OCCURRE	D AT THE REAR CHEEK OF THE NR 2 ROD JOURNAL IN THE RADII.  CRANKCASE, RODS, CAMSHAFT AND CLYINDERS ALL NOW N.G.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998043000257	19980430	00257	EA  	1998	4	30	98ZZZX774        	2	19980210	G	8520	LW17577	CRANKSHAFT      								LYC   	O360  	LIO360C1E6  	41515	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										CRANKSHAFT WAS REMOVED FROM INVENTORY FOR MPI FOLLOWING ADVISORY THAT IMPROPER MACHINE WORK WAS PERFORMED BY AIR AGENCY.	  SHAFT WAS FOUND TO HAVE CRACKS AT THE JOURNAL RADIUS.  THIS CRANKSHAFT WAS RE-WORKED BY FAA - AIR AGENCY AND IS SCRAP.										3	O			1E10
1998043000258	19980430	00258	EA  	1998	4	30	98ZZZX775        	2	19980210	G	8520	LW17577	CRANKSHAFT      			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  					JOURNAL RADII	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	15008		220  			347250346				PART WAS REMOVED FOR MPI AS A PRECAUTION.  THIS CRANKSHAFT WAS RE-WORKED BY AIR AGENCY AND WAS FOUND TO HAVE CRACKS IN T	HE JOURNAL RADII.					1	L	7	2 	3O	3	O		A7SO    	1E10
1998043000259	19980430	00259	EA  	1998	4	30	98ZZZX776        	2	19980210	G	8520	77037	CRANKSHAFT      			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					NR 5 JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	56WB		9    			284470				CRANKSHAFT WAS FOUND CRACKED AFTER PRECAUTIONARY REMOVAL FOLLOWING RECENT ENGINE OVERHALL (8.8 HRS).  CRANKSHAFT WAS PRO	CESSED BY REPAIR AGENCY PRIOR TO INSTALLATION.  SUSPECT PART MAY HAV BEEN IMPROPERLY MACHINED.  CRACK WAS AT NR 5 JOURNA	L RADIUS APPROX 2.50 INCHES IN LENGTH.				1	L	7	1 	3O	3	O		2A13    	E286
1998043000260	19980430	00260	SO  	1998	4	30	98ZZZX777        	2	19980128	G	8550	07560201	PISTON          			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  					OIL FILTER ADAPT	MISMANUFACTURED 	B	S		GJ1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	5772R					17253387				OIL FILTER ADAPTER LONGITUDINAL HOLE IN PISTON DOES NOT INTERSECT HOLES DRILLED THROUGH THE CIRCUMFERENCE.  NO OIL IS AL	LOWED TO THE FILTER ELEMENT.  REPLACED PISTON, OPERATION RETURNED TO NORMAL.  SUBMITTER STATED PART WAS NOT MADE ACCORDI	NG TO PRINT.				1	H	7	1 	3O	3	O	NT	3A12    	E253
1998022600054	19980226	00054	EU  	1998	2	26	98ZZZX788        	1	19980128	G	5330		SKIN            			AMD   	FALC50	FALCON50MYST	2730106	EU  										APU EXH AREA	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	99JD	6730 				129				INSPECTION FOUND SKIN UNDER APU EXHAUST SHIELD CORRODED.  REMOVED AND REPLACED AIRCRAFT SKIN PER MANUFACTURER'S ENG. INS	TRUCTIONS					2	L	7	3 	4F				A46EU
1998022600055	19980226	00055	CE  	1998	2	26	98ZZZX789        	1	19980210	G	3411	50BSH4H	VENT DRAIN      			LEAR  	35    	35A         	5170602	CE  										PITOT/STATIC	BLOCKED         	B			JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	32HM					187				NR 2 PITOT STATIC VENT DRAINS PLUGGED WITH SILICONE.  CLEANED DRAINS, INSTALLED NEW SEALS, AND CERTIFIED NR 2 PITOT-STAT	IC SYSTEM.  AIRCRAFT TSN:  6,492.4 HOURS.  AIRCRAFT LANDINGS:  5,782.					2	L	7	2 	4F				A10CE
1998022600056	19980226	00056	CE  	1998	2	26	98ZZZX790        	1	19980126	G	2911	ENFM15Y8LM	GAUGE           			BEECH 	200   	B200        	1152922	CE  										HYD ACCUMULATOR	STUCK           	B			LX5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	961LL	597  				BB1139				ACCUMULATOR PRESSURE GAUGE IS PART OF STC SA-4378-WP AVIADESIGN INC., HYDRAULIC LANDING GEAR RETRACTION SYSTEM.  GAUGE S	HOWED NEEDLE STUCK AT 250 PSI WITH ZERO PRESSURE ON SYSTEM DURING AIRCRAFT INSPECTION.  SUBMITTER RECOMMENDED A BETTER Q	UALITY GAUGE BE USED IN SYSTEM.				1	L	7	2 	4T				A24CE
1998022600057	19980226	00057	SO  	1998	2	26	98ZZZX791        	1	19980203	G	2530	LP212872	HOSE            			GULSTM	G1159 	GIV         	3980115	SO  										GALLEY	BURNED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	910B					1102				OUTFITTER - INSTALLED WATER FILL/DRAIN LINES INCORPORATE 120 VAC HEAT ELEMENT.  THREE OCCURRENCES OF THE ELEMENT BURNING	 HOLE IN HOSE.  ONE OF THE OCCURRENCES SINGED THE INSULATION AND SOUNDPROOFING.					2	L	7	2 	4F			RT	A12EA
1998022600059	19980226	00059	SO  	1998	2	26	98ZZZX793        	1	19980127	G	4990	C3444200225	ADAPTER         			GULSTM	G1159 	GIV         	3980115	SO  										APU OIL FILTER	FAILED          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	1PG	853  				1259				DURING OUTFITTING OF THE ACFT, AN ADDITIONAL INDICATION AND BYPASS SYTEM WAS ADDED TO THE APU WHICH INSTALLED AN OIL TEM	P BULB IN THE BOTTOM OF THE OIL FILTER HOUSING.  THE ADAPTER SCREWS INTO THE HOUSING IN ORDER TO ALLOW TEMP BULB, PN MS2	8034-1, TO BE INSTALLED.  THE APU WAS RETURNED FROM REPAIR AND THE MECHANIC, USING MINIMUM TORQUE, ATTEMPTED TO INSTALL 	THE ADAPTER WHICH SHEARED AT THE END OF THE THREADED AREA.  THIS AREA IS VERY THIN DUE TO THE UNDERCUTTING TO ALLOW FOR 	THE O-RING.		2	L	7	2 	4F			RT	A12EA
1998022600060	19980226	00060	EU  	1998	2	26	98ZZZX794        	1	19980206	G	3411		DRAIN VALVE     			BRAERO	DH125 	BAE125800A  	1500285	EU  										STATIC DRAIN	PLUGGED         	B	P		JGVR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	09	961JC					258062				DURING A 24-MONTH PITOT/STATIC SYSTEM CERTIFICATION,  ALL STATIC DRAIN VALVES WERE FOUND SEALED WITH 'RTV' SILICON SEALA	NT.  ONE DRAIN VALVE SPINDLE WAS FOUND TO PASS THROUGH VALVE BUSH WHEN THE STATIC DRAIN WAS CLEARED OF 'RTV'.  THE SPIND	LE HAD BEEN ALTERED TO PASS THROUGH THE DRAIN BUSH.				2	L	7	2 	4F			RT	A3EU
1998022600061	19980226	00061	EU  	1998	2	26	98ZZZX795        	1	19980209	G	3213	25UM403A	SPRING STRUT    			BRAERO	DH125 	BAE125800A  	1500285	EU  										MLG LT SIDE STAY	CORRODED        	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	84FA	6198 				258047				DURING AIRCRAFT PRE-BUY INSPECTION, LT SIDESTAY CLEARANCES COULD NOT BE OBTAINED.  SPRING STRUT WOULD NOT MOVE FULLY IN 	ITS SLOT.  INVESTIGATED CAUSE AND FOUND SPRING STRUT INTERNAL SPRING CORRODED INTO TWO PIECES.  PROBLEM HAS CAUSED FLAT 	SPOTTING ON ROLLER P/N 25UM391.  LACK OF LUBRICATION IS EVIDENT IN BEARINGS IN THE LINK P/N 25-8UM79-1A.				2	L	7	2 	4F			RT	A3EU
1998022600062	19980226	00062	SO  	1998	2	26	98ZZZX796        	1	19980129	G	5720	NAS116551L	BOLTS           			GULSTM	G1159 	G1159B      	3953535	SO  										WINGLET ATTACH	CORRODED        	B		A	LEGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	180AR	11786				148				REMOVED LEFT WING WINGLET ATTACHMENT BOLTS AND SLEEVES TO REMOVE WINGLET FOR ACCESS.  FOUND ALL SIX BOLTS EXCESSIVELY CO	RRODED.  THERE IS NO REQUIRED INSPECTION IN CHAPTER 5 FOR THESE BOLTS.  THERE IS ALSO NO REMOVAL OR INSTALLATION INSTRUC	TIONS FOR WINGLET IN MM.  SUBMITTER RECEIVED SPECIAL INSTRUCTIONS FROM ENGINEERING FOR SEALING AND TORQUES.  SUBMITTER S	UGGESTED WINGLET SHOULD HAVE CHAPTER 5 INSPECTION REQUIREMENT EVERY 5 YEARS, AND PROCEDURE TO INSTALL AND REMOVE.			2	L	7	2 	4F			RT	A12EA
1998022600063	19980226	00063	SO  	1998	2	26	98ZZZX797        	1	19980129	G	5720	NAS116565L	BOLTS           			GULSTM	G1159 	G1159B      	3953535	SO  										WINGLET ATTACH	CORRODED        	B		A	LEGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	180AR	11786				148				REMOVED LEFT WING WINGLET ATTACHMENT BOLTS AND SLEEVES TO REMOVE WINGLET FOR ACCESS.  FOUND ALL SIX BOLTS EXCESSIVELY CO	RRODED.  THERE IS NO REQUIRED INSPECTION IN CHAPTER 5 FOR THESE BOLTS.  THERE IS ALSO NO REMOVAL OR INSTALLATION INSTRUC	TIONS FOR WINGLET IN MM.  SUBMITTER RECEIVED SPECIAL INSTRUCTIONS FROM ENGINEERING FOR SEALING AND TORQUES.  SUBMITTER S	UGGESTED WINGLET SHOULD HAVE CHAPTER 5 INSPECTION REQUIREMENT EVERY 5 YEARS, AND PROCEDURE TO INSTALL AND REMOVE.			2	L	7	2 	4F			RT	A12EA
1998022600064	19980226	00064	SO  	1998	2	26	98ZZZX798        	1	19980129	G	5720	NAS116558L	BOLTS           			GULSTM	G1159 	G1159B      	3953535	SO  										WINGLET ATTACH	CORRODED        	B	S	A	LEGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	180AR	11786				148				REMOVED LEFT WING WINGLET ATTACHMENT BOLTS AND SLEEVES TO REMOVE WINGLET FOR ACCESS.  FOUND ALL SIX BOLTS EXCESSIVELY CO	RRODED.  THERE IS NO REQUIRED INSPECTION IN CHAPTER 5 FOR THESE BOLTS.  THERE IS ALSO NO REMOVAL OR INSTALLATION INSTRUC	TIONS FOR WINGLET IN MM.  SUBMITTER RECEIVED SPECIAL INSTRUCTIONS FROM ENGINEERING FOR SEALING AND TORQUES.  SUBMITTER S	UGGESTED WINGLET SHOULD HAVE CHAPTER 5 INSPECTION REQUIREMENT EVERY 5 YEARS, AND PROCEDURE TO INSTALL AND REMOVE.			2	L	7	2 	4F			RT	A12EA
1998022600066	19980226	00066	EU  	1998	2	26	98ZZZX799        	1	19980124	G	2430	724440250AV2	TERMINAL BLOCK  			BRAERO	DH125 	BAE125800A  	1500285	EU  										DA PANEL	BURNED          	B			QX2R	H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			EA	11	553M	6833 				258027				CREW REPORTED DURING FLIGHT, THE LT ALTERNATOR FAIL LIGHT ILLUMINATED AND A BRIGHT LIGHT WITH SPARKING NOISE CAME FROM I	NSIDE THE DA PANEL AT LEVEL OF COPILOT'S LT ELBOW.  LIGHT SMOKE AND ELEC FIRE SMELL NOTED.  ALTERNATORS SWITCHED OFF AND	 ACFT WAS LANDED.  INSP REVEALED TERMINAL BLOCK HM ON SUBPANEL E OF THE DA PANEL BURNT, AND CB B2 ON PANEL GG FOUND IN T	HE OPEN POSITION.   LT WINDSCREEN ANTI-ICE SYS DISABLED AND ACFT WAS FLOWN TO A REPAIR STATION.  REPLACED DEFECTIVE TERM	INAL BLOCK FROM DA PANEL.  CLEANED AFFECTED WIRES OF SMOKE DAMAGE.  TERMINATED WIRES WITH NEW TERMINALS PN 323758 AND IN	STALLED ON TERMINAL BLOCK.  OPERATION CHECKED W/S HEAT SYS.  PERFORMED OPER CHKS OF RT AND LT GENERATOR CONTROL UNITS.	2	L	7	2 	4F			RT	A3EU
1998022600067	19980226	00067	CE  	1998	2	26	98ZZZX800        	1	19980129	G	7160		FILTER SCREEN   			CESSNA	172   	172R        	2072401	CE  										AIR BOX	DEFECTIVE       	B			RH6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	406ES	22   				17280213				SCREEN HOLDING AIR FILTER IN PLACE IS ONLY SECURED IN LT AND RT VERTICAL POSITION.  TOP AND BOTTOM ARE NOT ATTACHED.  TH	ERE IS A LARGE GAP THAT AIR FILTER CAN FORCE ITSELF THROUGH.  SCREEN IS DISTORTED AND GOING TO PULL OUT OF ATTACH POINTS	.  AIR FLOW COULD PUSH AIR FILTER INTO INDUCTION SYSTEM BLOCKING ALT AIR DOOR AND AIR FLOWS.  AIR FILTER IS ALSO TEARING	 AT BOTTOM.  AD 96.09.06 DEALS WITH SIMILAR PROBLEM.  SUBMITTER STATED ENGINE FAILURE IS IMMINENT.			1	H	7	1 	3O			NT	3A12
1998022600068	19980226	00068	SO  	1998	2	26	98ZZZX801        	2	19980129	G	7322	194593	PLUNGER         			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CARBURETOR ACCEL	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	704AA					15078448	254842A			FOUND SMALL SCARS ON SIDE OF ACCELLERATOR PUMP LEATHER, CAUSED FAULTY ACCELLERATION.  REPLACED WITH NEW UNIT. ACCELLERAT	OR PUMP DID WORK.					1	H	7	1 	3O	3	O		3A19    	E252
1998022600069	19980226	00069	SO  	1998	2	26	98ZZZX802        	2	19980209	G	7414		MAGNETO         			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					RT MAGNETO	MISTIMED        	B		A	FTKR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	94RW					414A0662	813534R			UPON INSTALLATION OF 2 FACTORY REMANUFACTURED ENGINES, DIFFICULTY WAS EXPERIENCED IN GETTING MANIFOLD PRESSURE RPM TO CO	RROLATE BETWEEN ENGINES.   INDIVIDUALLY, BOTH ENGINES MET POWER SPECIFICATIONS.  OPERATION BETWEEN THE ENGINES AT LOWER 	POWER SETTINGS WAS DIFFICULT.  AFTER CONSIDERABLE RIGGING CHANGES, THE RIGHT MAGNETO TO ENGINE TIMING WAS CHECKED.  ENGI	NE WAS TIMED FROM THE FACTORY 10 DEGREES BTC, 10 DEGREES OFF.  TIMING WAS RESET AND NO FURTHER DIFFICULTIES RESULTED.			1	L	7	2 	3O	3	O		A7CE    	E8CE
1998022600070	19980226	00070	CE  	1998	2	26	98ZZZX803        	1	19980114	G	2810	SK18286C	FUEL CAP        			CESSNA	182   	182R        	2072731	CE  										FILL NOZZLE	MISMARKED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	21	9815H					18268044				C/W CESSNA SI TO REMOVE FLUSH-TYPE LARGE OPENING FUEL CAPS AND INSTALLING ABOVE WING CAPS WITH SMALL FILL OPENINGS SUPPL	IED IN KIT SK182-86C.  INSPECTED FILL ADAPTER PLATES PRIOR TO INSTALLATION AND FOUND FUEL CAPS OPEN IN A REVERSE/NON-STA	NDARD DIRECTION.  ORDERED NEW KIT AND FOUND IT CORRECT.  APPEARS STEEL ADAPTER PLATE STAMPED BACKWARDS AT MFG AND ASSEMB	LED WITH ADAPTER RING.  THESE PARTS HAVE 2 INSPECTORS' STAMPS ON THEM.			1	L	7	1 	3O			NT	3A13
1998022600071	19980226	00071	CE  	1998	2	26	98ZZZX804        	1	19980204	G	2822		PUMP            			CESSNA	310   	310Q        	2074242	CE  										FUEL TRANSFER	FAILED          	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	03	999HD					310Q0463				OPERATOR HAS PURCHASED 3 NEW PUMPS FROM CESSNA BETWEEEN NOV 1996 - DEC 1997.  ONE PUMP DEVELOPED A DIRECT SHORT, ONE PUM	P WAS INTERMITTENT, THE OTHER PUMP FAILED.  SUBMITTER STATED THIS IS A MANUFACTURER'S DEFECT.  WEST STAR FURTHER STATED 	THAT SEVERAL PUMPS WERE SOLD DURING THE SAME TIME FRAME.				1	L	7	2 	3O				3A10
1998022600074	19980226	00074	CE  	1998	2	26	98ZZZX806        	1	19980119	G	2912	MS2877422	O-RING          			CESSNA	650   	650         	2076802	CE  										RT HYD FILTER	MISMANUFACTURED 	B		A	GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01	38WP	522  				6500032				ON MAINTENANCE POST-FLIGHT, DISCOVERED RIGHT ENGINE HYDRAULIC MAIN FILTER WET WITH HYDRAULIC FLUID.  INVESTIGATION SHOWE	D LEAKAGE FROM FILTER BOWL SEAL AND TEFLON CHEVRON AREA.  INSPECTION OF O-RING SEAL AND BACK-UP TEFLON RINGS SHOWED BEVE	L DEFECT ON BACK-UP RING LETTING O-RING DEFORM.  THE BACK-UP RING SHOWED BEVELS CUT THE SAME ANGLE PREVENTING OVERLAP FR	OM A SMOOTH SURFACE.  REPLACED O-RING AND BACK-UP RINGS THAT CORRECTED THE CONDITION.  SUBMITTER RECOMMENDED TECHNICIAN'	S ATTENTION TO BACK-UP RING INSPECTION.  AT TIME OF INSTALLATION, PLACE ON FLAT SURFACE AND SEE HOW ENDS OVERLAP FOR A M	ATCHED SMOOTH SURFACE.	2	L	7	2 	4F			 	A9NM
1998022600436	19980226	00436	EU  	1998	2	26	98ZZZX807        	1	19980205	G	2810		FUEL BAY        			ISRAEL	1125  	ASTRASPX    	4500205	EU  										FUEL SYSTEM	CONTAMINATED    	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09		391  				087				CLEANED FUEL BAYS AND REMOVED 14.2 GRAMS OF LOOSE SEALER, METAL SHAVINGS, AND WHOLE AND PARTIAL BOLTS.  AIRCRAFT CANADIA	N REGISTRY.					2	L	7	2 	4F			RT	A16NM
1998022600437	19980226	00437	CE  	1998	2	26	98ZZZX808        	1	19980209	G	2520		BELT GUIDE      			CESSNA	182   	182S        	2072701	CE  										AFT SHOULDER	INTERFERENCE    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	416ES	15   				18280078				REAR SHOULDER BELT GUIDES ON OUTBOARD SIDES OF SEAT BACK STRIKES SHOULDER BELT REEL WHEN SEAT BACK IS RECLINED.  SUBMITT	ER SUGGESTED RE-DESIGNING THE BELT GUIDE OR LIMIT SEAT RECLINE ANGLE.  A LITTLE ENGINEERING REVIEW OF COMPONENT COMPATIB	ILITY WOULD ELIMINATE THESE TYPE PROBLEMS AT AN EARLY STAGE.				1	H	7	1 	3O			NT	3A13
1998022600438	19980226	00438	CE  	1998	2	26	98ZZZX809        	1	19980209	G	2520		SEAT FRAME      			CESSNA	182   	182S        	2072701	CE  										REAR SEAT	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	416ES	15   				18280078				REAR SEAT BOTTOM FRAME ATTACH POSITIONS DO NOT MATCH ALL 6 FUSELAGE MOUNTINGS BRACKET POSITIONS AND REQUIRES THE USE OF 	A 7 FOOT LONG 2 INCH BY 6 INCH LEVER TO FORCE ALIGNMENT AND INSTALL BOLTS.  SUGGEST MATCHING ALL PRODUCTION JIGS AND MUC	H IMPROVED SUPERVISION AND INSPECTION PROCEDURES RATHER THAN ALLOWING PRODUCTION CREWS TO USE BRUTE FORCE TO INSTALL A C	OMPONENT.			1	H	7	1 	3O			NT	3A13
1998022600439	19980226	00439	CE  	1998	2	26	98ZZZX810        	1	19980209	G	2434	991059111	ALTERNATOR      			CESSNA	182   	182S        	2072701	CE  										DC SYSTEM	SEIZED          	D				O				OTHER                   				H	W		ELECT. POWER LOSS-50 PC   	INADEQUATE Q C            		IN	INSP/MAINT     	1			WP	23	416ES	9    			A124384	18280078				ORIGINAL ALTERNATOR REPLACED AT THE FACTORY AFTER FACTORY FLIGHT TEST WAS COMPLETED DUE TO SUSPECTED UNDERSIZE WIRE PROB	LEM.  POST-FLIGHT INSPECTION AFTER 9:25 HOURS FERRYING FLIGHT HOME AND COOL DOWN FOUND THE ALTERNATOR FROZE AND POWDERED	 RUBBER STREAKS ON THE RIGHT COWL.  RECOMMEND BETTER VENDOR QUALITY CONTROL.				1	H	7	1 	3O			NT	3A13
1998022600440	19980226	00440	CE  	1998	2	26	98ZZZX811        	1	19980209	G	2520		SEAT BELT       	PACIFICSCIEN		CESSNA	182   	182S        	2072701	CE  										CABIN	BINDING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	416ES	15   			45402	18280078				REAR LAP BELTS ARE RESTRAINED FROM RETRACTING AS REQUIRED TO UNLOCK THE REEL AND ALLOW FULL EXTENSION FOR USE DUE TO FRI	CTION CAUSED BY ROUTING BETWEEN THE TIGHT FITTING SEAT BOTTOM AND SEAT BACK.  SUGGEST INSTALLING A FLAT PLASTIC 'TUNNEL'	 AROUND THE BELT TO ELIMINATE INTERFERENCE AND A LITTLE ENGINEERING REVIEW OF COMPONENT COMPATABILITY AFTER INSTALLATION	 IN THE AIRCRAFT.			1	H	7	1 	3O			NT	3A13
1998022600441	19980226	00441	CE  	1998	2	26	98ZZZX812        	1	19980209	G	2711		CONTROL CABLE   			CESSNA	182   	182S        	2072701	CE  										AIL TRIM TAB	MISROUTED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	416ES	15   				18280078				ONE TRIM TAB CABLE INSTALLED BETWEEN THE TWO PULLEYS AFT OF THE BAGGAGE COMPARTMENT.  SUBMITTER STATED BETTER SUPERVISIO	N ON THE PRODUCTION LINE AND COMPETENT INSPECTION WOULD AVOID THESE TYPE PROBLEMS.					1	H	7	1 	3O			NT	3A13
1998022600443	19980226	00443	GL  	1998	2	26	98ZZZX814        	1	19980204	G	3213	28171324	SKID LEG        			ENSTRM	F28   	280F        	3300550	GL  										LT AFT GEAR	BROKEN          	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	199TV	3918 				1510				DURING GROUND HANDLING OF THE HELICOPTER, THE LEFT AFT LANDING GEAR LEG PN 28-17132-4 BROKE DUE TO INTERNAL CORROSION. T	HE 4130 TUBING IS NOT SEALED AND FLYING IN RAIN OR BY WASHING AIRCRAFT WATER CAN ENTER TUBING AND HAS NO WAY OF DRAINING	 OUT.  ENSTROM SDB 0079 PERTAINS TO THIS PROBLEM.  SUBMITTER RECOMMENDED SDB 0079 BECOME AN AD.  NEW REPLACEMENT TUBES A	RE BETTER CONSTRUCTED AND WILL PREVENT CORROSION OR CRACKS FROM DEVELOPING.			1	G	7	1 	3O				H1CE
1998022600444	19980226	00444	SW  	1998	2	26	98ZZZX815        	1	19980205	G	7714	65013008	GAUGE           			BELL  	206   	206B        	1181511	SW  										N1 TACH	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	9907K		5    		1487D	2040				N1 WILL NOT GO PAST 13 PERCENT ON START AND SMALL NEEDLE DOES NOT CORRELATE WITH OUTSIDE SCALE NEEDLE.						1	G	7	1 	3U				H2SW
1998022600445	19980226	00445	WP  	1998	2	26	98ZZZX816        	1	19980102	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE EXHAUST	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	34   				900901D				EXHAUST STACK CRACKED BEYOND REPAIR.  SENT FOR ANALYSIS (METAL).  UNREPAIRABLE PER MCDONALD DOUGLAS MM.  THIS EXHAUST UN	IT ONLY HAS 34.0 HOURS TIS.					1	G	7	1 	3U				H3WE
1998022600446	19980226	00446	WP  	1998	2	26	98ZZZX817        	1	19980102	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE EXHAUST	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J	54   				900801D				EXHAUST STACK CRACKED BEYOND REPAIR.  SENT FOR ANALYSIS (METAL).  UNREPAIRABLE PER MCDONALD DOUGLAS MM.  THIS UNIT ONLY 	HAS 53.6 HOURS TIS.					1	G	7	1 	3U				H3WE
1998022600447	19980226	00447	WP  	1998	2	26	98ZZZX818        	1	19980102	G	7810	369A8230504	EXHAUST STACK   			HUGHES	369   	369D        	4470706	WP  										ENGINE EXHAUST	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				EXHAUST STACK CRACKED BEYOND REPAIR.  SENT FOR ANALYSIS (METAL).  UNREPAIRABLE PER MCDONALD DOUGLAS MM.  SUBMITTER STATE	D BECAUSE OF AMOUNT OF CRACKED STACKS, ALL WERE SENT FOR METAL ANALYSIS.					1	G	7	1 	3U				H3WE
1998030300013	19980303	00013	GL  	1998	3	3	98ZZZX819        	2	19980115	G	7230	6896888	SCROLL          			BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE COMP	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	404W		1360 		AP27963	52055	CAE895742			DURING SCHEDULED 100-HOUR INSPECTION, DISCOVERED COMPRESSOR SCROLL CRACKED IN ABOUT 2 O'CLOCK AREA OF RIGHT SHOULDER IN 	THE CURVATURE NEAR THE MATING SURFACE TO THE COMPRESSOR.  THIS WAS A REPAIRED SCROLL THAT HAD BEEN INSTALLED DUE TO A PR	EVIOUSLY CRACKED SCROLL WHEN THE ENGINE ONLY HAD 712.3 HOURS TIME SINCE NEW.  THE REPAIRED SCROLL ACCRUED 1,359.6 HOURS 	TIME SINCE REPAIR BEFORE IT FAILED IN THE SAME AREA AS THE PREVIOUS SCROLL THAT CRACKED.			1	G	7	1 	3U	3	U	NC	H2SW    	E1GL
1998022600448	19980226	00448	CE  	1998	2	26	98ZZZX820        	1	19980101	G	3411	201314218	AIR VALVE       			CESSNA	172   	172R        	2072401	CE  										ALTERNATE STATIC	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9715F					17280030				C/W AD 98-01-01 ALTERNATE STATIC AIR SOURCE VALVE WAS NOT RESTRICTED BY PLACARD AND BODY WOULD NOT SEPARATE FROM FLANGE.						1	H	7	1 	3O			NT	3A12
1998022600449	19980226	00449	SO  	1998	2	26	98ZZZX821        	1	19980204	G	2820	6515217	LINE ASSY       			PIPER 	PA28  	PA28235     	7102810	SO  										VLV TO LT TANK	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	11	8525N	2362 				2811324				DURING ANNUAL INSPECTION, FOUND MAIN LT FUEL SUPPLY LINE TO FUEL CONTROL VALVE WITH ONE OLD WET FUEL STAIN AND ONE NEW F	UEL WET STAIN.  INSPECTED AND FOUND HARD FUEL LINE CRACKED IN TWO LOCATIONS.					1	L	7	1 	3O				2A13
1998022600450	19980226	00450	CE  	1998	2	26	98ZZZX822        	1	19980204	G	2731	1260505146	CONTROL CABLE   			CESSNA	206   	U206F       	2073333	CE  										ELEV TRIM	MISMANUFACTURED 	B			V2AR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	8552Q					U206003408				ELEVATOR TRIM WOULD NOT RIG PER TCD'S.  AFTER MUCH WORK, ALL 4 CABLES WERE REPLACED.  AFT LT CABLE WAS FOUND TO BE 2 INC	HES LONGER THAN NEW ONE.  ONE END WAS FABRICATED FOR A CUT DOWN AN 569-S2L, CUT OFF AND DRILLED TO ACCEPT CHAIN LINK.  C	HAIN, PN S2295-25-47, HAD BEEN SHORTENED TO ALLOW CABLE TENSION TO BE SET.  AFTER INSTALLATION OF NEW PARTS, TRIM WAS RI	GGED WITHOUT DIFFICULTY.			1	H	7	1 	3O			 	A4CE
1998022600451	19980226	00451	SO  	1998	2	26	98ZZZX823        	1	19980110	G	5513	63587003	RIB             		6358500     	PIPER 	PA32  	PA32300     	7103212	SO  										LT STAB TRIM TAB	CRACKED         	B			NCLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	8917N	7161 				3240709				DURING ANNUAL INSPECTION, THE LT STABILATOR TRIM TAB INBOARD RIB WAS FOUND CRACKED.						1	L	7	1 	3O				A3SO
1998022600452	19980226	00452	SO  	1998	2	26	98ZZZX824        	2	19980126	G	8530		CYLINDER ASSY   			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					INT VLV SEAT	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	97523	589  				18267119	467992			DURING ANNUAL COMPRESSION CHECK, FOUND CYLINDERS COMP LOW.  INSPECTED CYLINDERS, FOUND INTAKE VALVES SEAT EXCESSIVELY WO	RN.  FURTHER INSPECTION FOUND ALL CERMACHROME ON CYLINDERS WORN AWAY.  ALL CYLINDERS REPLACED WITH FACTORY NEW CYLINDERS	.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1998022600453	19980226	00453	CE  	1998	2	26	98ZZZX825        	1	19980101	G	2720	365240795	CONTROL CABLE   			BEECH 	36    	A36         	1151604	CE  										RUDDER	MISINSTALLED    	B			DEBR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	246DY	252  				E3065				ON FIRST ANNUAL INSPECTION, RT RUDDER CABLE ASSY WAS FOUND INSTALLED OVER THE TOP OF PULLEY GUARD AT FS 257.6 AFT.  PULL	EY P/N MS24566-4B.  ON INSPECTION OF CABLE, FOUND BROKEN STRANDS FROM WEARING OVER PIN.					1	L	7	1 	3O			 	3A15
1998022600454	19980226	00454		1998	2	26	98ZZZX826        	4	19980122	G	6113	587330	BULKHEAD        			PIPER 	PA28  	PA28151     	7102805	SO  										SPINNER AFT	CRACKED         	B			MOGR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	25	808RK	605  				287415225				DURING ANNUAL INSPECTION, FOUND BOTH SPINNER BULKHEADS CRACKED.  CAUSE BELIEVED TO BE BALANCE WEIGHT INSTALLED ON FORWAR	D BULKHEAD BY PERSONS UNKNOWN.  REPLACED BULKHEAD WITH NEW UNIT.					1	L	7	1 	3O			 	2A13
1998022600455	19980226	00455	SO  	1998	2	26	98ZZZX827        	1	19980113	G	2750	6273800	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  										FLAP LEVER	CRACKED         	B	S		NCLR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	7479R	3452 				2822023				DURING C/W PIPER AD 96-11-03 (FLAP HANDLE ATTACH BOLT), FOUND 3 OF THE 4 CORNERS OF THE MOUNTING FLANGES WERE CRACKED AT	 THE RELIEF CUTS.					1	L	7	1 	3O				2A13
1998022600456	19980226	00456	SO  	1998	2	26	98ZZZX828        	1	19980108	G	3230	4693300	LINK ASSY       			PIPER 	PA42  	PA42        	7104202	SO  										NLG LOWER LUG	FAILED          	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	116JP					428001050				JANUARY 8, AIRCRAFT LANDED AND THE NOSE GEAR COLLAPSED.  INITIAL INVESTIGATION REVEALED A LINK ASSY FAILURE.  THE MECHAN	ICAL LINKAGE OF NOSE GEAR ASSY IS SUCH THAT IT WILL NOT INDICATE A GEAR UNSAFE CONDITION.  SUBMITTER RECOMMENDED A SPECI	AL INSPECTION FOR LINK ASSY.				1	L	7	2 	4T				A23SO
1998022600457	19980226	00457	SO  	1998	2	26	98ZZZX829        	2	19980131	G	7414	10357174	BREAKER ASSY    	BENDIX      	S6LN25      	CESSNA	337   	337         	2075702	CE  	CONT  	O360  	IO360C      	17025	SO  					RT MAG POINTS	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	337LA	266  			831392	3370134	12551335D			THE FAILURE OF THE RT MAG ON THE REAR ENGINE WAS NOTICED DURING A PRE-TAKEOFF MAG CHECK.						1	H	7	2 	3O	3	O		A6CE    	E1CE
1998022600458	19980226	00458		1998	2	26	98ZZZX830        	2	19980202	G	7322	MA4SPA	CARBURETOR      			AMTR  		LONGEZ      			LYC   		O320*       							ENGINE	FLOODS          	D				K				NONE                    				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			EA	07	27PM					1309				ENGINE RAN ROUGH AND WANTED TO QUIT AT LOWER POWER SETTINGS.  POST INCIDENT INSPECTION WITH THROTTLE OFF AND MIXTURE IDL	E CUT-OFF, BOOST PUMP ON, FUEL POURED OUT OF CARBURETOR.  CARBURETOR SENT BACK TO CONSOLIDATED.  SUBMITTER SUSPECTED FLO	AT PROBLEM.							0
1998022600460	19980226	00460	CE  	1998	2	26	98ZZZX832        	1	19980202	G	5210	05170193	HINGE           		24170031    	CESSNA	172   	172P        	2072436	CE  										LT CABIN DOOR	CRACKED         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	504MA	4592 				17275917				DURING PRE-FLIGHT INSPECTION, LEFT CABIN DOOR, LOWER FORWARD HINGE WAS FOUND CRACKED. REPLACED HINGE HALF.						1	H	7	1 	3O			NT	3A12
1998022600461	19980226	00461	CE  	1998	2	26	98ZZZX833        	1	19980209	G	3610	909700323	LINE            			BEECH 	90    	E90         	1152914	CE  										LT PNEUMATIC	CORRODED        	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	47AW	5755 				LW130				FOUND BOTH PNEUMATIC LINES AFT OF FIREWALL SEVERELY CORRODED WHERE AN ADELL CLAMP WENT.  INSTALLED NEW LEFT AND RIGHT PN	EUMATIC LINES.  SUBMITTER SUGGESTED CLOSE INSPECTION OF THESE LINES ON THESE OLDER AIRCRAFT.					1	L	7	2 	3T				3A20
1998022600462	19980226	00462	CE  	1998	2	26	98ZZZX834        	1	19980209	G	3610	909700213	LINE            			BEECH 	90    	E90         	1152914	CE  										LT PNEUMATIC	CORRODED        	B			EWGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	47AW	5755 				LW130				FOUND BOTH PNEUMATIC LINES AFT OF FIREWALL SEVERELY CORRODED WHERE AN ADELL CLAMP WENT.  INSTALLED NEW LEFT AND RIGHT PN	EUMATIC LINES.  SUBMITTER SUGGESTED CLOSE INSPECTION OF THESE LINES ON THESE OLDER AIRCRAFT.					1	L	7	2 	3T				3A20
1998022600463	19980226	00463	SO  	1998	2	26	98ZZZX835        	1	19980209	G	3221	9572300	TRUNNION ASSY   			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	FAILED          	D				K				NONE                    				O			OTHER                     			LD	LANDING        	1			WP	23	4581T	9800 				347250139				TRUNNION BROKE AT UPPER RIGHT ATTACH/PIVOT AREA AS A RESULT FROM HARD LANDING.  TRUNNION MAY HAVE HAD SMALL CRACK AT WEL	D AREA PRIOR TO HARD LANDING.  SUBMITTER RECOMMENDED REMOVING PAINT FROM BOTH UPPER TRUNNION AREAS (ESPECIALLY AROUND WE	LDS) AND INSPECT WITH HIGH POWER GLASS EACH 50 HOURS.  CAUSED COMPLETE NOSE GEAR COLLAPSE AND PROPELLER STRIKES.				1	L	7	2 	3O				A7SO
1998022600465	19980226	00465	SO  	1998	2	26	98ZZZX837        	2	19980115	G	8550	640766A4	SCAVENGE PUMP   		642087A28   	PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					TURBO OIL	FAILED          	B			FTKR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	19	357MM	821  			X89HEN	468508092	528514			ACFT UNDERWENT SCHEDULED 50-HR INSP.  UPON POST-INSP AND RUN AND LEAK TEST, OIL NOTED COMING FROM TURBOCHARGER OUTLETS A	ND WASTEGATE SEAL DRAIN.  FURTHER INVESTIGATION REVEALED SCAVENGE PUMP FAILURE.  UPON DISASSY, END BEARING FOUND LOOSE C	AUSING A BREAK IN SECTION AND SUBSEQUENT PUMP FAILURE.  TURBOCHARGERS AND WASTGATE SENT FOR REPAIR.  ENGINE REMOVED FOR 	STARTER ADAPTER REMOVAL.  INSP REVEALED SCAVENGE PUMP'S RETAINING CLIP FOR END BEARING WAS NOT INSTALLED AND NO GROOVE I	N SCAVENGE HOUSING FOR RETAINER CLIP.  A SERVICEABLE HOUSING, NEW BEARING, AND GEARS INSTALLED.  ACFT REASSEMBLED AND TE	STED WITH NO FURTHER DEFECTS.  1-15-98 HOBBS:  1387.4  TSN:  821.2 HRS	1	L	7	1 	3O	3	O		A25SO   	E8CE
1998022600466	19980226	00466	SO  	1998	2	26	98ZZZX838        	1	19980208	G	3230	452334	ROD END BEARING 			PIPER 	PA34  	PA34200     	7103405	SO  										NLG DWNLK LINK	BROKEN          	D	S	A		K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	1045U	44   				347250029				INVESTIGATION AFTER SENECA NOSE GEAR COLLAPSE REVEALED BROKEN ROD END BEARING, P/N 452-334, ON DOWNLOCK LINK ASSY.  SUBM	ITTER SUGGESTED POSSIBLE CAUSES AS UNREPORTED HARD LANDING AND/OR DEFECTIVE ROD END.					1	L	7	2 	3O				A7SO
1998022600467	19980226	00467	SO  	1998	2	26	98ZZZX839        	1	19980209	G	2842	6810102	SENDER          	STWARNER    		PIPER 	PA28  	PA28*       		SO  										RT FUEL TANK	FAILED          	D				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	13										SUDDENLY, RT FUEL TANK INDICATED TOTALLY EMPTY.  FLIGHT WAS TERMINATED AND FUEL QUANTITY VISUALLY VERIFIED AS NEARLY ONE	-HALF FULL.  TANK WAS TOPPED OFF AND STILL INDICATED BONE DRY.  MECHANICS TESTED GAUGE WITH A VARIABLE RESISTOR INSERTED	 IN GROUND CIRCUIT AND GAUGE INDICATED AS SPECIFIED IN ACFT MM.  THEN, WHEN FUEL TANK REMOVED, DISCOVERED THE FLOAT HAD 	WORN THROUGH AND FALLEN OFF OF THE SENDING UNIT ARM, WHICH, OF COURSE, ACTED JUST AS IT WOULD IF THE FLOAT WAS AT A LEVE	L NEAR THE BOTTOM OF THE TANK, IT INDICATED AN EMPTY TANK.  FLOAT RE-ATTACHED TO THE SENDER'S ARM AND OPERATES AS  ADVER	TISED ONCE AGAIN.	1	L	7	1 	3O				2A13
1998022600468	19980226	00468	SW  	1998	2	26	98ZZZX840        	1	19980209	G	2840	3033	HOSE            			MOONEY	M20   	M20F        	5870214	SW  										FUEL GAUGE	LEAKING         	D		A		K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13										PILOT COMPLAINED THAT FOLLOWING THE LAST SEVERAL FLIGHTS, HE HAD NOTICED FUEL DRIPPING FROM THE RT SIDE OF THE COWLING. 	 MECHANICS THEN PRESSURIZED THE FUEL SYS WITH THE PUMP AND SAW A FAN-SHAPED SPRAY PATTERN EMITTING FROM THE FUEL LINE WH	ICH LEADS TO THE COCKPIT PRESSURE GAUGE BETWEEN THE FUEL CONTROL AND THE FIREWALL.  THIS SPRAY PATTERN WAS IMPACTING DIR	ECTLY ON AN EXHAUST DOWN TUBE.			1	L	7	1 	3O				2A3
1998022600469	19980226	00469	CE  	1998	2	26	98ZZZX841        	1	19980123	G	2820		FUEL SYSTEM     			CESSNA	172   	172R        	2072401	CE  										LT/RT SYSTEMS	MALFUNCTIONED   	B			N3XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	401ER	500  				17280159				THIS OPERATOR HAS A FLEET OF CESSNA 172R AIRCRAFT (15).  THERE IS A TREND DEVELOPING WHERE THE PILOTS WRITE UP THE FUEL 	SYSTEM FOR UNEVEN BURN FROM LT AND RT TANKS WHEN THE FUEL SELECTOR IS ON 'BOTH'.  THERE IS NO DEFINITIVE REPAIR YET, BUT	 THE PROBLEM IS BECOMING MORE REPETITIVE.  THE INVESTIGATION IS ONGOING.				1	H	7	1 	3O			NT	3A12
1998022600470	19980226	00470	CE  	1998	2	26	98ZZZX842        	1	19980123	G	2820		FUEL SYSTEM     			CESSNA	172   	172R        	2072401	CE  										LT/RT SYSTEMS	MALFUNCTIONED   	B		A	N3XR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	417ER	500  				17280305				THIS OPERATOR HAS A FLEET OF CESSNA 172R AIRCRAFT (15).  THERE IS A TREND DEVELOPING WHERE THE PILOTS WRITE UP THE FUEL 	SYSTEM FOR UNEVEN BURN FROM LT AND RT TANKS WHEN THE FUEL SELECTOR IS ON 'BOTH'. THERE IS NO DEFINITIVE REPAIR YET, BUT 	THE PROBLEM IS BECOMING MORE REPETITIVE.  THE INVESTIGATION IS ONGOING.				1	H	7	1 	3O			NT	3A12
1998022600861	19980226	00861	WP  	1998	2	26	98ZZZX843        	1	19980211	G	2780	1451311	VALVE BODY      	WHITTAKER   	240705      	DOUG  	DC10  	DC10*       		WP  										FLT CONT BYPASS	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19					126					FLIGHT CONTROL BYPASS VALVE HAS HAD SEVERAL INSTANCES WHERE THE VALVE BODY HAS BEEN CRACKED.  VALVE CRACKED IN RADIUS BE	TWEEN INSIDE DIAMETER AND BOTTOM OF BODY.					2	L	7	3 	4F				A22WE
1998022600862	19980226	00862	WP  	1998	2	26	98ZZZX844        	1	19980211	G	2780	1451311	VALVE BODY      	WHITTAKER   	240705      	DOUG  	DC10  	DC10*       		WP  										FLT CONT BYPASS	CRACKED         	B			DM4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	19					123					HAD SEVERAL INSTANCES WHERE FLIGHT CONTROL VALVE BODY WAS CRACKED.  CRACK IS LOCATED IN THREAD RELIEF AREA.						2	L	7	3 	4F				A22WE
1998022600863	19980226	00863	CE  	1998	2	26	98ZZZX845        	1	19980204	G	3710	LW12540	ADAPTER         			BEECH 	65    	L23F        	1152804	CE  										VACUUM SYSTEM	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	115HF					LF56				ADAPTER IS INSTALLED ON A BEECHCRAFT MODEL 65 WITH EXCALIBUR CONVERSION.  SUBMITTER STATED HAVE HAD NUMEROUS VACUUM ADAP	TERS CRACK.  TOTAL TIME ON PART SINCE NEW 89.3 HOURS.					1	L	7	2 	3O				3A20
1998022600864	19980226	00864	SO  	1998	2	26	98ZZZX846        	1	19980203	G	7120	2149700	MOUNT           			PIPER 	PA24  	PA24        	7102402	SO  										ENGINE	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	6593P					241715				DISCOVERED CRACKED HORIZONTAL TUBE MEMBER ON ENGINE MOUNT.  THE CRACKED MEMBER IS THE .50 INCH DIAMETER TUBE RUNNING FRO	M THE OUTSIDE .6250 INCH TUBE TO THE CENTER LANDING GEAR MOUNTING POSITION.  THIS CONDITION WAS DISCOVERED DURING AN ANN	UAL INSPECTION.  NO EVIDENCE OF A HARD LANDING.  AIRCRAFT TOTAL TIME 3,100 HOURS.				1	L	7	1 	3O				1A15
1998022600865	19980226	00865	SW  	1998	2	26	98ZZZX847        	1	19980202	G	2435	99121252	STARTER         			GULSTM	560   	560         	0141402	SW  										BRUSH END	FAILED          	B	L		AC1R	K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			SO	01	356WC	182  			1561X2	5600432				WHILE T/S A VIBRATION, THE RT STARTER/GEN WAS FOUND TO HAVE A BAD VIBRATION.  LISTENING TO RUN DOWN OF THE ENGINES AFTER	 MOTORING THEM TO 10 PERCENT, THE RT STARTER MADE AN UNUSUAL NOISE.  WHEN STARTER WAS REMOVED, INSP REVEALED THE BRUSH E	ND BEARING HAD FAILED.  THERE WAS EXCESS PLAY IN THE SHAFT AND PART OF THE BEARING CAGE FELL OUT.  A REPLACEMENT STARTER	 INSTALLED.  OPER  CHK REVEALED THE STARTER WAS THE SOURCE OF THE VIBRATION.  CESSNA ACFT CONTACTED US TO GET THE TT.  A	PPARENTLY,  A BEARING PROBLEM WITH THIS MODEL STARTER.  SB 560-80-03 IS IN THE WORKS TO ADDRESS THIS PROBLEM.  SUBMITTER	 STATED OPERATORS SHOULD BE ADVISED TO LOOK FOR BEARING GREASE BEING SLUNG FROM THE BEARING.	1	H	7	2 	3O				6A1
1998022600866	19980226	00866	EA  	1998	2	26	98ZZZX848        	2	19980212	G	7314	LW13909	PUMP            			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE FUEL	LEAKING         	B			KRTR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	09	245S	106  			D8739	4636104	L980961A			FUEL PUMP GASKET BLOWN OUT AND PUMPS LEAK AT THE ADJUSTMENT VALVE PARTING SURFACE GASKET.  SUBMITTER STATED THIS IS THE 	SECOND PUMP FAILURE ON THIS MODEL AIRPLANE, AND BOTH WERE NEW AIRCRAFT.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1998022600867	19980226	00867	CE  	1998	2	26	98ZZZX849        	1	19980212	G	2820		FUEL SYSTEM     			CESSNA	500   	550         	2076604	CE  										LT WING	LEAK            	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	75ZA					5500214				DURING RELEASING AIRCRAFT FOR WORK ALREADY DONE, NOTED EXCESSIVE FUEL LEAKING (CLASS D, TYPE 4) UNDER LEFT WING, INBOARD	 OF WHEEL AND BEHIND LEFT WING HEATED LEADING EDGE.  ALSO, NOTED THE NOSE TIRE WAS CUT TO THE CORD AND REPLACEMENT IS RE	QUIRED.  CUSTOMER WAS NOTIFIED VERBALLY AND WITH LETTER IN REGARDS TO FINDINGS AND AIRWORTHINESS.  CUSTOMER SAID HE WILL	 REPAIR AT A LATER DATE.			1	L	7	2 	4F				A22CE
1998022600870	19980226	00870	EU  	1998	2	26	98ZZZX850        	1	19980211	G	5711		SPAR CAP        			AMD   	FALC20	FALCOND     	2720304	EU  										RT WING	CRACKED         	B		A	EUJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	218CR					218				INSPECTION FOUND LOWER SPAR CAP CRACKED ON RT WING.  LENGTH OF CRACK IS APPROXIMATELY 32 INCHES LOCATED IN RADIUS.  A ST	ANDARD REPAIR WILL BE ACCOMPLISHED USING FALCON SRM.  TOTAL AIRCRAFT TIME, 22,326.5 HOURS.  LANDINGS, 16,576.  CRACK WAS	 DISCOVERED WHILE INSPECTING FOR FUEL LEAKS.				2	L	7	2 	4F				A7EU
1998022600871	19980226	00871	CE  	1998	2	26	98ZZZX851        	1	19980211	G	3030	420241	STATIC PLATE    			RAYTHN	DH125 	HAWKER800XP 		CE  										PITOT STATIC AI	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	2286U	74   			2353	258336				DURING 30-DAY INSPECTION, DISCOVERED BOTH STATIC PLATES WERE NOT HEATING.  AIRCRAFT WAS FERRIED TO MANUFACTURER'S FACILI	TY WHERE STATIC PLATES WERE REPLACED.  OPERATIONAL CHECKED OK.					2	L	7	2 	4F			RT	A3EU
1998022600873	19980226	00873	EU  	1998	2	26	98ZZZX853        	1	19980203	G	7120	NAS567C49	BOLT            	LORD        		AMD   	FALC50	FALCON50MYST	2730106	EU  										ENGINE MOUNT	SEIZED          	B			AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	50FJ	322  				254				ENGINES NR 1 AND NR 3 WERE BEING REMOVED FOR MAINTENANCE.  WHEN THE UPPER MOUNT BOLTS, WHICH ATTACH ENGINES TO THE AIR F	RAME, WERE BEING REMOVED THE BOLT STOPPED TURNING AND WAS FROZEN SOLID INTO ENGINE MOUNT.  BOLT HEAD WAS CUT OFF TO REMO	VE ENGINE.  BOLT IS MADE OF STAINLESS STEEL.  UPPER MOUNT AND BOLT REQUIRED REPLACEMENT.  LOWER MOUNT BOLT WAS REMOVED W	ITH NO THREAD DAMAGE.			2	L	7	3 	4F				A46EU
1998022600874	19980226	00874	EU  	1998	2	26	98ZZZX854        	1	19980203	G	7120	NAS567C49	BOLT            	LORD        		AMD   	FALC50	FALCON50MYST	2730106	EU  										ENGINE MOUNT	SEIZED          	B			AN3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	PTWSC	322  				253				ENGINE NR 1 WAS BEING REMOVED FOR MAINTENANCE.  WHEN THE UPPER MOUNT BOLT, WHICH ATTACHES ENGINE TO AIR FRAME WAS BEING 	REMOVED, THE BOLT STOPPED TURNING AND WAS FROZEN SOLID INTO ENGINE MOUNT.  BOLT HEAD WAS CUT OFF TO REMOVE ENGINE.  BOLT	 IS MADE OF STAINLESS STEEL.  UPPER MOUNT AND BOLT REQUIRED REPLACEMENT.  LOWER MOUNT BOLT WAS REMOVED WITH NO THREAD DA	MAGE.			2	L	7	3 	4F				A46EU
1998030500001	19980305	00001	NE  	1998	3	5	98ZZZX855        	3	19980124	G	6111	7756722	BLADE PIN       		SFA13N10A   	DHAV  	DHC8  	DHC8*       		NM  						HAMSTD	14SF	14SF23      	NE  	PROPELLER BLADE	LOOSE           	B			BN4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					87365623					REFERENCE:  FR34201.  REASON FOR REMOVAL: LOOSE BLADE PIN.  RECOMMENDATIONS:  BLADE HISTORY TO BE REVIEWED FOR PIN INSTA	LLATION ISSUES.  CUSTOMER:  ALM ANTILLEAN AIRLINES.					2	H	7	2 	4T			RT	A13NM   		6	C	P7NE
1998030500004	19980305	00004	EA  	1998	3	5	98ZZZX858        	1	19980207	G	3250	71025	LVDT            			CNDAIR	CL601 	CL6013A     	8070802	EA  										NLG STEERING	DIRTY           	D				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EA	25	399SW	4981 				5009				NOSE WHEEL STEERING FAILED DURING TAXI FOR TAKEOFF AT KEWR.  PERFORMED NOSE WHEEL STEERING CONTROL BOX BITE CHECK PER MM	 32-50-00, NO FAULTS INDICATED.  PERFORMED INSPECTION OF CONNECTORS AND FOUND THE LINEAR VARIABLE DIFFERENTIAL TRANSFORM	ER (LVDT) DIRTY WITH TRACES OF GLYCOL.  CLEANED THE LVDT AND PERFORMED CHECK IAW MM 32-50-00.  ALL CHECKS NORMAL.				2	L	7	2 	4F			RT	A21EA
1998030500005	19980305	00005		1998	3	5	98ZZZX859        	4	19980218	G	2562	RS2B	RESISTOR        	POINTER     	30001       	CESSNA	650   	650         	2076802	CE  										ELT	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	510SD	644  			323189	6500161				RESISTOR HAD OVERHEATED CAUSING HEAT DAMAGE TO THE CASE AND PC BOARD. THE DECAL ON THE OUTSIDE OF THE CASE WAS DISCOLORE	D.  ACCORDING TO THE AIRCRAFT RECORDS, THE LAST ELT OF THIS TYPE WAS ALSO REPLACED BECAUSE OF INTERNAL HEAT DAMAGE. SUBM	ITT ER STATED A DIFFERENT RESISTOR SHOULD BE USED.				2	L	7	2 	4F				A9NM
1998030500006	19980305	00006		1998	3	5	98ZZZX860        	4	19980213	G	3445	M3901661052	RELAY           			BAG   	BAE146	BAE146200A  	1500266	EU  										TCAS SYSTEM	MALFUNCTIONED   	B			AY55	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	816AS					E2087				THE FOLLOWING WAS FOUND DURING FUNCTIONAL TEST OF TCAS DURING AIRCRAFT INSPECTION.  COULD NOT OBTAIN CLIMB ADVISORY ON T	CAS.  TROUBLESHOT AND FOUND THAT CLIMB INHIBIT WAS ACTIVATED DUE TO 2 EACH RELAYS INOP (COILS OPEN).  ONE RELAY IS LOCAT	ED AT 3440-K1 AND THE OTHER IS LOCATED AT 3440-K2. CONFIRMED PROPER OPERATION IN CLIMB INHIBIT MODE.  REPLACED BOTH RELA	YS AND OPERATIONAL TEST PERFORMED GOOD.  NOTE:  TCAS INDICATOR DOES NOT DISPLAY CLIMB INHIBIT MODE AT ANY TIME AS NORMAL	 OPERATION.		2	H	7	4 	4F			RT	A49EU
1998030500007	19980305	00007		1998	3	5	98ZZZX861        	4	19980213	G	3445	M3901661052	RELAY           			BAG   	BAE146	BAE146200A  	1500266	EU  										TCAS SYSTEM	MALFUNCTIONED   	B			AY55	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	815AS					E2084				THE FOLLOWING WAS FOUND DURING FUNCTIONAL TEST OF TCAS DURING AIRCRAFT INSPECTION.  COULD NOT OBTAIN CLIMB ADVISORY ON T	CAS. TROUBLESHOT AND FOUND THAT CLIMB INHIBIT WAS ACTIVATED DUE TO 2 EACH RELAYS INOP (COILS OPEN).  ONE RELAY IS LOCATE	D AT 3440-K1 AND THE OTHER IS LOCATED AT 3440-K2.  CONFIRMED PROPER OPERATION IN CLIMB INHIBIT MODE.  REPLACED BOTH RELA	YS AND OPERATIONAL TEST PERFORMED GOOD.  NOTE:  TCAS INDICATOR DOES NOT DISPLAY CLIMB INHIBIT MODE AT ANY TIME AS NORMAL	 OPERATION.		2	H	7	4 	4F			RT	A49EU
1998030500008	19980305	00008	CE  	1998	3	5	98ZZZX862        	1	19980206	G	2730	1156100153	TORQUE TUBE     			BEECH 	99    	C99         	1154006	CE  										ELEVATOR	CRACKED         	B	S	A	EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	6645K					U209				AS PART OF A CONTINUOUS SURVEILLANCE PROGRAM, OPERATOR VISUALLY INSPECTED THE AREA AROUND THE TAPER PINS EACH 100-HOUR I	NSP.  BEECH WROTE SB 2145 WHICH PERTAINS TO DISASSEMBLY AND INSPECTION OF THIS COMPONENT EACH 1,000 HOURS.  AFTER THE FI	RST 1,000-HOUR INSPECTION, OPERATOR VISUALLY INSPECTED THE SUPPORT EVERY 100 HOURS AND FOUND CRACKS AROUND THE TAPER PIN	.  TT:  1,400-1,700 HOURS.  SUBMITTER STATED THIS IS A $1,400 PART WHICH COULD BE MADE STRONGER IN SUCH A HIGH VIBRATION	 AREA.  SYSTEMATICALLY BALANCING THE PROPELLERS HAS NOT ELIMINATED THIS PROBLEM.		1	L	7	2 	3T				A14CE
1998030500009	19980305	00009	EU  	1998	3	5	98ZZZX863        	1	19980112	G	6520	4639003001	GEARBOX         			BOLKMS	117   	BK117B1     	5626012	EU  										T/R	CRACKED         	B			BAQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	912TG	5594 			409	7174				DURING PRE-FLIGHT INSPECTION, A CRACK IN THE TAIL ROTOR GEARBOX HOUSING WAS FOUND IN THE AREA OF THE MOUNTING STUDS.						1	G	7	2 	3U				H13EU
1998030500010	19980305	00010		1998	3	5	98ZZZX864        	4	19980217	G	2312	064101900	TRANSCEIVER     	KING        	KY196       	BELL  	206   	206B3       	1181506	SW  										COCKPIT	DEFECTIVE       	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY		489  		5764	2871				TRANSCEIVER FREQUENCY KNOB WILL NOT WORK.  STANDBY SELECT SWITCH WILL NOT WORK.						1	G	7	1 	3U				H2SW
1998030500011	19980305	00011	SW  	1998	3	5	98ZZZX865        	1	19980212	G	6710	206062721001	LINEAR ACTUATOR 			BELL  	206   	206B3       	1181506	SW  										ENGINE	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY		380  		7483	2871				LINEAR ACTUATOR MOTOR WILL NOT RUN.						1	G	7	1 	3U				H2SW
1998030500012	19980305	00012	CE  	1998	3	5	98ZZZX866        	1	19980204	G	3500	17227001	REGULATOR       		17627450    	CESSNA	525   	525         	2076601	CE  										OXYGEN BOTTLE	BURNED          	B	L	A	HI5R	K				NONE                    				A			FLAME/FIRE                			IN	INSP/MAINT     	1			GL	25	26CB	616  			4100	5250117				DURING RE-INSTALLATION OF OXYGEN BOTTLE AFTER HYDROSTATIC TEST, MECHANIC NOTED SOUND LIKE OXYGEN LEAK.  DURING ATTEMPT T	O TIGHTEN FITTING, NOTED GREEN GLOW AT REGULATOR, WITH SPARKS.  MECHANIC CLEARED AREA AND 2 EXPLOSIONS NOTED.  FIRE BURN	ED HOLES IN AIRCRAFT NOSE SKIN BELOW OXYGEN REGULATOR, FIRE EXTINGUISHER USED, FIRE PUT OUT.  INSPECTION FOUND REGULATOR	 BURNED THROUGH ABOUT MID-WAY.			1	L	7	2 	4F			RT	A1WI
1998030500013	19980305	00013	SO  	1998	3	5	98ZZZX867        	1	19980101	G	2133	54191651	GEAR ASSY       		10274642    	GULSTM	G1159 	G1159       	3953505	SO  										PRESS OUTFLOW	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	281RB				122316	200				DURING A START-UP FOR DEPARTURE, THE PRESSURIZATION OUTFLOW VALVE FAILED AND LOCKED IN THE CLOSED POSITION.  THE CABIN D	OOR WAS CLOSED AND THE APU AIR WAS SELECTED ON TO PREPARE FOR ENGINES STARTING.  AT THAT TIME, THE CABIN STARTED PRESSUR	IZING UNCONTROLLABLY!!  THE PRESSURIZATION OUTFLOW VALVE COULD NOT BE OPERATED VIA THE (EMERGENCY) DC MOTOR.  SUSPECT TH	E OUTFLOW VALVE PLANET GEAR ASSEMBLY HAD A FAILURE (THE BUTTERFLY WAS FREE).			2	L	7	2 	4F			RT	A12EA
1998030500019	19980305	00019	GL  	1998	3	5	98ZZZX873        	3	19980218	G	6110	B468	SPACER          		D495        											HARTZL	HCD4N3	HCD4N3A     	GL  	FORK	BROKE           	B			SJ3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05					92NR			FY75A		DURING DISASSEMBLY FOR OVERHAUL, 1 OF THE 4 FORK SPACERS BROKE.  THE THREAD PORTION REMAINED IN THE FORK ASSEMBLY.  SUSP	ECTED CAUSE OF FAILURE COULD BE THAT THE B-468 IS TOO HARD AND BRITTLE.  RC SHOULD BE 33-37 AND PART CHECKS AT 40, 42, 4	3, AND 44 RC ON 4 DIFFERENT TESTS.  SINCE THIS HAS BEEN A KNOWN PROBLEM IN THE PAST, SUBMITTER RECOMMENDED A STRICTER CO	NTROL ON CHECKING FOR PROPER HARDNESS IN ORDER TO PREVENT FUTURE OCCURRENCES.													5	C	STC
1998030500020	19980305	00020	SO  	1998	3	5	98ZZZX874        	2	19980205	G	8550		PUMP            			CESSNA	337   	337H        	2075732	CE  	CONT  	O360  	IO360G      	17025	SO  					ENGINE OIL	FAILED          	B			EHHR	E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CL	CLIMB          	1			EA	17	132CM	955  				33701817	24451112			FOLLOWING TAKEOFF, AIRSPEED SLOWED.  REAR ENGINE INSTRUMENTS INDICATED ENGINE WAS LOSING POWER.  OIL PRESSURE WAS DROPPI	NG AND THE PROPELLER WENT INTO FEATHER.  THE ENGINE WAS SHUT DOWN AND A LANDING WAS MADE.  AN INSPECTION OF THE ENGINE D	ETERMINED THE OIL PUMP HAD FAILED.				1	H	7	2 	3O	3	O		A6CE    	E1CE
1998030500022	19980305	00022	GL  	1998	3	5	98ZZZX876        	3	19980101	G	6110	C34112	BEARING         			CESSNA	182   	182P        	2075816	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER ASSY	CRACKS          	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	21457	1863 				18261642		727574		PROPELLER ASSEMBLY HAS NUMEROUS CRACK INDICATIONS ON THE SURFACE THAT FACES THE HUB.						1	H	7	1 	3O			NT	TA13    		5	C	P3EA
1998030500023	19980305	00023	CE  	1998	3	5	98ZZZX877        	1	19980112	G	5400	0851601202	WEB             			CESSNA	340   	340A        	2076405	CE  										NAC EXH TUNNEL	CORRODED        	B		A	DJFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	2699D					340A0787				DURING ANNUAL INSPECTION, FOUND LOWER AREA OF NACELLE WEB IN EXHAUST TUNNEL EXFOLIATED.  ONLY ONE OF THE TUNNELS ON THIS	 AIRCRAFT WAS CORRODED, BUT SKIN CRACKS WERE FOUND IN AREA OF EXHAUST CLAMP ON ONE OTHER TUNNEL.  ACTT:  3,998.1 HOURS.					1	L	7	2 	3O				3A25
1998030500024	19980305	00024	SW  	1998	3	5	98ZZZX878        	1	19980216	G	3610	S19213	COUPLING        			GULSTM	560   	560         	0141402	SW  										BLEED AIR	CRACKED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	31RC	3691 				5600023				DURING ENGINE CHANGE, FOUND BLEED AIR CLAMP CRACKED IN RADIUS OF BOLT GUIDE SLEEVE, ALMOST COMPLETELY AROUND THE CIRCUMF	ERENCE.					1	H	7	2 	3O				6A1
1998030500025	19980305	00025	SW  	1998	3	5	98ZZZX879        	1	19980210	G	3010	65141025	LINE ASSY       			GULSTM	560   	560         	0141402	SW  										WING DEICE	CHAFE           	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	341QS	83   				5600341				TWO WING DEICE LINES AND CLAMPS LOCATED AT FUSELAGE AND WING LEADING EDGE, CHAFE FUSELAGE SKIN.  SUBMITTER STATED SHRINK	 WRAP AND THERMOPROTECTION TAPE SHOULD BE EXTENDED FORWARD.					1	H	7	2 	3O				6A1
1998030500026	19980305	00026	SW  	1998	3	5	98ZZZX880        	1	19980210	G	3010	65141023	LINE ASSY       			GULSTM	560   	560         	0141402	SW  										WING DEICE	CHAFE           	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	341QS	83   				5600341				TWO WING DEICE LINES AND CLAMPS LOCATED AT FUSELAGE AND WING LEADING EDGE, CHAFE FUSELAGE SKIN.  SUBMITTER STATED SHRINK	 WRAP AND THERMOPROTECTION TAPE SHOULD BE EXTENDED FORWARD.					1	H	7	2 	3O				6A1
1998030500027	19980305	00027	SW  	1998	3	5	98ZZZX881        	1	19980210	G	2752	99123441	ACTUATOR        			GULSTM	560   	560         	0141402	SW  										FLAP	BROKEN          	B		A	CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	361QS					5600361				DURING PHASE 2 INSPECTION, FOUND HEAD OF BOLT SHEARED CLEAN. THIS IS ONE OF FOUR BOLTS HOLDING BARREL TO BASE OF THE FLA	P ACTUATOR.  BOLT HEAD WAS HELD CAPTIVE BY SAFETY WIRE IN CONJUNCTION WITH THREE REMAINING BOLTS.  DID NOT APPEAR TO BE 	OVERTORQUED.  POSSIBLE BAD BATCH OF BOLTS.				1	H	7	2 	3O				6A1
1998030500028	19980305	00028	SW  	1998	3	5	98ZZZX882        	1	19980216	G	5220	48191301	PANEL           			GULSTM	560   	560         	0141402	SW  										EMERG EXIT	MALFUNCTIONED   	B		A	CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	335QS	2416 				5600335				DURING INSPECTION, ATTEMPTED TO REMOVE THE EMERGENCY EXIT DOOR.  FOUND NUMEROUS PROBLEMS.  EXTERIOR HANDLE ROTATION DIFF	ICULT.  HATCH HAD TO BE HIT HARD AT TOP TO MAKE IT RELEASE FROM OPENING.  DETERMINED RUBBER SEAL THAT IS GLUED TO DOOR W	ITH 1300L, WAS ADHERED TO 890 THAT IS UTILIZED TO CREATE A BETTER PRESSURIZATION SEAL.  CAUSED SITUATION WHEREAS DEALING	 WITH THE SEAL BECAME A PART OF THE OPERATION TO REMOVE THE EMERG EXIT.  ALSO, INTERIOR TRIM PIECE THAT IS VELCROED INTO	 PLACE WAS TRAPPED IN PLACE WITH SEAT IN OTBD POSITION.  THIS TRIM PIECE BLOCKED 6-8 INCHES OF THE LOWER PORTION OF THE 	EXIT OPENING.	1	H	7	2 	3O			 	6A1
1998030500029	19980305	00029	SO  	1998	3	5	98ZZZX883        	2	19980206	G	8520		CRANKCASE       			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  					RT SIDE	BROKEN          	B			NT2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	3959G	2646 	1291 			340A0243	509502			CRANKCASE BROKE AT UPPER REAR BETWEEN MAGNETOS DOMINATING ON THE RT SIDE OF THE CRANKCASE PARTING SURFACE.  NO CRANKCASE	 PARTS WERE MISSING, BUT IT APPEARS TO BE INTERNAL FAILURE.  THE ENGINE WAS REMOVED AND SENT TO RAM AIRCRAFT OFR OVERHAU	L.				1	L	7	2 	3O	3	O		3A25    	E8CE
1998030500030	19980305	00030	CE  	1998	3	5	98ZZZX884        	1	19980219	G	2520		BELT            			CESSNA	182   	182S        	2072701	CE  										REAR LAP	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	416ES	15   				18280078				REAR LAP BELT REEL MOUNTING BRACKETS ANGLE THE REELS OUTBOARD OTHER THAN INBOARD WHICH CAUSES THE BOLT EDGE TO WEAR AGAI	NST THE REEL ENCLOSURE IN NORMAL USE.  RIGHT AND LEFT BRACKETS APPEAR TO BE SWITCHED AT THE FACTORY.  RECOMMEND ALIGNING	 REELS AND BELTS TO NORMAL PULL-OFF ANGLE TO AVOID BELT EDGE FRAYING.				1	H	7	1 	3O			NT	3A13
1998030500031	19980305	00031	CE  	1998	3	5	98ZZZX885        	1	19980211	G	2810		HOSE            			CESSNA	172   	172N        	2072434	CE  										FUEL VENT	DETERIORATED    	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	5318E	2556 				17271836				FUEL TANK VENT LINES ARE CONNECTED WITH 6 SHORT PIECES OF RUBBER HOSE IN THE CABIN OVERHEAD AT THE WING ROOTS.  THE HOSE	S WERE ORIGINAL, ONE WITH A 3Q78 DATE.  THIS IS THE THIRD ARICRAFT WITH VENT HOSES AT LEAST 20 YEARS OLD.  SUBMITTER REC	OMMENDED 5-10 YEAR REPLACEMENT.				1	H	7	1 	3O			NT	3A12
1998030500032	19980305	00032	SW  	1998	3	5	98ZZZX886        	1	19980219	G	2430		BATTERY         			MOONEY	M20   	M20F        	5870214	SW  										AFT AVION TRAY	POOR GROUND     	C	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	9612M					670189				TROUBLESHOOTING FOR POOR BATTERY CHARGING, INTERMITTENT CRANKING, AND INTERMITTENT GPS/COMM FAILURES, FOUND PAINT ON AIR	 FRAME STRUCTURE CAUSING POOR BATTERY GROUND.  SUBMITTER SUGGESTS REMOVING PAINT UNDER BOLTS AND NUT AND ADD A HEAVY GRO	UND STRAP.				1	L	7	1 	3O				2A3
1998030500036	19980305	00036	SO  	1998	3	5	98ZZZX890        	1	19980214	G	2434	4111810	ALTERNATOR      	ELECTROSYS  		PIPER 	PA28  	PA28181     	7102807	SO  										DC SYSTEM	FAILED          	B			R7LR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	6870F	177  			60604165	287790170				ALTERNATOR WAS OVERHAULED BY ELECTROSYSTEMS, FAILED AFTER 177 HOURS.  ON INSPECTION, FOUND 2 DIODE TABS CRACKED AND ARCI	NG DIODES OBVIOUSLY NOT REPLACED AT OVERHAUL.   SUBMITTER STATED THIS IS SECOND ELECTROSYSTEMS ALTERNATOR THAT FAILED AF	TER VERY SHORT SERVICE LIFE.				1	L	7	1 	3O				2A13
1998030500037	19980305	00037	SO  	1998	3	5	98ZZZX891        	1	19980101	G	7810	5327F32	EXHAUST SYSTEM  			MAULE 	MX7   	MXT7180     	5470206	SO  										ENG MUFFLER	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	800CP					14058C				OVER A PERIOD OF THREE YEARS, NINE OCCURRENCES OF EXHAUST/MUFFLER PROBLEMS.  THESE INCLUDE EXCESSIVE VIBRATION RESULTING	 IN CRACKING OF WELDS, AT CONNECTION OF EXHAUST PIPES AND MUFFLER.  IN ADDITION, CRACKING OF WELD SPOTS AT VARIOUS LOCAT	IONS TO INCLUDE ROD CONNECTING THE TWO TAILPIPES.  ON ONE OCCASION, EXHAUST PIPE HAD PULLED AWAY FROM MANIFOLD CREATING 	A SEVERE FIRE HAZARD.			1	H	7	1 	3O			NC	3A23
1998030500042	19980305	00042	CE  	1998	3	5	98ZZZX896        	1	19980112	G	7120	35415377	MOUNT BRACKET   			BEECH 	35    	C35BEECH    	1151508	CE  										AFT ENG MOUNT	CRACKED         	G		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	613D					D2870				DURING ANNUAL INSPECTION, NOTICED RT REAR ENGINE MOUNT BRACKET RIVETS WERE LOOSE.  AFTER REMOVAL OF ENGINE, FOUND BOTH R	EAR MOUNTS WERE CRACKED AT FORWARD EDGE OF REAR SUPPORT MEMBER.  TOTAL TIME OF AIRCRAFT WAS A CONTRIBUTING FACTOR, BUT E	XTRA CARE SHOULD BE USED WHEN INSPECTING THIS AREA.  POSSIBLE ROTATING OR REPLACING OF LORD MOUNTS WOULD HAVE HELPED THI	S PROBLEM.			1	L	7	1 	3O				A777
1998030500043	19980305	00043	GL  	1998	3	5	98ZZZX897        	3	19980210	G	6111	90DA8	BLADE           			CESSNA	182   	182J        	2072722	CE  						MCAULY	2A34C	2A34C201    	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	979ND	3812 	180  		K21738	18257443		694620		PROPELLER WAS SHOWING SIGNS OF ERRATIC PITCH CHANGE AND STICKING.  BLADE SHOWS EVIDENCE OF PREVIOUS IMPACT STRIKE.  THIS	 AIRCRAFT HAD PREVIOUSLY HAD A STUCK PRESSURE RELIEF VALVE IN THE GOVERNOR WHICH, AFTER DISCUSSION WITH THE PILOT, MAY H	AVE CAUSED AN OVERSPEED TO THE PROPELLER.				1	H	7	1 	3O			NT	3A13    		5	C	P3EA
1998030500614	19980305	00614	CE  	1998	3	5	98ZZZX906        	1	19980201	G	2430	MS227598	WIRE            			BEECH 	90    	C90         	1152913	CE  										STARTER/GEN	SPLIT           	B			GMNR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	901AJ					LJ829				ALL FOUR CABLE LEADS COMING FROM STARTER/GENERATOR ON LEFT SIDE, P/N'S P10C4, P10A4, K2D4, K2F4, SHIELDING IS SPLITTING 	ALL ALONG THE LENGTH OF WIRE EXPOSING BARE CABLE WHICH COULD RESULT IN ARCING.  REF:  CHAPTER 24 DC GENERATION OF WIRING	 MANUAL.				1	L	7	2 	3T			 	3A20
1998030500615	19980305	00615	NM  	1998	3	5	98ZZZX907        	1	19980219	G	7400	VB81KA723	RELAY SOCKET    			DOUG  	600N  	600N        	3027377	NM  										ENG IGNITION	FAILED          	B		A	JRP2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	957SD					RN011				DURING GROUND TEST ENGINE RUN, ENG FLAMED OUT AFTER LESS THAN A MINUTE.  FUEL GAUGES INDICATED APPROX 70 POUNDS OF FUEL.	  AFTER TANKS TOPPED OFF AND FUEL LINES PURGED, ATTEMPTED RESTART WITHOUT SUCCESS.  FURTHER T/S LOCATED INOP IGNITER FUN	CTION.  THIS WAS T/S TO INTERMITTENT IGNITER RELAY SOCKET.  VIBRATION ON WIRING HARNESS WOULD CAUSE RELAYS TO DE-ENERGIZ	E INTERMITTENTLY.  SEVERAL RELAYS AFFECTED.  CURRENT MD600 MM ARE TOO INADEQUATE TO IDENTIFY THE FUNCTION OF RELAYS.  SU	BMITTER SUSPECTS THAT 3 RELAYS ARE:  FADEC START RELAY.  FADEC IGNITION RELAY AND BATTERY HITEMP RELAY.  SUSPECTED FADEC	 ECU MAY HAVE SHUT ENG DOWN DUE TO LOSS OF SIGNAL LINES FROM INTERMITTENT RELAYS.  TSN:  12.6 HRS.	1	G	7	1 	3U			NC	H3WE
1998030500616	19980305	00616	SO  	1998	3	5	98ZZZX908        	1	19980209	G	7810	8629907	MUFFLER         			PIPER 	PA44  	PA44180     	7104402	SO  										LT ENG AFT	FAILED          	B	L	A	I57S	O				OTHER                   				A			FLAME/FIRE                			TX	TAXI/GRND HDL  	1			SO	15	61PF	1860 				447995187				ACFT EXPERIENCED A FIRE IN THE LT ENG NAC JUST AFTER A RUN-UP.  FIRE STARTED AFTER ACFT TURNED DOWNWIND AND BEGAN TAXIIN	G.  FIRE EXTINGUISHED.  INSP REVEALED AFT MUFFLER HAD CRACKED AND SPLIT CIRCUMFERENTIALLY NEAR THE LT (OTBD INLET.)  HOT	 EXHAUST GASSES IGNITED LOWER FIBERGLASS COWLING CAUSING FIRE/HEAT DAMAGE, IGNITION HARNESS, STARTER CABLE, FUEL PUMP, A	ND CHT PROBE.  CLOSER INSP OF MUFFLER (PIPER P/N 86299-07) REVEALED METAL CORRODED AND 'PAPER THIN' ADJ TO THE CRACK.  S	MALL PORTIONS OF METAL NEXT TO THE CRACK WERE BENT OUTWARD SUGGESTING ENG "AFTERFIRE" MAY HAVE CONTRIBUTED TO MUFFLER FA	ILURE.  MUFFLER FAILURE POINT WELDS INDICATING MUFFLER PREVIOUSLY CRACKED.	1	L	7	2 	3O				A19S0
1998030500618	19980305	00618	EU  	1998	3	5	98ZZZX910        	1	19980105	G	6520	4639306006	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	ROUGH           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					2077					BEARING WAS ROUGH WHEN INSTALLED ON LEVER GEAR SHAFT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998030500619	19980305	00619	EU  	1998	3	5	98ZZZX911        	1	19980105	G	6520	4639311003	BEARING         			BOLKMS	117   	BK117A3     	5626015	EU  										T/R GEARBOX	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					871					OUTPUT SHAFT WOULD NOT FIT THROUGH ROLLERS WHEN BEARING WAS INSTALLED IN COVER OF T/R GEARBOX.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998030500620	19980305	00620	EU  	1998	3	5	98ZZZX912        	1	19980105	G	6520	4639310012	BEARING         			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	ROUGH           	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					1879					BEARING WAS ROUGH WHEN INSTALLED ON BEVEL GEAR SHAFT.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1998030500622	19980305	00622	EU  	1998	3	5	98ZZZX914        	1	19980106	G	6320	4639311042	BEVEL GEAR      			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					978					GEAR WOULD NOT GET A CONTACT PATTERN WITHIN ACCEPTABLE LIMITS WHEN MATED TO BEVEL.  GEARSHAFT P/N 4639311043, S/N 797. R	EMOVED AND REPLACED.					1	G	7	2 	3U			NC	H13EU
1998030500623	19980305	00623	EU  	1998	3	5	98ZZZX915        	1	19980106	G	6520	4639311043	BEVEL GEAR SHAFT			BOLKMS	BK117 	BK117C1     	5626025	EU  										T/R GEARBOX	DEFECTIVE       	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05					797					GEAR COULD NOT GET A CONTACT PATTERN WITHIN ACCEPTABLE LIMITS WHEN MATCHED TO BEVEL.  GEAR SHAFT P/N 4639311042, S/N 978	.  REMOVED AND REPLACED.					1	G	7	2 	3U			NC	H13EU
1998030500624	19980305	00624	EA  	1998	3	5	98ZZZX916        	2	19980210	G	8520	77037	CRANKSHAFT      			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A3A     	41514	EA  					NR 5 JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	56WB	9    			88894	284470				CRANKSHAFT WAS FOUND CRACKED AFTER PRECAUTIONARY REMOVAL FOLLOWING RECENT ENGINE OVERHAUL (8.8 HRS).  CRANKSHAFT WAS PRO	CESSED BY REPAIR AGENCY PRIOR TO INSTALLATION.  SUBMITTER SUGGGESTED PART MAY HAVE BEEN IMPROPERLY MACHINED.  CRACK WAS 	AT NR 5 JOURNAL RADIUS APPROXIMATELY 2.50 INCHES IN LENGTH.				1	L	7	1 	3O	3	O		2A13    	E286
1998030500626	19980305	00626	SO  	1998	3	5	98ZZZX918        	1	19980217	G	3340		HARNESS         			PIPER 	PA44  	PA44180     	7104402	SO  										TAIL STROBE	ARCED           	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	15	9290P	57   				4496019				SEVERAL LOUD POPS WERE HEARD IN THE TAILCONE OF THE AIRCRAFT WHEN THE STROBE LIGHTS WERE TURNED ON.  INSPECTION OF STROB	E POWER SUPPLY WIRING REVEALED BARE WIRES WHERE THE EXTERIOR INSULATION HAD BEEN STRIPPED.  THE GRAY INSULATION WAS STRI	PPED BY A TOOL THAT CUT TOO DEEPLY AND LEFT THE UNDERLYING RED, WHITE, AND BLACK WIRES EXPOSED.  THE RED WIRE ARCED TO T	HE SURROUNDING AIRCRAFT STRUCTURE DAMAGING THE INSULATION FURTHER.			1	L	7	2 	3O			 	A19S0
1998030500627	19980305	00627	SW  	1998	3	5	98ZZZX919        	1	19980224	G	5741	AN413	BOLT            			BBAVIA	8     	8GCBC       	1220803	SW  										AFT WING SPAR	WORN            	B	P	A	AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	8638V	4184 				16275				DURING WING REMOVAL, BOTH AFT SPAR TO FUSELAGE ATTACH BOLTS (AN4-13) WERE FOUND EXTREMELY WORN.  THE HOLES IN THE FUSELA	GE ATTACH POINTS WERE ALSO WORN OVERSIZE (APPROXIMATELY .3125 INCH).  APPARENT CAUSE OF THIS DEFECT IS INSUFFICIENT BEAR	ING AREA OF THE FUSELAGE ATTACH POINTS AND INSUFFICIENT CLAMPING ACTION BETWEEN THE AFT SPAR FITTING AND FUSELAGE ATTACH	 POINT ALLOWING RELATIVE MOVEMENT.  THIS 180 HP 'SCOUT' HAS BEEN USED EXTENSIVELY AS A GLIDER TOW-PLANE.			1	H	7	1 	3O				A21CE
1998030500629	19980305	00629	GL  	1998	3	5	98ZZZX921        	2	19980219	G	7321	23057344	FUEL CONTROL    	BENDIX      		HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	992SD	1075 			326671	510E				HOT START ON FIRST START OF DAY ONLY.  FOUND DURING A RECEIVED TEST.  FIRST 2 TEST POINTS FOUND RICH CAUSED BY LEAKING S	TART-DERICH BELLOWS.  REPLACED BELLOWS AND RETESTED.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998030500630	19980305	00630	GL  	1998	3	5	98ZZZX922        	2	19980219	G	7321	2537688	BELLOWS         	BENDIX      	23057344    	HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	DEFECTIVE       	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	991SD				303518	0500E				FUEL CONTROL DEFECT.  UNABLE TO GET MAXIMUM SPEED; FOUND DURING TESTING.  GOVERNOR SETTING 75 RPM, LOW BELOW MINIMUM.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998030500631	19980305	00631	EA  	1998	3	5	98ZZZX923        	2	19980210	G	8520	LW17577	CRANKSHAFT      			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	LIO360C1E6  	41515	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	15008		220  		1260K	347250346				PART REMOVED FOR MPI, AS A PRECAUTION.  THIS CRANKSHAFT WAS RE-WORKED BY AIR AGENCY AND WAS FOUND TO HAVE CRACKS IN THE 	JOURNAL RADII.					1	L	7	2 	3O	3	O		A7SO    	1E10
1998030500632	19980305	00632	EA  	1998	3	5	98ZZZX924        	2	19980210	G	8520	LW17031	CRANKSHAFT      								LYC   	O320  	O320D2J     	41508	EA  					JOURNAL	CRACKED         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03					U9077					PART REMOVED FROM INVENTORY AND PRECAUTIONARY MPI PERFORMED.  CRACKS IN JOURNAL RADII WERE APPARENT.  THIS UNIT WAS PREV	IOUSLY GROUND AND POLISHED BY AIR AGENCY.  PART IS SCRAP.										3	O			E274
1998030500633	19980305	00633	EA  	1998	3	5	98ZZZX925        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235L2C     	41505	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					143715					PART REMOVED FROM STOCK FOR PRECAUTIONARY MPI.  UNIT WAS GROUND AND POLISHED BY AIR AGENCY AND FOUND TO HAVE CRACKS IN T	HE JOURNAL RADII.										3	O			E223
1998030500634	19980305	00634	EA  	1998	3	5	98ZZZX926        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235C1      	41505	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART REMOVED FROM INVENTORY FOR PRECAUTIONARY MPI.  CRANKSHAFT WAS GROUND AND POLISHED BY AIR AGENCY AND FOUND TO HAVE C	RACKS IN THE JOURNAL RADII.										3	O			E223
1998030500635	19980305	00635	EA  	1998	3	5	98ZZZX927        	2	19980210	G	8520	75006	CRANKSHAFT      								LYC   	O320  	O320*       	41508	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					121682					PART WAS REMOVED FROM INVENTORY FOR MPI FOLLOWING ADVISORY THAT AIR AGENCY MAY HAVE IMPROPERLY MACHINED CRANKSHAFT.  PAR	T WAS FOUND TO HAVE CRACKS IN THE JOURNAL RADII.  PART IS NOT SERVICEABLE.										3	O			E274
1998030500636	19980305	00636	SO  	1998	3	5	98ZZZX928        	2	19980210	G	8520		CRANKSHAFT      								CONT  	C145  	C145*       	17012	SO  					CTWT JOURNAL	BROKE           	G				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			NE	03			11   		424					CRANKSHAFT BROKE AT THE COUNTERWEIGHT JOURNAL AREA IN-FLIGHT.  PART WAS SERVICED BY AIR AGENCY PRIOR TO INSTALLATION DUR	ING OVERHAUL.  PART WILL BE SENT TO CONTINENTAL FOR EVALUATION.										3	O			E253
1998030500638	19980305	00638	EA  	1998	3	5	98ZZZX930        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235*       	41505	EA  					JOURNAL	CRACKED         	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										CRANKSHAFT WAS REMOVED FROM INVENTORY FOR PRECAUTIONARY MPI.  CRANKSHAFT WAS PROCESSED BY AIR AGENCY AND WAS FOUND CRACK	ED AT THE JOURNAL RADII.										3	O			E223
1998030500639	19980305	00639	EA  	1998	3	5	98ZZZX931        	2	19980210	G	8520		CRANKSHAFT      								LYC   	O235  	O235L2C     	41505	EA  					JOURNAL	CRACKED         	G				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03										PART WAS REMOVED FROM INVENTORY FOLLOWING ADVISORY THAT CRANKSHAFTS PROCESSED BY AIR AGENCY MAY BE DEFECTIVE.  CRANKSHAF	T WAS MPI AND FOUND TO HAVE CRACKS IN THE JOURNAL RADII.										3	O			E223
1998030500640	19980305	00640	CE  	1998	3	5	98ZZZX932        	1	19980220	G	2821	07560052	FUEL STRAINER   			CESSNA	150   	150M        	2071830	CE  										FUEL SYSTEM	MISMANUFACTURED 	B			PF2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	66381					15076005				FUEL STRAINER HEAD ASSY PURCHASED FACTORY NEW 1997.  UPON INSTALLATION, SCREEN COULD NOT BE INSTALLED.  PICK-UP TUBE HAD	 BEEN STAKED AT AN ANGLE TO BODY.  THIS DID NOT OFFER CLEARANCE BETWEEN DRAIN STEM AND PICK-UP TUBE.  ASSY MACHINE OR PA	RT NOT JIGGED PROPERLY DURING ASSY PROCESS.				1	H	7	1 	3O				3A19
1998030500641	19980305	00641		1998	3	5	98ZZZX933        	4	19980202	G	6113	055023613	SPINNER         			CESSNA	172   	172R        	2072401	CE  										PROPELLER	CHAFED          	B	S		WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9897F					17280181				INTERFERENCE BETWEEN PROPELLER AND PROPELLER SPINNER CAUSING CHAFING ON PROPELLER.						1	H	7	1 	3O			NT	3A12
1998030500653	19980305	00653		1998	3	5	98ZZZX938        	4	19980116	G	2211	11788292	COMPUTER        			BOLKMS	117   	BK117A4     	5626017	EU  										SPAS	FAILED          	B			TI1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	05	117NG	130  			018711139	7083				SPAS COMPUTER WILL NOT PASS COLLECTIVE TRANSDUCER TEST.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998030500654	19980305	00654		1998	3	5	98ZZZX939        	4	19980115	G	3446	78806059008	DISPLAY         			BOLKMS	117   	BK117A4     	5626017	EU  										STORMSCOPE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NG				UED01103885	7083				STORMSCOPE DISPLAY INOPERATIVE.  FAILED APPROXIMATELY 1 MONTH AFTER INSTALLATION.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998030500658	19980305	00658	SW  	1998	3	5	98ZZZX943        	1	19980119	G	2430	1820300150	SHUNT           			BELL  	230   	230         	1182149	SW  										GENERATOR SYSTEM	BURNT           	B			TI1R	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	05	4UV					23019				GENERATOR SYSTEM SHUNT DISCOLORED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998030500659	19980305	00659	SW  	1998	3	5	98ZZZX944        	1	19980109	G	2910	AE1009102G014	HOSE            			BELL  	230   	230         	1182149	SW  										HYDRAULIC SYSTEM	CHAFED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV					23019				HYDRAULIC HOSE CHAFED.    REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998030500660	19980305	00660		1998	3	5	98ZZZX945        	4	19980107	G	3424	222375072105	INDICATOR       			BELL  	230   	230         	1182149	SW  										TURN GYRO	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1436 			5581	23019				TURN INDICATOR INOPERATIVE.  GYRO WILL NOT SPIN UP.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1998030500661	19980305	00661		1998	3	5	98ZZZX946        	4	19980114	G	3446	80510950001	STORMSCOPE      		WX95        	BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4493X				JCP05700973	S7038				STORMSCOPE UNIT NOT RECEIVING INPUT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998030500663	19980305	00663	EU  	1998	3	5	98ZZZX948        	1	19980107	G	8000	151PS01A6A	SWITCH          			BOLKMS	117   	BK117A3     	5626015	EU  										START SYSTEM	INTERMITTENT    	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	1140H					7078				SWITCH ONLY MAKING CONTACT INTERMITTENTLY.  DEFECTIVE UPON INSTALLATION.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998030500664	19980305	00664	EU  	1998	3	5	98ZZZX949        	1	19980119	G	2432	RG390E	BATTERY         			BOLKMS	117   	BK117A3     	5626015	EU  										DC SYSTEM	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH	198  			CBC295219	7061				BATTERY WEAK, SLOW STARTS, WILL NOT TOP CHARGE AFTER 4 HOURS.  GREEN LIGHT WOULD NOT COME ON.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998030500665	19980305	00665		1998	3	5	98ZZZX950        	4	19980129	G	3454	3137LB63B	INDICATOR       			BOLKMS	117   	BK117A1     	5626010	EU  										COCKPIT RMI	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117M				5853	S7023				RMI INDICATOR 'OFF'  FLAG WILL NOT STOW.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1998043000417	19980430	00417		1998	4	30	98ZZZX954        	4	19980204	G	6122	3011028	SPRING          	WOODWARD    	8210004     															PROPELLER GOV	FAILED          	B			IG0R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03										DURING PROPELLER GOVERNOR CHECK WHEN TENSION WAS APPLIED TO SPRING, IT FAILED  (BROKE INTO 2 PIECES).
1998043000418	19980430	00418	SO  	1998	4	30	98ZZZX955        	1	19980201	G	7820	6751Q7000	MUFFLER         			PIPER 	PA32  	PA32R300    	7103213	SO  										TAILPIPE WELD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	47684					32R7880018				DURING ANNUAL INPSECTION, THE CENTER MUFFLER WAS FOUND CRACKED ONE-QUARTER AROUND IN THE WELD UNDER REINFORCEMENT PLATE.	  IT APPEARS THE WELD DID NOT PENETRATE THE TAILPIPE COMPLETELY.					1	L	7	1 	3O				A3SO
1998043000420	19980430	00420	EA  	1998	4	30	98ZZZX957        	2	19980219	G	7414	1016301010	MAGNETO         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENG LT MAG	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	40259	94   			J109709ER	277305069				ENGINE HAD 200 RPM DROP ON LEFT MAGNETO.  CHECKED MAG TO ENGINE TIMING, AND COULD NOT GET MAG TIMED TO ENGINE.  REMOVED 	MAG FOR INSPECTION.  WHEN MAG WAS OPENED, FOUND MAGNET SHAFT SHEARED AT KEYWAY.  THIS MAGNETO WAS A NEW/REBUILD FROM TEL	EDYNE CONTINENTAL INSTALLED ON THIS AIRCRAFT 94.0 HOURS BEFORE.				1	L	7	2 	3O	3	O		1A10    	1E4
1998043000421	19980430	00421	CE  	1998	4	30	98ZZZX958        	1	19980130	G	5210	95380010	HANDLE          			BEECH 	33    	35B33       	1151406	CE  										CABIN DOOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9617Y	2600 				CD583				DOOR HANDLE WILL UNLOCK WITHOUT DEPRESSING LOCK RELEASE BUTTON IN HANDLE.  ALTHOUGH THIS HANDLE IS THE SAME PART NUMBER 	AS HANDLES ON OTHER AIRCRAFT THAT AD 97-14-15 APPLIES TO, THE AD DOES NOT LIST THE 35-B33.  SUBMITTER SUGGESTED THE AD S	HOULD BE CORRECTED TO INCLUDE MODELS OMITTED WITH THIS SAME HANDLE.				1	L	7	1 	3O				3A15
1998043000422	19980430	00422	CE  	1998	4	30	98ZZZX959        	1	19980130	G	5210	35400395	PLATE           			BEECH 	33    	35B33       	1151406	CE  										CABIN DOOR	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9617Y	2600 				CD583				DOOR HANDLE WILL UNLOCK WITHOUT DEPRESSING LOCK RELEASE BUTTON IN HANDLE.  ALTHOUGH THIS HANDLE IS THE SAME PART NUMBER 	AS HANDLES ON OTHER AIRCRAFT THAT AD 97-14-15 APPLIES TO, THE AD DOES NOT LIST THE 35-B33.  SUBMITTER SUGGESTED THE AD S	HOULD BE CORRECTED TO INCLUDE MODELS OMITTED WITH THIS SAME HANDLE.				1	L	7	1 	3O				3A15
1998043000425	19980430	00425	CE  	1998	4	30	98ZZZX962        	1	19980119	G	5755	20083	BRACKET         			CESSNA	340   	340A        	2076405	CE  										RT SPOILER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	4572N	950  				340A0551				AIRCRAFT HAS THE SPEED BRAKE KIT, P/N SP8000, INSTALLED IAW STC NR SA4948NM.  PILOT REPORTED THE RIGHT WING SPOILER WOUL	D NOT FULLY RETRACT.  FOUND BOTH FLANGES BROKEN OFF ON THE TOP ATTACH DOUBLER, P/N 2008-1, AT THE ACTUATOR.  LOWER BRACK	ET, P/N 2008-3, HAD BOTH FLANGES CRACKED.				1	L	7	2 	3O				3A25
1998043000426	19980430	00426	CE  	1998	4	30	98ZZZX963        	1	19980119	G	5755	20081	BRACKET         			CESSNA	340   	340A        	2076405	CE  										RT SPOILER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	4572N	950  				340A0551				AIRCRAFT HAS THE SPEED BRAKE KIT, P/N SP8000, INSTALLED IAW STC NR SA4948NM.  PILOT REPORTED THE RIGHT WING SPOILER WOUL	D NOT FULLY RETRACT.  FOUND BOTH FLANGES BROKEN OFF ON THE TOP ATTACH DOUBLER, P/N 2008-1, AT THE ACTUATOR.  LOWER BRACK	ET, P/N 2008-3, HAD BOTH FLANGES CRACKED.				1	L	7	2 	3O				3A25
1998043000427	19980430	00427	SO  	1998	4	30	98ZZZX964        	1	19980109	G	3222	6710010	GEAR ASSY       			PIPER 	PA28  	PA28R200    	7102811	SO  										NLG RETRACT	FAILED          	G				K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	13	225PA					28R7635443				AFTER LANDING, PILOT STATED ON ROLL-OUT THE NLG BEGAN TO SHIMMY.  STOPPED THE AIRCRAFT AND STARTED TO SHUT DOWN ENGINE. 	 THE NOSE WHEEL COLLAPSED FORWARD WITH PROPELLER STRIKING THE NLG TIRE AND RIM.  INVESTIGATION REVEALED THE RETRACT LUG 	ON NLG ASSY HAD BROKEN.				1	L	7	1 	3O				2A13
1998043000429	19980430	00429	CE  	1998	4	30	98ZZZX966        	1	19980218	G	2701	1005241201	SPROCKET ASSY   			BEECH 	200   	200BEECH    	1152920	CE  										YOKE BS 100	CRACKED         	D		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			SW	05	800LS	6171 				BB457				PILOT REPORTED YOKE POSITION 30 DEGREES OFF FROM LEVEL FLIGHT.  PERFORMED VISUAL INSPECTION, FOUND PRIMARY SPROCKET ASSE	MBLY WELD TO AFT CRACKED RESULTING IN NO AILERON CONTROL.  RECOMMEND NDT PERIODICALLY.					1	L	7	2 	4T				A24CE
1998043000430	19980430	00430	CE  	1998	4	30	98ZZZX967        	1	19980209	G	5610	45AS3100113	WINDSHIELD      	PPG         		BEECH 	MU300 	400A        	1155402	CE  										LEFT COCKPIT	DISBONDED       	B			RF5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	205R	1355 			9519H1598	RK30				DUE TO DISBONDING OF MAIN WINDSHIELD HEAT TERMINAL BLOCK, FOUND LEFT WINDSHIELD UNAIRWORTHY DURING C/W BEECH SAFETY COMM	UNIQUE.  THIS BLOCK IS LCOATED AT LOWER LEFT CORNER OF WINDSHIELD.  PART TT:  1,355 HOURS,  LANDINGS, 953.					2	H	7	2 	4F			RT	A16SW
1998043000431	19980430	00431	EU  	1998	4	30	98ZZZX968        	1	19980217	G	5330		SKIN            			AMD   	FALC20	FALCONE     	2720305	EU  										FUS FWD LOWER	CORRODED        	B	S		EUJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	977TW					13				THE FOLLOWING CORROSION WAS DISCOVERED DURING B, C INSPECTIONS:  FUSELAGE FORWARD LOWER SECTION - CORROSION BETWEEN SKIN	 AND FRAMES/STRINGERS.  FRAME 7 TO FRAME 19 ON PANELS BETWEEN S22L AND S22R.  REPLACEMENT OF BOTH SKIN PANELS AND CLEANI	NG AND TREATING OF ATTACHING SKINS.  SUBMITTER SUGGESTED CONDENSATION AND MOISTURE RETAINED BY SOUNDPROOFING COULD BE A 	POSSIBLE CAUSE.  ACFT TT:  28,446 HRS.  LANDINGS:  23,592.			2	L	7	2 	4F				A7EU
1998043000432	19980430	00432	EU  	1998	4	30	98ZZZX969        	1	19980217	G	5330		SKIN            			AMD   	FALC20	FALCONE     	2720305	EU  										FUS LT AFT LAV	CORRODED        	B	S		EUJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	977TW					13				THE FOLLOWING CORROSION WAS DISCOVERED DURING B, C INSPECTIONS:  FUSELAGE LEFT AFT SECTION LAVATORY AREA - CORROSION BET	WEEN SKIN AND FRAMES/STRINGERS.  FRAME 29 TO FRAME 33 LOCATED BETWEEN STR 19 AND STR 22.  REPLACEMENT OF SKIN PANEL AND 	CLEANING AND TREATING OF ATTACHING SKIN, STRINGERS, AND FRAMES.  SUBMITTER SUGGESTED MOISTURE AND SPILLAGE IN LAVATORY A	REA AS A POSSIBLE CAUSE.   ACFT TT:  28,446 HRS.  LANDINGS:  23,592.			2	L	7	2 	4F				A7EU
1998043000433	19980430	00433	EU  	1998	4	30	98ZZZX970        	1	19980217	G	5330		SKIN            			AMD   	FALC20	FALCONE     	2720305	EU  										FUS LT AFT LAV	CORRODED        	B	S		EUJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	76662					306				THE FOLLOWING CORROSION WAS DISCOVERED DURING MAJOR CORROSION INSPECTION (MCI):  FUSELAGE LEFT AFT SECTION LAVATORY AREA	 - CORROSION BETWEEN SKIN AND FRAMES/STRINGERS.  FRAME 29 TO FRAME 33 LOCATED BETWEEN STR 19 AND STR 22.  REPLACEMENT OF	 SKIN PANEL AND CLEANING AND TREATING OF ATTACHING SKIN, STRINGERS, AND FRAMES.  SUBMITTER SUGGESTED MOISTURE AND SPILLA	GE IN LAVATORY AREA AS A POSSIBLE CAUSE.			2	L	7	2 	4F				A7EU
1998043000435	19980430	00435	EA  	1998	4	30	98ZZZX972        	2	19980216	G	7322	MA4SPA	CARBURETOR      			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  					THROTTLE ARM	DEFECTIVE       	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13	91QS					17268167				INSPECTION OF THE CARBURETOR DETERMINED THE THROTTLE ARM BECAME LOOSE ON THE SHAFT.  THIS CONDITION RESULTED IN LOSS OF 	CONTROL OF ENGINE RPM.  THE NUT AND COTTER PIN WERE INTACT.  SUSPECT THE ORIGINAL INSTALLATION WAS NOT PROPERLY INSTALLE	D AND TORQUED ALLOWING THE ARM TO BECOME LOOSE.  IT IS SUGGESTED THAT CORRECT INSTALLATION AND TORQUE WOULD PREVENT THIS	 CONDITION.			1	H	7	1 	3O	3	O	NT	3A12    	E286
1998043000436	19980430	00436	CE  	1998	4	30	98ZZZX973        	1	19980220	G	5412		FIREWALL        			CESSNA	172   	172R        	2072401	CE  										LT COWL SHOCK MT	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	365ES					17280023				DURING 100-HOUR INSPECTION, FOUND FIREWALL CRACKED AT THE LOWER LEFT COWL SHOCK MOUNT BELOW THE BATTERY BOX.  VISIBLE PO	RTION OF CRACK WAS APPROXIMATELY .50 INCH LONG.  AFTER CLOSER EXAMINATION FROM INSIDE THE CABIN, THE CRACK APPEARED TO B	E ABOUT 3 INCHES LONG AND ORIGINATING FROM A RIVET HOLE.  DOUBLER WAS FABRICATED AND INSTALLED ON INSIDE OF CABIN.  CRAC	K DEVELOPED POSSIBLY FROM IMPROPER SHEET METAL PRACTICES AT MANUFACTURE.			1	H	7	1 	3O			NT	3A12
1998043000437	19980430	00437	CE  	1998	4	30	98ZZZX974        	1	19980220	G	5512		RIVETS          			CESSNA	172   	172R        	2072401	CE  										HORIZONTAL STAB	FAILED          	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	365ES					17280023				DURING 100-HOUR INSPECTION, FOUND 4 OF THE AN426 RIVETS SECURING THE UPPER HORIZONTAL STABILIZER SKIN PULLED COMPLETELY 	THROUGH ON THE LEFT SIDE.  ALL OF THE REMAINING RIVETS BOTH LEFT AND RIGHT SIDE SHOWED SIGNS OF WORKING THESE RIVETS ARE	 INBOARD UNDER THE STABILZIER ROOT FAIRING.  OLDER 172'S USE UNIVERSAL HEAD RIVETS WITH NO PROBLEMS OF WORKING.  OBTAINE	D REPAIR PROCEDURE FROM CESSNA AND PROBLEM WAS CORRECTED.			1	H	7	1 	3O			NT	3A12
1998043000438	19980430	00438	CE  	1998	4	30	98ZZZX975        	1	19980115	G	7603	C2995050102	THROTTLE CONTROL			CESSNA	172   	172M        	2072418	CE  										ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	1098U					17266847				PILOT REPORTED A SNAP OR SOMETHING GAVE AS HE ADVANCED THROTTLE ON GROUND.  ENGINE RPM STAYED AT 1,100 RPM.  INVESTIGATI	ON REVEALED THAT CABLE OUTER HOUSING SLIPPED OUT OF METAL RETAINER AT CLAMP NEAR CARBURETOR.  OUTER HOUSING APPARENTLY S	HRUNK FROM HEAT.  REPLACEMENT PART FROM CESSNA HAS RUBBERIZED HOUSING.  EXISTING UNITS SHOULD BE INSPECTED.				1	H	7	1 	3O			NT	3A12
1998043000439	19980430	00439	SO  	1998	4	30	98ZZZX976        	1	19980121	G	5521		SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										LT/RT ELEVATOR	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	35497	6777 				318052039				UPON C/W PIPER SB 998, BOTH ELEVATOR SPARS WERE CRACKED .50 INCH IN FROM OUTBOARD END.  (BOTH SPARS REPLACED).  ELEVATOR	 SPAR REPLACEMENT NR'S 40075-020 AND DASH 021 ARE IMPROVED DESIGNS.					1	L	7	2 	3O				A20SO
1998043000441	19980430	00441	CE  	1998	4	30	98ZZZX978        	1	19980128	G	5551		ATTACH FITTING  			CESSNA	150   	150G        	2071816	CE  										HORIZONTAL STAB	WORN            	B		A	FE4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	8623J	3110 				15066523				DURING AN ANNUAL INSPECTION, FOUND THE HORIZONTAL STABILZIER LOOSE AT THE REAR ATTACHMENTS.  THE STABILIZER COULD BE MOV	ED UP AND DOWN ABOUT .25 INCH.  THE REAR ATTACH FITTINGS WERE FOUND TO BE EXCESSIVELY WORN.					1	H	7	1 	3O				3A19
1998043000442	19980430	00442		1998	4	30	98ZZZX979        	1	19980217	G	8011		STARTER         	CONT        																FIELD COIL	SHORTED         	B			IC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15					Y289468					STARTER FAILED AT LESS THAN 200 HOURS SINCE FACTORY REMANUFACTURE.  DISASSEMBLY SHOWED A SHORTED FIELD COIL TO THRU BOLT	.  BOLT HAD ABRADED THROUGH COTTON TAPE INSULATION.  NO EVIDENCE OF VARNISH INSULATION HAVING BEEN APPLIED TO COILS.  AL	SO, NOTED WAS IMPROPER LOCATION OF THRU BOLTS.
1998043000443	19980430	00443	SO  	1998	4	30	98ZZZX980        	1	19980210	G	2740	65248	CONTROL ARM     			PIPER 	PA32  	PA32260     	7103206	SO  										STAB TRIM TAB	WRONG PART      	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	07	3255W					3277				UNABLE TO RIG TRIM TAB TRAVEL TO SPECIFICATION.  FOUND TRIM TAB CONTROL ARM WRONG.  OVERALL LENGTH OF PART IS TOO SHORT.	  BEND OF TUBE IS IN WRONG PLACE.  ANGLE OF TUBE TO PLATE IS WRONG.  WITNESS HOLE FOR ROD END IS MISSING.  SUBMITTER SUG	GESTED DIAGRAM OF CONTROL TAB AND STABILATOR TRAVELS CAN BE DIFFICULT TO READ ON MICROFICHE READER.  MAY HAVE BEEN INTER	PRETED WRONG.			1	L	7	1 	3O			 	A3SO
1998043000444	19980430	00444	CE  	1998	4	30	98ZZZX981        	1	19980218	G	2797	CC4	WIRE            			CESSNA	207   	207A        	2073604	CE  										RT WING FLAP	SHORTED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	62AK	13332				20700780				FLAP UP WIRE CHAFED ON STRINGER IN WING BETWEEN STA 85.62 AND STA 100.00; WIRE SHORTED AND BURNED HOLE IN WING.  INSPECT	ION OF 10-AMP CIRCUIT BREAKER FOUND A FAILURE OF BREAKER TO 'POP'.  SUBMITTER RECOMMENDED RUNNING WIRES IN A PLASTIC CON	DUIT FROM LEADING EDGE WIRE GROMMETS TO FLAP MOTOR PLUG.				1	H	7	1 	3O			 	A16CE
1998043000445	19980430	00445	SO  	1998	4	30	98ZZZX982        	1	19980221	G	8011	PM1201	STARTER         	PREAIR      		PIPER 	PA24  	PA24250     	7102404	SO  										RING GEAR	INOPERATIVE     	D	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	6484P				80083819	241602				THIS NEW STARTER WOULD NOT ENGAGE THE ENG RING GEAR WITHOUT MANUAL MANIPULATION OF THE BENDIX DRIVE PINION GEAR EVEN THO	UGH IT WAS BEING SUPPLIED WITH 14V BATTERY POWER THROUGH COPPER AIRCRAFT CABLES.  THE STARTER DID START THE ENG, HOWEVER	, UPON ENG SHUTDOWN AND RESTART, IT FAILED TO ENGAGE THE RING GEAR WITHOUT MANUAL MANIPULATION OF THE PINION GEAR.  THIS	 PERMANENT MAGNET STARTER CREATED SUCH A LARGE MAGNETIC FIELD DURING ENGINE ROTATION THAT IT CAUSED THE AIRPLANE WET COM	PASS TO SWING MORE THAN 90 DEGREES.  LAMAR STARTER (PM1202) WAS REMOVED AND REPLACED WITH A FRESHLY OVERHAULED ELECTROSY	STEMS STARTER (MZ422R) WHICH STARTED THE ENGINE SEVERAL TIMES WITHOUT AFFECTING THE MAGNETIC COMPASS.	1	L	7	1 	3O				1A15
1998043000446	19980430	00446	CE  	1998	4	30	98ZZZX983        	1	19980223	G	3230	08421022	IDLER GEAR      			CESSNA	310   	310J        	2074226	CE  										NLG RETRACT	FAILED          	D		A		O				OTHER                   				W			INADEQUATE Q C            			CL	CLIMB          	1			SW	15	3141L	10097				310J0141				IDLER IN NOSE GEAR RETRACT LINKAGE BROKE DURING RETRACTION DUE TO INTERFERENCE OF NOSE GEAR AND WHEELWELL DOORS.  NOSE G	EAR FAILED TO EXTEND DUE TO LOSS OF NITROGEN CHARGE IN STRUT.  STRUT HAD BEEN OVERSERVICED WITH HYDRAULIC FLUID.  WITH T	HE STRUT BEING OVERSERVICED WITH FLUID, THE EXTENSION APPEARED NORMAL ON THE GROUND.  PROPER SERVICING OF OLEO STRUT WOU	LD HAVE CAUSED A COLLAPSED STRUT WHEN THE NITROGEN CHARGE WAS LOST AND A COMPLETE PRE-FLIGHT INSPECTION WOULD HAVE NOTED	 THIS DISCREPANCY.		1	L	7	2 	3O			 	3A10
1998043000447	19980430	00447	SW  	1998	4	30	98ZZZX984        	1	19980210	G	7933	P87	CONNECTOR       			GULSTM	560   	560         	0141402	SW  										ENG OIL TEMP	MISMARKED       	B			CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	314QS	208  				5600441				CONNECTOR FOR OIL TEMPERATURE AT ENGINE MISLABELED, P.93.  PER MANUFACTURER, CONNECTOR SHOULD BE LABELED P.87.						1	H	7	2 	3O			 	6A1
1998043000448	19980430	00448	GL  	1998	4	30	98ZZZX985        	2	19980224	G	7313	47086	FILTER          		6890917     						ALLSN 	250C  	250C20B     	03013	GL  					FUEL NOZZLE	COLLAPSED       	D				K				NONE                    				C			F.O.D.                    			IN	INSP/MAINT     	1			WP	23					AG49560					FUEL NOZZLE FILTER IS PARTIALLY COLLAPSED DUE TO FOREIGN OBJECT INSERTED INTO INLET.											3	U			E4CE
1998043000449	19980430	00449	GL  	1998	4	30	98ZZZX986        	2	19980224	G	7321	23057344	FUEL CONTROL    	BENDIX      	252464429   						ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23			639  		BR55894		AE406008			FUEL CONROL UNIT WENT FROM 63 PERCENT TO 80 PERCENT AT FLIGHT IDLE SETTING, UNCOMMANDED.											3	U			E4CE
1998043000450	19980430	00450	EU  	1998	4	30	98ZZZX987        	1	19980214	G	7810	TD2056010006	MUFFLER         			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  										ENGINE	FAILED          	B	L		XHYR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			EA	09	2507T	1880 	4    			914				MUFFLER SEAM SPLIT FOLLOWING REPAIR.  TIS WAS 1 HOUR.  SECOND REPAIR LASTED 3 HOURS THEN MUFFLER EXPLODED.  INVESTIGATIO	N FOUND MUFFLER WAS FOR LYC O320 INSTEAD OF IO540.					1	L	7	1 	3O			RT	A51EU
1998043000453	19980430	00453	SO  	1998	4	30	98ZZZX990        	2	19980210	G	8530	537750	BOLT            		654654A1    	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					NR 5 CYL ROCKER	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NE	01	88604	1500 				421C0604	292083R			PILOT REPORTED OIL LEAKING FROM RIGHT ENGINE.  FOUND HOLE IN NR 5 CYLINDER ROCKER COVER.  HEAD OF BOLT BROKE OFF THAT AT	TACHES ROCKER ARM AND SHAFT TO CYLINDER ASSEMBLY.  NEW BOLTS INSTALLED AND NEW ROCKER COVER.					1	L	7	2 	3O	3	O		A7CE    	E7CE
1998043000454	19980430	00454	GL  	1998	4	30	98ZZZX991        	1	19980215	G	3220	2045000	GEAR            			AMTR  	QSTAIR	QUESTAIR20  		GL  										NLG	COLLAPSED       	H				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			SO	05	94FA					0017				UPON RETRACTION OF THE LANDING GEAR, PILOT NOTED THE 'RED LIGHT' REMAINED ILLUMINATED ON THE INSTRUMENT PANEL.  THIS LIG	HT IS A POSSIBLE INDICATION THE LANDING GEAR IS NOT FULLY RETRACTED.  THE PILOT CONTINUED THE FLIGHT TO GREENSBORO WHERE	 UPON LANDING THE NOSE GEAR FAILED AND THE PILOT LOST CONTROL OF THE AIRCRAFT.  THE AIRCRAFT FLIPPED OVER AND SUSTAINED 	SUBSTANTIAL DAMAGE.  THE PILOT WAS HOSPITALIZED, BUT RECEIVED ONLY MINOR INJURIES AND WAS RELEASED THE FOLLOWING DAY.			1	L	7	1 	3O			RC	EXPA1L71
1998043000455	19980430	00455	CE  	1998	4	30	98ZZZX992        	1	19980212	G	2731	0310625	ACTUATOR        		12600491    	CESSNA	172   	172E        	2072412	CE  										RT STAB TRIM	CORRODED        	B			FTSR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	2709T	2682 				17251609				DURING ROUTINE ANNUAL, TRIM ACTUATOR WAS FOUND ALMOST COMPLETELY STRIPPED.  DUE TO CORROSION VERY FEW THREADS REMAINED I	NSIDE ACTUATOR.  AIRCRAFT HAD BEEN ON F LOATS MOST OF ITS LIFE.					1	H	7	1 	3O			NT	3A12
1998043000456	19980430	00456	CE  	1998	4	30	98ZZZX993        	1	19980221	G	5500	0422344	RING            			CESSNA	210   	210D        	2073414	CE  										TAIL	FAILED          	D	L	A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	3772Y					21058272				THE TAIL TIE-DOWN RING BROKE WHEN THE OWNER ATTEMPTED A MINOR RE-ALIGNMENT.  REMOVAL OF THE FAILED PARTS REVEALED AN UNA	PPROAVED PART HAD BEEN INSTALLED BY SOMEONE IN THE PAST.  THIS RING BOLT CAN BE FOUND IN MOST ANY HARDWARE STORE.  IT HA	D BEEN WIRE FORMED OF LOW QUALITY STEEL WIRE, .25 INCH IN DIAMETER.  A FIELD WELD HAD BEEN USED TO CLOSE THE RING AT THE	 BOLT SHANK.  COMMON HARDWARE .25 INCH COARSE THREAD NUTS HAD BEEN USED TO SECURE THE RING IN THE AIRPLANE.			1	H	7	1 	3O			 	3A21
1998043000457	19980430	00457	SO  	1998	4	30	98ZZZX994        	1	19980213	G	5712	78500003	RIB             			PIPER 	PA34  	PA34200     	7103405	SO  										WING	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	1039U	2474 				347250024				DISCOVERED RIB SEVERELY CRACKED FROM RT FORWARD LOWER CORNER TO TOP CENTER DIAGONALLY DURING 100-HOUR INSPECTION.  SUSPE	CT FROM HARD LANDINGS.  AIRCRAFT USED FOR FLIGHT TRAINING ALMOST EXCLUSIVELY.  NEW PART OF SAME NUMBER IS MUCH STRONGER 	WITH MANY STRUCTURAL MODIFICATIONS.  SUSPECT PIPER IS AWARE OF PROBLEM.  RIB LOCATED IMMEDIATELY OUTBOARD OF MAIN GEAR A	TTACH POINT.			1	L	7	2 	3O				A7SO
1998043000458	19980430	00458	CE  	1998	4	30	98ZZZX995        	1	19980202	G	7120	626089	BRACKET         			BEECH 	35    	M35         	1151526	CE  										ENGINE MOUNT	FAILED          	D	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	9880R	3185 	396  			D6437				DURING NORMAL ANNUAL INSPECTION, FOUND BOTH ENGINE MOUNTS BROKEN THROUGH THE MIDDLE.  THIS CAUSED ENGINE TO LAY FARTHER 	DOWN ON ITS LEFT SIDE CAUSING FURTHER DAMAGE TO VALVE COVERS, COWLING, INTAKE MANIFOLD.  MOUNTS HAD BROKEN SINCE LAST OI	L CHANGE APPROXIMATELY 30 HOURS.  PILOT WAS UNAWARE OF PROBLEM.  SUBMITTER SUGGESTED DYE PENN INSPECTIONS OF PART ANYTIM	E ENGINE IS REMOVED FROM MOUNTS.  MECHANIC DYE PENETRATE INSPECTED OTHER 2 MOUNTS, NO DEFECTS NOTED.			1	L	7	1 	3O				3A15
1998043000459	19980430	00459	SO  	1998	4	30	98ZZZX996        	1	19980120	G	3213	6703704	STRUT           			PIPER 	PA44  	PA44180     	7104402	SO  										LT MLG	FAILED          	H	S		CE8S	K				NONE                    				O			OTHER                     			LD	LANDING        	1			SO	15	2103K	8100 				447995183				DURING LANDING, THE  LEFT MAIN GEAR OLEO STRUT ASSEMBLY SHEARED AT THE BASE OF THE STRUT TUBE WHERE IT ATTACHES TO THE L	OWER CASTING, AND SEPARATED FROM THE AIRCRAFT CAUSING DAMAGE TO THE WING, FLAP, PROPELLER, STABILATOR, AND VERTICAL FIN.					1	L	7	2 	3O				A19S0
1998043000460	19980430	00460	SO  	1998	4	30	98ZZZX997        	1	19980130	G	2750	62701101	CONTROL CABLE   			PIPER 	PA44  	PA44180     	7104402	SO  										FLAP	FRAYED          	H	S	A	CE8S	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	21113	7100 				447995040				DURING PREFLIGHT, DISCREPANCY WAS FOUND THAT WHEN THE FLAPS ARE SELECTED TO 10 DEGREES, FLAPS BARELY MOVED.  FURTHER INS	PECTION REVEALED FLAP CABLE WAS FRAYED ONLY TO TWO STRANDS.  THE AREA IN WHICH THE CABLE FRAY IS LOCATED IN AN AREA THAT	 IS NOT EASILY ACCESSIBLE TO INSPECT.  CABLE WAS REPLACED AND RIGGED TO MANUFACTURER'S SPECIFICATION.				1	L	7	2 	3O			 	A19S0
1998031200099	19980312	00099	SO  	1998	3	12	98ZZZX998        	1	19980223	G	2410	635796	COUPLING        			PIPER 	PA28  	PA28RT201T  	7102817	SO  	CONT  	O360  	TSIO360FB   	17025	SO  					ALTERNATOR DRIVE	FAILED          	B			TRKR	A				UNSCHED LANDING         				J	H		WARNING INDICATION        	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			SO	15	2175K	1000 				28R7931028				ALTERNATOR FAILED WHEN GEAR WAS RETRACTED.  GEAR LOWERED AND RETURNED TO FIELD.  PILOT REPORTED ALTERNATOR CHANGED ABOUT	 10 HOURS AGO AND REGULATOR CHANGED ABOUT 20 HOURS AGO FOR SAME PROBLEM.  FOUND ALTERATOR DRIVE SHEARED.  REF:  SPECIAL 	AIRWORTHINESS BULLETIN NR ANE 97-04 DATED JULY 24, 1997.  INSTALLED NEW DRIVE, OPERATION CHECKS GOOD.				1	L	7	1 	3O	3	O		2A13    	E9CE
1998031200100	19980312	00100	CE  	1998	3	12	98ZZZX999        	1	19980203	G	3240	070009993	LINE            			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  					LT BRAKE	FAILED          	D				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O	K		OTHER                     	FLUID LOSS                		TO	TAKEOFF        	1			SW	01	2939E	4082 				18268222	470551			LEFT BRAKE FAILED ON TAKEOFF ROLL AND TAKEOFF ABORTED.   FOUND SMALL HOLE WORN THROUGH ALUMINUM BRAKE LINE WHERE LINE CH	AFED ON AFT SIDE OF ENTRY STEP CASTING. INSTALLED NEW 0700099-93 BRAKE LINE.  SUGGEST REMOVING LANDING GEAR STRUT FAIRIN	GS FOR INSPECTION AT ANNUAL INSPECTION.				1	L	7	1 	3O	3	O	NT	3A13    	E273
1999010800574	19990108	00574	SW  	1999	1	8	99ZZZM13         	1	19980815	G	2820	714763	FUEL LINE       			BBAVIA	8     	8GCBC       	1220803	SW  										RT WING	DAMAGED         	B			CL4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	778AC	275  			38197	38197				DURING 100 HOURS INSPECTION, DELTA AIRCRAFT MAINTENANCE REPORTED THE BOLT HOLDING THE LOWER CABLE GUARD ON THE RIGHT FLA	P BELLCRANK IN THE RIGHT WING ROOT WAS CONTACTING THE FUEL LINE WHEN THE FLAPS ARE ACTUATED.  THE BOLT HAS CAUSED DAMAGE	 TO THE FUEL LINE, AND IF ALLOWED TO CONTINUE, WILL CAUSE A FUEL LINE FAILURE.  (M)				1	H	7	1 	3O				A21CE
1999010800570	19990108	00570	SW  	1999	1	8	99ZZZM9          	1	19980712	G	2710		AILERON         			BBAVIA	8     	8GCBC       	1220803	SW  										WING	OUT OF RIG      	B			CL4R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	03	695AC	30   			39498	39498				PILOT FLYING NEW AIRCRAFT FROM AMERICAN CHAMPION FACTORY TO ANCHORAGE,ALASKA, REPORTED THE AIRCRAFT FLEW 'HALF OF A BALL	' OUT OF TRIM, AND WAS UNABLE TO CORRECT THE PROBLEM BY ADJUSTING THE RUDDER TRIM TAB.  FLAPS AND AILERONS FOUND NOT TO 	BE RIGGED IAW SCOUNT SERVICE MANUAL.  (M)				1	H	7	1 	3O				A21CE
1999010800011	19990108	00011	CE  	1999	1	8	99ZZZX1          	1	19981203	G	2810		FUEL CELL       			CESSNA	172   	172R        	2072401	CE  										LT WING	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07	9710F	496  				17280017				LEFT WING FUEL BAY AREA, OUTBOARD CORNER AREA WHERE BOXED CORNER MEETS THE SKIN CORNER RELIEF FOR FUEL BAY.  AREA HAS B-	2 FUEL BAY SEALERS OFF, AND WAS LEAKING FUEL.  ON THE BACKSIDE OF THIS AREA IS WING COURTESY LIGHT.  ALSO, CORNER RELIEF	 FOR BOX IS .25 INCH.  SUBMITTER STATED COULD CAUSE FIRE IF FUEL LEAKS ON COURTESY LIGHT.  SENT CONDITION REPORT TO CESS	NA.			1	H	7	1 	3O			NT	3A12
1999010800020	19990108	00020	NE  	1999	1	8	99ZZZX10         	2	19980319	G	7421	CH346593	IGNITER         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	DAMAGED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	318QS					5600418	JC0323			REMOVED IGNITER FOR PHASE 4 INSPECTION.  DETERMINED CENTER ELECRTRODE MISSING.  SUBMITTER STATED THIS IS SUPPOSED TO BE 	NEW STYLE PLUG, TO PREVENT THIS.  REPLACED PLUG WITH NEW.  BORESCOPED ENGINE.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA
1999010800336	19990108	00336	CE  	1999	1	8	99ZZZX100        	1	19980917	G	2913	993880023	POWER PACK      			BEECH 	99    	99          	1154002	CE  										HYDRAULIC SYSTEM	LEAKING         	H				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			GL	13	399CZ		1026 		82	U52				UNABLE TO RETRACT GEAR DUE TO PUMP WEAKENING CAUSED BY LEAKING/WORN SEALS AND BLEED DOWN OF SYSTEM.						1	L	7	2 	3T				A14CE
1999031901006	19990319	01006	CE  	1999	3	19	99ZZZX1005       	1	19981015	G	2140	59181022	AUX ELEC HEATER 			CESSNA	425   	425         	2076018	CE  										CABIN	FAILED          	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	09	5PP	4300 				4250198				OPERATOR NOTED LOW HEAT OUTPUT.  MAINTENANCE REMOVED AUXILIARY ELECTRIC HEATER AND FOUND TWO OUT OF THREE HEATER COILS B	URNED THROUGH WHERE THEY ATTACH TO THE WIRE HARNESS POST.  ALSO NOTED SOME CARBON BUILD-UP ON ATTACH POST SCREW THREADS.	  CAUSE OF FAILED COILS UNDETERMINED.  MAINTENANCE INSTALLED NEW AUXILIARY ELECTRIC HEATER.				1	L	7	2 	3T			RT	A7CE
1999031901008	19990319	01008	CE  	1999	3	19	99ZZZX1007       	1	19981202	G	2910	LW12540	ADAPTER         			BEECH 	65    	65          	1152802	CE  										HYDRAULIC PUMP	CRACKED         	H	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	01	5080L					LF59				WHILE INSPECTING ENGINE, LEAK WAS FOUND COMING FROM REAR.  AFTER CLOSER INSPECTING, SUSPECTED CRACK WAS FOUND AND ADAPTE	R WAS REMOVED FOR POSITIVE VERIFICATION.  WEIGHT OF VACUUM PUMP STRESSING PUMP ADAPTER CAUSING IT TO CRACK.  SUBMITTER S	UGGESTED MORE MATERIAL NEEDS TO BE ON FLANGE FOR MORE STRENGTH.  STC NR SA444SW.				1	L	7	2 	3O				3A20
1999010800337	19990108	00337	CE  	1999	1	8	99ZZZX101        	1	19980925	G	2432	SACUBMN001	WIRE            			CESSNA	172   	172R        	2072401	CE  										RT ENGINE	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	234CF	337  				17280110				P/N SACU-BMN001 POSITIVE BATTERY WIRE AT ALTERNATOR CHAFED HOLE IN P/N 0555228-24 BAFFLE ASSY, RIGHT FORWARD ENGINE COMP	ARTMENT.  THIS BEING NEW 172 WITH 337.2 TT HOURS, RECOMMEND MANDATORY SB OR POSSIBLE AD.					1	H	7	1 	3O			NT	3A12
1999032600146	19990326	00146	SO  	1999	3	26	99ZZZX1011       	2	19981210	G	8520	628488	LIFTER          			CESSNA	206   	TU206F      	2073353	CE  	CONT  	O520  	TSIO520C    	17040	SO  					ENGINE	FAILED          	G	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04	51237	112  				U20601983	14093372C			THE EXHAUST LIFTER, PN 628488, IS CALLED FOR INSTALLATION IN TSIO520C IN TCM MANUAL NR X30579A.  SIX NEW LIFTERS WERE IN	STALLED AT OVERHAUL OF ENGINE.  ONE YEAR AND 112 HOURS LATER, ALL SIX NEW TCM CYLINDER ASSYS HAD WORN OUT EXHAUST VALVES	 AND GUIDES.				1	H	7	1 	3O	3	O		A4CE    	E8CE
1999010800338	19990108	00338	CE  	1999	1	8	99ZZZX102        	1	19980903	G	2820		FUEL SYSTEM     			CESSNA	185   	A185F       	2072821	CE  										ENGINE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	11	61387		578  			18504168				CONTAMINATED FUEL RECEIVED AT AIRPORT DURING JULY, AUG, 1998, IS BELIEVED RESPONSIBLE FOR:  INCREASED OIL CONSUMPTION, C	YLINDER COMPRESSIONS RAPIDLY DETERIORATING, INJECTORS PLUGGING, SPARKPLUGS FOULING, FUEL SYSTEM COMPONENTENTS FAILING. A	IRCRAFT ARRIVED WITH 300 HRS TSO, NEW CYLINDERS, CURRENTLY 578 HRS TSO APPROX.  CONSUMING 1 QUART OIL EVERY 2 HRS, ALL C	OMPRESSIONS LOW 60'S, OCCASIONAL 50'S.  ELECTRIC FUEL PUMP FAILURE, FUEL COMPUTER FAILURE, CONTAMINENTS PRESENT IN FUEL 	(ARGAS 100LL) FOR MANY MONTHS.		1	H	7	1 	3O				3A24
1999032600159	19990326	00159	CE  	1999	3	26	99ZZZX1024       	1	19981023	G	5751	16913000516	BRACKET         			BEECH 	23    	C23         	1151242	CE  										AILERON	CRACKED         	B			GN1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	6704J	3178 				M2238				DURING ANNUAL INSPECTION, FOUND BRACKET CRACKED AT AILERON CONTROL ARM ATTACH POINT.						1	L	7	1 	3O				A1CE
1999032600161	19990326	00161	CE  	1999	3	26	99ZZZX1026       	1	19981223	G	2140		LINE            		8259JR2     	CESSNA	310   	T310R       	2074246	CE  										HEATER	CORRODED        	H				A				UNSCHED LANDING         				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			SW	99	6177X	1450 			486	310R1316				PILOT REPORTED THE SMELL OF FUEL IN COCKPIT ONCE CABIN COMBUSTION HEATER WAS TURNED ON.  PILOT SHUT DOWN HEATER AND LAND	ED. UPON INSPECTION OF HEATER INSTALLATION IN NOSE COMPARTMENT, FUEL WAS FOUND 'POOLED'.  THE FUEL LINE FROM COMBUSTION 	HEATER FUEL PUMP TO FUEL NOZZLE WAS FOUND CORRODED AND LEAKING BADLY.  CESSNA MEB-95-9 WAS PERFORMED JUST 39 HOURS PRIOR	.  (HEATER HOBBS.)  MEB-95-9 DOES NOT ADDRESS FAILED FUEL LINE, ONLY FUEL LINE TO HEATER.  ALL HEATER FUEL LINES FROM WI	NG ROOT CONTROL VALVE/FILTER WERE REPLACED WITH STAINLESS STEEL ASSEMBLIES.  THIS TECH RECOMMENDS REPLACMENT OF ALL HEAT	ER SUPPLY FUEL LINES WITH STAINLESS STEEL.	1	L	7	2 	3O				3A10
1999032600163	19990326	00163	SO  	1999	3	26	99ZZZX1028       	1	19981216	G	2842	6810102	FUEL SENDER     			PIPER 	PA28  	PA28181     	7102807	SO  										RT FUEL TANK	DAMAGED         	B			TIMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	75337					287690332				THE SQUARE FLOAT BLOCK ON THE FUEL SENDING UNIT HAD DETERIORATED AND SLID OFF CONNECTING ROD.  FUEL QUANTITY WAS INDICAT	ING EMPTY WHEN TANK WAS FULL.					1	L	7	1 	3O				2A13
1999010800339	19990108	00339	SO  	1999	1	8	99ZZZX103        	2	19980820	G	7414	4301	MAGNETO         	SLICK       		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9349U				98031536	15078298				MAGNETO INTERNALLY TIMED 180 DEGREES OUT.						1	H	7	1 	3O	3	O		3A19    	E252
1999032600168	19990326	00168	CE  	1999	3	26	99ZZZX1033       	1	19981215	G	3230	98811221	RESERVOIR       		98811241    	CESSNA	182   	R182        	2072734	CE  										MLG	LEAKING         	D	L			O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	01	757VE	1604 			1765	R18201267				MAIN LANDING GEAR FAILED TO EXTEND NORMALLY OR WITH EMERGENCY HAND PUMP.  A SUCCESSFUL PARTIAL GEAR LANDING WAS MADE WIT	H MINIMAL DAMAGE.  INVESTIGATION SHOWED NO FLUID IN HYDRAULIC POWER PACK AND EVIDENCE OF MINOR LEAKAGE AT NOSE GEAR ACTU	ATOR AND MAIN GEAR DOWNLOCK ACTUATORS.  AFTER SERVICING RESERVOIR, HYDRAULIC GEAR SYSTEM OPERATED NORMALLY.				1	H	7	1 	3O			RT	3A13
1999010800340	19990108	00340	SO  	1999	1	8	99ZZZX104        	2	19980820	G	7414	4301	MAGNETO         	SLICK       		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	9349U				98051625	15078298				MAGNETO INTERNALLY TIMED 180 DEGREES OUT.						1	H	7	1 	3O	3	O		3A19    	E252
1999010800341	19990108	00341	EA  	1999	1	8	99ZZZX105        	2	19980812	G	8500		ENGINE          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NOSE	MAKING METAL    	B			WIWR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	07	123GJ	4689 	49   			17270706	L607276T			WHILE DOING NIGHT TOUCH-AND-GOES, PILOT REPORTED ENGINE BEGAN TO RUN ROUGH AND 'MISS' AT RPM'S GREATER THAN 1,700.  FURT	HER INVESTIGATION SHOWED LARGE AMOUNTS OF METAL CONTAMINATION IN FILTERS AND SCREEN.  SOME FLAKES WERE AS MUCH AS .25 IN	CH IN DIAMETER.  ENGINE WAS REMOVED AND SENT BACK TO LYC FOR REPAIR.  OIL CHANGE AND AD 80-04-03R2 HAD BEEN ACCOMPLISHED	 3.1 HRS EARLIER WITH NO CONTAMINATION FOUND AT THAT TIME.			1	H	7	1 	3O	3	O	NT	3A12    	E274
1999032600187	19990326	00187	EA  	1999	3	26	99ZZZX1053       	2	19981206	G	8540	67514	GEAR            			BNORM 	BN2   	BN2B26      	1520350	EU  	LYC   	O540  	O540E4C5    	41532	EA  					CRANKSHAFT	BROKEN          	D				A				UNSCHED LANDING         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			SO	21	861VL	7548 	1953 			2155	L1291640A			FLT 709 - VIEQUES TO LUIS MUNOS MARIN INT'L AIRPORT OVER PLAZA CAROLINA, LEFT ENGINE LOST POWER AND QUIT.  REAR CASE OPE	NED AND FOUND CRANKSHAFT GEAR BROKEN AND ENGINE CONTAMINATED.					1	H	7	2 	3O	3	O	RT	A17EU   	E295
1999032600188	19990326	00188	SO  	1999	3	26	99ZZZX1054       	1	19981001	G	3211	2040100	FITTINGS        			PIPER 	J3    	J3C65       	7100510	SO  										LT AFT MLG	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	88522	3879 				16147				DURING A ROUTINE INSPECTION, FOUND CRACK ON THE BASE OF THE MOUNTING LUG ON THE AFT RT WING STRUT/GEAR ATTACH FITTING, P	N 20401-01.  AFTER PEELING OFF THE REMAINING DOPE FINISH ON THE FITTING, DISCOVERED A SECOND CRACK.  AT LT FITTING, PN 2	0401-00, AND AFTER SCRAPING OFF THE DOPE FINISH, DISCOVERED TWO MORE CRACKS.  POSSIBLE CAUSE, PREVIOUS AIRCRAFT DAMAGE. 	 SUBMITTER RECOMMENDED PAINTING FITTINGS, NOT COVER THEM UP WITH DOPE FINISH.			1	H	7	1 	3O				A691
1999032600189	19990326	00189	SO  	1999	3	26	99ZZZX1055       	1	19981001	G	3211	2040101	FITTINGS        			PIPER 	J3    	J3C65       	7100510	SO  										RT AFT MLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	88522	3879 				16147				DURING A ROUTINE INSPECTION, FOUND CRACK ON THE BASE OF THE MOUNTING LUG ON THE AFT RT WING STRUT/GEAR ATTACH FITTING, P	N 20401-01.  AFTER PEELING OFF THE REMAINING DOPE FINISH ON THE FITTING, DISCOVERED A SECOND CRACK.  AT LT FITTING, PN 2	0401-00, AND AFTER SCRAPING OFF THE DOPE FINISH, DISCOVERED TWO MORE CRACKS.  POSSIBLE CAUSE, PREVIOUS AIRCRAFT DAMAGE. 	 SUBMITTER RECOMMENDED PAINTING FITTINGS, NOT COVER THEM UP WITH DOPE FINISH.			1	H	7	1 	3O				A691
1999010800342	19990108	00342	SO  	1999	1	8	99ZZZX106        	2	19980921	G	8530	652956	VALVE           		654651      						CONT  	O520  	IO520D      	17032	SO  					ENGINE	MISMANUFACTURED 	B				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07							566203			PURCHASED 4 NEW VALVES, (2 INTAKE AND 2 EXHAUST) IN LIEU OF TCM SB 98-1B.  ONE EXHAUST VALVE, THE SUBJECT OF THIS REPORT	, WAS FOUND TO BE .0005 INCH UNDER THE MINIMUM NEW PART DIMENSION PER TCM OVERHAUL MANUAL TABLE OF LIMITS.										3	O			E5CE
1999032600195	19990326	00195	SO  	1999	3	26	99ZZZX1061       	2	19980129	G	8520		CAMSHAFT        			CESSNA	182   	182N        	2072730	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	92311	708  				18260145	321101R			OVER THE LIFE OF THE ENGINE, THIS ENGINE HAS BEEN ON OIL ANALYSIS.  THE TEST SHOWED A TREND OF HIGH AL AND FE STARTING A	T 529 HOURS WITH THE RECOMMENDATION FOR RE-TEST IN 25 HOURS.  THE TREND CONTINUED WITH NO DECREASE, BORESCOPES WERE USED	 TO DETECT.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1999032600196	19990326	00196	SO  	1999	3	26	99ZZZX1062       	1	19980416	G	3710	142418	PRESS MANIFOLD  			PIPER 	PA46  	PA46310P    	7104605	SO  										VACUUM SYSTEM	WORN            	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9125R	1907 				4608057				OPERATOR HAS EXPERIENCED MULTIPLE VACUUM PUMP FAILURES OF STANDBY PUMP.  HE OPERATES PUMP CONTINUOUSLY.  AT LAST PUMP RE	PLACEMENT, FOUND PUMP SEVERELY OVERHEATED.  TRACED POSSIBLE CAUSE TO DEFECTIVE PRESSURE MANIFOLD ALLOWING PRESSURE FROM 	PRIMARY VACUUM PUMP TO BACK UP INTO STANDBY PUMP.  AIRBORNE PRODUCT REF MEMO NR 39 REFERS TO THIS VALVE AND RECOMMENDS A	NNUAL TESTING AND REPLACEMENT AFTER 10 YEARS.  VALVE ON THIS AIRCRAFT WAS 12 YEARS OLD.			1	L	7	1 	3O			RT	A25SO
1999032600319	19990326	00319	CE  	1999	3	26	99ZZZX1066       	1	19980707	G	2730	8ST56	BELLCRANK       			GLSDKS	DG8003	DG800B      	805015 	CE  										ELEVATOR	LOOSE           	B			L1MR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	98NL					8126B55				ELEVATOR PUSH ROD ATTACHMENT BOLT THROUGH ST3/5 FORK AND 85T/56 BELLCRANK APPARENTLY VIBRATED OUT FROM LACK OF NYLOC NUT	.  THERE WAS NO VISIBLE SIGN OF NUT OR WASHERS IMPRINTED ON FORK OR THREADS OF BOLT.  BOLT WAS FOUND ON TOP OF FORWARD C	ORNER OF TAILWHEEL CLOSE-OUT BULKHEAD.  NO NUT OR WASHERS WERE FOUND.  SUBMITTER RECOMMENDED INSPECTIONS.				1	K	7	1 	3I			CR	G01CE
1999032600321	19990326	00321	SO  	1999	3	26	99ZZZX1068       	1	19980627	G	5730	6206102	SKIN            			PIPER 	PA28  	PA28151     	7102805	SO  										FWD RT WINGWALK	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9516K	6471 				287615210				CRACKS FOUND DURING ANNUAL INSPECTION.  SUBMITTER STATED THIS IS POSSIBLY THE 4TH ONE SHOP HAS FOUND.						1	L	7	1 	3O				2A13
1999032600322	19990326	00322	SO  	1999	3	26	99ZZZX1069       	1	19980627	G	5730	6206104	SKIN            			PIPER 	PA28  	PA28151     	7102805	SO  										AFT RT WINGWALK	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	9516K	6471 				287615210				CRACKS FOUND DURING ANNUAL INSPECTION.  SUBMITTER STATED THIS IS POSSIBLY THE 4TH ONE SHOP HAS FOUND.						1	L	7	1 	3O				2A13
1999010800343	19990108	00343	CE  	1999	1	8	99ZZZX107        	1	19981201	G	3230		METER           			BEECH 	95    	95B55       	1152729	CE  										COCKPIT	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	98HA					TC2111				LANDING GEAR RELAY CIRCUIT BREAKER TRIPS.  REPAIRED SHORTED HOBBS METER WIRE IN PILOT'S SIDE PANEL.						1	L	7	2 	3O			RT	3A16
1999032600326	19990326	00326	CE  	1999	3	26	99ZZZX1073       	1	19981221	G	8120	40679558	TURBOCHARGER    		TH08A67     	CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  					ENGINE	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23					AG020191					SUBJECT AIRCRAFT IS LOCATED IN AUSTRALIA.  IT WAS REPORTED THAT THIS ENGINE WAS SURGING IN-FLIGHT.  INVESTIGATION THERE 	FOUND A TURBOCHARGER WITH 'EXCESSIVE END FLOAT'.  THE TURBOCHARGER WAS RETURNED TO ALLIED SIGNAL AND INSPECTION FOUND A 	WORN THRUST BEARING.				1	L	7	2 	3O	3	O		3A25    	E8CE
1999032600327	19990326	00327	CE  	1999	3	26	99ZZZX1074       	1	19980928	G	8120	4067958	TURBOCHARGER    		TH08A67     	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					THRUST BEARING	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	414GP				AJ039587	414A0331				SUBJECT AIRCRAFT WOULD NOT DEVELOP SPECIFIED BOOST.  INVESTIGATION FOUND EXCESSIVE AXIAL PLAY IN THE TURBOCHARGER AND OT	HER UNRELATED EXHAUST SYSTEM PROBLEMS.  THE TURBOCHARGER WAS RETURNED TO ALLIED SIGNAL AND INSPECTION FOUND A WORN THRUS	T BEARING.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1999032600330	19990326	00330	CE  	1999	3	26	99ZZZX1077       	1	19981230	G	8010	S15801A	SOLENOID        			CESSNA	210   	210N        	2073453	CE  										STARTER	FAILED          	B			DC1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	07	4617C	54   				21063577				PILOT REPORTED TOTAL ELECTRICAL FAILURE FOUND BATTERY CONTACTOR INOPERATIVE.  NO POWER FROM BATTERY SWITCH TERMINAL.  OP	EN CIRCUIT.  CONTACT LAST CHANGED ON 10-5-98.  INFO ON CONTACTOR LABEL:  W-4/RBM.  PN 8781-9 COIL 24 VDC CONT.  SN S-158	0A1.				1	H	7	1 	3O				3A21
1999012000013	19990120	00013	SW  	1999	1	20	99ZZZX108        	1	19980822	G	2730	91303000	BELLCRANK       			MOONEY	M20   	M20M        	5870222	SW  										ELEVATOR	LOOSE           	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	1085S	711  				270036				BELLCRANK IS PARTING DUE TO RIVETS WORKING LOOSE.						1	L	7	1 	3O			RT	2A3
1999010800344	19990108	00344	CE  	1999	1	8	99ZZZX109        	1	19980731	G	5210	5043003115	BELLCRANK       			BEECH 	200   	B200        	1152922	CE  										PASSENGER DOOR	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	3092S	604  				BB1498				DOOR WOULD NOT LATCH PROPERLY, AND SOMETIMES GET LOCKED IN CLOSED POSITION.  ALSO, LARGE PRESSURIZATION LEAK DEVELOPED A	T FORWARD UPPER CORNER OF DOOR.  UPON FURTHER INSPECTION, FOUND FORWARD BELLCRANK, P/N 50-430031-15, BENT AND IMPROPERLY	 MANUFACTURED AT 60 DEGREES INSTEAD OF 90 DEGREES BETWEEN BELLCRANK ARMS.				1	L	7	2 	4T				A24CE
1999010800021	19990108	00021	CE  	1999	1	8	99ZZZX11         	1	19980227	G	3260	664100036	NUT             			CESSNA	500   	560CESSNA   	2076750	CE  										MLG	MISSING         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	325QS	614  				5600425				WHILE INSPECTING LANDING GEAR ASSY DETERMINED BOTH MAIN LANDING GEAR SQUAT SWITCHES MISSING JAM NUT THAT SECURES THE ROD	 END TO THE TORQUE LINK.  THE SQUAT SWITCH ASSY COULD BE TURNED AND MOVED.					2	L	7	2 	4F			RT	A22CE
1999010800345	19990108	00345	CE  	1999	1	8	99ZZZX110        	1	19980824	G	2820	AN627021312	HOSE            			BEECH 	35    	N35         	1151528	CE  										FUEL SYSTEM	FAILED          	H	L	A		O				OTHER                   				K	B	A	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                	LD	LANDING        	1			SW	99	1503Z					D6825				AFTER STARTING ENGINE AND TAXIING DOWN TO TAKEOFF.  AT TAKEOFF, PILOT REPORTED HE SMELLED SMOKE, BUT THOUGHT IT MAY BE P	AINT BURNING OFF EXHAUST BECAUSE ACFT HAD JUST BEEN PAINTED.  ON APPROACH FOR LANDING, CHT WAS HIGHER THAN NORMAL SO PIL	OT REPORTED OPENING COWL FLAPS.  ON LANDING, PILOT SAW FLAMES COMING OUT OF ENG COWLING.   FIRE EXTINGUISHED.  UPON INVE	ST, APPEARS FIRE STARTED AT FUEL LINE THAT COMES OUT OF FUEL CONTROL TO BLKHD FITTING AT TUNNEL AREA FOR FUEL PRESS GAUG	E.  HOSE LOOKS LIKE IT SPLIT IN THE MIDDLE AND SPRAYED FUEL BACK ONTO MUFFLER AND KEEL AREA OF NOSE WW AREA.  IN TURN, W	HEN COWL FLAPS WERE OPEN, ACTED AS AN ACETYLENE EFFECT AND BURNED THRU KEEL AREA THAT MELTED STEERING ROD IN HALF.	1	L	7	1 	3O				3A15
1999010800346	19990108	00346		1999	1	8	99ZZZX111        	2	19981001	G	8520		CRANKSHAFT      																	ENGINE	MISOVERHAULED   	F				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	13										DURING DISASSY OF CORE ENGINES RETURNED TO TEXTRON LYC, NOTICED ON SEVERAL INSTANCES, 7 AS OF THIS DATE, WHERE CRANKSHAF	TS ARE BEING GROUND OR POLISHED IN THE CHEEK AREAS BY OVERHAULING AGENCIES, PRESUMABLY TO BALANCE THE UNIT.  TEXTRON LYC	 HAS NO APPROVED DATA TO PERFORM THIS PROCESS.  ANY GRINDING ON CRANKSHAFT REQUIRES RE-NITRIDING.  IN ADDITION, THE CLOS	ER THE GRINDING MARKS ARE TO THE BEARING JOURNAL OR FILLET AREA, THE MORE CRITICAL THE CONDITION, AS STRESS RISERS ARE I	NDUCED.  SUGGEST ALL MECH BE AWARE OF AND INSPECT FOR THIS CONDITION DURING ASSY AND HAVE ANYONE INVOLVED WITH ENG O/H T	O ASK FACILITY THAT RE-CONDITIONS CRANKSHAFT IF THEY GRIND OR POLISH THE CHEEK AREAS, AND, IF SO, BY WHAT APPROVED DATA.
1999032600371	19990326	00371	GL  	1999	3	26	99ZZZX1118       	2	19980924	G	7250	A23031938	NOZZLE          								ALLSN 	250C  	250C20B     	03013	GL  					SECOND STAGE	CRACKED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17										THE FAA-PMA NOZZLE WAS REMOVED FROM AN ALLISION 250-C20B TURBINE THAT WAS RECEIVED FOR OVERHAUL.  UPON FLUORESCENT PENET	RANT INSPECTION, FOUND A SERIES OF CRACKS ON BOTH SIDES OF THE DIAPHRAGM IN THE RADIUS OF THE BEND AT ITS OUTER DIAMETER	.  THE CRACKS ON THE AFT SIDE EXTEND ABOUT 75 PERCENT OF THE WAY AROUND THE DIAPHRAGM, BUT ARE NOT COMPLETELY THROUGH TH	E METAL.  THE MANUFACTURER STATES IN THEIR ICA THAT ALTHOUGH THE OEM HAS THIS PROBLEM WITH THEIR PARTS, DIAPHRAGM CRACKI	NG HAS NOT BEEN A PROBLEM IN THE PMA PART.							3	U			E4CE
1999032600372	19990326	00372	NM  	1999	3	26	99ZZZX1119       	1	19981014	G	2460	584076	RELAY           			PIPER 	PA60  	PA60601P    	7106012	NM  										BATTERY BOX	FAILED          	B			GN1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NE	01	45HJ	880  				61P060379632				BATTERY MASTER RELAY PRIMARY COIL FAILED (SHORTED), HAD NO CIRCUIT PROTECTION.  CONTROL WIRE TOOK HEAVY CURRENT AND BURN	ED THE LENGTH OF FUSELAGE TO MASTER SWITCH AND THEN TO GROUND.  RELAY HAD DAMAGE FROM HEAVY CURRENT DRAW.  INSPECTED WIR	E BUNDLE, REPLACED WIRE WITH NEW.  REPLACED RELAY AND DIODES WITH NEW.				1	M	7	2 	3O			RT	A17WE
1999010800347	19990108	00347	SO  	1999	1	8	99ZZZX112        	1	19981004	G	2710	62701002	CONTROL CABLE   			PIPER 	PA28  	PA28180     	7102808	SO  										AILERON	FRAYED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	8294W	5325 				282458				DURING ANNUAL INSPECTION, TOP OF TUNNEL BETWEEN PILOT AND PASSENGERS SEAT WAS REMOVED.  P/N 62701-002 AILERON CABLE, BOT	H LT AND RT FOUND FRAYED.  THE DAMAGE WAS BEHIND 2 METAL ROLLER PULLEYS THAT BOTH CABLES PASSED UNDER.  PULLY P/N 62825-	00.  DAMAGE HARD TO SEE DUE TO LOCATION, BUT COULD BE FELT WITH A RAG RUN DOWN CABLE ON BOTH SIDES.  CABLE REMOVED AND W	HEN TWISTED, CABLE OPENED UP TO REVEAL ABOUT 25 PERCENT OF THE CABLE WORN THRU.  THIS WAS ALSO FOUND ON ANOTHER PIPER PA	-28-160, AT SAME AIRPORT.  TIME DIFFERENCE BETWEEN ACFT 1,500 HRS.  POSSIBLE CAUSE WAS CABLE WORK HARDENING AROUND METAL	 PULLEYS.	1	L	7	1 	3O			 	2A13
1999032600375	19990326	00375	SO  	1999	3	26	99ZZZX1122       	2	19981106	G	8530	631521	VALVE SPRINGS   		653452D     	CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					CYLINDER HEAD	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	748CA	1152 				421C0905	604132			UPON AIRCRAFT AND ENGINES ROUTINE OPS 1 AND 2 (100 HRS) INSPECTIONS, COMPRESSION ON NR 5 CYLINDER WAS 52/80 AND LEAKING 	BY THE STATIC SEAL (EXHAUST VALVE).  CYLINDER WAS DISSASSEMBLED AND VISUALLY INSPECTED.  FOUND BOTH INTAKE AND EXHAUST V	ALVE INNER VALVE SPRINGS WERE BROKEN IN 2 EACH PIECES AND VALVE FACES HAD EXCESSIVE WEAR.  SPECULATION ON POSSIBLE CAUSE	 AND RECOMMENDATION TO PREVENT RECURRENCE CANNOT BE GIVEN AT THIS TIME.  INVESTIGATION OF PARTS IS STILL ONGOING WITH MA	INTENANCE AND TCM REP.		1	L	7	2 	3O	3	O		A7CE    	E7CE
1999032600680	19990326	00680	SO  	1999	3	26	99ZZZX1133       	1	19980211	G	5410	12008527DD1	FRAME           			EMB   	120   	EMB120RT    		SO  										LT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	215AS					120010				RECOMMEND REPLACING BOTH FRAMES, AND CONTINUE MOINITORING IAW EXISTING MAINTENANCE CHECKS.						2	L	7	2 	4T			RT	A31SO
1999032600681	19990326	00681	SO  	1999	3	26	99ZZZX1134       	1	19980211	G	5410	12003852001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT/RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	215AS					120010				DURING ROUTINE MAINTENANCE CHECKS, CRACKS WERE FOUND ON BOTH ENGINE NACELLE NR 1 FRAMES.  ON THE LT FRAME, THE CRACK IS 	LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB, BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF TH	E FRAME.  ON THE RT FRAME, THE CRACK IS LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB, BETWEEN THE TOP OUTBOARD MOUNTI	NG BOLT HOLE AND THE OUTBOARD EDGE OF THE FRAME.  RECOMMEND REPLACING BOTH FRAMES AND CONTINUE MONITORING IAW EXISTING M	AINTENANCE CHECKS.		2	L	7	2 	4T			RT	A31SO
1999010800349	19990108	00349	SO  	1999	1	8	99ZZZX114        	1	19981211	G	3610		SHAFT           	AIRBORNE    	842CW       	PIPER 	PA31  	PA31P       	7103120	SO  										PNEUMATIC PUMP	SHEARED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	6805L	420  			12AK000086	31P7				PUMP SEIZED, SHAFT SHEARED.  SUBMITTER STATED CONTINUE TO HAVE SHORT LIFE WITH THESE PUMPS.						1	L	7	2 	3O				A8EA
1999032600691	19990326	00691	CE  	1999	3	26	99ZZZX1144       	1	19981210	G	5330		PANEL           			CESSNA	500   	S550        	2076607	CE  										WINGS	CORRODED        	B			GW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	39TF	4775 				S5500139				REMOVAL OF TKS PANELS REVEALED LIGHT TO MODERATE CORROSION ON TKS PANEL WING ATTACH FLANGES.  NUTPLATES ARE INSTALLED ON	 ATTACH FLANGES FOR SECURING TKS PANELS TO THE WING STRUCTURE.  INVEST SHOWED DURING SYS OPER, TKS FLUID MIGRATED PAST A	TTACH SCREWS TO THE ATTACH FLANGES AND NUTPLATES.  ALL SILVER PLATED NUTPLATES WERE REPLACED WITH CESSNA APPROVED DRY FI	LM NUTPLATES;  AREA TREATED, PRIMED, AND PAINTED TO PROTECT AFFECTED AREA, PANELS REINSTALLED PER S550 MM.  DURING INSTA	LL OF ATTACH HDWE, CLOSE ATTN PAID TO APPLY TYPE I PRC SEALANT UNDER HEAD OF ATTACH SCREWS TO SEAL AREA AGAINST MIGRATIO	N OF TKS FLUID THRU FASTENER HOLES TO ATTACH FLANGES.	1	L	7	2 	4F			RT	A22CE
1999010800350	19990108	00350	CE  	1999	1	8	99ZZZX115        	1	19981207	G	7602		CLAMP           			CESSNA	180   	180         	2072602	CE  										ENGINE BAY	LOOSE           	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	6560A					32457				ENGINE HAS HIGH BURN RATE DURING CRUISE.  FOUND MIXTURE CONTROL CABLE HOUSING VERY LOOSE.  INSTALLED TWO NEW CLAMPS.						1	H	7	1 	3O			NC	5A6
1999010800351	19990108	00351	WP  	1999	1	8	99ZZZX116        	1	19980128	G	2150	203470	COOLING TURBINE 	AIRESRCH    	5661614     	DOUG  	TA3B  	TA3B        	3026206	WP  										BLADES	FAILED          	B				O	G			OTHER                   	O2 MASK DEPLOYED        			B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			WP	23	579HA				86307	144858				NOSE AIR CONDITIONING UNIT COOLING TURBINE FAILED.  APPARENT TURBINE BLADE FAILURE.  CAUSE UNKNOWN.  FAILURE CAUSED SMOK	E IN COCKPIT AND SPARKS EMITTED FROM OUTSIDE THE AIRCRAFT.   PILOT PUT EVERYONE ON OXYGEN, CLEARED CABIN WITH RAM AIR AN	D SHUT DOWN AIR CONDITIONERS.  NO FURTHER INDICATION OF TROUBLE.  NORMAL LANDING AT VAN NUYS.  THIS IS AN ISOLATED INCID	ENT AND NO SPECIAL CORRECTIVE ACTION IS NECESSARY.			2	H	7	2 	4J			RT	EXPA2H72
1999040200049	19990402	00049	CE  	1999	4	2	99ZZZX1165       	1	19981015	G	2750	35115236	SUPPORT         			BEECH 	100   	100BEECH    	1152916	CE  										FLAP TRACK	CRACKED         	B		A	IGXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	701RJ	6370 				B23				SUPPORT FOR OUTBOARD FLAP, INBOARD FLAP TRACK PN 35-115236 CRACKED ALLOWING FULL BURDEN OF SUPPORT OF FLAP TO BE PLACED 	ON REAR SPAR WEB.  FLAP TRACK STARTED TO PULL AFT CRACKING AFT SPAR WEB.  RIB ANGLE JUST FORWARD OF TRACK ALSO CRACKED. 	 CONTRACTED BEECH FOR ENGINEERING OF SPAR REPAIR.				1	L	7	2 	3T				A14CE
1999010800352	19990108	00352	SO  	1999	1	8	99ZZZX117        	2	19981208	G	8530	CN635448EC	CYLINDER        			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	6585A		904  			21063554	554598			COMPRESSION TEST REVEALED 58/80 FOR NR 2 CYLINDER.  USED LEAK DETECTOR LIQUID TO DETECT CRACK ADJACENT TO EXHAUST PORT B	ETWEEN 16TH AND 17TH FIN.  CRACK EXTENDS FROM EXHAUST VALVE TO SPARK PLUG HOLE.					1	H	7	1 	3O	3	O		3A21    	E5CE
1999040200058	19990402	00058	CE  	1999	4	2	99ZZZX1174       	1	19981026	G	2810	BTC67	FUEL CELL       	GOODYEARAERO		CESSNA	182   	R182        	2072734	CE  										LT WING	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	17	58FR				7747957	R18200403				CESSNA, PN 1200065-23, LEFT FUEL CELL.  FUEL CELL RECEIVED FROM HARTWIG AIRCRAFT FUEL CELL REPAIR AS A REPAIRED UNIT.  I	T WAS EXTREMELY STIFF AND HARD TO WORK.  UPON INSTALLATION, THE BLADDER LEAKED SOMEWHERE NEAR THE TOP.					1	H	7	1 	3O			RT	3A13
1999010800353	19990108	00353		1999	1	8	99ZZZX118        	4	19981106	G	3418	146	SWITCH          	SAFEFLIGHT  		CESSNA	206   	TU206G      	2073357	CE  										COCKPIT	INOPERATIVE     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	232MT	947  				U20606200				DURING ANNUAL INSPECTION, FOUND STALL WARNING LIFT DETECTOR INOPERABLE DUE TO HIGH RESISTANCE.  ALSO DISCOVERED THE WRON	G LIFT SWITCH WAS INSTALLED PER CONVERSATION WITH SAFE FLIGHT.  REPLACED P/N 146 WITH CORRECT P/N 150.					1	H	7	1 	3O				A4CE
1999010800354	19990108	00354	SO  	1999	1	8	99ZZZX119        	1	19981208	G	8120	4063040008	TURBINE WHEEL   	GARRTT      	4066109021  	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					TURBOCHARGER	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01	63851	93   			AJ045279	277854003	L499561A			TURBO REMOVED AND INSPECTED.  FOUND SHAFT BROKEN BETWEEN TURBINE AND COMPRESSOR BLADES.  TURBINE BLADES WERE NOT FOUND O	N THE SHAFT THAT TURBINE BLADES WERE ON.  TURBINE BLADES WERE EXHAUSTED OUT THE AIRCRAFT THROUGH TAILPIPE.  COMPRESSOR W	HEELS HAD SIGNS OF BROKEN AND CRACKED BLADES TO THE UNBALANCED TURBO.  ALL LINES WERE CHECKED AND NO OBSTRUCTIONS OF ANY	 KIND FOUND.  TURBO HAD OIL IN THE BEARING AND CAM AREAS.  TURBO INSTALLED 6-29-98.			1	L	7	2 	3O	3	O		1A10    	E14EA
1999040200082	19990402	00082	CE  	1999	4	2	99ZZZX1198       	1	19981214	G	3231	HMX5XG	ROD END         			CESSNA	310   	310R        	2074245	CE  										MLG	CRACKED         	B	P		C85R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	5093J	2862 				310R0213				DURING ROUTINE ANNUAL INSPECTION, FOUND ROD END BEARING CRACKED.  ROD END ATTACHES TO GEARBOX LINKAGE TO DO GEAR UP/GEAR	 DOWN.  GREASE WAS NOTED SQUISHING IN/OUT OF CRACK AS GEAR OPERATED DURING ROUTINE RETRACTION TEST.  CESSNA P/N S2049-5F	G.  HEIM P/N HMX-5XG.				1	L	7	2 	3O				3A10
1999010800355	19990108	00355	SO  	1999	1	8	99ZZZX120        	2	19981208	G	8530	TM639272E	CYLINDER        			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	9163M		1470 			21062067	270463R			COMPRESSION TEST REVEALED 64/80 FOR NR 6 CYLINDER.  USED LEAK DETECTOR LIQUID TO DETECT CRACK ADJACENT TO EXHAUST PORT B	ETWEEN 18TH AND 19TH FIN.					1	H	7	1 	3O	3	O		3A21    	E5CE
1999040200086	19990402	00086	CE  	1999	4	2	99ZZZX1202       	1	19981122	G	3220		NLG             			CESSNA	182   	R182        	2072734	CE  										NOSE	FAILED          	G	P			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	25	42GV					R18200219				NOSE COLLAPSED OR FAILED TO EXTEND DURING LANDING.  PILOT STATES HE FELT NOTHING UNTIL THE PROP AND LOWER NOSE COWL STAR	TED STRIKING GROUND.  INSPECTION SHOWS TWO SCREWS MISSING FROM INBD FWD LOWER EDGE OF NOSE COWL WHICH IS ALLOWING THE NO	SE COWL SKIN TO EXTEND .25 INCH AWAY FROM COWL.  THIS CONDITION CAUSES NOSE GEAR DOORS TO GET CAUGHT ON THE COWL SKIN NO	T ALLOWING THE GEAR DOOR TO OPEN.  THIS HAS YET TO BE DETERMINED IF THIS CONDITION IS A RESULT OF IMPACT FORCES OR WAS C	ASUAL.  TWO WITNESSES, AN A/C FUELER AND ATC CONTROLLER, BOTH BELIEVE THEY SAW THE NOSE GEAR EXTENDED.		1	H	7	1 	3O			RT	3A13
1999040200089	19990402	00089	CE  	1999	4	2	99ZZZX1205       	1	19980201	G	5744	35115247	FLAP TRACK      			BEECH 	35    	V35A        	1151544	CE  										RT WING	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	628V					D8607				FOUND FLAP TRACKS WORN BY ROLLERS.  CANNOT BE PROPERLY DETECTED WITH FLAP INSTALLED, BOTH FLAPS.  THIS IS SECOND AIRCRAF	T IN 2 MONTHS.					1	L	7	1 	3O				3A15
1999040200090	19990402	00090	CE  	1999	4	2	99ZZZX1206       	1	19980201	G	5744	3511524710	FLAP TRACK      			BEECH 	35    	V35A        	1151544	CE  										LT WING	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	628V					D8607				FOUND FLAP TRACKS WORN BY ROLLERS.  CANNOT BE PROPERLY DETECTED WITH FLAP INSTALLED, BOTH FLAPS.  THIS IS SECOND AIRCRAF	T IN 2 MONTHS.					1	L	7	1 	3O				3A15
1999040200093	19990402	00093	SO  	1999	4	2	99ZZZX1209       	1	19981202	G	2820		LINE            			PIPER 	PA23  	PA23250     	7102308	SO  										RT ENGINE	LEAKING         	G				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SO	17	805BC					278054054				FLOW DIVIDER RETURN LINE (RUBBER) AFT OF CYLINDER BAFFLE ALLOWED FUEL TO COME INTO CONTACT WITH TURBO.  UNABLE TO DETERM	INE PART NUMBER WITH CURRENT RESOURCES.					1	L	7	2 	3O				1A10
1999010800356	19990108	00356	SO  	1999	1	8	99ZZZX121        	2	19981208	G	8530	TM653446B	CYLINDER        			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 1	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	732QA		868  			21061679	554056			COMPRESSION TEST REVEALED 71/80 FOR NR 1 CYLINDER AND 25/80 FOR NR 2 CYLINDER.  UPON APPLICATION OF LEAK DETECTOR LIQUID	, A CRACK WAS FOUND IN NR 1 CYLINDER ADJACENT TO INTAKE PORT BETWEEN 16TH AND 17TH FIN.  CRACK EXTENDS FROM EXHAUST VALV	E TO SPARK PLUG HOLE IN NR 2 CYLINDER.				1	H	7	1 	3O	3	O		3A21    	E5CE
1999040200099	19990402	00099	CE  	1999	4	2	99ZZZX1215       	1	19980622	G	2810	052600058	FUEL TANK       			CESSNA	172   	172N        	2072434	CE  										FUSELAGE	CRACKED         	D	S			O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	09	4903F	4798 				17273100				FUEL STAINS FOUND ON FUSELAGE.  FUEL LEAK FOUND ON FURTHER INSPECTION.  CRACK WAS FOUND ON TOP OF RIGHT FUEL TANK, 11 IN	CHES OUT FROM INBOARD AND 11.50 INCHES UP FROM AFT SIDE OF BANK.  IT IS MECHANIC'S OPINION THE DEFECT COULD HAVE BEEN CA	USED BY SOMEONE STANDING OR PLACING A HEAVY OBJECT ON THE WING.				1	H	7	1 	3O			NT	3A12
1999010800357	19990108	00357	SO  	1999	1	8	99ZZZX122        	2	19981208	G	8530	TM642594G	CYLINDER        			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 2	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	732QA		868  			21061679	554056			COMPRESSION TEST REVEALED 71/80 FOR NR 1 CYLINDER AND 25/80 FOR NR 2 CYLINDER.  UPON APPLICATION OF LEAK DETECTOR LIQUID	, A CRACK WAS FOUND IN NR 1 CYLINDER ADJACENT TO INTAKE PORT BETWEEN 16TH AND 17TH FIN.  CRACK EXTENDS FROM EXHAUST VALV	E TO SPARK PLUG HOLE IN NR 2 CYLINDER.				1	H	7	1 	3O	3	O		3A21    	E5CE
1999040200234	19990402	00234	SW  	1999	4	2	99ZZZX1221       	1	19980715	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1075W	2387 			A2142	45377				DISCOVERED DURING DAILY INSPECTION, TRAILING EDGE EXTRUSION CORRODED.						1	G	7	1 	3U				H2SW
1999040200236	19990402	00236	NE  	1999	4	2	99ZZZX1223       	1	19980823	G	6210	7615009100049A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	PEELING         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547K	12180	455  		A08600881	760085				DISCOVERED DURING 500-HOUR INSPECTION, UPPER SURFACE PAINT PEELING EXCESSIVELY.						1	G	7	2 	3U				H1NE
1999040200238	19990402	00238	SW  	1999	4	2	99ZZZX1225       	1	19980711	G	6210	206015001107	BLADE           			BELL  	206   	206L4       	1182110	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	176AL	3291 			A1773	52146				DISCOVERED DURING DAILY INSPECTION, SKIN CORRODED, SEPARATED AND TORN ON LOWER SIDE TIP.						1	G	7	1 	3U			NC	H2SW
1999040200239	19990402	00239	SW  	1999	4	2	99ZZZX1226       	1	19980701	G	6210	206015001101	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3174Y	3240 			A1833	51038				DISCOVERED DURING DAILY INSPECTION, CORROSION AND SEPARATION AT TIP.						1	G	7	1 	3U				H2SW
1999010800358	19990108	00358	SO  	1999	1	8	99ZZZX123        	2	19981208	G	8530	TM639272E	CYLINDER        			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 1, 5, 6	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	761PS		1610 			21062415	901281H			COMRPESSION TEST REVEALED NR 1 CYLINDER 30/80, NR 5 CYLINDER 52/80, AND NR 6 CYLINDER 42/80.  UPON APPLICATION OF LEAK D	ETECTOR LIQUID, CRACKS WERE FOUND IN ALL THREE CYLINDER HEADS.					1	H	7	1 	3O	3	O		3A21    	E5CE
1999040200247	19990402	00247	SW  	1999	4	2	99ZZZX1234       	1	19980830	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	365AL	3093 			A1695	51376				DISCOVERED DURING DAILY INSPECTION, CORROSION AND SEPARATION AT TIP.						1	G	7	1 	3U				H2SW
1999040200248	19990402	00248	SW  	1999	4	2	99ZZZX1235       	1	19980830	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	365AL	3093 			A1695	51376				DISCOVERED DURING DAILY INSPECTION, CORROSION AND SEPARATION AT TIP.						1	G	7	1 	3U				H2SW
1999010800359	19990108	00359	EU  	1999	1	8	99ZZZX124        	1	19981002	G	3411		DRAIN           			BRAERO	DH125 	BAE125800A  	1500285	EU  										PITOT SYSTEM	CORRODED        	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	621MT	5285 				258036				NR 1 PITOT SYSTEM DRAIN VALVE RESERVOIR P/N 25-7SF235 HAS HOLE CORRODED THROUGH THE SIDE OF THE RESERVOIR BODY ASSEMBLY.	  RESERVOIR BODY HAS PLIER MARKS FROM PREVIOUS REMOVAL/INSTALLATIONS.					2	L	7	2 	4F			RT	A3EU
1999010800360	19990108	00360	GL  	1999	1	8	99ZZZX125        	1	19980910	G	7603	0509448	CONTROL CABLE   			AMTR  	WITMAN	TAILWIND    	       	GL  										THROTTLE CONTROL	BROKEN          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	61810	105  				JJS4				ON RETARDING THROTTLE TO IDLE AT ENGINE START, THROTTLE CABLE (ROD) BROKE APPROXIMATELY 5 INCHES AFT OF THROTTLE ARM (IN	SIDE OUTER CABLE SHEATHING).  FAILURE OF INNER CABLE APPARENTLY CAUSED BY BAD QUALITY INNER CABLE.  BREAK SHOWED CLEAN A	ROUND OUTER PERIPHERY OF CABLE, DARK, OLDER AREA IN CENTER.  NO SPECIFIC RECOMMENDATIONS, SHIPPED TO MFG FOR INSPECTION.				1	H	7	1 	3O			 	EXPA1H71
1999040200266	19990402	00266	EU  	1999	4	2	99ZZZX1253       	1	19981023	G	7712	1179405303	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										TRIPLE TACH	INOPERATIVE     	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117CH				178	7061				NR 2 N2 NEEDLE INOPERATIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999040200267	19990402	00267	EU  	1999	4	2	99ZZZX1254       	1	19980825	G	5312	117601141	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUSELAGE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	950  				7509				FIREWALL CRACKED IN SEVERAL PLACES.  REF:  RMA NR R016840.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200268	19990402	00268	EU  	1999	4	2	99ZZZX1255       	1	19980825	G	5312	1176625502	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUSELAGE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	950  				7509				FIREWALL CRACKED IN SEVERAL PLACES.  REF:  RMA NR R016840.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200269	19990402	00269	EU  	1999	4	2	99ZZZX1256       	1	19980825	G	5312	1176625501	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										FUSELAGE	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	950  				7509				FIREWALL CRACKED IN SEVERAL PLACES.  REF:  RMA NR R016840.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200270	19990402	00270	EU  	1999	4	2	99ZZZX1257       	1	19981007	G	7712	117902131	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										TRIPLE TACH	INACCURATE      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	1043 			0950821	7509				INDICATOR HAS INTERMITTENT TORQUE SPLITS.  AIRCRAFT HAD 920.5 HOURS WHEN PROBLEM STARTED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200271	19990402	00271		1999	4	2	99ZZZX1258       	4	19981202	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	PRECESSING      	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	206AZ	2    			1895	51007				INDICATOR SLOW TO ERECT.  PRECESSES 10 DEGREES ON 2 MIN. SITTING ON GROUND.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1999040200272	19990402	00272	NE  	1999	4	2	99ZZZX1259       	2	19981112	G	7314	430201407	PUMP            			BELL  	222   	222U        	1182140	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					FUEL SYSTEM	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	222HX	34   			1AFD335B	47533	LE47071			FUEL PUMP LEAKING FUEL FROM OVERBOARD DRAIN.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H9SW    	E5NE
1999010800361	19990108	00361	CE  	1999	1	8	99ZZZX126        	1	19980808	G	5320		FRAME           			BEECH 	200   	200BEECH    	1152920	CE  										PASSENGER DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	520MC	9004 				BB43				DURING AN INSPECTION OF THE AIRCRAFT, THE HINGE FOR THE ENTRY DOOR WAS LOOSE.  THE HINGE WAS REMOVED AND INSPECTION REVE	ALED FRAME, P/N 50-430043-328, TO BE CRACKED AT 4 OF THE AFT RIVET HOLES.  ALSO NOTED 3 RIVETS ATTACHING THE FRAME, P/N 	50-430043-324, TO THE 2 CENTER FRAMES, WERE MISSING CAUSING FLANGES AT BOTTOM OF CENTER FRAMES TO BE CRACKED.  REPAIRED 	BY INSTALLING INTERNAL AND EXTERNAL DOUBLERS.			1	L	7	2 	4T				A24CE
1999040200273	19990402	00273	EU  	1999	4	2	99ZZZX1260       	1	19980827	G	7712	117902131	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										RPM CONTROL	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	230  			019403003	7505				INDICATOR HAS EXCESSIVE TORQUE SPLITS.  REF:  RMA NR R017301.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200274	19990402	00274	EU  	1999	4	2	99ZZZX1261       	1	19980918	G	6240	117945661	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										MAST MOMENT	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	3257 			401004	7505				UNRELIABLE INDICATION. REF:  RMA NR R017135.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200275	19990402	00275	EU  	1999	4	2	99ZZZX1262       	1	19981023	G	7170	0174078010	VALVE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										START DRAIN	LEAKING         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	3415 			163M	7505				VALVE LEAKING EXTERNALLY AT SPLIT LINE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200276	19990402	00276		1999	4	2	99ZZZX1263       	4	19981008	G	3454	071121627	CONTROL UNIT    			BELL  	230   	230         	1182149	SW  										COCKPIT	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1929 			5803	23019				BRIGHT/DIM SENSOR NOT WORKING PROPERLY.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999040200277	19990402	00277		1999	4	2	99ZZZX1264       	4	19981008	G	3454	071121627	CONTROL UNIT    			BELL  	230   	230         	1182149	SW  										COCKPIT	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1207 			5211	23019				BRIGHT/DIM SENSOR NOT WORKING PROPERLY.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999040200278	19990402	00278	SW  	1999	4	2	99ZZZX1265       	1	19981030	G	6220	222031613103	LIFT LINK       			BELL  	230   	230         	1182149	SW  										MAIN ROTOR	DEBONDED        	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1953 				23019				LIFT LINK DEBONDED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999040200279	19990402	00279	SW  	1999	4	2	99ZZZX1266       	1	19981028	G	7810	230062301102	EJECTOR DUCT    			BELL  	230   	230         	1182149	SW  										EXHAUST	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1953 				23019				EJECTOR DUCT CRACKED.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999040200280	19990402	00280	GL  	1999	4	2	99ZZZX1267       	2	19981111	G	7320	222360703101	SOLENOID        			BELL  	230   	230         	1182149	SW  	ALLSN 	250C  	250C30G2    	03013	GL  					ENGINE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1970 			678	23019				SOLENOID WILL NOT ACTUATE.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	NC	H9SW    	E1GL
1999010800362	19990108	00362	CE  	1999	1	8	99ZZZX127        	1	19980727	G	3244	184F102	WEIGHT          			LEAR  	35    	35A         	5170602	CE  										NOSE WHEEL	LOOSE           	D				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			NM	03	553V	100  			71981842	35A141				DURING TAKEOFF ROLL THERE WAS AN ABNORMAL VIBRATION FROM THE NOSE GEAR AT LIFT-OFF.  THE AIRCRAFT RETURNED AND LANDED WI	THOUT INCIDENT.  THE NOSE WHEEL WAS DISASSEMBLED AND THE BALANCE WEIGHT HAD BROKEN LOOSE FROM INSIDE THE TIRE.					2	L	7	2 	4F				A10CE
1999040200283	19990402	00283	EU  	1999	4	2	99ZZZX1270       	1	19980816	G	7714	32005008	TACH GENERATOR  		230880      	BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	BROKEN          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LF	1    				S663				SHAFT BROKEN.  REMOVED AND REPLACED.						1	G	7	2 	3U				H3EU
1999040200284	19990402	00284	NE  	1999	4	2	99ZZZX1271       	2	19981028	G	7250	408211801	SPRING CARRIER  			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101650C  	41560	NE  					POWER TURBINE	SPALLED         	B			TI1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	05	911MK	120  				47515				SPRING CARRIER FAILED IN POWER TURBINE.  METAL PICK-OUT AT BEARING MATING SURFACE.  REMOVED AND REPLACED SPRING CARRIER.						1	G	7	2 	3U	3	U		H9SW    	E5NE
1999040200285	19990402	00285	EU  	1999	4	2	99ZZZX1272       	1	19981031	G	7712	105957411	INDICATOR       			BOLKMS	105   	BO105LSA3   	5626020	EU  										DUAL TORQUE	STICKS          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911SV	29   			108	2033				NR 1 NEEDLE HANGS UP.  RMA NR R017687.  REMOVED AND REPLACED.						1	G	7	2 	3U				H3AU
1999040200295	19990402	00295	EU  	1999	4	2	99ZZZX1276       	1	19980818	G	6420	1053170023	BEARING         			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	117TX					7177				DEFECTIVE FROM STOCK.  BEARING NOT CENTERED IN HOUSING.  RMA NR R016886.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999040200296	19990402	00296		1999	4	2	99ZZZX1277       	4	19980922	G	3160	066040211411	SYMBOL GEN      			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117MK				1436	7196				UNIT SMOKED ON POWER UP.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999040200297	19990402	00297	SW  	1999	4	2	99ZZZX1278       	1	19980908	G	3340	6035571	POWER SUPPLY    			BELL  	222   	222         	1182122	SW  										STROBE	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	800HH				0189	47054				NO OUTPUT POWER.  REMOVED AND REPLACED.						1	G	7	2 	3U				H9SW
1999040200299	19990402	00299	EU  	1999	4	2	99ZZZX1279       	1	19980331	G	5312	1176625501	FIREWALL        			BOLKMS	BK117 	BK117C1     	5626025	EU  										ENGINE BAY	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05	317MC					7505				FIREWALL DEFECTIVE.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999010800363	19990108	00363	CE  	1999	1	8	99ZZZX128        	1	19981005	G	3320	PWFLC28	POWER SUPPLY    			BEECH 	100   	A100        	1152915	CE  										CABIN	FAILED          	B			FZRR	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			NM	11	753DB					B172				AIRCRAFT WAS ON DOWN-WIND:  CABIN FILLED WITH SMOKE.  FOUND CABIN FLUORESCENT LIGHT POWER SUPPLY FAULTY, OVERHEATED, RUP	TURED, BURNT, AND LEAKING.  CIRCUIT BREAKER DID NOT TRIP.  CHECKED CIRCUIT BREAKER FOR CORRECT OPERATION.					1	L	7	2 	3T				A14CE
1999040200300	19990402	00300	NE  	1999	4	2	99ZZZX1280       	2	19980922	G	7250	411105067	ROTOR ASSY      			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					GAS PRODUCER	DAMAGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	118  			4233	47520	LE47020			SEALING PLATE IS SEPARATING FROM BLADES.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H9SW    	E5NE
1999040200301	19990402	00301	NE  	1999	4	2	99ZZZX1281       	2	19980928	G	7250	411105064	ROTOR ASSY      			BOLKMS	117   	BK117A1     	5626010	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					GAS PRODUCER	DEFECTIVE       	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117M	1212 			BK7438	S7023	LE45156			POSSIBLY IMBALANCE OF ROTOR.  C/W SB 0192.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H13EU   	E5NE
1999040200304	19990402	00304	SW  	1999	4	2	99ZZZX1284       	1	19980902	G	5610	222031290125	HINGE           			BELL  	230   	230         	1182149	SW  										WINDOW	BROKEN          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1844 				23019				SUPPORT HINGE BROKEN.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999040200305	19990402	00305	NE  	1999	4	2	99ZZZX1285       	2	19981006	G	7323	430121204	GOVERNOR        			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117MK	664  			30666	7196	LE45614			ENGINE MGT, NG, AND TORQUE SURGES 10 TO 20 PERCENT.  REMOVED AND REPLACED GOVERNOR WHICH CURED PROBLEM.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1999010800364	19990108	00364	CE  	1999	1	8	99ZZZX129        	1	19980204	G	7330	178011	PROBE           			CESSNA	500   	S550        	2076607	CE  										FUEL TANK	MALFUNCTIONED   	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	106QS				284	S5500106				AFTER INSTALLATION IN TKS TANK, WITH TANK FULL, GAUGE READ ZERO.  INSTALLATION OF ANOTHER NEW GAUGE SHOWED SYSTEM WORKED	 CORRECTLY.					1	L	7	2 	4F			RT	A22CE
1999010800023	19990108	00023		1999	1	8	99ZZZX13         	4	19981130	G	2210	80821000218	AUTOPILOT       			GULSTM	690TP 	690A        	0141722	SW  										COCKPIT	MISINSTALLED    	B			MV5R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	11	848CE				4162386	11303				AUTOPILOT WOULD NOT CAPTURE NAV OR SLOW TO CAPTURE.  AUTOPILOT WOULD DRIFT FROM PROPER COURSE WHEN CAPTURED.  THIS WAS D	UE TO INCORRECT HSI MODE RELAY INTERFACE WIRING FOR GPS.  WIRING WAS INTERRUPTED AT AUTOPILOT FLIGHT DETECTOR INDICATOR 	FD 112V AND SHOULD HAVE BEEN INTERRUPTED AT THE BACK OF THE NR 1 NAV RECEIVER.  THIS AUTOPILOT IS A COLLINS AP106.				1	H	7	2 	3T				2A4
1999010800365	19990108	00365	CE  	1999	1	8	99ZZZX130        	1	19980727	G	2612	302157	FIRE DETECTOR   	PYROTECTOR  		BEECH 	200   	200BEECH    	1152920	CE  										LEFT	MALFUNCTIONED   	D				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			NM	03	520MC	8983 				BB43				AFTER TAKEOFF, CLIMBING THROUGH 15,000 FEET, THE LEFT FIRE WARNING LIGHT CAME ON.  THE PILOT RETURNED AND LANDED WITHOUT	 INCIDENT.  MAINTENANCE INSPECTED THE AIRCRAFT AND NO EVIDENCE OF FIRE WAS FOUND.  THE FIRE WARNING WAS CHECKED FOR PROP	ER OPERATION AND CHECKED GOOD.  MAINTENANCE WAS UNABLE TO DUPLICATE THE PROBLEM.  THE AIRCRAFT WAS IN A HEAVY RAINSTORM 	PRIOR TO THE FLIGHT, AND SUSPECT THIS CONTRIBUTED TO THE FALSE INDICATION.			1	L	7	2 	4T				A24CE
1999010800366	19990108	00366	CE  	1999	1	8	99ZZZX131        	1	19981207	G	2710		CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										AILERON	OUT OF RIG      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	779QS					6507079				DURING ROUTINE DAILY CHECK, AILERON WING CABLE TENSION WAS FOUND SO LOW THE CABLES WERE DRAGGING ON THE LOWER SURFACE OF	 THE WING TRAILING EDGE.  TENSION CHECKED 18 POUNDS.  MAINTENANCE MANUAL CHAPT 27-10-00 PG 501 SPECS TENSION AT 35 PLUS 	OR MINUS 5 POUNDS AT 70 DEGREES FAHRENHEIT.  RE-RIGGED AND RE-TENSIONED AILERON WING CABLES.  SUBMITTER SUGGESTED TIGHTE	R MANUFACTURING CONTROL.  ACFT TTSN:  1,075.6 HOURS.			2	L	7	2 	4F			 	A9NM
1999010800367	19990108	00367		1999	1	8	99ZZZX132        	4	19981209	G	3418	SLZ9958	COMPUTER        			ISRAEL	1125  	ASTRASPX    	4500205	EU  										STALL WARNING	FAILED          	B			QRRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	273RA	118  			DK1094	097				'STALL FAIL' LIGHT ON.  WILL NOT EXTINGUISH.  AOA WILL NOT TEST.  REPLACED COMPUTER.  ALL TESTS NORMAL.  RETURNED TO SER	VICE.					2	L	7	2 	4F			RT	A16NM
1999010800368	19990108	00368	CE  	1999	1	8	99ZZZX133        	1	19981207	G	2710		CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										AILERON	OUT OF RIG      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	789QS					6507089				DURING ROUTINE DAILY CHECK, AILERON WING CABLE TENSION WAS FOUND TO BE SO LOW THAT THE CABLES WERE DRAGGING ON THE LOWER	 SURFACE OF THE WING TRAILING EDGE.  TENSION CHECKED 19 POUNDS.  MAINTENANCE MANUAL CHAPTER 27-10-00 PG 501 SPECS TENSIO	N AT 35 PLUS OR MINUS 5 POUNDS AT 70 DEGREES FAHRENHEIT.  RE-RIGGED AND TENSIONED WING AILERON CABLES.  SUBMITTER SUGGES	TED TIGHTER MANUFACTURING CONTROL.  ACFT TTSN:  178.0 HOURS.			2	L	7	2 	4F			 	A9NM
1999010800369	19990108	00369	CE  	1999	1	8	99ZZZX134        	1	19981207	G	2710		CONTROL CABLE   			CESSNA	650   	650         	2076802	CE  										AILERON	OUT OF RIG      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	787QS					6507087				DURING ROUTINE DAILY CHECK, AILERON WING CABLE TENSION WAS FOUND TO BE SO LOW THAT THE CABLES WERE DRAGGING ON THE LOWER	 SURFACE OF THE WING TRAILING EDGE.  TENSION CHECKED 15 POUNDS.  MAINTENANCE MANUAL CHAPT 27-10-00 PG 501 SPECS TENSION 	AT 35 PLUS OR MINUS 5 POUNDS AT 70 DEGREES FAHRENHEIT.  RE-RIGGED AND TENSIONED AILERON WING CABLES.  SUBMITTER SUGGESTS	 TIGHTER MANUFACTURING CONTROL.  ACFT:  TTSN:  329.4 HOURS.			2	L	7	2 	4F			 	A9NM
1999010800370	19990108	00370	CE  	1999	1	8	99ZZZX135        	1	19980204	G	7330	178011	PROBE           			CESSNA	500   	S550        	2076607	CE  										FUEL TANK	MALFUNCTIONED   	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	98QS				214	S5500098				ORIGINAL PROBE WOULD ONLY READ HALF OF A TANK WHEN FULL.  INSTALLED NEW PROBE.  WITH TANK FULL GAUGE READ ZERO.  INSTALL	ED SERVICEABLE PROBE AND SYSTEM WORKED CORRECTLY.					1	L	7	2 	4F			RT	A22CE
1999040200803	19990402	00803		1999	4	2	99ZZZX1356       	4	19980930	G	2360	16935	DISCHARGER      																	ELEVATOR	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05										BORE IS THREADED INCORRECTLY.  BAD FROM STOCK.  REMOVED AND REPLACED.
1999040200804	19990402	00804		1999	4	2	99ZZZX1357       	1	19980930	G	6720	222012765103	LINK            																	PITCH CONTROL	MISMANUFACTURED 	B			TI1R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	05										WALL THICKNESS ON LARGE BEARING END HOUSING BELOW MINIMUM THICKNESS.  MFG DEFECT.  BAD FROM STOCK.  REMOVED AND REPLACED	.
1999010800371	19990108	00371	CE  	1999	1	8	99ZZZX136        	1	19981201	G	2820	652635523	LINE            			CESSNA	500   	550         	2076604	CE  										FUEL SYSTEM	CHAFED          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2734K					550595				REF CESSNA IPC 28-20-01 FIG 1 ITEM NR 1.  DURING RECENT PHASE 5J AND 5K INSPECTIONS, PRESSURE LINE TO EJECTOR TRANSFER P	UMP (ITEM NR 40) WAS FOUND CHAFING AGAINST THE WIGGINS COUPLING (ITEM NR 6) ON THE T-CONNECTION BETWEEN MANUAL SHUT OFF 	(ITEM NR 1) AND FUEL FILTER (ITEM B).  A ONE-TIME INSP OF FUEL LINE WAS CONDUCTED ON ALL C-500'S IN U. S. CUSTOMS INVENT	ORY.  ANOTHER FUEL LINE (ITEM NR 40) WAS FOUND CHAFING IN THE SAME MANNER.  THIS IS THE 3RD LINE FOUND CHAFING AT THIS S	ITE.  LINE REPLACED.  SUBMITTER RECOMMENDED LINE BE RE-DESIGNED TO ENABLE IT TO HAVE MORE CLEARANCE AND A BETTER FIT IN 	FUEL SYS  COMPONENT BAY AND A ONE-TIME INSP OF LINE ON CESSNA C550 ACFT AND IT BE MADE AN INSP ITEM ON PHASE 5J AND 5K.	1	L	7	2 	4F				A22CE
1999040200816	19990402	00816	EA  	1999	4	2	99ZZZX1369       	2	19980903	G	7412	103815504	IGNITION EXCITER			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RT ENGINE	FAILED          	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15					866221C	PT6A20				UNIT RECEIVED AS OVERHAULED UNIT AND INSTALLED ON RT ENGINE OF C-90 KINGAIR.  UNIT FAILED AFTER ONE START.  FROM APPEARA	NCE OF EXTERIOR OF EXCITER, IT MAKES YOU WONDER WHAT THE INTERIOR LOOKS LIKE.  FAULTY, SLOPPY OF SOLDERING ON EXTEIROR O	F CASE.  TAGS ON THE EXTERIOR OF THE UNIT DRAW A QUESTION AS TO ITS ORIGIN AND SERVICEABILITY.				1	L	7	2 	3T	3	T		3A20    	E4EA
1999010800372	19990108	00372	SO  	1999	1	8	99ZZZX137        	2	19981208	G	8530	SA646612	VALVE           	SUPAIRPART  	SA10220A20P 	CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					EXHAUST	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	18022	1752 				15073738	21467972A			EXHAUST VALVE PART FAILED INSIDE CYLINDER CAUSING SUBSEQUENT ENGINE FAILURE AND EMERGENCY LANDING.  VALVE FACE SEEMED TO	 SEPARATE FROM STEM IN SEVERAL PIECES.  SUBMITTER STATED THIS IS THE SECOND FAILURE OF THIS TYPE IN 931 HOURS.					1	H	7	1 	3O	3	O		3A19    	E252
1999010800373	19990108	00373	SO  	1999	1	8	99ZZZX138        	1	19981120	G	3230	9506189	BRACKET         			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	FAILED          	B	L		WIWR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	56187	12   				347350302				AIRCRAFT EXPXERIENCED NOSE GEAR FAILURE DURING LANDING ROLL-OUT.						1	L	7	2 	3O				A7SO
1999040200832	19990402	00832	NE  	1999	4	2	99ZZZX1385       	2	19980911	G	7261	0292107790	VALVE           			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1E    	60030	NE  					ENGINE OIL	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	3296 				7505	18012			NR 2 ENGINE OIL PRESSURE LOW.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU
1999040200833	19990402	00833	NE  	1999	4	2	99ZZZX1386       	2	19980910	G	7261	0292105230	PUMP            			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1E    	60030	NE  					ENGINE OIL	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	3294 			16S0	7505	18012			NR 2 ENGINE OIL PRESSURE LOW.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU
1999010800374	19990108	00374	CE  	1999	1	8	99ZZZX139        	1	19981009	G	3220		LEG             			CESSNA	150   	150J        	2071820	CE  										TAIL GEAR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	03	51258					15069877				A STRESS CORROSION FRACTURE OCCURRED IN THE RADIUS AREA WHERE THE HIGH CARBON SPRING STEEL MAIN LANDING GEAR LEG AND THE	 LANDING GEAR EXTENSION CONTACT.  SUBMITTER SUGGESTED IMMEDIATE INSPECTION AND REPETITIVE INSPECTIONS AFTER 50 LANDINGS 	OR 50 HOURS WHICHEVER OCCURS FIRST.  STC 268GL.				1	H	7	1 	3O				3A19
1999040900080	19990409	00080		1999	4	9	99ZZZX1394       	1	19981014	G	7800	77611	GASKET          																	EXHAUST	MISMANUFACTURED 	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	17										BLOW-PROOF GASKET INNER PORTION OF GASKET SEAL, ONE SIDE EXTENDS OUT TO MAKE SEAL, THE OTHER DOESN'T.
1999010800024	19990108	00024		1999	1	8	99ZZZX14         	4	19981130	G	2210	81438000232	AUTOPILOT       			GULSTM	690TP 	690B        	7630516	SW  										COCKPIT	MISINSTALLED    	B			MV5R	O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			GL	11	690TG				5412613	11444				AUTOPILOT WOULD NOT CAPTURE NAV OR SLOW TO CAPTURE.  AUTOPILOT WOULD DRIFT FROM PROPER COURSE WHEN CAPTURED.  THIS WAS D	UE TO INCORRECT HSI MODE RELAY INTERFACE WIRING FOR GPS.  WIRING WAS INTERRUPTED AT AUTOPILOT FLIGHT DIRECTOR FD 112V AN	D SHOULD HAVE BEEN INTERRUPTED AT THE BACK OF THE NR 1 NAV RECEIVER.  THIS AUTOPILOT IS A COLLINS AP106.				1	H	7	2 	3T				2A4
1999012000014	19990120	00014	EA  	1999	1	20	99ZZZX140        	2	19981120	G	7322	IO5135	CARBURETOR      	FACET       		PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	2092M	2266 			CK48740	287816250				IN-FLIGHT, P/N 229-164, 'PUMP DISCHARGE TUBE' BECAME LOOSE DISTURBING AIRFLOW AND DISTORTING ACCELERATOR DISCHARGE CAUSI	NG ERRATIC ENGINE OPERATION AND LOSS OF POWER.					1	L	7	1 	3O	3	O		2A13    	E274
1999010800375	19990108	00375	SO  	1999	1	8	99ZZZX141        	1	19981124	G	7160	434134	GROMMET         		8547402     	PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149C	65   				2843190				DURING A SCHEDULED INSPECTION, THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  SUBM	ITTER STATED THESE BUSHINGS AND GROMMETS SHOULD BE REPLACED EVERY 50 TO 100 HOURS OF OPERATION.					1	L	7	1 	3O				2A13
1999010800376	19990108	00376	SO  	1999	1	8	99ZZZX142        	1	19981124	G	7160	453494	BUSHING         		8547402     	PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149C	65   				2843190				DURING A SCHEDULED INSPECTION, THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  SUBM	ITTER STATED THESE BUSHINGS AND GROMMETS SHOULD BE REPLACED EVERY 50 TO 100 HOURS OF OPERATION.					1	L	7	1 	3O				2A13
1999040900163	19990409	00163	NE  	1999	4	9	99ZZZX1426       	2	19980827	G	7321		FCU             			BOLKMS	117   	BK117A4     	5626017	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 1 ENGINE	MALFUNCTIONED   	H		A		O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			AP	APPROACH       	1			SW	09	330HH		152  			7133	LE45654			DURING FINAL APPROACH FOR LANDING AFTER A TEST FLIGHT FOR NR 1 FUEL CONTROL CHANGE, THE NR 1 ENGINE TORQUE DROPPED TO ZE	RO, N1 DROPPED TO 30 PERCENT, AND N2 DROPPED TO BELOW 50 PERCENT. PILOT MADE AN UNEVENTFUL SINGLE ENGINE LANDING.  REPLA	CED FUEL CONTROL.  THIS FUEL CONTROL WAS REPAIRED BY MFG AT 37.6 HRS TSO FOR HUNG STARTS AND SLOW ACCELERATION ON START.	  REPAIRED AGAIN BY MFG AT 141.7 HRS TSO FOR THE SAME SYMPTOMS DESCRIBED ABOVE ON ANOTHER ENGINE.  IT WAS STILL GIVING V	ERY SLOW STARTS WITH POOR ACCELERATION.  THIS FUEL CONTROL UNIT HAS BEEN RETURNED TO MFG FOR EVALUATION.		1	G	7	2 	3U	3	U		H13EU   	E5NE
1999061000003	19990610	00003	EU  	1999	6	10	99ZZZX1427       	1	19981113	G	5330	11203025217A	DOUBLER         			BOLKMS	117   	BK117A4     	5626017	EU  										TAIL BOOM	CRACKED         	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	330HH	6426 				7133				ON DAILY INSPECTION, FOUND 1.5 INCH CRACK IN DOUBLER, PN 1120.30252.17A, JUST FORWARD OF THE LEFT HORIZONTAL STABILIZER.	  FURTHER INVESTIGATION REVEALED A SIMILAR SIZE CRACK IN THE SKIN PN 117-30252.09 BENEATH THE DOUBLER.  THESE PARTS ARE 	ORIGINAL AND HAVE 6,425.8 HOURS TOTAL TIME IN SERVICE.  BOTH CRACKS ORIGINATED FROM RIVET HOLES.  THE MANUFACTURER HAD N	O COMMENT ON CAUSE OR PREVENTION.  SUBMITTER RECOMMENDED PAYING CLOSE ATTENTION TO THIS AREA ON BOTH SIDES OF THE TAILBO	OM DURING PREFLIGHT INSPECTION.		1	G	7	2 	3U				H13EU
1999061000004	19990610	00004	EU  	1999	6	10	99ZZZX1428       	1	19981113	G	5330	1173025209	SKIN            			BOLKMS	117   	BK117A4     	5626017	EU  										TAIL BOOM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09	330HH	6426 				7133				ON DAILY INSPECTION, FOUND 1.5 INCH CRACK IN DOUBLER, PN 1120.30252.17A, JUST FORWARD OF THE LEFT HORIZONTAL STABILIZER.	  FURTHER INVESTIGATION REVEALED A SIMILAR SIZE CRACK IN THE SKIN PN 117-30252.09 BENEATH THE DOUBLER.  THESE PARTS ARE 	ORIGINAL AND HAVE 6,425.8 HOURS TOTAL TIME IN SERVICE.  BOTH CRACKS ORIGINATED FROM RIVET HOLES.  THE MANUFACTURER HAD N	O COMMENT ON CAUSE OR PREVENTION.  SUBMITTER RECOMMENDED PAYING CLOSE ATTENTION TO THIS AREA ON BOTH SIDES OF THE TAILBO	OM DURING PREFLIGHT INSPECTION.		1	G	7	2 	3U				H13EU
1999010800377	19990108	00377	SO  	1999	1	8	99ZZZX143        	1	19981208	G	2740	6270141	CONTROL CABLE   			PIPER 	PA32  	PA32301T    	7103209	SO  										TRIM CONTROL	FRAYED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	8185Y	3136 				328024018				WHILE INSPECTING FOR A STIFF STABILIZER TRIM CONTROL, TRIM CABLE FOUND SEVERELY FRAYED AT ELECTRIC TRIM SERVO.  ONLY A C	OUPLE OF STRANDS REMAIN HOLDING CABLE.					1	L	7	1 	3O			 	A3SO
1999040900172	19990409	00172	EA  	1999	4	9	99ZZZX1437       	2	19980325	G	7310	GE2541803	DIAPHRAGM       	BENDIX      	RSA10ED1    						LYC   	O540  	TIO540*     	41532	EA  					FUEL SYSTEM	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	11										WHILE UNSCREWING NUT ON STEM, STEM UNSCREWED FROM DIAPHRAGM INDICATING STEM WAS LOOSELY ATTACHED TO DIAPHRAGM SINCE MANU	FACTURE. SUBMITTER STATED IF STEM SEPARATED DURING ENGINE OPERATION, THE ENGINE WOULD STOP RUNNING WITHOUT WARNING.										3	O			E14EA
1999010800378	19990108	00378	SO  	1999	1	8	99ZZZX144        	1	19981214	G	7160	434134	GROMMET         		8547402     	PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A	72   				2843189				DURING A SCHEDULED INSPECTION, THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  SUBM	ITTER STATED BUSHINGS AND GROMMETS SHOULD BE REPLACED EVERY 50 TO 100 HOURS OF OPERATION.					1	L	7	1 	3O				2A13
1999010800379	19990108	00379	SO  	1999	1	8	99ZZZX145        	1	19981214	G	7160	453491	BUSHING         		8547402     	PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A	72   				2843189				DURING A SCHEDULED INSPECTION, THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  SUBM	ITTER STATED BUSHINGS AND GROMMETS SHOULD BE REPLACED EVERY 50 TO 100 HOURS OF OPERATION.					1	L	7	1 	3O				2A13
1999010800380	19990108	00380	SO  	1999	1	8	99ZZZX146        	1	19981214	G	7160	434134	GROMMET         		8547402     	PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149T	100  				2843192				DURING A SCHEDULED INSPECTION, THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  SUBM	ITTER STATED BUSHINGS AND GROMMETS SHOULD BE REPLACED VERY 50 TO 100 HOURS OF OPERATION.					1	L	7	1 	3O				2A13
1999010800381	19990108	00381	SO  	1999	1	8	99ZZZX147        	1	19981214	G	7160	453491	BUSHING         		8547402     	PIPER 	PA28  	PA28181     	7102807	SO  										AIRBOX	WORN            	B			UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149T	100  				2843192				DURING A SCHEDULED INSPECTION, THE CARBURETOR AIRBOX VALVE BUSHING AND GROMMET WERE FOUND COMPLETELY WORN THROUGH.  SUBM	ITTER STATED BUSHINGS AND GROMMETS SHOULD BE REPLACED VERY 50 TO 100 HOURS OF OPERATION.					1	L	7	1 	3O				2A13
1999010800382	19990108	00382	NE  	1999	1	8	99ZZZX148        	1	19981228	G	5711		SPAR            			CONAER	LA4   	LA4250      	5110320	NE  										RT/LT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	80MP					17				DURING REPAIR OF RT AND LT WINGS, CRACKS WERE DISCOVERED IN LOWER SPAR CAP OF BOTH WINGS NEAR THE 2ND MOST INBD WING ATT	ACH BOLT HOLE.  CRACK APPEARED TO START WHERE THE SPAR DOUBLER, P/N 2-1610-081, INTERSECTS A ROUTED AREA OF INBD END OF 	THE LOWER SPAR CAP.  THE SPAR CAP WAS ROUTED TO CLEAR THE STRUCTURE OF THE ROOT RIB.  THE PLACEMENT OF THE SPAR DOUBLER 	MAY BE WITHIN THE BEND RADIUS OF THE EXTRUDED SPAR CAP AND WHEN THE WING ATTACH BOLTS ARE TIGHTENED, IT IMPINGES ON THE 	RADIUS AND ATTEMPTS TO JOGGLE THE END OF THE SPAR CAP SETTING UP A STRESS THAT COULD PROMOTE THE CRACK.		1	H	7	1 	3O				1A13
1999010800383	19990108	00383	NE  	1999	1	8	99ZZZX149        	1	19981228	G	3233		ROD             			LAKEAC	LAKE  	250LAKE     	5110322	NE  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	8407W									INSPECTED NOSE GEAR ACTUATOR ROD FOR CRACKS AT THE THREADED END.  CRACK DISCOVERED IN THE BOTTOM OF THE THREAD GROOVE BE	LOW JAM NUT SECURING FITTING, P/N 2-4420-001.  SEVERAL PREVIOUS ACTUATORS ON OTHER ACFT REPLACED DUE TO CRACKING AND/OR 	SEPARATION OF THE ACTUATOR AT THIS POINT.  SUBMITTER SUGGESTED AT EACH ANNUAL 100-HOUR INSPECTION, THE THREADED END OF T	HE ACTUATOR BE EXAMINED VISUALLY WITH A 10X MAGNIFIER TO LOOK FOR CRACKS IN THE BOTTOM OF THE THREAD GROOVE.  CRACKS HAV	E ALSO BEEN DETECTED BELOW THREADED AREA ON SOME ACTUATORS.  TO PROPERLY INSPECT, IT IS NECESSARY TO REMOVE ACTUATOR FRO	M ACFT AND REMOVE FITTING AND JAM NUT FROM ACTUATOR.	1	H	7	1 	3O			NC	1A13
1999010800025	19990108	00025	CE  	1999	1	8	99ZZZX15         	1	19981214	G	3230	62171022	UPLOCK          			CESSNA	650   	650         	2076802	CE  										RT MLG	FAILED          	B			DBCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	50DS	3436 				650078				RIGHT MAIN GEAR WOULD NOT LOCK UP.  FOUND BAD UPLOCK SWITCH.  REMOVED AND REPLACED SWITCH.  NEW P/N 6217102-2.						2	L	7	2 	4F				A9NM
1999041700270	19990417	00270	NM  	1999	4	17	99ZZZX1528       	1	19981207	G	5330		SKIN            			BOEING	727   	7272B7      	138407L	NM  										BS 500	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, FOUND CORROSION ON SKIN BULGE AT BS 500 AT AREA BETWEEN STR 26 - STR 27R.						2	L	7	3 	4F				A3WE
1999041700271	19990417	00271	NM  	1999	4	17	99ZZZX1529       	1	19981207	G	5320		BRACKET         			BOEING	727   	7272B7      	138407L	NM  										BS 1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON FLOOR TRACK BRACKET BS 1070, LBL 50.						2	L	7	3 	4F				A3WE
1999041700272	19990417	00272	NM  	1999	4	17	99ZZZX1530       	1	19981204	G	5320		WEB             			BOEING	727   	7272B7      	138407L	NM  										BS 1110-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION WAS NOTED AT FS 1110 - FS 1130, UNDER SIDE OF CUSP WEB RBL 64.						2	L	7	3 	4F				A3WE
1999041700273	19990417	00273	NM  	1999	4	17	99ZZZX1531       	1	19981204	G	5320		ANGLE           			BOEING	727   	7272B7      	138407L	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED IN AFT AIR STAIRS, RT SUPPORT ARM CASTING (THE ZEE ANGLES WERE CORRODED).						2	L	7	3 	4F				A3WE
1999041700297	19990417	00297	EA  	1999	4	17	99ZZZX1555       	2	19980619	G	8530		VALVE           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 3 CYLINDER	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	94PF					288516042	L915739A			EXHAUST VALVE STUCK IN GUIDE CAUSING PISTON STRIKE AND BENT PUSH ROD.  AIRCRAFT ON GROUND DOING RUN-UP.						1	L	7	1 	3O	3	O		2A13    	E274
1999041700298	19990417	00298	EA  	1999	4	17	99ZZZX1556       	2	19981222	G	8530		VALVE           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 2 CYLINDER	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	94PF					288516042	L915739A			EXHAUST VALVE STUCK CAUSING BENT PUSH ROD.  ENGINE REPORTED ROUGH ON RUN-UP.  ZERO COMPRESSION ON NR 2 CYLINDER.  CYLIND	ER REMOVED AND OVERHAULED.					1	L	7	1 	3O	3	O		2A13    	E274
1999041700299	19990417	00299	EA  	1999	4	17	99ZZZX1557       	2	19981127	G	8530		VALVE           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					NR 4 CYLINDER	DAMAGED         	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	30PF	577  				2841265	L1336239A			EXHAUST VALVE STUCK IN GUIDE CAUSING PISTON STRIKE AND BENT PUSH ROD.  AIRCRAFT MADE AN EMERGENCY ON AIRPORT LANDING.  N	O DAMAGE TO AIRCRAFT.					1	L	7	1 	3O	3	O		2A13    	E274
1999010800026	19990108	00026	NM  	1999	1	8	99ZZZX16         	1	19981119	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION NOTED AT FS 1050 AT STR 27L.						2	L	7	3 	4F				A3WE
1999011500199	19990115	00199	WP  	1999	1	15	99ZZZX163        	1	19981111	G	2710	3701479	SUPPORT         		5705321     	DOUG  	DC8   	DC852       	3021922	WP  										AILERON	CRACKED         	B			C20R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	VRBIA				181LH	45658				AFTER REMOVING SUPPORT ASSY ON A DC-8 INBOARD AILERON, CRACKS WERE NOTED ON 3 SUPPORT ASSEMBLIES.   THE CRACKS WERE NOTE	D ON THE UPPER HOLES WHERE THE FITTING ASSEMBLY ATTACHES TO THE AFT SPAR OF THE INBOARD AILERON.					2	L	7	4 	4F				4A25
1999011500200	19990115	00200		1999	1	15	99ZZZX164        	4	19981113	G	3421	501119705	GYRO            			ISRAEL	1125  	ASTRASPX    	4500205	EU  										COCKPIT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	275RA	184  			6314	098				EMERGENCY ATTITUDE GYRO INDICATOR WOULD NOT STABILIZE.  ROLLS TO RIGHT.  VERY LOW TIME ON UNIT.						2	L	7	2 	4F			RT	A16NM
1999011500201	19990115	00201	SO  	1999	1	15	99ZZZX165        	1	19981205	G	3211	LY61AG0350T6	NUT             			EMB   	120   	EMB120RT    		SO  										MLG	LOOSE           	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	260AS					120132				DURING C-CHECK INSPECTION OF THE LT AND RT MLG, THE NUT RETAINING THE INBOARD TRUNNION BEARING WAS FOUND TO HAVE PLAY. T	HE LOCK WASHER WAS ALL THAT WAS HOLDING NUT IN PLACE.  UPON REMOVAL OF GEARS, IT WAS FOUND THAT THE ADJUSTMENT SKIN ON T	HE OUTBOARD SIDE OF GEAR WAS DETERIORATING.				2	L	7	2 	4T			RT	A31SO
1999011500202	19990115	00202	SO  	1999	1	15	99ZZZX166        	1	19981205	G	3211	LY61AG0350T6	NUT             			EMB   	120   	EMB120RT    		SO  										MLG	LOOSE           	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	236AS					120049				DURING C-CHECK INSPECTION OF THE LT AND RT MLG, THE NUT RETAINING THE INBOARD TRUNNION BEARING WAS FOUND TO HAVE PLAY. T	HE LOCK WASHER WAS ALL THAT WAS HOLDING NUT IN PLACE.  UPON REMOVAL OF GEARS, FOUND THE ADJUSTMENT SHIM OF THE OUTBOARD 	SIDE OF GEAR WAS DETERIORATING.				2	L	7	2 	4T			RT	A31SO
1999011500203	19990115	00203	SO  	1999	1	15	99ZZZX167        	1	19980815	G	2750		PIN             		6339100     	PIPER 	PA28  	PA28R180    	7102809	SO  										TE FLAP	FRACTURED       	D	L			O				OTHER                   				E			VIBRATION/BUFFET          			AP	APPROACH       	1			SO	15	7624J	2555 				28R31102				WHILE ON BASE LEG FOR LANDING WITH 2ND NOTCH OF FLAPS APPLIED THERE WAS A LOUD BANG AND ACFT PITCHED DOWN SUDDENLY.  FLA	P HANDLE HAD RETRACTED TO ZERO DEGREE FLAP POSITION.  A SAFE ZERO DEGREE FLAP LANDING WAS MADE.  DISASSY OF FLAP HANDLE 	AREA REVEALED THE LATCHING PIN HAD FRACTURED IN THE MIDDLE WHERE IT WAS WEAKENED BY A .062 INCH DIAMETER HOLE WHICH HAD 	A ROLL PIN THROUGH IT TO RETAIN IT IN PLUG/PLUNGER (P/N 62734-00).  THE 2 HALVES FELL OUT OF THE PLUNGER ALLOWING FLAPS 	TO RETRACT.  IT IS IMPOSSIBLE TO INSPECT THIS PART AT THE FRACTURE LOCATION IN THE ASSY AND THE ASSY IS MADE SUCH THAT T	HE RETAINING ROLL PIN CANNOT BE REMOVED WITHOUT DESTROYING PARTS IN ORDER TO INSPECT AREA.	1	L	7	1 	3O				2A13
1999043000040	19990430	00040	NE  	1999	4	30	99ZZZX1679       	2	19981227	G	7230	536210	BLADE           			SKRSKY	S64   	S64E        	8142604	NE  	PWA   	JFTD12	JFTD12A4A   	52047	NE  					COMPRESSOR	DAMAGED         	B			JYDR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	164AC	665  				64034D	676466			DURING DAILY INSPECTION, THE POSSIBILITY OF A TABLOCK FAILURE WAS INVESTIGATED USING A 'BRIGHT LIGHT'.  THE ENGINE WAS R	EMOVED AND SENT TO EAC WHERE A BORESCOPE INSPECTION WAS PERFORMED.  DURING THE INSPECTION, ONE 3RD STAGE BLADE TABLOCK W	AS FOUND MISSING.  THE 3RD STAGE BLADE FROM WHICH THE TABLOCK WAS MISSING HAD MOVED SLIGHTLY REARWARD, BUT HAD NOT YET C	ONTACTED THE 3RD STAGE STATOR (PN 685503).  THE TABLOCK COMING LOOSE CAUSED INTERNAL DAMAGE TO OTHER PARTS OF THE COMPRE	SSOR.  APPROXIMATELY 3 VANES FROM THE 2ND (PN 566282) AND 3RD (PN 385503) STAGE STATORS WERE DAMAGED.		2	G	7	2 	4U	4	U		H4EA    	E15EA
1999011500204	19990115	00204	CE  	1999	1	15	99ZZZX168        	1	19981204	G	2710	HM4	ROD             		3552115204  	BEECH 	35    	E35         	1151512	CE  										AILERON	LOOSE           	H				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			SW	07	7342B					D3805				ON TAKEOFF JUST AFTER LIFT-OFF, PILOT NOTICED AILERON CONTROLS WERE HARD TO MOVE.  SHORTLY AFTER THE PILOT NOTICED THE R	T AILERON WAS NOT WORKING, RETURNED TO AIRPORT.  UP ON A MAINTENANCE CHECK, NOTED THE CONTROL ROD FOR THE RT AILERON CON	TROL WAS LOOSE.  REMOVAL OF THE CONTROL ROD SHOWED A BROKEN ROD END.  THE ROD END WAS BROKEN NEXT TO THE JAM NUT WHERE I	T CONNECTED TO AILERON BELLCRANK.  THE ROD END BEARING WAS FROZEN IN PLACE FROM DIRT AND CORROSION.  THIS ROD END DOES N	OT HAVE ANY WAY TO LUBRICATE IT WHEN IT IS IN PLACE.  IT MUST BE LUBRICATED AT INSTALLATION.  SUBMITTER STATED DUE TO TH	IS FACT, THERE SHOULD BE A 5-YEAR OR 500-HOUR LUBRICATION SCHEDULE SET UP.  ACFT TT:  3,987.8 HRS.	1	L	7	1 	3O				A777
1999011500205	19990115	00205	NE  	1999	1	15	99ZZZX169        	2	19981203	G	7230		BLADE           			DOUG  	DC10  	DC1010      	3022110	WP  	GE    	CF6   	CF66K       	30020	NE  					NR 2 ENGINE	SEPARATED       	H				A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SW	99	450AX					46942	451166			CREW REPORTED AFTER POWER REDUCTION FROM TAKEOFF POWER TO CLIMB POWER, NR 2 ENGINE FAILED WITH A SEVERE VIBRATION.  INIT	IAL MAINTENANCE SURVEY REPORT SEVERAL BLADES MISSING FROM THE 5TH STAGE LPT AND METAL SPRAY.  THE PART/COMPONENT CAUSING	 FAILURE WILL HAVE TO BE DETERMINED THROUGH SHOP TEAR DOWN AND INSPECTION FINDINGS.  ADDITIONAL SDR'S WILL FOLLOW.				2	L	7	3 	4F	4	F		A22WE   	E23EA
1999010800027	19990108	00027	NM  	1999	1	8	99ZZZX17         	1	19981119	G	5311		FRAME           			BOEING	727   	727259      	138408J	NM  										BS 990	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED AT FS 990, OUTBOARD OF STR 27R ON WEB SECTION OF FRAME.						2	L	7	3 	4F				A3WE
1999011500206	19990115	00206	SO  	1999	1	15	99ZZZX170        	1	19981121	G	3250		CENTERING TRACK 			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	BENT            	G				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			NE	03	15008					347250346				AIRCRAFT LANDED WITH NOSE LANDING GEAR RETRACTED.  NOSE GEAR DID NOT EXTEND DUE TO DAMAGE TO NOSE GEAR RETRACTION CENTER	ING TRACK PREVIOUSLY CAUSED BY EXCEEDING THE STEERING LIMITS DURING AIRCRAFT TOWING OPERATIONS.					1	L	7	2 	3O				A7SO
1999011500207	19990115	00207	CE  	1999	1	15	99ZZZX171        	1	19981106	G	6120		ROD             			BBAVIA	8     	8KCAB       	2110612	CE  										PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	1194E	1149 	777  			32177				ROD HAS A LINEAR INDICATION APPROXIMATLEY 1.75 INCHES LONG.						1	H	7	1 	3O				A21CE
1999011500208	19990115	00208	SO  	1999	1	15	99ZZZX172        	1	19981106	G	6120		FORK            			PIPER 	PA31  	PA31350     	7103110	SO  										PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17		2137 	688  							FORK HAS CRACKS EXTENDING AROUND CORNER IN 2 OPPOSING SLOTS.						1	L	7	2 	3O				A20SO
1999011500209	19990115	00209	SO  	1999	1	15	99ZZZX173        	1	19980520	G	3230	173527	UPLOCK          		159LM101241 	GULSTM	G159  	G159        	3952202	SO  										RT MLG	FAILED          	B			QU2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	18TF	12953				52				AIRCRAFT ARRIVED WITH DISCREPANCY, 'RIGHT MAIN LANDING GEAR FORWARD DOORS DO NOT CLOSE ALL THE TIME'.  PERFORMED RETRACT	ION TESTS, FOUND UPLOCK BOOK ASSY, P/N 159LM10124-1, STRIKING PISTON/AXLE ASSY CASTING, P/N 173527, IN RETRACTED POSITIO	N NOT COMPLETING CYCLE OF LANDING GEAR, THUS, NOT ALLOWING FORWARD DOORS TO CYCLE CLOSED.  DISASSEMBLED UPLOCK ASSY, REM	OVED UNAPPROVED SHIMS, INSPECTED, AND REASSEMBLED IAW MM.  THE LANDING GEAR WILL NOW COMPLETE ITS CYCLE, BUT THE HOOK AS	SY IS STIFF CHAFING THE CASTING ASSY ON INBD SIDE OF CASTING, CLEARANCES REMAIN INADEQUATE.  SUBMITTER SUGGESTED  REALIG	NMENT OF THE REAR ATTACHMENT OF THE UPLOCK SUPPORT BEAM WOULD BE REQUIRED TO ELIMINATE DISCREPANCY.	2	L	7	2 	4T				1A17
1999011500210	19990115	00210	SW  	1999	1	15	99ZZZX174        	1	19980913	G	3221	14534117	FORK            			TMPSON	NAVION	NAVIONA     	6150104	SW  										NLG	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	81010	2400 				NAV4434				ON ANNUAL INSPECTION, NOTED THE OLEO CENTERING BUNGEE HAD NEVER BEEN REMOVED PER NORTH AMERICAN SB'S.  (IT ALSO WAS BENT	 AND CRACKED) ON REMOVAL OF THE NOSE ASSY FROM ACFT.  A SLIGHT BUBBLING OBSERVED ON THE LANDING GEAR FORK.  AFTER DEEP C	LEANING (4 LAYERS OF PAINT), THE ENTIRE T/E OF THE FORK HAD LAYERS OF EXFOLIATION ON THE BOTTOM OF THE FORK, WHERE THE A	N-4-17A BOLTS ARE INSERTED, LARGE SURROUND OF LAYERED EXFOLIATION SEEN AROUND HEAD OF BOLT.  TRUNNION BEARING LT, AND RT	 SIDE TOTALLY WORN OUT WITH .0312 INCH VERTICAL, LATERAL PLAY.  ACFT TT:  2,400 HRS.		1	L	7	1 	3O				A782
1999011500211	19990115	00211	SO  	1999	1	15	99ZZZX175        	1	19980910	G	5620	1159SCB31004	WINDOW          			GULSTM	G1159 	G1159A      	3970109	SO  										FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	506T	6665 				484				DURING POST-FLIGHT INSPECTION WHAT APPEARED TO BE A DELAMINATION OF THE SIDE WINDOW WAS DETERMINED TO BE AN IN-PLANE STR	UCTURAL FAILURE OF THE ACRYLIC OUTER PANE.  UPON REMOVAL OF THE WINDOW, DISCOVERED THE ENTIRE PERIPHERY OF THE OUTER PAN	E WAS CRACKED AT EACH ATTACH HOLE BUSHING.  THESE CRACKS EMANATED FROM THE BUSHING HOLES AND PROGRESSED IN BOTH DIRECTIO	NS TO THE WINDOW EDGE AND TO THE WINDOW CENTER.  A NEW WINDOW WITH A LATER DASH NUMBER WAS INSTALLED.  THE NEW DASH NUMB	ERED WINDOW HAS BUSHINGS MOUNTED IN A RUBBER GROMMET WITH A LARGER SURFACE BEARING AREA TO ALLOW FOR WINDOW FLOAT DURING	 PRESSURIZATION.	2	L	7	2 	4F				A12EA
1999011500212	19990115	00212	CE  	1999	1	15	99ZZZX176        	1	19980923	G	2150		SWITCH          			MTSBSI	MU2   	MU2B35      	5780411	CE  										COCKPIT	MALFUNCTIONED   	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	503AA					633				WITH AIR CONDITIONER ON AUTO, PILOT GOT COOL AND TURNED MANUAL HOT SWITCH ON AND LEFT IT THERE.  THIS CAUSED EXCESS HEAT	 IN AIR DUCTS AND HIGH CONDENSATION.  PILOT RETURNED MANUAL HEAT SWITCH BACK TO NORMAL AND LANDED IMMEDIATELY.  THE AIR 	CLEARED AND SYSTEM WORKED NORMALLY.  GROUND CHECK, MAINTENANCE HAS CHECKED SYSTEM AND INSPECTED AREA UNDER COVER PANEL W	ITH NO DAMAGE TO AREA UNDER PANELS.  SUBMITTER SUSPECTED OVERTEMP SWITCH MAY HAVE NOT WORKED PROPERLY AT TIME OF TROUBLE	.  REPLACED SWITCH AS PRECAUTIONARY.		1	H	7	2 	3T			RT	A10SW
1999011500213	19990115	00213	SO  	1999	1	15	99ZZZX177        	1	19981214	G	2740	16067002	TORQUE TUBE     		16067000    	PIPER 	PA23  	PA23250     	7102308	SO  										HORIZ STABILIZER	DAMAGED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	5216Y	10369				272264				STABILIZER TORQUE TUBE HOLES FOR STABILIZER MOUNT WERE FOUND ELONGATED.  THIS WAS DISCOVERED WHILE INSPECTING THE LEFT S	TABILIZER FOR A CREAKING NOISE THAT WAS DISCOVERED DURING PRE-FLIGHT.  THE ELONGATION OF THE HOLES ALLOWED MOVEMENT OF T	HE STABILIZER.  THIS ACTION WORE THE ATTACHMENT BOLTS FOR THE OUTBOARD MOUNT FITTING P/N 16809-003 RESULTING IN MOVEMENT	 OF THE FITTING AGAINST THE SPAR.  SUBMITTER SUGGESTED INSPECTION OF THE HOLES FOR WEAR AT 500 OR 1,000 HOUR INTERVALS. 	 RELATED AD 74-13-03.		1	L	7	2 	3O				1A10
1999011500214	19990115	00214		1999	1	15	99ZZZX178        	1	19981202	G	2621	OA897776	CARTRIDGE       	OVERLD      	899066      															FIRE EXTINGUISH	FAILED          	B			YN2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01					SBII4					ON 12-2-98, OWNER/OPERATOR SENT THIS UNIT TO BE OVERHAULED.  DURING THE RECEIVING INSPECTION PROCESS, THE DISCHARGE OUTL	ET WAS NOTED AS DESTROYED DUE TO EXCESSIVE DISCHARGE OF THE CARTRIDGE (SQUIB).  THIS CARTRIDGE WAS IDENTIFIED BY THE OVE	RLAND AVIATION SB 26-20-02 ISSUED 6-22-98.  OWNER/OPERATOR NOTIFIED OF SB AND THIS REPORT.
1999011500215	19990115	00215		1999	1	15	99ZZZX179        	1	19981215	G	2621	OA472001	CARTRIDGE       	OVERLD      	4724202     															FIRE EXTINGUISH	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23					SBII1					ON 12-15-98, OWNER/OPERATOR SENT FIRE BOTTLE  FOR OVERHAUL.  DURING THE RECEIVING AND INSPECTION PROCESS, THE DISCHARGE 	OUTLET WAS NOTED AS DESTROYED DUE TO EXCESSIVE DISCHARGE OF THE SQUIB.  THIS SQUIB WAS IDENTIFIED BY THE OVERLAND AVIATI	ON SB 26-20-02 ISSUED ON 6-22-98.  OWNER/OPERATOR NOTIFIED OF SB AND THIS REPORT.
1999010800028	19990108	00028	NM  	1999	1	8	99ZZZX18         	1	19981119	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 960-999	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 960 - FS 999 LBL 24.						2	L	7	3 	4F				A3WE
1999011500216	19990115	00216	SO  	1999	1	15	99ZZZX180        	2	19981129	G	7414		GEAR            	SLICK       	4301        	UNIVAR	415   	415C        	0420302	NM  	CONT  	C90   	C9012F      	17009	SO  					MAGNETO	BROKEN          	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	99597				96042333	2220	40548812			LEFT MAGNETO FAILED DURING PRE-TAKEOFF MAG CHECK.  THREE TEETH ON LT MAG DRIVE GEAR MISSING.  DURING REMOVAL OF OIL TANK	, ACCESSORIES, AND ACCESSORY DRIVE CASE, ONE TOOTH WAS FOUND IN OIL TANK, TWO TEETH IN ACCY DRIVE CASE.  BOTH MAGNETOS W	ITH DRIVE GEARS SENT TO LYCON REBUILDING CO TO C/W AIRWORTHINESS BULLETIN CE-98-21R1.  BOTH GEARS FAILED ROCKWELL C SCAL	E HARDNESS TEST.   BOTH TESTED 7, SHOULD HAVE BEEN 38-42.  CAM GEAR INSPECTED, OIL TANK CLEANED, ENG RE-ASSEMBLED WITH S	ERVICEABLE MAGNETO DRIVE GEARS.  ENG AND ACCESSORIES HAVE 395 SMOH BY LYCON ON JAN '97.  SUBMITTER RECOMMENDS SPECIAL AI	RWORTHINESS BULLETIN CE-98-21R1 BE UPGRADED TO AN AD TO PREVENT FUTURE CATASTROPHIC ENGINE FAILURES.	1	L	7	1 	3O	3	O		A718    	E252
1999011500217	19990115	00217	EU  	1999	1	15	99ZZZX181        	1	19981031	G	2910	326705	VALVE           			AIRBUS	320   	A320214     		EU  										HYDRAULIC SYSTEM	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	716AW					716				CHECK VALVE FAILED CAUSING AC PUMP (YELLOW SYSTEM) TO BE BACK DRIVEN BY N2 ENGINE EDP.  CHECK VALVE FIN 8083.  NOTE:  FA	ILED CHECK VALVE WAS DISCOVERED AFTER SECOND PUMP REPLACEMENT.					2	L	7	2 	4F			RT	A28NM
1999043000656	19990430	00656	NM  	1999	4	30	99ZZZX1819       	1	19981009	G	2923	654468311	MODULE          			BOEING	737   	737*        		NM  										HYDRAULIC SYSTEM	CRACKED         	B	P		HN6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										FOUND APPROXIMATELY 7 UNITS IN THE PAST 2 MONTHS WITH PIN HOLE CRACKS AT NR 1 PRESSURE PORT DURING THE INCOMING FUNCTION	AL TEST OF THE UNIT.  MOST UNITS WOULD SHOW LEAKS AT 3,000 PSI DURING PROOF PRESSURE TEST.  THESE UNITS ARE INSTALLED ON	 THE BOEING 737 AT THE AFT BULKHEAD OF THE WHEEL WELL.  THE MODULAR PACKAGE OPERATES THE HYDRAULIC ACTUATORS ON THE LEAD	ING EDGE FLAPS AND THE RUDDER OF THE AIRCRAFT.			2	L	7	2 	4F			RT	A16WE
1999011500218	19990115	00218		1999	1	15	99ZZZX182        	2	19981221	G	8520	75060	BOLT            																	ENGINE	MISMANUFACTURED 	B		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17										INSPECTED NEW ROD BOLTS OUT OF LYCOMING PACKAGING, FOUND 22 OUT OF 28 BOLTS HAD NOT BEEN MACHINED ON THE HEAD OF THE BOL	T, ONLY ON THE THREAD END.  LYCOMING CONTACTED AND THE BOLTS RETURNED TO THE FACTORY.  SUBMITTER RECOMMENDED INSPECTING 	ALL NEW PARTS PRIOR TO INSTALLATION.
1999043000658	19990430	00658	NM  	1999	4	30	99ZZZX1821       	1	19980504	G	3610	322684003	VALVE           	JANITROL    	322684003   	BOEING	737   	737297      	1384480	NM  										AIR DIST	MISOVERHAULED   	B	P		HN6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	147AW	2827 			10800106	22630				RED, TI-TEMP RTV HAS BEEN APPLIED IN THE THROAT OF THE HOUSING AROUND THE BUTTERFLY SEAL SEAT.  THIS BUTTERFLY SEAL IS D	ESIGNED TO FLOAT IN THE HOUSING, BUT IN THIS CASE, THE SEAL WAS PRESSED INTO THE BEAD OF SEALANT.  SUBMITTER STATED THIS	 IS NOT AN ASSEMBLY STEP IN THE JANITROL AERO OHM, NOR IS IT A KNOWN PRACTICE OF A CUSTOMER E.O., OR SB.  THIS MATERIAL 	WAS NOT 'IN PLACE OF' PACKING ITEM NR 10.  THE PACKING WAS REMOVED FROM FLANGE, ITEM 7, INTACT.			2	L	7	2 	4F				A16WE
1999043000660	19990430	00660	NM  	1999	4	30	99ZZZX1823       	1	19981215	G	5540	65C258521	FITTING         		65C25841    	BOEING	737   	737300      	1384610	NM  										BS 27	GOUGED          	B			HN6R	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01										THE AUXILIARY ACTUATOR FITTING IS CONSTANTLY BEING RECEIVED INTO FACILITY WITH GOUGES ON THE INNER FACE OF THE LOWER ARM	.  THIS IS A WEAR AREA CIRCULAR IN SHAPE CAUSED BY THE ACTUATOR.   AVERAGE GOUGE DEPTH IS .020 INCH - .025 INCH. THIS IS	 A COMMON PROBLEM REQUIRING REPLACEMENT OF THE FITTING.				2	L	7	2 	4F			RT	A16WE
1999050700002	19990507	00002		1999	5	7	99ZZZX1832       	1	19981105	G	2720	69356111	SLEEVE          	BOEING      	65C370527   															YAW DAMPENER	GOUGED          	B	P	A	IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1464					AREA IS GOUGED.  CAM SEGMENT RUBBED DURING OPERATION.
1999050700003	19990507	00003		1999	5	7	99ZZZX1833       	1	19981105	G	2720	69356121	PISTON          	BOEING      	65C370527   															YAW DAMPENER	WORN            	B	P	A	IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					1464					ANGULAR WEAR IN CAM SEGMENT MATING AREA.  CAM SEGMENT ACTUATING BACK AND FORTH DURING OPERATION.
1999050700004	19990507	00004		1999	5	7	99ZZZX1834       	1	19981104	G	2740	69778551	SPRINGS         	BOEING      	654997025   															STAB TRIM GEARBX	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		18419			KE01575					FAILED AUXILIARY BRAKE TEST.  BROKEN SPRINGS.  INSTALLED PN 69-77855-2 SPRINGS.
1999050700005	19990507	00005		1999	5	7	99ZZZX1835       	1	19981215	G	2720	69579061	SPRING          	BOEING      	65C254105   															RUDDER CONTROL	BROKEN          	B			IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01		24123			849					SPRING, PN 69-57906-1, IS BROKEN.  IMPROPER HEAT TREATING, INCORRECT ALLOYS IN SPRING OR OVERSTRESSED.  SUBMITTER STATED	 SPRING, PN 69-57906-1, SHOULD BE REPLACED WITH SPRING, P/N 69-57906-2.
1999050700011	19990507	00011		1999	5	7	99ZZZX1841       	1	19981104	G	5540	69356071	CAM SEGMENT     	BOEING      	6935649     															RUDDER	GOUGED          	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01										GOUGES ARE ON THE 0.170 INCH DIAMETER OF THE SEGMENT.  APPEARS TO BE CAUSED BY RUBBING ON SLEEVE OF YAW DAMPER LAP ASSEM	BLY.
1999011500221	19990115	00221		1999	1	15	99ZZZX185        	1	19980903	G	2622		CARTRIDGE       	OVERLD      	892480      															FIRE EXTINGUISH	CORRODED        	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					13780					UPON DISASSEMBLY OF THIS WALTER KIDDE FIRE EXTINGUISHER, AN OVERLAND AVIATION CARTRIDGE (P/N 1386) WAS FOUND INSTALLED. 	 ALSO NAME PLATE (P/N 242779), TURN LABEL (P/N 211759), CAUTION AND INSTRUCTIONS DECALS DO NOT APPEAR TO BE OF ORIGINAL 	EQUIPMENT MANUFACTURE.  THE FIRE EXTINGUISHER WAS LAST SERVICED IN FEBRUARY, 1996, AT WHICH TIME THE UNIT DID NOT MEET T	HE ORIGINAL EQUIPMENT MANUFACTURER'S SPECIFICATIONS.
1999050700035	19990507	00035		1999	5	7	99ZZZX1865       	1	19981104	G	2720	69356071	CAM SEGMENT     																	RUDDER	GOUGED          	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					874A					GOUGES ARE ON THE 0.170 INCH DIAMETER OF THE SEGMENT.  APPEARS TO BE CAUSED BY RUBBING ON SLEEVE OF YAW DAMPER LAP ASSEM	BLY.
1999050700036	19990507	00036		1999	5	7	99ZZZX1866       	1	19981104	G	3232	65583661	HOUSING         	BOEING      	65585581    															MLG	CRACKED         	B	P		IU6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01					DA2005					HOUSING IS CRACKED AT BEARING LUG.
1999011500223	19990115	00223	EU  	1999	1	15	99ZZZX187        	1	19981209	G	7830	717571	VALVE           			ISRAEL	1125  	ASTRASPX    	4500205	EU  										THRUST REVERSER	MALFUNCTIONED   	B			QRRR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	275RA	258  			0054	098				GIVES A THRUST REVERSER 'UNSAFE' LIGHT, INTERMITTENTLY.  THIS IS A KNOWN PROBLEM WITH THIS UNIT PER THE MANUFACTURER.  T	HEY ARE COMING OUT WITH A NEW UNIT IN 1999.  THIS IS A FALSE INDICATION.  REPLACED UNIT WITH REPAIRED ONE.  TESTED AND R	ETURNED AIRCRAFT TO SERVICE.				2	L	7	2 	4F			RT	A16NM
1999050700042	19990507	00042	SO  	1999	5	7	99ZZZX1872       	1	19980808	G	3230	126051	TORQUE TUBE     			GRUMAV	G21   	G21A        	3951204	SO  										MLG	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	327					1051				THE TORQUE TUBE IS DESIGNED TO SHEER IF THE AIRPLANE IS RAISED BY THE GEAR LEGS IN SHALLOW WATER.  ONCE THE GEAR IS DOWN	, THERE IS VERY LITTLE FORCE ON THE TORQUE TUBE.  THE TORQUE TUBE MAY HAVE BEEN CRACKED PREVIOUSLY.  THE TORQUE TUBE SHE	ARED AT THE DESIGN SHEER POINT WITHOUT ANY PROVOCATION.  SUBMITTER SUGGESTED IT MAY HAVE BEEN AN OLD CRACK FROM A PREVIO	US ACCIDENT IN 1994.			1	H	7	2 	3R				TC654
1999011500224	19990115	00224	SO  	1999	1	15	99ZZZX188        	1	19981216	G	3230	65319004	HOUSING         			PIPER 	PA28  	PA28151     	7102805	SO  										LEFT MLG	BROKEN          	H	S			O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			NE	05	43375	4800 				287415480				UPON LANDING, AIRCRAFT BECAME HARD TO STEER.  FOUND EAR ON HOUSING BROKEN CLEAN OFF ON RIGHT GEAR.  INSPECTED LEFT SIDE 	AND FOUND THE HOUSING ALSO CRACKED.  SUGGEST FREQUENT INSPECTION.   THIS IS THE SECOND AIRCRAFT FOUND WITH THIS PROBLEM 	IN THE LAST MONTH.				1	L	7	1 	3O				2A13
1999011500225	19990115	00225	CE  	1999	1	15	99ZZZX189        	1	19981119	G	3250	35820111	BEARING         			BEECH 	35    	E35         	1151512	CE  										NLG	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	03	3324C					D3990				ZERKS ON FRONT OF NOSE STRUT ASSY WOULD NOT TAKE GREASE.  FOUND THE BEARING (P/N 35-820111, FIG 50, INDEX 5) AFT OF ZERK	 DID NOT HAVE THE GREASE HOLE DRILLED IN TOP AND BOTTOM BEARING.					1	L	7	1 	3O				A777
1999010800029	19990108	00029	NM  	1999	1	8	99ZZZX19         	1	19981119	G	5342		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 344-380	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED AT FS 344 - FS 380 LBL 45, SEAT TRACK.						2	L	7	3 	4F				A3WE
1999011500226	19990115	00226	CE  	1999	1	15	99ZZZX190        	1	19981220	G	2820		LINE            			BEECH 	18    	D18S        	1151004	CE  										FUEL SYSTEM	CHAFED          	H	S			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	14	90502	4800 				A346				FUEL LEAKING FROM THE LEFT SIDE BETWEEN THE BELLY OF THE FUSELAGE AND THE WING ROOT WHILE THE AIRCRAFT WAS IN THE LEVEL 	POSITION.  TAIL WAS SET BACK DOWN ON THE GROUND AND LEAK STOPPED.  SEAT WAS PUT BACK TO LEVEL AND THE LEAK STARTED AGAIN	.  FOUND THE MAIN 76 GALLON LEFT TANK FUEL LINE LEADING TO THE FUSELAGE, UNDER THE BATTERY BOX, VERY HARD TO SEE.  YEARS	 OF BATTERY SPILL HAD CORRODED THE ALUMINUM FUEL LINE AND CAUSED A PIN HOLE LEAK ONLY WHEN THE AIRCRAFT WAS IN THE LEVEL	 POSITION OR FLIGHT.		1	L	7	2 	3R				A765
1999051400513	19990514	00513	GL  	1999	5	14	99ZZZX1908       	3	19981222	G	6111	V84336	BLADE           			GULSTM	500   	500A        	0141104	SW  						HARTZL	HCA2V	HCA2VF2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6127X	4250 	879  		A31927	500A97032		Y1634		BLADE FAILED EDDY CURRENT TESTING.						1	H	7	2 	3O				6A1     		5	C	P24E
1999051400514	19990514	00514	GL  	1999	5	14	99ZZZX1909       	3	19981222	G	6111	83810	CLAMP           			GULSTM	500   	500A        	0141104	SW  						HARTZL	HCA2V	HCA2VF2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6127X	4250 	879  		G1788HT			Y1051		CLAMP HAS A CRACK DISCOVERED DURING VISUAL INSPECTION APPROXIMATELY 3 INCHES LONG STARTING AT THE A321 HOLE.						1	H	7	2 	3O				6A1     		5	C	P24E
1999011500227	19990115	00227	SO  	1999	1	15	99ZZZX191        	2	19981109	G	8530		CYLINDER HEAD   			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					RT ENGINE	BROKEN          	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			WP	07	8170G		86   			348233116	268372R			CONDITION OCCURRED DURING CRUISE CONFIGURATION.  PILOT REPORTED LOSS OF MANIFOLD PRESSURE AND DIMINISHED PERFORMANCE ON 	RT ENGINE.  PILOT NOTED OIL COMING FROM ENGINE COWLING AND SHUT ENGINE DOWN.  AN INSPECTION REVEALED CYL NR 4 HAD A BROK	EN HEAD.  THE BREAK RAN AROUND THE CIRCUMFERENCE OF THE HEAD AND OCCURRED AT THE JUNCTION OF THE HEAD AND BARREL ASSY. C	YL ASSY HAD 86 HRS TSO, TT UNKNOWN.  SUBMITTER STATED SINCE NO RECORDS ARE KEPT OF TOTAL RUNNING TIME ON THESE PARTS, SU	SPECT THE PART MAY HAVE HAD A HIGH TOTAL TIME RESULTING IN METAL FATIGUE.  PREVIOUS FIELD EXPERIENCE INDICATES A RECURRE	NCE OF THIS PROBLEM ON THIS ENGINE.	1	L	7	2 	3O	3	O		A7SO    	E9CE
1999051400515	19990514	00515	GL  	1999	5	14	99ZZZX1910       	3	19981222	G	6111	V84336	BLADE           			GULSTM	500   	500A        	0141104	SW  						HARTZL	HCA2V	HCA2VF2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	6127X	4250 	387  		A51280			Y1051		BLADE FAILED EDDY CURRENT TESTING.						1	H	7	2 	3O				6A1     		5	C	P24E
1999011500228	19990115	00228	EA  	1999	1	15	99ZZZX192        	2	19980706	G	7414		CAM             	SLICK       	6363        	PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					MAGNETO	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	06	9214H	238  			96121593	4622114				ENGINE WOULD NOT START.  REMOVED MAG, FOUND CAM FOR POINTS WAS ROUNDED FLAT AND GEARS INSIDE WERE WORN BAD.  TALKED TO T	ECH REP WITH UNISON AND WAS TOLD ON A PRESSURED MAG, 238 HRS WAS MORE THAN THE MFG EXPECTS TO GET OUT OF THE PART.  THE 	NYLON REACTS TO THE MOISTURE INTRODUCED TO THE MAG WITH PRESSURIZATION OF A MAG AND TURNS THE NYLON PARTS TO GOO AND THA	T 150 HRS IS ALL THAT SHOULD BE EXPECTED FROM THIS MAG.  THE MAGS A FEW YEARS AGO WERE MADE WITH PHENOLIC, BUT POINTS NE	EDED TO BE ADJUSTED EVERY FEW HUNDRED HRS AND CHANGED TO NYLON.  THIS WORKS WELL EXCEPT WITH PRESSURIZED MAGS.  SUBMITTE	R STATED THE FAA SHOULD REQUIRE THAT PHENOLIC IS USED IN THE MFG OF A MAG TO BE USED ON A PRESSURIZED AIRPLANE.	1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1999051400119	19990514	00119	GL  	1999	5	14	99ZZZX1929       	3	19981222	G	6111	V8433N4	BLADE           		D10132      											HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER	CRACKED         	B			LU4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17										EDDY CURRENT INDICATION IN EXCESS OF MANUFACTURER'S SPECS.  THIS WAS A SPARE BLADE SENT BY CUSTOMER FOR INSPECTION.  NO 	OTHER INFORMATION AVAILABLE.															5	C	P24E
1999011500229	19990115	00229	SW  	1999	1	15	99ZZZX193        	1	19981120	G	3230	19805	U BOLT          		71291       	BBAVIA	7     	7ECA        	21101NN	SW  										LT MLG	FAILED          	H		A	HE8S	O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CE	09	86983	1702 				103174				THE LT MLG LEG DEPARTED THE AIRCRAFT DURING LANDING ROLL-OUT.  SUBSEQUENT INVESTIGATION DISCLOSED A FATIGUE FAILURE AT T	HE FORWARD ATTACH POINT OF THE GEAR LEG U-BOLT, BELLANCA P/N 1-9805.  THIS CONDITION INDUCED THE INSTANTANEOUS FAILURE O	F THE REAR ATTACH POINT, AND CENTER MOUNT BOLT, P/N MS2005-32.  THE BELLANCA 7EAC INSPECTION GUIDE REFERENCES REPLACEMEN	T OF THE MLG ATTACH HARDWARE AT 500-HOUR INTERVALS.  REVIEW OF THE AIRCRAFT MAINTENANCE RECORDS ESTABLISHED THAT THE ATT	ACH BOLTS HAD BEEN IN SERVICE FOR 1,702 HRS.		1	H	7	1 	3O				A759
1999011500230	19990115	00230	CE  	1999	1	15	99ZZZX194        	1	19980923	G	8120	NH100089770	COUPLING        			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					WASTEGATE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	5751C	290  				340A0974	290929R			DURING C/W AD 75-23-08R5, THE WASTEGATE OUTLET COUPLING WAS FOUND SEVERELY CRACKED.  THE CRACK WAS FOUND RADIALLY ALONG 	THE COUPLING AND EXTENDED ABOUT 50 PERCENT OF THE TOTAL CIRCUMFERENCE OF THE PART.  THIS NEW COUPLING IS NOT LIFE-LIMITE	D PER TABLE ONE OF THE ABOVE MENTIONED AD.				1	L	7	2 	3O	3	O		3A25    	E8CE
1999051400183	19990514	00183	SW  	1999	5	14	99ZZZX1949       	1	19981227	G	6210	206010200133	BLADE           			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3912Q	2486 			A2560	3271				DURING DAILY INSPECTION FOUND CORROSION AND DEBONDING AT SKIN/SPAR BENEATH GRIP FINGER DOUBLER.						1	G	7	1 	3U				H2SW
1999011500231	19990115	00231	SO  	1999	1	15	99ZZZX195        	1	19980807	G	3233	83604	ACTUATOR        			PIPER 	PA46  	PA46310P    	7104605	SO  										NLG	OUT OF ADJUST   	H		A		O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	14	2138C	2430 				468608020				AIRCRAFT BECAME UNCONTROLLABLE DURING LANDING ROLL-OUT.  INVESTIGATION REVEALED NOSE GEAR LEG ANGLED AFT DUE TO MIS-ADJU	STMENT OF ACTUATOR LENGTH WHICH CHANGED GEOMETRY OF TIRE CONTACT.  PIPER SERVICE INSTRUCTIONS DO NOT CONTAIN PROCEDURE F	OR RIGGING NOSE GEAR GEOMETRY.  SUBMITTER RECOMMENDS AD FOR ALL PA-46 AIRCRAFT TO VERIFY CORRECT RIGGING OF NOSE GEAR IN	 DOWN POSITION.			1	L	7	1 	3O			RT	A25SO
1999011500232	19990115	00232	SO  	1999	1	15	99ZZZX196        	1	19980807	G	3233	89786	ACTUATOR        			PIPER 	PA46  	PA46310P    	7104605	SO  										NLG	OUT OF ADJUST   	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			SO	14	2138C	2430 				468608020				AIRCRAFT BECAME UNCONTROLLABLE DURING LANDING ROLL-OUT.  INVESTIGATION REVEALED NOSE GEAR LEG ANGLED AFT DUE TO MIS-ADJU	STMENT OF ACTUATOR LENGTH WHICH CHANGED GEOMETRY OF TIRE CONTACT.  PIPER SERVICE INSTRUCTIONS DO NOT CONTAIN PROCEDURE F	OR RIGGING NOSE GEAR GEOMETRY.  SUBMITTER RECOMMENDS AD FOR ALL PA-46 AIRCRAFT TO VERIFY CORRECT RIGGING OF NOSE GEAR IN	 DOWN POSITION.			1	L	7	1 	3O			RT	A25SO
1999011500233	19990115	00233		1999	1	15	99ZZZX197        	4	19981201	G	3400		GEARS           	NARCO       	NAV122D     	CESSNA	150   	150M        	2071830	CE  										COCKPIT	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	704HQ	1    			10007	15078627				UNIT HAS APPROXIMATELY ONE HOUR OF OPERATION SINCE NEW CHANNELING GEARS BROKEN.  RETURNED TO NARCO FOR REPAIRS.						1	H	7	1 	3O				3A19
1999051400375	19990514	00375	SO  	1999	5	14	99ZZZX1973       	1	19981130	G	2913		DRIVE GEAR      			PIPER 	PA28  	PA28R201T   	7102813	SO  										OIL PUMP	FAILED          	H				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			SW	99	6558C		1450 			28R7803238				DURING LEVEL FLIGHT AT 8,500 FEET, PROPELLER SURGE OCCURRED.  OBSERVED ZERO RPM, ZERO OIL PRESSURE.  SHUT DOWN ENGINE. S	TOPPED PROPELLER.  GLIDE TO NEAREST AIRPORT 9.8 MILES.  LANDED ON RUNWAY, ROLL OUT TO RAMP AREA.  TEST, NO OIL PRESSURE,	 NO TACHOMETER.  SUBMITTER SUSPECTED DRIVE GEAR.  TEAR DOWN, REMOVED AND REPLACED.  LEAK CHECK  TEST RUN.  TEST FLY OK. 	 PART APPEARED OVERTORQUED BY ASSEMBLER AT OVERHAUL.			1	L	7	1 	3O				2A13
1999011500234	19990115	00234		1999	1	15	99ZZZX198        	4	19981201	G	3400		DISPLAY         	NARCO       	NAV122D     	CESSNA	150   	150M        	2071830	CE  										COCKPIT	MALFUNCTIONED   	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	704HQ				10007	15078627				OUT OF BOX FAILURE.  DISPLAY PRODUCES NOSIE IN NAV AUDIO.  RETURNED UNIT TO NARCO FOR REPAIR.						1	H	7	1 	3O				3A19
1999051400383	19990514	00383	NE  	1999	5	14	99ZZZX1981       	3	19981209	G	6111	6607132886	BLADE           	ROTOL       												ROTOL	R389	R3894123F25 	NE  	PROPELLER	CRACKED         	B			MS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	27		20679	6795 		700			DRG421283		PROPELLER WAS RECEIVED IN DISASSEMBLED CONDITION  OR ROUTINE OVERHAUL.  DURING CLEANING OF BLADE, NOTED A CRACK IN THE O	UTER SLEEVE RUNNING FROM PTFE AREA TO BEARING AREA.  BLADE WAS REJECTED FROM FURTHER SERVICE.															6	C	P30N
1999011500695	19990115	00695	SO  	1999	1	15	99ZZZX199        	1	19981130	G	5411	1200385001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	126AM					120102				FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN LEFT FORWARD NACELLE NR 1 FRAME.  REPETITIVE DISCREPANCY AS PREVIOU	SLY DETAILED AND REPORTED.  SUBMITTER STATED POSSIBLE CAUSE REMAINS UNDETERMINED, WOULD SUSPECT ENGINE TORQUE AND VIBRAT	ION AS CONTRIBUTING FACTORS.  SUGGESTED TIMED INTERVAL REPETITIVE INSPECTION OF AREA.				2	L	7	2 	4T			RT	A31SO
1999010800012	19990108	00012	CE  	1999	1	8	99ZZZX2          	1	19981028	G	3230	12416185	SUPPORT         			CESSNA	210   	P210N       	2073454	CE  										LT AND RT MLG	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	5486W	2578 				P21000696				AIRPLANE HAD NO  GREEN LIGHT INDICATION FOR GEAR DOWN.  FOUND MAIN GEAR DOWNLOCK SUPPORT ASSEMBLY LOOSE.  THE LOOSE BOLT	S ALLOWED THE SHIM TO SHIFT OUT OF POSITION.  THE BOLTS WERE NOT SAFETIED.  SUBMITTER RECOMMENDED OTHER OPERATORS CHECK 	THEIR 210 NEXT TIME ON JACKS (GEAR INTRANSIT POSITION).  NOTE:  P210 OPERATORS ALLOW A CONSIDERABLE AMOUNT OF TIME TO DI	G THROUGH .50 INCH - .75 INCH OF PROSEAL AT PANEL LOCATED AT AFT DOOR POST BULKHEAD.  FACTORY QA COMMENTED BOLTS ARE ALW	AYS PROPERLY TORQUED AT SAFETY WHEEL.  ACFT ALWAYS QA INSPECTED IN FACTORY PER FACTORY SPECS.		1	H	7	1 	3O				3A21
1999012000008	19990120	00008	SO  	1999	1	20	99ZZZX20         	1	19981104	G	5350		FASTENER        			GULSTM	GV    	GV          		SO  										FAIRING	CRACKED         	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	313RG	653  				504				DURING COMPLIANCE OF SB-BR700-72-900062, FOUND FASTENER MISSING AND NUMEROUS FASTENERS CRACKED.						2	L	7	2 	4F			RT	A12EA
1999011500696	19990115	00696	SO  	1999	1	15	99ZZZX200        	1	19981130	G	5411	1200385002	FRAME           			EMB   	120   	EMB120RT    		SO  										RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	126AM					120102				FLUORESCENT PENETRANT INSPECTION INDICATED CRACKS IN RIGHT FORWARD NACELLE NR 1 FRAME.  REPETITIVE DISCREPANCY AS PREVIO	USLY DETAILED AND REPORTED.  SUBMITTER STATED POSSIBLE CAUSE REMAINS UNKNOWN, WOULD SUSPECT ENGINE TORQUE AND VIBRATION 	AS CONTRIBUTING FACTORS.  SUGGESTED TIMED INTERVAL REPETITIVE INSPECTION OF AREA.				2	L	7	2 	4T			RT	A31SO
1999011500697	19990115	00697	SO  	1999	1	15	99ZZZX201        	1	19981124	G	5411	12003852001	FRAME           			EMB   	120   	EMB120RT    		SO  										RT/LT NACELLE	CRACKED         	B	P		WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	126AM					120102				DURING ROUTINE MAINTENANCE CHECKS, CRACKS WERE FOUND ON BOTH ENGINE NACELLE NR 1 FRAMES.  ON THE LT FRAME, THE CRACK IS 	LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF THE	 FRAME.  THE CRACK IS .45 INCH FROM THE CENTER OF THE BOLT HOLE, AND .225 INCH IN LENGTH.  ON THE RT FRAME, THE CRACK IS	 LOCATED ON THE LOWER SIDE OF THE STIFFENEING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF T	HE FRAME.  THE CRACK IS .52 INCH FROM THE CENTER OF THE BOLT HOLE, AND .250 INCH IN LENGTH.  SUBMITTER RECOMMMENDED REPL	ACING BOTH FRAMES AND CONTINUE MONITORING IAW EXISTING MAINTENANCE CHECKS.	2	L	7	2 	4T			RT	A31SO
1999011500698	19990115	00698	SO  	1999	1	15	99ZZZX202        	1	19981202	G	5530	HL225	RIVET           			EMB   	120   	EMB120RT    		SO  										VERT STABILIZER	SHEARED         	B	P		WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	260AS					120132				DURING C-CHECK INSPECTION, A RIVET HEAD WAS FOUND SEVERED FROM ITS SHAFT.  THE RIVET LOCATION IS AT FRAME 47, STA X16128	, AT THE LEFT HAND SIDE OF THE VERTICAL STABILIZER BASE.  THERE IS NO INDICATION AS TO WHAT CAUSED THE RIVET HEAD TO BEC	OME SEVERED.  THE HOLE DOES NOT SHOW EVIDENCE OF ANY DAMAGE.  SUBMITTER RECOMMENDED REPLACING RIVET AND CONTINUE MONITOR	ING WITH ESTABLISHED C-CHECKS.			2	L	7	2 	4T			RT	A31SO
1999052100060	19990521	00060		1999	5	21	99ZZZX2028       	4	19980724	G	3416	AT50A	TRANSPONDER     	NARCO       		PIPER 	PA28  	PA28151     	7102805	SO  										COCKPIT	MALFUNCTIONED   	B			OPXR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	01	4320F				47971	287715016				TRANSPONDER MODE 'C' REPORTED BY ATC AS BEING INVALID 7-24-98.						1	L	7	1 	3O				2A13
1999011500699	19990115	00699	SO  	1999	1	15	99ZZZX203        	1	19981210	G	5330	12D066321DD1	SKIN            			EMB   	120   	EMB120RT    		SO  										BS 15	CORRODED        	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	260AS					120132				TWO AREAS OF CORROSION WERE FOUND ON THE INNER SIDE WHICH EXCEEDED THE MANUFACTURER'S ALLLOWABLE LIMITS.  THE CAUSE OF C	ORROSION IN THIS AREA IS DUE TO THE PRESENCE OF EXCESSIVE MOISTURE, AND OTHER CONTAMINENTS WHICH ARE FREQUENTLY PRESENT.	  THE FIRST AREA WAS APPROXIMATELY 1 INCH AFT OF FRAME 15 IN BETWEEN STR 16L AND STR 17L, ON THE CHEM-MILLED AREA OF THE	 INNER SKIN.  DEPTH OF THE CORROSION WAS .050 INCH.  THE SECOND AREA OF CORROSION EXTENDED FROM THE EDGE OF THE AFT SIDE	 OF FRAME 15A, 1.5 INCHES, AND EXTENDED FROM THE CENTER RIVET LINE OF STR 18L, 2.2 INCHES TOWARDS STR 17L.  THE DEPTH OF	 CORROSION WAS .030 INCH.	2	L	7	2 	4T			RT	A31SO
1999052100063	19990521	00063	EA  	1999	5	21	99ZZZX2031       	2	19981221	G	8550	040034312	BREATHER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FROZE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	7385W					15284502	L2127015			BREATHER PIPE FROZEN.  DID NOT HAVE SECONDARY HOLE, HIGH ENOUGH IN TUBE CAUSED SEAL TO BLOW OUT.						1	H	7	1 	3O	3	O	NT	3A19    	E223
1999052100064	19990521	00064	EA  	1999	5	21	99ZZZX2032       	2	19981221	G	8550	040034313	BREATHER        			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	FROZE           	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	21	7385W					15284502	L2127015			BREATHER PIPE FROZEN.  DID NOT HAVE SECONDARY HOLE, HIGH ENOUGH IN TUBE CAUSED SEAL TO BLOW OUT.						1	H	7	1 	3O	3	O	NT	3A19    	E223
1999011500700	19990115	00700	SO  	1999	1	15	99ZZZX204        	1	19981211	G	5411	12003852001	FRAME           			EMB   	120   	EMB120RT    		SO  										LT/RT NACELLE	CRACKED         	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	236AS					120049				DURING ROUTINE MAINTENANCE CHECK, CRACKS WERE FOUND ON BOTH ENGINE NACELLE NR 1 FRAMES.  ON THE LT FRAME, THE CRACK IS L	OCATED ON THE LOWER SIDE OF THE STIFFENING WEB BETWEEN THE TOP OUTBOARD MOUNTING BOLT HOLE AND THE OUTBOARD EDGE OF THE 	FRAME.  ON THE RT FRAME, THE CRACK IS LOCATED ON THE LOWER SIDE OF THE STIFFENING WEB BETWEEN THE TOP OUTBOARD MOUNTING 	BOLT HOLE AND THE OUTBOARD EDGE OF THE FRAME.  SUBMITTER RECOMMENDED REPLACING BOTH FRAMES AND CONTINUE MONITORING IAW E	XISTING MAINTENANCE CHECKS.		2	L	7	2 	4T			RT	A31SO
1999011500701	19990115	00701	SO  	1999	1	15	99ZZZX205        	1	19981205	G	5751	12017909003	RIB             			EMB   	120   	EMB120RT    		SO  										AILERON	GOUGED          	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	236AS					120049				DURING PERFORMANCE OF C-CHECK INSPECTION TASK ON THE LEFT WING, THE AILERON ATTACH RIB 20 WAS FOUND TO HAVE A GOUGE APPR	OXIMATELY 1 INCH LONG BY .027 INCH DEEP ON THE OUTBOARD SIDE.  THIS WAS APPARENTLY CAUSED BY PREVIOUS REMOVAL OR INSTALL	ATION OF AILERON.  THE AREA OF DAMAGE IS HARD TO SEE WITH AILERON INSTALLED.				2	L	7	2 	4T			RT	A31SO
1999011500702	19990115	00702	SO  	1999	1	15	99ZZZX206        	1	19981210	G	5320	12046155001	BEAM            			EMB   	120   	EMB120RT    		SO  										BS 4088-6467	CORRODED        	B			WVER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	09	236AS					120049				LEFT OMEGA BEAM, IN BETWEEN STA 4088.D AND STA 6467.6, WAS FOUND CORRODED BEYOND THE MANUFACTURER'S ALLOWABLE LIMITS.  T	HE OMEGA BEAM HAD THREE AREAS OVER A 12 INCH LENGTH WHICH WERE OUT OF LIMITS.  THE FIRST AREA WAS 1.5 INCHES WIDE BY 1 I	NCH IN LENGTH, AND WAS .017 INCH DEEP.  THE SECOND AREA WAS .75 INCH WIDE BY 1 INCH IN LENGTH AND WAS .008 INCH DEEP.  T	HE THIRD AREA WAS .250 INCH IN WIDTH BY 1 INCH IN LENGTH BY .012 INCH DEEP AND WAS LOCATED ON THE OUTBOARD RADIUS OF THE	 BEAM.  DUE TO THE EXTENT OF THE CORROSION, THE CUSTOMER ADVISED THE SECTION OF OMEGA BEAM BE REPLACED.		2	L	7	2 	4T			RT	A31SO
1999011500703	19990115	00703	SW  	1999	1	15	99ZZZX207        	1	19980312	G	5320	206033201	BEAM            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	187AL	12175				51135				ON DAILY INSPECTION FOUND CRACK NEAR AFT LEFT SIDE NODAL BEAM SUPPORT APPROXIMATELY .3 INCH OUTBOARD OF NODAL BEAM SUPPO	RT NEAR A RIVET HEAD .					1	G	7	1 	3U				H2SW
1999011500704	19990115	00704	NE  	1999	1	15	99ZZZX208        	1	19980331	G	6320	23035179	GEARBOX         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL				CAG90541	760280				UPON INSPECTION OF GEARBOX PARTS DURING DISASSEMBLY, FOUND CUT O-RING UNDER SCREEN NR 6840136 IN OIL DELIVERY TUBE OIL P	ASSAGE.  THIS COULD HAVE CAUSED RESTRICTED OIL FLOW TO OIL DELIVERY TAKE WHICH LUBES 2-1/2 BEARING AREA.  SUBMITTER STAT	ED LACK OF OIL  IN 2-1/2 BEARING WAS POSSIBLY CAUSE FOR 2-1/2 BEARING BREAK-UP.				1	G	7	2 	3U				H1NE
1999052800332	19990528	00332	GL  	1999	5	28	99ZZZX2088       	3	19980212	G	6111	7636D4	BLADE           													HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					B73702			856R		BLADE IS CRACKED AT TRAILING EDGE RETENTION AREA.																5	C	P23E
1999052800333	19990528	00333	GL  	1999	5	28	99ZZZX2089       	3	19980310	G	6111		BLADE           													HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					B13500					BLADE IS CRACKED AT TRAILING EDGE RETENTION AREA.																5	C	P23E
1999011500705	19990115	00705	SW  	1999	1	15	99ZZZX209        	1	19981125	G	5510	206023119110	SUPPORT         		407023800101	BELL  	407   	407         		SW  										HORIZ STABILIZER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	577AL					53247				DURING DAILY INSPECTION FOUND SLAT SUPPORT, P/N 206-023-119-110, (LEFT SIDE, 2ND FROM INBOARD) CRACKED.  REMOVED AND REP	LACED CRACKED SUPPORT.					1	G	7	1 	3U			O	H2SW
1999052800334	19990528	00334	GL  	1999	5	28	99ZZZX2090       	3	19980212	G	6111	7636D4	BLADE           													HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					B73137			856R		BLADE IS CRACKED AT TRAILING EDGE SIDE IN RETENTION AREA.																5	C	P23E
1999052800335	19990528	00335	GL  	1999	5	28	99ZZZX2091       	3	19980310	G	6111		BLADE           													HARTZL	HC82	HC82VL2     	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					B13481					BLADE IS CRACKED AT TRAILING EDGE CAMBER SIDE RETENTION AREA.																5	C	P23E
1999052800336	19990528	00336	GL  	1999	5	28	99ZZZX2092       	3	19980212	G	6111	V7636N	BLADE           													HARTZL	HCA3V	EHCA3VF2    	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					14378			BR585		BLADE IS CRACKED AT RETENTION AREA TRAILING EDGE SIDE OF BLADE.																5	C	P6EA
1999052800337	19990528	00337	GL  	1999	5	28	99ZZZX2093       	3	19980212	G	6111	V84334	BLADE           													HARTZL	HCA3V	EHCA3VF2    	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					A18577					BLADE IS CRACKED AT RETENTION AREA TRAILING EDGE OF BLADE.																5	C	P6EA
1999052800338	19990528	00338	GL  	1999	5	28	99ZZZX2094       	3	19980212	G	6111	V7636N	BLADE           													HARTZL	HCA3V	EHCA3VF2    	GL  	PROPELLER	CRACKED         	B			NWOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05					D13538			BR585		BLADE IS CRACKED AT RETENTION AREA TRAILING EDGE SIDE.																5	C	P6EA
1999012000009	19990120	00009	SO  	1999	1	20	99ZZZX21         	1	19981104	G	5350		FASTENER        			GULSTM	GV    	GV          		SO  										FAIRING	CRACKED         	B			JZBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	25	158AF	603  				506				DURING COMPLIANCE OF SB-BR700-72-900062, FOUND NUMEROUS FASTENERS CRACKED.						2	L	7	2 	4F			RT	A12EA
1999011500706	19990115	00706	GL  	1999	1	15	99ZZZX210        	2	19981022	G	7230	23008014	CARBON SEAL     		23051643    						ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC90031B					INSPECTED SEAL AND FOUND CHIPPED EDGE AND CRACK THROUGH CARBON SEAL.											3	U			E1GL
1999011500707	19990115	00707	WP  	1999	1	15	99ZZZX211        	1	19981027	G	7120	J81333	MOUNT           	LORD        		HILLER	UH12  	UH12E       	4360122	WP  										FLANGE	SEPARATED       	B		A	OUGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	180HA	96   				HA3080				RUBBER MOUNT SEPARATION FROM MOUNTING FLANGE.  RUBBER CURE DATE 11-95, MFG BY LORD.  PART HAS BEEN IN SERVICE 12 MONTHS.						1	G	7	1 	3O				4H11
1999011500711	19990115	00711	GL  	1999	1	15	99ZZZX215        	2	19981207	G	7421	CH34168	IGNITER         			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW					470117D				IGNITER SLOW TO FIRE ON COLD MORNINGS.  REMOVED AND REPLACED.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1999011500712	19990115	00712	EA  	1999	1	15	99ZZZX216        	1	19981215	G	4930	2261143	PUMP            			CNDAIR	CL600 	CL6002B16   	1900305	EA  										APU	FAILED          	B			QRRR	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			EA	13	270RA	625  			605	5337				APU FUEL PUMP 'FAIL' LIGHT ON.  REMOVED FAILED APU FUEL PUMP.  INSTALLED REPLACEMENT UNIT.  OPERATION NORMAL.						2	L	7	2 	4F			RT	A21EA
1999011500713	19990115	00713	EA  	1999	1	15	99ZZZX217        	1	19981215	G	4930	2261143	PUMP            			CNDAIR	CL600 	CL6002B16   	1900305	EA  										APU	FAILED          	B			QRRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	270RA				788	5337				UNIT RECEIVED IN FAILED CONDITION.  PREVIOUS TEAR-DOWN REPORT, UNIT INOPERABLE, BLOWN FUSE, BRUSHES WORN UNEVENLY, ARMAT	URE GROOVED, BRUSHES CHIPPED.  UNIT REPAIRED.  WHEN INSTALLED IN AIRCRAFT, UNIT RAN SLOWLY, MADE GRINDING NOISES.  UNIT 	REMOVED FROM AIRCRAFT.				2	L	7	2 	4F			RT	A21EA
1999061100146	19990611	00146	CE  	1999	6	11	99ZZZX2171       	1	19980807	G	2121	66002311	BLOWER FAN      		B4766       	LEAR  	55    	55LEAR      	5170702	CE  										AIR DISTRIBUTION	MISMARKED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	455RH				4657	110				RECEIVED FROM LEARJET AND INSTALLED 2 NEW BLOWER FANS.  BOTH FANS COME BAGGED WITH PART NUMBER TAGS 6600231-1.  AFTER TR	OUBLESHOOTING, FOUND THESE MOTORS WERE BOTH 12-VOLT (NEW FROM LEARJET) AND THEY WERE SUPPOSED TO BE 24-VOLT.					2	L	7	2 	4F				A10CE
1999061100147	19990611	00147	CE  	1999	6	11	99ZZZX2172       	1	19980807	G	2121	66002311	BLOWER FAN      		B4766       	LEAR  	55    	55LEAR      	5170702	CE  										AIR DISTRIBUTION	MISMARKED       	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	11	455RH				4660	110				RECEIVED FROM LEARJET AND INSTALLED 2 NEW BLOWER FANS.  BOTH FANS COME BAGGED WITH PART NUMBER TAGS 6600231-1.  AFTER TR	OUBLESHOOTING, FOUND THESE MOTORS WERE BOTH 12-VOLT (NEW FROM LEARJET) AND THEY WERE SUPPOSED TO BE 24-VOLT.					2	L	7	2 	4F				A10CE
1999011500714	19990115	00714	EA  	1999	1	15	99ZZZX218        	1	19981215	G	4930	2261143	PUMP            			CNDAIR	CL600 	CL6002B16   	1900305	EA  										APU	FAILED          	B			QRRR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	270RA		51   		787	5337				UNIT WAS INSTALLED ON AIRCRAFT FOR ONLY 51 HOURS BEFORE FAILURE.  (PREVIOUS TEAR-DOWN REPORT READ - 'CAUSE FOR REMOVAL U	NCONFIRMED'.  CAUSE WAS LISTED AS 'APU PUMP FAIL LIGHT' ON.  BENCH CHECKED. OK).  THIS FAILURE WAS THE SAME.  APU PUMP '	FAIL' LIGHT ON.  INSTALLED REPLACEMENT UNIT.  NORMAL OPERATION.				2	L	7	2 	4F			RT	A21EA
1999011500715	19990115	00715		1999	1	15	99ZZZX219        	4	19981120	G	3417	9246076	LAMP            		466114      	CESSNA	650   	650         	2076802	CE  										COCKPIT	FAILED          	B		A	PZUR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	2UP				147	650027				SPRING CONTACT IN LAMP 18 ASSY SEPARATED CAUSING A SHORT CREATING CURRENT OVERLOAD TO COMPONENT U217.  U217 BURNED.  CAU	SE UNKNOWN.  SUBMITTER SUSPECTS MISALIGNED OR MISGUIDED CONTACTS ON BULB CHANGE OR WEAK SPRING CONTACTS.  PRODUCT HISTOR	Y REVIEWED WITH NO COMMON ANOMALIES NOTED.  MFG OF LAMP ASSY HAS BEEN NOTIFIED OF THIS ISOLATED FAILURE AND URGED TO TAK	E REMEDIAL ACTION TO PREVENT RECURRENCE.  REPAIR STATION PZUR517K WILL CONTINUE TO MONITOR TO IDENTIFY TRENDS.			2	L	7	2 	4F				A9NM
1999010800030	19990108	00030	EU  	1999	1	8	99ZZZX22         	1	19981130	G	2520	3410	SEAT            			AIRBUS	320   	A320232     	3930326	EU  										CABIN	CRACKED         	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	403UA					442				THIS IS THE FIRST HEAVY MAINTENANCE VISIT FOR THIS AIRCRAFT (HMV-1).  VIRTUALLY 100 PERCENT OF THE SEAT PANS ON THE RECA	RO MODEL 3410, 720 SERIES PASSENGER SEATS WERE FOUND CRACKED.					2	L	7	2 	4F			RT	A28NM
1999011500716	19990115	00716		1999	1	15	99ZZZX220        	4	19981204	G	3416	6226523208	TRANSPONDER     	COLLINS     		BEECH 	1900  	1900D       	1154162	CE  										E/E BAY	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	01	228YV		1044 		11552	UE228				TRANSPONDER CONTROL HEAD GIVING INCORRECT ALTITUDE TO TRANSPONDER.  THE A2 LINE IS BEING SHORTED TO GROUND BY SOLDER MIG	RATION FROM GROUND.  THIS IS AT CR-8 CATHODE ON THE A5 BOARD.  SUBMITTER STATED THIS IS THE SECOND CONTROL HEAD FOUND WI	TH THIS PROBLEM.				2	L	7	2 	4T			RT	A24CE
1999011500723	19990115	00723	NE  	1999	1	15	99ZZZX227        	2	19980905	G	7250	6530031	NUT             			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					NR 1 ENGINE	LOOSE           	B		A	BAQR	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			EA	03	117LG					7032	LE45381			DURING TAKEOFF, AIRCRAFT'S NR 1 ENGINE EXPERIENCED AN UNCOMMANDED DECELERATION TO IDLE.  THE AIRCRAFT LANDED WITHOUT ANY	 FURTHER INCIDENT.  THE ENGINE WAS REMOVED AND SENT TO CORPORATE JETS, INC.  DURING TEAR-DOWN INSPECTION, TECH FOUND THE	 NUT ON THE P.T. RETENTION HAD LOST ITS TORQUE.  THIS CAUSED THE FLANGE TO CONTACT THE PY ELBOW WHICH IN TURN CAUSED THE	 ENGINE TO DECELERATE TO IDLE.  ALL PARTS INVOLVED IN THIS INCIDENT HAVE BEEN SENT TO ALLIED SIGNAL. THEY ARE CURRENTLY 	INVESTIGATING THIS INCIDENT.  LOCK CUP WAS ALSO FOUND TORN.		1	G	7	2 	3U	3	U		H13EU   	E5NE
1999011500760	19990115	00760	SW  	1999	1	15	99ZZZX228        	1	19981201	G	6330	206033506103	RESTRAINT       			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CHAFED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	36R	38   			LK0428	52203				REPLACED RESTRAINT AND MOUNT WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW
1999011500761	19990115	00761	SW  	1999	1	15	99ZZZX229        	1	19981201	G	6330	206033542003	MOUNT           			BELL  	206   	206L4       	1182110	SW  										TRANSMISSION	CHAFED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	36R	38   				52203				REPLACED RESTRAINT AND MOUNT WITH NEW PARTS.						1	G	7	1 	3U			NC	H2SW
1999010800031	19990108	00031	NM  	1999	1	8	99ZZZX23         	1	19981208	G	2510		SEAT            			UNIVAR	108   	1082        	9230406	NM  										COCKPIT	BROKEN          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	23	381C	2878 				1083381				SEAT BROKE AT BOTH HORIZONTAL LEGS.  MATERIAL .50 INCH OUTSIDE DIAMETER, .035 INCH WALL 4130 STEEL TUBES.  FRACTURES SHO	W EVIDENCE OF CRYSTALLIZATION FROM BENDING STRESSES.  EXAMINATION REVEALED COPILOT'S SEAT PREVIOUSLY REPAIRED SAME LOCAT	ION.  THIS FAILURE OCCURRED DURING LANDING ROLL-OUT RESULTING IN GROUND LOOP DUE TO PILOT FALLING INTO BACK SEAT.  SUBMI	TTER SUGGESTED INSTALLING 4130 TUBE INSERTS AND WELDING.			1	H	7	1 	3O				A767
1999011500763	19990115	00763	SW  	1999	1	15	99ZZZX231        	1	19981207	G	7714	2060702669	INDICATOR       			BELL  	206   	206B        	1181511	SW  										COCKPIT	MALFUNCTIONED   	B			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	90322		1309 		2081D	1736				BIG NEEDLE AND LITTLE NEEDLE DO NOT CORRESPOND ON COCKPIT INDICATOR.						1	G	7	1 	3U				H2SW
1999011500764	19990115	00764	EA  	1999	1	15	99ZZZX232        	2	19981203	G	7414	LW15416	BEARING         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAGNETO	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	61477	792  				0074	L3588636A			BEARING CAGE DEBRIS FOUND IN THE OIL SUCTION SCREEN DURING 100-HOUR INSP.   RT MAGNETO REMOVED AND THE MAG CUSHION DRIVE	 ADAPTER BEARING CAGE WAS FOUND TO HAVE COME APART AND COLLECTED IN THE OIL SUMP.  LT MAG BEARING CAGE WAS FOUND CRACKED	 ALONG THE AREA WHERE IT IS RIVETED TOGETHER.  ENG OIL PUMP FOUND SLIGHTLY DAMAGED.  NO FURTHER ENG DAMAGE NOTED.  THE O	IL SUMP SCREEN PICKED UP MOST OF THE CAGE MATERIAL WITH REMAINING MATERIAL FOUND IN THE SUMP.  ENG OIL FILTER SHOWED NO 	METAL IN IT.  SUBMITTER SUSPECTS PROBLEM LIES WITH THE BEARING CAGE MANUFACTURE.  THE CAGE IS RIVETED TOGETHER BESIDE EA	CH BALL BEARING.  DETECTED STRESS CRACKS IN THE CAGE ADJACENT TO THE RIVET.  RECOMMEND RE-DESIGNING BEARING CAGE ASSY.	1	G	7	1 	3O	3	O	O	4H12    	E286
1999011500765	19990115	00765	GL  	1999	1	15	99ZZZX233        	2	19980626	G	7240	6876772	BEARING         			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	FAILED          	D		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	25	3298G	5242 	1763 			1909	822891			FORCED LANDING AT BRIGANTINE BAY, NJ.  NR 1 BEARING FAILED.  NO CHIP LIGHT.  COMPRESSOR ROTOR DAMAGED.  PARTS OF BEARING	 CAGE WERE LODGED IN OIL PORT.  THIS MAY HAVE STOPPED OIL SUPPLY.  NO SIGN OF OIL IN BEARING AREA OR ON COMPRESSOR ROTOR	.  NO BALL BEARINGS WERE FOUND IN BEARING AREA.				1	G	7	1 	3U	3	U		H2SW    	E4CE
1999011500766	19990115	00766	SW  	1999	1	15	99ZZZX234        	1	19981124	G	3411		LINE            			BELL  	206   	206B        	1181511	SW  										PITOT SYSTEM	BLOCKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	17	862M					4473				FAILURE OF PITOT STATIC SYSTEM.  BLOCKAGE OF RESTRICTOR FITTING.  COMPLETE FAILURE OF STATIC SYSTEM AND LOSS OF MODE C A	LT REPORTING.					1	G	7	1 	3U				H2SW
1999011500767	19990115	00767		1999	1	15	99ZZZX235        	1	19980925	G	6300		O RING          			AMTR  		MINI500     												CLUTCH	PINCHED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	10	248F	5    				402B				FILM OF OIL OBSERVED AROUND INSIDE OF THE SPRAGUE CLUTCH.  A CALL TO  REVOLUTION HELICOPTER CONFIRMED RED COLOR.  INSPEC	TION REVEALED NO REMAINING FLUID AND A PINCHED O-RING.  SEIZURE WAS IMMINENT.  SUBMITTER SUGGESTED POOR QC AT ASSEMBLY A	ND RECOMMENDED ALL CLUTCHES BE INSPECTED FOR LEAKAGE.  NO MEANS PROVIDED TO CHECK LUBRICANT QUANTITY WITHOUT DISASSEMBLY	.						0
1999062500356	19990625	00356	NM  	1999	6	25	99ZZZX2351       	1	19981027	G	3340	61482	BALLAST         	DAYRAY      		BOEING	727   	727231      	1384079	NM  										BS 1183	FAILED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319				6248	20052				DURING C-CHECK, VISUAL INSPECTION OF UPPER LOBE, NOTED THAT BALLAST ABOVE AFT ENTRY DOOR BURNED, STA 1183, BETWEEN S1 AN	D S2R.					2	L	7	3 	4F				A3WE
1999011500768	19990115	00768		1999	1	15	99ZZZX236        	1	19980925	G	8011		COVER           			AMTR  		MINI500     												STARTER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	248F	1    				402B				AFTER APPROXIMATELY 1 HOUR OF ENGINE OPERATION, THE STARTER HOUSING WAS OBSERVED TO BE CRACKED ON EITHER SIDE OF THE STR	ATER MOTOR.  SUBMITTER SUGGESTED STARTER WAS IMPROPERLY MOUNTED, AS DELIVERED IN THE KIT.  THE O-RINGS WERE COMPRESSED T	O THE POINT THERE WAS NO DAMPENING.  FAILURE WAS IMMINENT.  CAREFUL INSPECTION IS REQUIRED.							0
1999011500769	19990115	00769	WP  	1999	1	15	99ZZZX237        	1	19981109	G	5320	269A54239	STRUT           			HUGHES	269   	269C        	4470504	WP  										FUSELAGE	CRACKED         	B	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	2011A	2066 				0016				ONE INCH CRACK LOCATED AT UPPER PART OF DRIVE PULLEY FRAME STRUT ASSEMBLY.  CRACK ORIGINATED AT WELD.						1	G	7	1 	3O				4H12
1999062500387	19990625	00387	CE  	1999	6	25	99ZZZX2382       	1	19981121	G	3231	12810331	ACCUMULATOR     			CESSNA	210   	T210M       	2073451	CE  										MLG DOOR	FAILED          	H	P	A		O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			WP	07	761KC	5284 			2884	21062308				AFTER LANDING, GEAR WAS CYCLED DOWN AND RIGHT AFTER A GREEN LIGHT CAME ON, A LOUD BANG WAS HEARD FOLLOWED BY LOSS OF HYD	RAULIC PRESSURE.  A SAFE LANDING WAS MADE.  DISCOVERED THE MLG DOOR ACCUMULATOR HAD FAILED AT THE SNAP RING.  A HOLE WAS	 PUT IN THE RIGHT SKIN AND A STRINGER WAS CRUSHED.				1	H	7	1 	3O				3A21
1999011500771	19990115	00771	EA  	1999	1	15	99ZZZX239        	2	19981112	G	8550		BEARING         			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					ENGINE	FAILED          	H				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	23	103WP	1091 				S1573	L2504051A			WHILE IN-FLIGHT, PILOT NOTICED SLIGHT VIBRATION COMING FROM THE ENGINE AND A DROP IN OIL PRESSURE STARTING TO OCCUR.  PI	LOT OPTED FOR A PRECAUTIONARY LANDING.  UPON COMPLETION, OIL PRESSURE NOTED TO BE AT 15 PSI WITH A LOUD SQUEAL COMING FR	OM THE ENGINE.  PILOT SHUT DOWN AND SECURED AIRCRAFT FOR TRAILERING BACK TO MAINTENANCE FACILITY.  UPON INVESTIGATION, N	OTED A LARGE AMOUNT OF METAL IN THE SUCTION SCREEN AS WELL AS THE SUMP.  ENGINE REMOVED AND SENT FOR OVERHAUL.			1	G	7	1 	3O	3	O	 	4H12    	1E10
1999010800032	19990108	00032		1999	1	8	99ZZZX24         	4	19981205	G	6122	8210393A	GEAR            	WOODWARD    																PROPELLER GOV	BROKEN          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03			2264 		2700084					AT TEAR DOWN INSPECTION, FOUND IDLER GEAR FLOATING FREE IN GEAR POCKET.  FOUND IDLER STUB BROKEN OFF AND EXTENSION DAMAG	E TO GEAR POCKET.  METAL FROM GEAR POCKET WAS INTRODUCED INTO ENGINE OIL SYSTEM.  IT IS SUSPECTED THAT DAMAGE WAS CAUSED	 BY LACK OF LUBRICATION OR PREVIOUS METAL CONTAMINATION.
1999062500405	19990625	00405	NM  	1999	6	25	99ZZZX2401       	1	19981027	G	3340	61482	BALLAST         			BOEING	727   	727231      	1384079	NM  										BS 1183	FAILED          	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	64319				25673	20052				DURING C-CHECK, VISUAL INSPECTION OF UPPER LOBE, NOTED THAT BALLAST ABOVE AFT ENTRY DOOR BURNED.  STA 1183 BETWEEN S1 AN	D S2R.					2	L	7	3 	4F				A3WE
1999011500773	19990115	00773	SW  	1999	1	15	99ZZZX241        	1	19981222	G	6300	2040111281	UNIVERSAL       			BELL  	204   	UH1H        	1181407	SW  										MAIN ROTOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	53AG					7221588				BEARING HAS BECOME UNSTAKED.  REMOVED AND REPLACED.						1	G	7	1 	4U				EXPA1G71
1999011500774	19990115	00774		1999	1	15	99ZZZX242        	4	19981222	G	3423	C2300L4124B	COMPASS         			HUGHES	369   	369D        	4470706	WP  										COCKPIT	LEAKING         	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	7097J				3694	900801D				COMPASS LEAKS FLUID.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999011500775	19990115	00775	WP  	1999	1	15	99ZZZX243        	1	19981222	G	6420	369D21800501	SWASHPLATE      			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	RATCHETING      	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	1097J					900801D				RATCHETING BEARING.  ROUGH AFTER DRESSING.  REPLACED.						1	G	7	1 	3U				H3WE
1999011500776	19990115	00776	SW  	1999	1	15	99ZZZX244        	1	19981222	G	2435	123032027	STARTER         			BELL  	206   	206B3       	1181506	SW  										STARTER/GEN	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	206BY		1226 		15446	2871				ENGINE STARTER SEALS FAILED PREMATURELY.  REMOVED AND REPLACED.						1	G	7	1 	3U				H2SW
1999011500777	19990115	00777	CE  	1999	1	15	99ZZZX245        	1	19981111	G	2420	70000150	CIRCUIT BREAKER 			BEECH 	200   	B200        	1152922	CE  										COCKPIT	FAILED          	B			DBCR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	72GG					BB1080				NR 1 BUSS CIRCUIT BREAKER TRIPPED, LEFT HAND SIDE.  LOSS OF POWER TO ESSENTIAL BUSS.  NR 1 RIGHT HAND BUSS FEED CIRCUIT 	BREAKER BAD.  REMOVED AND REPLACED NR 1 RIGHT HAND CIRCUIT BREAKER WITH NEW UNIT P/N 700-001-50.					1	L	7	2 	4T				A24CE
1999011500778	19990115	00778	NM  	1999	1	15	99ZZZX246        	1	19981130	G	2120		AIR DISTRIBUTION			DOUG  	MD11  	MD11        	3023602	NM  										CABIN	SMOKE           	H				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			WP	03	105EV					48544				PILOT REPORTED AT LIFT-OFF SMOKE WAS NOTICED FROM THE GALLEY AREA, CAUSED AIR-TURNBACK.  MAINTENANCE RAN ALL THREE ENGIN	ES AT HIGH POWER WITH GALLEY POWER OFF, THEN ON BLEED CHECK.  NO INDICATION OF SMOKE, FOG.  CHECKED GALLEY AREA, NO SMOK	E FOUND.  AIRCRAFT RETURNED TO SERVICE.				2	L	7	3 	4F			RT	A22WE
1999011500779	19990115	00779	CE  	1999	1	15	99ZZZX247        	1	19981223	G	3020		BRACKET         			CESSNA	500   	560CESSNA   	2076750	CE  										ANTI ICE SYSTEM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	09	744R					5600291				DURING INSPECTION, THE TUBE ON ENG INLET WHICH CONNECTS TO THE ANTI-ICE TUBE VALVE ASSY WAS FOUND MAKING A 'RATTLING' NO	ISE WHEN SIDEWAYS LOADS WERE APPLIED.  BORESCOPING REVEALED NO PROBLEM.  DISASSEMBLY OF  INLET FOUND THE 4 BRACKETS WELD	ED TO THE PICCOLO TUBE ASSY AND RIVETED TO THE INSIDE OF INLET FWD BLKHD CRACKED COMPLETELY THROUGH ON BOTH SIDES OF EAC	H BRACKET.  THE ONLY POINT ATTACHING THIS TUBE TO THE INSIDE OF THE INLET WAS THE PLATE WELDED TO THE PICCOLO TUBE WHERE	 IT EXITS AFT AND OUT OF THE INLET L/E.   AT THIS POINT, THE PLATE IS RIVETED TO THE INLET FWD BLKHD.  INVEST REVEALED S	AME CONDITION ON OPPOSITE ENG.  CESSNA HAS BEEN NOTIFIED.  INLET, PN 675525001,  PICCOLO ASSY, PN 65525023.	2	L	7	2 	4F			RT	A22CE
1999011500780	19990115	00780	NE  	1999	1	15	99ZZZX248        	2	19980831	G	7240	9531M61G06	COMBUSTOR       								GE    	CFM56 	CFM56*      	13802	NE  					ENGINE	CRACKED         	B	P		LY2R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	07		18810			AMC12428		857518			CRACKED PORTION OF COMBUSTOR WORE THROUGH FUEL NOZZLE STEM CAUSING LEAKAGE WHICH CAUSED BURN-THROUGH OF COMBUSTION CASE.											4	F			E2GL
1999011500781	19990115	00781	EA  	1999	1	15	99ZZZX249        	1	19981210	G	3250	200813607	SHAFT           	ROTOL       	200813214   	CNDAIR	CL600 	CL6002A12   	1900304	EA  										NLG STEERING	CORRODED        	B			KW3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	125PS	3826 				3058				SHAFT CENTER WAS CORRODED BEYOND USABLE LIMITS.						2	L	7	2 	4F			RT	A21EA
1999010800033	19990108	00033	NE  	1999	1	8	99ZZZX25         	2	19981208	G	8530	116733	CYLINDER        			DOUG  	DC3   	DC3C        	3021457	WP  	PWA   	R1830 	R1830*      	52020	NE  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	17	941AT		310  			4293040				CRACK ACROSS EXHAUST PORT.						2	L	7	2 	4R	4	R		A669    	5E4
1999011500782	19990115	00782	GL  	1999	1	15	99ZZZX250        	2	19980909	G	7230	6898607	BEARING         								ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	DAMAGED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					HAR2727					UPON DISASSEMBLY OF A COMPRESSOR MODULE FOR OVERHAUL, FOUND THE NR 1 BEARING MISSING 2 OF 8 BALLS.  SUBMITTER STATED IT 	IS NOT KNOWN WHEN IT WAS ASSEMBLED WITHOUT ALL PARTS.  REF:  KES W.O. AOD938.										3	U			E4CE
1999011500783	19990115	00783	NM  	1999	1	15	99ZZZX251        	1	19981118	G	5260	MS20470DD8	RIVET           		25W331120501	ISRAEL	1125  	1125        		NM  										CABIN DOOR	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	1125E	2735 				058				FOUND 3 OF 4 RIVET HEADS BROKEN OFF ON MAIN CABIN DOOR LOCKING ROD.  NO CAUSE KNOWN.  INSTALLED 4 NEW RIVETS.						2	L	7	2 	4F			RT	A16NM
1999011500784	19990115	00784	GL  	1999	1	15	99ZZZX252        	2	19981215	G	7230	6898607	BEARING         								ALLSN 	250C  	250C20      	03013	GL  					COMPRESSOR	DAMAGED         	B			YKER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17					HAX405					UPON DISASSEMBLY OF A COMPRESSOR MODULE FOR REPAIR, FOUND THE NR 1 BEARING MISSING 1 OF 8 BALLS.  SUBMITTER STATED IT IS	 NOT KNOWN WHEN IT WAS ASSEMBLED WITHOUT ALL PARTS.  REF:  KES W.O. A01088.										3	U			E4CE
1999011500785	19990115	00785	NM  	1999	1	15	99ZZZX253        	1	19981228	G	3246	BFG101201	WHEEL           	BFGOODRICH  	313061      	BOEING	727   	727200      	138407E	NM  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					680					CRACK DETECTED VISUALLY AND CONFIRMED BY EDDY CURRENT AT THE BOLT BOSS AREA.  NO CRACK PERMITTED THIS AREA.  B.F. GOODRI	CH OVERHAUL MANUAL 32-40-21 REV 3 DATE 4-30-83.  INSPECTION SECTION PARA 2B.					2	L	7	3 	4F			RT	A3WE
1999011500786	19990115	00786	NE  	1999	1	15	99ZZZX254        	2	19981227	G	7200		ENGINE          			BOEING	747   	74745E      	1384947	NM  	GE    	CF6   	CF680C2B7   		NE  					NR 2	FAILED          	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			WP	03	403EV	23852				27141	702969			PILOT OBSERVED ENGINE NR 2 OIL QUANTITY DECREASING DURING CRUISE.  AFTER SOME TIME, OIL QUANTITY DROPPED TO ZERO, AND AF	TER 50 MINUTES, PRESSURE INDICATING IN AMBER BAND 29 PSI.  ENGINE NR 2 SHUT DOWN.  MAINTENANCE REPLACED NR 2 ENGINE AND 	ENGINE RUN-UP CHECK CONDITION NORMAL IAW MM 71-00-00.				2	L	7	4 	4F	4	F	RT	A20WE   	E13NE
1999011500787	19990115	00787	WP  	1999	1	15	99ZZZX255        	1	19981222	G	3246	152059	WHEEL           	BENDIX      	1542511     	DOUG  	DC8   	DC8*        		WP  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					B2771					CRACK DETECTED BY EDDY CURRENT PER SPEC MIL-I-6870, IN THE INBOARD FACE SPOKE AREA.  NO CRACKS PERMITTED THIS AREA.  OHM	 32-40-05 REV 15 DATE 10-15-96.  CHECK SEC C PARA 2B.					2	L	7	4 	4J			F	4A25
1999011500789	19990115	00789		1999	1	15	99ZZZX257        	4	19981213	G	3140	20035012007	MFDU            			DOUG  	MD11  	MD11        	3023602	NM  										COCKPIT	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	03	105EV	19292			C0206	48544				ALERT MESSAGE 'NR 2 AIR MANIFOLD FAIL' DURING IN-FLIGHT AND DIVERTED TO CTS.  PER MEL 32-23-1 RELEASE A/C.  REPLACED MAN	IFOLD FAULT DETENTION CONTROLLER (NFDC) AND GROUND CHECK NORMAL.					2	L	7	3 	4F			RT	A22WE
1999012200058	19990122	00058	GL  	1999	1	22	99ZZZX258        	2	19981222	G	7230		BLADE           		6890550     	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P	4868 	3246 		CAC38571F	611002D				FIRST STAGE BLADES NEED DRESSED OUT.  DRESSED BLADES, RETURNED TO SERVICE.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1999012200059	19990122	00059	WP  	1999	1	22	99ZZZX259        	1	19981207	G	7722	369A45217	INDICATOR       			HUGHES	369   	369D        	4470706	WP  										COCKPIT	MALFUNCTIONED   	B			LS1R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	5027P		2129 		0197	611002D				UNIT REMOVED DUE TO HIGH AND ERRATIC READING.  REMOVED AND REPLACED.						1	G	7	1 	3U				H3WE
1999010800034	19990108	00034	GL  	1999	1	8	99ZZZX26         	3	19981217	G	6114	D5858C406	HUB             			BEECH 	45    	T34A        	1152008	CE  						MCAULY	3A32C	3A32C406    	GL  	PROPELLER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99								922011		HEAVY CORROSION ON FACE AND INBOARD EDGE OF BLADE SOCKET NR 1.  HUB WAS PLACED IN SERVICE IN 1992 OR 1993.  TSN IS UNKNO	WN.					1	L	7	1 	3O				5A3     		5	C	P21EA
1999012200061	19990122	00061	EU  	1999	1	22	99ZZZX261        	1	19980122	G	3250	157440	SERVO           		AIR453965   	HWKSLY	DH125 	DH1253ARA   	423013P	EU  										NLG STEERING	MALFUNCTIONED   	D	L			O				OTHER                   				O			OTHER                     			LD	LANDING        	1			NM	03	55G		2206 		LK0207	NA709				AIRCRAFT HAD NORMAL LANDING UNTIL NOSE GEAR TOUCHED DOWN.  THE AIRCRAFT HAD BEEN TRACKING STRAIGHT DOWN THE RUNWAY UNTIL	 THE NOSE WHEEL TOUCHED DOWN WHEN THE ACFT BEGAN DRIFTING TO THE RIGHT.  THE PILOT ATTEMPTED TO STEER LEFT USING THE BRA	KES AND LATER USING THE STEERING TILLER, BUT FOUND IT TO BE LOCKED UP OR JAMMED.  THEY WERE UNABLE TO KEEP IT FROM GOING	 OFF RUNWAY.  ONCE ACFT DEPARTED RUNWAY AND WENT OVER A TAXIWAY WITH A BUMP, THE TILLER WHEEL BEGAN TO WORK NORMALLY.  A	CFT CAME TO REST APPROX 100 FEET TO THE RIGHT OF THE RUNWAY WHERE THE GROUND WAS FROZEN.  ACFT WAS TOWED TO HANGAR.		2	L	7	2 	4J				A3EU
1999012200062	19990122	00062	CE  	1999	1	22	99ZZZX262        	1	19981221	G	7920	832461120	O RING          			RAYTHN	DH125 	HAWKER800XP 		CE  										NR 2 ENGINE	LEAKING         	B				E				ENGINE SHUTDOWN         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			SW	11	281XP	1618 				258281				AIRCRAFT DEPARTED.  SHORTLY AFTER TAKEOFF, NR 2 ENGINE OIL PRESSURE FELL BELOW 25 PSII.  ENGINE SHUT DOWN.  UPON INVESTI	GATION, FOUND O-RING ON OIL TRANSFER TUBE BETWEEN GEARBOX AND OIL/FUEL HEATER DAMAGED.  REPLACED O-RING, SERVICED ENGINE	 OIL, OPS AND LEAK CHECKED GOOD.  RETURNED TO SERVICE.				2	L	7	2 	4F			RT	A3EU
1999012200063	19990122	00063	CE  	1999	1	22	99ZZZX263        	1	19981222	G	3010	KW15632H	VALVE           			CESSNA	500   	550         	2076604	CE  										RT ENGINE	MALFUNCTIONED   	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	26496				2965	5500607				DURING FLIGHT, THE RT HAND ANTI-ICE APPEARED TO WORK NORMALLY FOR 6 MINUTES, LIGHT FLICKERED FOR 3 MINUTES, THEN REMAINE	D STEADY.  AMMETER FOR BOTH LT AND RT GENERATORS MATCHED.  LIGHT FLICKERED AT LOW AMPERAGE.  TROUBLESHOOTING OF ANTI-ICE	 SYSTEM REVEALED STAT BLEED VALVE WAS INTERMITTENT.  BLEED VALVE REMOVED AND REPLACED WITH A SECOND UNIT.  IN PREPARATIO	N FOR AN OPERATIONAL CHK, ACFT POWER WAS ON.  AT THAT TIME, THE SURFACE ANTI-ICE CIRCUIT BREAKER TRIPPED.  INSPECTION FO	UND STATOR BLEED VALVE WAS SHORTED INTERNALLY.  THIS STATOR BLEED VALVE REMOVED AND REPLACED WITH ANOTHER SERVICEABLE UN	IT.  SYS OPER CHECKED GOOD.	1	L	7	2 	4F				A22CE
1999072300001	19990723	00001	SO  	1999	7	23	99ZZZX2630       	1	19980818	G	3320	BC10047017	LAMP            	BRUCE       		GULSTM	G1159 	GIV         	3980115	SO  										CABIN	BROKEN          	B		A	TA1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	315GA	600  				1315				LAMP POPPED OUT OF FIXTURE.  COULD CAUSE ARCING.  SUBMITTER STATED SEVERAL OF THESE ASSEMBLIES HAVE BEEN REPLACED RECENT	LY FOR THE SAME REASON.  RETAINING CAP BREAKS DUE TO EXCESSIVE SPRING TENSION ON LAMP.					2	L	7	2 	4F			RT	A12EA
1999012200064	19990122	00064	EU  	1999	1	22	99ZZZX264        	1	19980807	G	2701		CONTROL CABLE   		MY2021501   	AMD   	FALC20	FALCON20F5  	2730105	EU  										CNTRL COLUMN LT	DAMAGED         	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	892SB	7085 			66	379				WHILE PERFORMING RECENT REQUIREMENT OF 1,500 HOUR LUBE ON CONTROL COLUMNS, FOUND 3 OUT OF 4 UPPER CABLES, AND 1 OUT OF 2	 LOWER CABLES, WITH BROKEN STRANDS WHERE THEY RUN OVER PULLEYS.  P/N'S: MY2021520810-1, 1 EACH.  MY20215-20820-1, 2 EACH	.  MY20215-20830, 1 EACH.  FROM COMPONENT MM 27-10-01, PAGE 1003-0, THERE IS ALREADY A 3,000 HOUR INSPECTION ON CONTROL 	COLUMNS.			2	L	7	2 	4F			RT	A7EU
1999012200065	19990122	00065	EU  	1999	1	22	99ZZZX265        	1	19980807	G	2701		CONTROL CABLE   		MY20215011  	AMD   	FALC20	FALCON20F5  	2730105	EU  										CNTRL COLUMN RT	DAMAGED         	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	892SB	7085 			65	379				WHILE PERFORMING RECENT REQUIREMENT OF 1,500 HOUR LUBE ON CONTROL COLUMNS, FOUND 3 OUT OF 4 UPPER CABLES, AND 1 OUT OF 2	 LOWER CABLES, WITH BROKEN STRANDS WHERE THEY RUN OVER PULLEYS.  P/N'S: MY2021520810-1, 1 EACH.  MY20215-20820-1, 2 EACH	.  MY20215-20830, 1 EACH.  FROM COMPONENT MM 27-10-01, PAGE 1003-0, THERE IS ALREADY A 3,000 HOUR INSPECTION ON CONTROL 	COLUMNS.			2	L	7	2 	4F			RT	A7EU
1999012200068	19990122	00068	EA  	1999	1	22	99ZZZX268        	1	19981229	G	3250	70263	SERVO VALVE     	ABEX        	71025       	CNDAIR	CL600 	CL6002B16   	1900305	EA  										NLG	FAILED          	B			QRRR	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			EA	13	270RA	713  			576	5337				NOSE WHEEL STEERING FAILS UPON TOUCH-DOWN (RESETTABLE).  FAILURE COULD BE INDUCED BY FREEZING THE TORQUE-MOTOR.  WHEN ST	EERING WAS ARMED, NOSE WHEELS TURNED RIGHT WITHOUT INPUT FROM THE OPERATOR, AND THEN STEERING SYSTEM FAILED (1/2 SECOND 	TIME FRAME).  INSTALLED NEW TORQUE MOTOR.  STEERING OPS NORMAL.				2	L	7	2 	4F			RT	A21EA
1999010800035	19990108	00035	CE  	1999	1	8	99ZZZX27         	1	19981207	G	2400	MS25306222	SWITCH          			CESSNA	210   	P210N       	2073454	CE  										COCKPIT	FAILED          	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	130RC	2179 				P21000822				DURING PRE-FLIGHT, MAIN AVIONICS POWER SWITCH WAS FOUND INOPERATIVE.  TROUBLESHOOTING REVEALED A LOOSE POSITION SWITCH. 	 SWITCH WAS REPLACED.  SUBMITTER STATED CAUSE COULD BE TENSION ON WIRING BUNDLE ATTACHED TO SWITCH.					1	H	7	1 	3O				3A21
1999012200071	19990122	00071	EA  	1999	1	22	99ZZZX270        	2	19981208	G	7414	LW15416	ADAPTER         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAGNETO	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	61431	697  				0064	L3533736A			BEARING CAGE DERIS WAS FOUND IN THE OIL SUCTION SCREEN DURING A 100-HOUR INSPECTION. THE RT MAGNETO WAS REMOVED AND THE 	MAGNETO CUSHION DRIVE ADAPTER BEARING CAGE WAS FOUND TO HAVE COME APART AND COLLECTED IN THE OIL SUMP.  NO FURTHER ENGIN	E DAMAGE NOTED.  ENGINE OIL FILTER SHOWED NO METAL IN IT.  SUBMITTER SUSPECTED THE PROBLEM WAS WITH THE BEARING CAGE MAN	UFACTURE.  THE CAGE IS RIVETED TOGETHER BESIDE EACH BALL BEARING.  RECOMMENDED RE-DESIGNING BEARING CAGE ASSY.  SUBMITTE	R STATED THIS IS FOURTH FAILURE SINCE 11-11-98.		1	G	7	1 	3O	3	O	O	4H12    	E286
1999012200072	19990122	00072	EA  	1999	1	22	99ZZZX271        	2	19981203	G	7414	LW15416	ADAPTER         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAGNETO	FAILED          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	6147L	1533 				0055	L3513736A			PILOT REPORTED AN EXCESSIVE MAGNETO DROP ON THE RT MAGNETO DURING ENGINE RUN-UP.  THE RT MAGNETO WAS REMOVED AND THE MAG	NETO CUSHION DRIVE ADAPTER BEARING CAGE WAS FOUND TO HAVE COME APART.  BEARING CAGE DEBRIS WAS FOUND IN THE OIL SUCTION 	SCREEN.  THE OIL SUMP SCREEN PICKED UP MOST OF THE CAGE MATERIAL WITH THE REMAINING MATERIAL FOUND ON THE BOTTOM OF THE 	SUMP.  THE ENGINE OIL FILTER SHOWED NO METAL IN IT.  SUBMITTER SUSPECTED THE PROBLEM WAS WITH THE BEARING CAGE MANUFACTU	RE.  THE CAGE IS RIVETED TOGETHER BESIDE EACH BALL BEARING.  DETECTED STRESS CRACKS IN THE CAGE ADJACENT TO THE RIVET. R	ECOMMENDED RE-DESIGNING BEARING CAGE ASSY.  SUBMITTER STATED THIS IS 3RD SUCH FAILURE SINCE 11-11-98.	1	G	7	1 	3O	3	O	O	4H12    	E286
1999012200073	19990122	00073	EA  	1999	1	22	99ZZZX272        	2	19980829	G	8520		BEARING         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					ENGINE	FAILED          	H		A		A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			WP	03	6148D	239  				0078	L3594936A			DURING A TRAINING FLIGHT, THE PILOT REPORTED A LOUD RUMBLING SOUND COMING FROM THE ENGINE AND FELT A SEVERE VIBRATION. T	HE ENGINE NEVER QUIT AND LANDED WITH NO DAMAGE TO HELICOPTER.  OIL FILTER ANALYSIS REVEALED SEVERE PARTICULATE MATTER.  	SUSPECTED CONNECTING ROD BEARING FAILURE.  ENGINE TEAR DOWN WILL BE COMPLETED AT LYCOMING FACILITIES.				1	G	7	1 	3O	3	O	O	4H12    	E286
1999072300541	19990723	00541	EA  	1999	7	23	99ZZZX2726       	2	19980914	G	7414		BEARING         								LYC   	O540  	O540E4C5    	41532	EA  					LT/RT MAGNETO	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	23			654  				RL1371340			OPERATORS OF AVCO LYCOMING O-540-E4C5 ENGINES FITTED TO BRITTEN NORMAN ISLANDER AIRCRAFT IN GUYANA HAVE BEEN EXPERIENCIN	G PREMATURE FAILURE OF THE MAGNETO DRIVE GEAR BEARINGS.  THERE HAVE BEEN INSTANCES OF REPORTED HARD STARTING.  ON INVEST	IGATION, THE BEARINGS ARE DISCOVERED DAMAGED.  THE ENGINES ARE THEN REMOVED FROM SERVICE.									3	O			E295
1999012200074	19990122	00074	EA  	1999	1	22	99ZZZX273        	2	19981112	G	7414	LW15416	BEARING         			HUGHES	269   	269C1       	8059504	SW  	LYC   	O360  	HO360C1A    	41514	EA  					MAGNETO	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	03	61426	1094 				0062	L3522636A			THE MAGNETO DRIVE ADAPTER BEARING CAGE FAILED AND WAS DISCOVERED DURING A 100-HOUR INSPECTION.  DEBRIS WAS REMOVED FROM 	THE OIL SUMP.  NO FURTHER DAMAGE WAS NOTED IN THE OIL PUMP OR THE REST OF THE ENGINE.					1	G	7	1 	3O	3	O	O	4H12    	E286
1999012200075	19990122	00075	EA  	1999	1	22	99ZZZX274        	2	19981230	G	7322	HA6	CARBURETOR      	PRECISION   		CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					ENGINE	CONTAMINATED    	B			GSZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19	6161S				DC0318	R18201633				PILOT REPORTED THE ENGINE WAS RUNNING EXCESSIVELY RICH AT ALL SETTINGS EXCEPT IDLE.  PILOT DECIDED THE CARBURETOR SHOULD	 BE REPLACED.  WHEN THE CARBURETOR WAS REMOVED, A ROUND PIECE OF HARD PEPPERMINT CANDY WAS FOUND WEDGED IN VENTURI.  PIL	OT HAD COMPLAINED THAT RODENTS HAD FOUND HIS CANDY STASH ABOUT 3 WEEKS EARLIER AND SCATTERED CANDY ALL OVER THE AIRCRAFT	.			1	H	7	1 	3O	3	O	RT	3A13    	E295
1999012200076	19990122	00076	SO  	1999	1	22	99ZZZX275        	1	19981230	G	3246		WHEEL           	CLEVELAND   		PIPER 	PA38  	PA38112     	7103812	SO  										MLG	CRACKED         	B			GSZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										TIRE BEAD AREA CRACKING ON CLEVELAND MFG WHEEL MODEL 40-77, 4-78, AND 40-87 SERIES USING 162-02800 AND 161-03100 WHEEL H	ALF ASSEMBLIES.  BEAD AREA CRACKING AND TOTAL FAILURE. THREE OCCURRENCES.					1	L	7	1 	3O				A18SO
1999012200077	19990122	00077	SW  	1999	1	22	99ZZZX276        	1	19981230	G	3246		WHEEL           	CLEVELAND   		MTSBSI	MU2   	MU2*        		SW  										NLG	CRACKED         	B			GSZR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	19										TIRE BEAD AREA CRACKING ON CLEVELAND MFG WHEEL MODEL 40-77, 4-78, AND 40-87 SERIES USING 162-02800 AND 161-03100 WHEEL H	ALF ASSEMBLIES.  BEAD AREA CRACKING AND TOTAL FAILURE. THREE OCCURRENCES.					1	H	7	2 	3T				A2PC
1999012200078	19990122	00078	CE  	1999	1	22	99ZZZX277        	1	19981230	G	3246		WHEEL           	CLEVELAND   		MTSBSI	MU2   	MU2B40      		CE  										NLG	CRACKED         	B			GSZR	K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			SW	19										TIRE BEAD AREA CRACKING ON CLEVELAND MFG WHEEL MODEL 40-77, 4-78, AND 40-87 SERIES USING 162-02800 AND 161-03100 WHEEL H	ALF ASSEMBLIES.  BEAD AREA CRACKING AND TOTAL FAILURE. THREE OCCURRENCES.  BEAD FAILURE WHILE TAXIING.					1	H	7	2 	3T				A10SW
1999012200079	19990122	00079	EA  	1999	1	22	99ZZZX278        	2	19981215	G	7313	25244509	FUEL INJECTOR   			PIPER 	PA28  	PA28R201    	7102816	SO  	LYC   	O360  	IO360C1C6   	41514	EA  					ENGINE	MALFUNCTIONED   	B			OG5R	A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			GL	21	803ND	756  			7011806	2837003	L2526051A			ENGINE RAN EXTREMELY RICH IN-FLIGHT.  QUIT ON FLAIR/ROLL-OUT, COULD NOT RESTART.  MAINTENANCE WAS ABLE TO RESTART, BUT A	LSO FOUND MIXTURE EXTREMELY RICH AND WAS UNABLE TO ADJUST TO SPECS.  SUSPECT INTERNAL LEAKAGE.  NO EXTERNAL EVIDENCE.  I	NJECTOR WAS REPLACED, MIXTURE AND IDLES ADJUSTED AND AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	1 	3O	3	O		2A13    	1E10
1999010800036	19990108	00036	CE  	1999	1	8	99ZZZX28         	1	19981203	G	7160	4079449012	VALVE           			CESSNA	210   	P210N       	2073454	CE  										ENGINE	LEAKING         	B			MOGR	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			GL	25	130RC		796  		TKR1120	P2100082				DURING CLIMB THROUGH 14,000 FEET, PILOT REPORTED A 'POP' FOLLOWED BY A REDUCTION OF MANIFOLD PRESSURE TO NORMALLY ASPIRA	TED LEVEL.  TROUBLESHOOTING REVEALED PRESSURE RELIEF VALVE FOR INDUCTION SYSTEM WAS LEAKING.  REPLACED VALVE.					1	H	7	1 	3O				3A21
1999012200081	19990122	00081	GL  	1999	1	22	99ZZZX280        	1	19981216	G	2810	2028110000	FUEL CELL       			DIAMON	DA20  	DA20A1      		GL  										FUSELAGE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	556SS	990  				10127				UPON REMOVAL OF FUEL CELL TO RIG RUDDER CABLES, NOTED THE INTERNAL BAFFLE SPOT WELDS WERE CRACKING THROUGH TO THE TANK O	UTER SKIN.  LEAKS WERE DETECTED AND REPAIRED.  THERE ARE NO PROVISIONS TO INSPECT THESE WELDS WITHOUT TANK REMOVAL.  IF 	THE CONDITION GOES UNDETECTED, FIRE AND/OR DEATH CAN RESULT.  SUBMITTER STATED A MANDATORY INSPECTION SHOULD BE ACCOMPLI	SHED AS SOON AS POSSIBLE AND AT INTERVALS THEREAFTER.			1	L	7	1 	3O			NT	TA4CH
1999073000432	19990730	00432	CE  	1999	7	30	99ZZZX2808       	1	19980827	G	3060	SMR11886	BOOT            	SMR         		CESSNA	441   	441         	2076020	CE  										PROPELLER	DAMAGED         	B			ME4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19		185  			BVA6687					HARTZELL PROPELLER MODEL NR HC-B3TN-5E/T10178B-11, S/N BVA6687 WAS OVERHAULED 8-27-98 WITH NEW FAA-PMA B/E AEROSPACE SMR	 TECHNOLOGIES BOOTS, P/N SMR1188-6 INSTALLED.  BOOTS FAILED AFTER 184.9 TT AND 11 MONTHS SINCE INSTALLATION.  OLD BOOT S	/N'S 0159, 0160 AND 0161 HAVE A CURE DATE OF 2Q98.  BOOTS DETERMINED INOPERATIVE ELEMENT RESISTANCE CHECK.  ALL BOOTS HA	D SHORT OR OPEN CIRCUIT.  NO BURN HOLES NOTED.  NO DEFECT NOTED WITH INSTALLATION OR REMAINING DEICING SYSTEM.  INSPECTI	ON ACCOMPLISHED IAW BE GOODRICH INSTALLATION AND MM ATA 30-60-02.  BF GOODRICH P/N 4E1188-6 BOOTS INSTALLED AND OPS CHEC	K GOOD.	1	L	7	2 	3T			RT	A28CE
1999012200082	19990122	00082	GL  	1999	1	22	99ZZZX281        	1	19981216	G	5720	AN960C616	WASHER          			DIAMON	DA20  	DA20A1      		GL  										WING	WRONG PART      	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	556SS	990  				10127				UPON INSPECTION OF THE WING ATTACH A-BOLT, NOTED THE WASHER LISTED IN THE PARTS MANUAL, AN 960-C616, PAGE I-53-2, IS INC	ORRECT IN SIZE AND WILL ALLOW THE BOLT TO PULL THROUGH THE ATTACH BRACKET.  THE PROPER BOLT, P/N MS 16212-13, WAS OBTAIN	ED THROUGH DIAMOND ACFT AND WAS INSTALLED.  SUBMITTER STATED A MANDATORY INSPECTION IS NEEEDED AS SOON AS POSSIBLE TO EN	SURE ALL ACFT HAVE THE CORRECT PART INSTALLED.			1	L	7	1 	3O			NT	TA4CH
1999012200083	19990122	00083	EU  	1999	1	22	99ZZZX282        	2	19981218	G	7520	922325	BOTTLE          			DIAMON	DA20  	DA20A1      		GL  	ROTAX 	912   	ROTAX912    	55555	EU  					RADIATOR	MELTED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	524SS	994  				10084	4380741			DURING ROUTINE MAINTENANCE, NOTED THE RADIATOR WATER LEVEL WAS EMPTY.  ON INSPECTION, THE OVERFLOW WAS FOUND MELTED AT T	HE LOWER, INBOARD, FORWARD CORNER.  SEVERAL OTHER AIRCRAFT HAVE BEEN INSPECTED AND ALL ARE DEVELOPING THE SAME PROBLEM. 	 REPLACEMENT AND MODIFICATION IS RECOMMENDED.				1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
1999012200084	19990122	00084	CE  	1999	1	22	99ZZZX283        	1	19981214	G	3710	1J71	FILTER          	AIRBORNE    		BEECH 	23    	C23         	1151242	CE  										VACUUM SYSTEM	CONTAMINATED    	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	09	5289M					M2021				MAIN VACUUM FILTER WAS LOCATED UNDER WINDSHIELD FORWARD SEAM.  DUE TO HEAVY RAINFALL AND A LEAKING SEAL BETWEEN WINDSHIE	LD AND BOOT COWL, THE MAIN FILTER BECAME SATURATED WITH WATER.  ON START-UP THE GYROS FILLED WITH WATER.   REPAIRED AND 	REPLACED GYROS.  DRIED OUT SYSTEM, AND REPLACED FILTERS.  MOVED MAIN FILTER UNDER WINDSHIELD AND SEALED FWD WINDSHIELD W	ITH RTV.  SYSTEM TEST OK.			1	L	7	1 	3O				A1CE
1999012200085	19990122	00085	GL  	1999	1	22	99ZZZX284        	1	19981216	G	7910	654493	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  										ENGINE OIL	BROKEN          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	237ND	14   				C0022				OIL FILLER TUBE SUPPORT BRACKET FOUND BROKEN AT 90 DEGREE BEND DURING ACCEPTANCE INSPECTION.  SUBMITTER STATED THIS IS T	HE SECOND ONE FOUND BROKEN DURING AN ACCEPTANCE INSPECTION OF SIMILAR AIRCRAFT.  PART REPLACED AND AIRCRAFT RETURNED TO 	SERVICE.				1	L	7	1 	3O			NT	TA4CH
1999012200086	19990122	00086	GL  	1999	1	22	99ZZZX285        	1	19981215	G	7910	654493	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  										ENGINE OIL	BROKEN          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	236ND	17   				C0036				DURING ACCEPTANCE INSPECTION OF AIRCRAFT, FOUND OIL FILLER TUBE SUPPORT BRACKET BROKEN AT 90 DEGREE BEND.  SUBMITTER STA	TED LEFT UNCORRECTED, THIS COULD ALLOW FILLER TUBE TO BECOME DISLODGED FROM OIL TANK.  CONTINENTAL WAS NOTIFIED.  PART R	EPLACED AND AIRCRAFT RETURNED TO SERVICE.				1	L	7	1 	3O			NT	TA4CH
1999081400024	19990814	00024	EU  	1999	8	14	99ZZZX2857       	1	19981110	G	6220	1051410157	BOLT            			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	SCORED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117MH	484  			ADS1	7112				MAIN BOLT SCORED.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999012200087	19990122	00087	CE  	1999	1	22	99ZZZX286        	1	19981222	G	7810	NH10089710	COUPLING        			CESSNA	340   	340A        	2076405	CE  										RT ENGINE	CRACKED         	B	S		DPOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	200CC	266  				340A0674				DURING A PHASE INSPECTION WHILE C/W AD 75-23-08R5, EXHAUST INSPECTION ON RIGHT ENGINE, DISCOVERED WYE TO WASTEGATE ELBOW	 V-CLAMP (ONE-PIECE COUPLING) CRACKED ALMOST COMPLETELY AROUND CIRCUMFERENCE.  THIS PART WAS CHANGED DURING A RAM CONVER	SION 12/97.  DURING PRESSURE CHECK OF EXHAUST SYSTEM, THE COUPLING DID NOT LEAK.  SUBMITTER STATED DUE TO THE AREA IN QU	ESTION, IT IS ESSENTIAL THAT A THOROUGH INSPECTION OF EXHAUST SYSTEM BE COMPLETED.			1	L	7	2 	3O				3A25
1999081400033	19990814	00033	NE  	1999	8	14	99ZZZX2866       	2	19981218	G	7421	9550166670	IGNITER PLUG    			BOLKMS	BK117 	BK117C1     	5626025	EU  	TMECA 	ARRIEL	ARRIEL1     	60030	NE  					ENGINE	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC					7505				IGNITER PLUG WORN.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U	NC	H13EU   	E19EU
1999012200088	19990122	00088	CE  	1999	1	22	99ZZZX287        	1	19981201	G	7920	701520	LINE            			BEECH 	33    	E33         	1151422	CE  										ENGINE OIL	FAILED          	H	L			A				UNSCHED LANDING         				K	B	P	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	NO WARNING INDICATION     	CL	CLIMB          	1			EA	07	917CE					CD1171				OIL PRESSURE GAUGE LINE FAILED DURING TAKEOFF ROLL.  OBSERVERS ON GROUND SPOTTED A SMOKE TRAIL AND CONTACTED PILOT BY RA	DIO.  FLT RETURNED AND LANDED WITHOUT INCIDENT.  PILOT REPORTED  OIL PRESS GAUGE STILL SHOWED IN THE GREEN DESPITE LINE 	FAILURE AND THERE WAS NO SMOKE IN THE CABIN OR OTHER INDICATION OF FAILURE.  OIL LOSS, 6 PLUS QUARTS LOST IN APPROX 10-1	5 MINUTES.  THE BREAK WAS INSIDE THE COLLAR WHICH THE LINE'S FITTING SCREWS DOWN AGAINST TO MAKE A TIGHT CONNECTION WITH	 THE MATING FITTING ON THE ENG CASE.  COPPER TUBING CRACKED CIRCUMFERENTIALLY RIGHT AT THE FLARE.  DESPITE CRACK, TUBE D	ID NOT FULLY PART FROM FITTING.  SPRAY OF LEAKING OIL HIT MUFFLER LOCATED UNDER ENG OIL PRESS PORT, CAUSED SMOKE TRAIL.	1	L	7	1 	3O				3A15
1999012200089	19990122	00089	SO  	1999	1	22	99ZZZX288        	1	19981029	G	7160	434134	GROMMET         			PIPER 	PA28  	PA28181     	7102807	SO  										AIR BOX	WORN            	B		A	UC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4144K	196  				284315				DURING A 100-HOUR INSPECTION, CARBURETOR AIR BOX GROMMET ON THE CONTROL VALVE SHAFT WAS FOUND COMPLETELY WORN THROUGH AN	D STARTED TO ELONGATE THE HOLE IN THE TOP OF THE CARBURETOR AIR BOX IN WHICH THE GROMMET IS INSTALLED.  FOUND THIS PROBL	EM ON SEVERAL OTHER ACFT IN FLEET OF ARCHER III'S WITH ANYWHERE FROM 50 HOURS ON.  SUBMITTER STATED PIECES FROM THE GROM	MET COULD BE SUCKED INTO THE ENGINE AND POSSIBLY CAUSE AN ENGINE FAILURE.  PIPER HAS BEEN CONTACTED.			1	L	7	1 	3O				2A13
1999012200090	19990122	00090	GL  	1999	1	22	99ZZZX289        	1	19981103	G	5740		FITTING         			AMTR  	WAG   	WAGARO      	05655YX	GL  										RT WING	FAILED          	G		A		O				OTHER                   				D	F		INFLIGHT SEPARATION       	FLT CONT AFFECTED         		NR	NOT REPORTED   	1			GL	21	285BB					BA285				AIRCRAFT SUFFERRED AN IN-FLIGHT BREAK-UP DUE TO SEPARATION OF THE RIGHT WING LOWER STRUT CONNECT FITTING.  WING SEPARATE	D FROM AIRCRAFT.  PRELIMINARY INVESTIGATION REVEALS POSSIBLE FRACTURE OF ATTACH FITTING AT THE WELD TO FUSELAGE.  REF: P	TRS NR GL219901523.				1	H	7	1 	3O			NC	EXPA1H71
1999010800037	19990108	00037	CE  	1999	1	8	99ZZZX29         	1	19981201	G	8120	640877	GASKET          			CESSNA	210   	P210N       	2073454	CE  	CONT  	O520  	TSIO520AF   	17040	SO  					TURBOCHARGER	MISSING         	B			MOGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	130RC					P21000822	245242R			WHILE TROUBLESHOOTING LOW MANIFOLD PRESSURE, THE GASKET BETWEEN THE TURBOCHARGER TURBINE INLET AND EXHAUST SYSTEM WAS FO	UND MISSING CREATING A SERIOUS EXHAUST LEAK.  GASKET WAS INSTALLED PER P210N MM.  THIS PART IS NOT ILLUSTRATED IN THE PA	RTS MANUAL, BUT IS LISTED IN PARTS LISTING.  NOTE:  EXHAUST STACK WAS REPLACED 1-8-98 AT 2,060.1 HOURS.  DEFECT FOUND AT	 2,178.8 HOURS.			1	H	7	1 	3O	3	O		3A21    	E8CE
1999012200091	19990122	00091	EA  	1999	1	22	99ZZZX290        	2	19981201	G	7322	10S135	CARBURETOR      	FACET       		CESSNA	172   	172I        	2072426	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	MALFUNCTIONED   	H				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NE	05	35446				CK817258	17256773				ENGINE RAN ROUGH IN CRUISE.  CARBURETOR HEAT HELPED SOME.  REMOVED PLUGS, FOUND TO BE RUNNING LEAN.  REMOVED CARBURETOR,	 DISASSEMBLED AND FOUND ONE PIECE VENTURI LOOSE IN UPPER CARBURETOR PIECE.  SUBMITTER SUSPECTS AIR BYPASSING VENTURI AND	 CAUSING LEAN MIXTURE WEAR ON VENTURI AND UPPER CARBURETOR PIECE IS CONSIDERABLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1999082100050	19990821	00050	NE  	1999	8	21	99ZZZX2907       	2	19980521	G	7314	79247	SOLENOID        	CHNDLREVANS 	10TDA4      						LYC   	T53   	T5313B      	41549	NE  					FUEL SYSTEM	LEAKING         	G	L	A		O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			NE	03		20209	209  		17299		LE22813B			DURING A FLIGHT TEST BY THE ROYAL AUSTRALIAN AIR FORCE, LEAKAGE WAS NOTED ON THE ENGINE. THE PART AND ITS HOST REGULATOR	 WOULD BE THE SAME AS THAT USED BY COMMERCIAL AIRCRAFT.  THE AUSTRALIAN DEPOT PERFORMING THE INVESTIGATION FOUND THE END	 CAP OF THE SOLENOID WAS DISPLACED ALLOWING FUEL TO LEAK PAST.  SUBMITTER STATED ON-SITE OBSERVATIONS INDICATE THAT SEAL	S WITHIN THE PART HAD DETERIORATED.								4	U			E17EA
1999012200092	19990122	00092	CE  	1999	1	22	99ZZZX291        	1	19981214	G	3233	NAS464P4A29	BOLT            		12810001    	CESSNA	210   	210L        	2073448	CE  										NLG	SHEARED         	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	321BT	3368 				21060127				DURING AN ANNUAL INSPECTION, THE BOLT WAS FOUND SHEARED OFF AT THE END OF THE THREADS.  THIS ACTUATOR HAS 3 OF THESE BOL	TS INSTALLED.  OVER THE YEARS, HAVE FOUND THIS CONDITION 4 OTHER TIMES.  SUBMITTER SUGGESTED REMOVE AND MAGNAFLUX EVERY 	500 HOURS AND/OR AFTER ANY HARD LANDING.				1	H	7	1 	3O				3A21
1999012200093	19990122	00093	SO  	1999	1	22	99ZZZX292        	1	19981201	G	8120	07A19846	BRACKET         			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					RT TURBOCHARGER	CRACKED         	B	P	A	AMYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	788ES	1069 				4636058				DURING A ROUTINE MAINTENANCE CHECK, DISCOVERED THE RIGHT TURBOCHARGER MOUNT CRACKED.  THE CRACK OCCURRED JUST BELOW THE 	UPPER ATTACH STUD BOSS.					1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1999012200094	19990122	00094	SO  	1999	1	22	99ZZZX293        	1	19981201	G	7120	8319702	MOUNT           			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					ENGINE	CRACKED         	B	S		AMYR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	190RW	963  				4622113	L917361A			DURING AN ANNUAL INSPECTION, DISCOVERED A CRACK ON THE ENGINE MOUNT.  THE CRACK IS LOCATED ON THE RIGHT SIDE OF THE AFT 	NOSE GEAR ACTUATOR MOUNT.  THIS IS AN AREA OF HIGH STRESS AS IT SERVES AS BOTH ACTUATOR MOUNT AND NOSE GEAR DRAG BRACE S	UPPORT.				1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1999012200095	19990122	00095	SO  	1999	1	22	99ZZZX294        	1	19981201	G	5510	8422504	FITTING         			PIPER 	PA46  	PA46350P    		SO  										HORIZ STABILIZER	MISMANUFACTURED 	B	S	A	AMYR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	190RW	963  				4622113				BOTH HORIZONTAL STABILIZER REAR ATTACH FITTINGS WERE FOUND TO HAVE UNAIRWORTHY CREVICES (NOT NECESSARILY CRACKS) IN THE 	MIDDLE OF BOTH OF THEIR WELDS.  THE DISCOVERY WAS MADE DURING AN ANNUAL INSPECTION.  DYE PENETRANT CHECKS AND BORESCOPE 	CHECKS WERE INCONCLUSIVE.  THIS WARRANTED REMOVAL OF FITTINGS.  AFTER REMOVAL, CONCLUDED WELDS TO BE UNAIRWORTHY.  AIRCR	AFT DOES HAVE SPOILERS.			1	L	7	1 	3O			RT	A25SO
1999012200096	19990122	00096	SO  	1999	1	22	99ZZZX295        	1	19981201	G	5510	8422505	FITTING         			PIPER 	PA46  	PA46350P    		SO  										HORIZ STABILIZER	MISMANUFACTURED 	B		A	AMYR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CE	05	190RW	963  				4622113				BOTH HORIZONTAL STABILIZER REAR ATTACH FITTINGS WERE FOUND TO HAVE UNAIRWORTHY CREVICES (NOT NECESSARILY CRACKS) IN THE 	MIDDLE OF BOTH OF THEIR WELDS.  THE DISCOVERY WAS MADE DURING AN ANNUAL INSPECTION.  DYE PENETRANT CHECKS AND BORESCOPE 	CHECKS WERE INCONCLUSIVE.  THIS WARRANTED REMOVAL OF FITTINGS.  AFTER REMOVAL, CONCLUDED WELDS TO BE UNAIRWORTHY.  AIRCR	AFT DOES HAVE SPOILERS.			1	L	7	1 	3O			RT	A25SO
1999012200097	19990122	00097	SW  	1999	1	22	99ZZZX296        	1	19981215	G	2820	714761	LINE            			BBAVIA	8     	8GCBC       	1220803	SW  										LT AND RT WING	WORN            	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	655AC	75   				39198				AFTER REMOVING THE WINGS FROM A VERY LOW TIME AIRCRAFT, THE REAR FUEL LINES ENTERING THE FUSELAGE WERE FOUND SEVERELY WO	RN FROM THE MOVEMENT OF THE FLAP MECHANISM.  THE FUEL LINES ARE .3750 INCH OUTSIDE DIAMETER ALUMINUM TUBING, AND THE MOR	E SEVERELY WORN LINE WAS FOUND CUT TO A DEPTH OF .0625 INCH, NEARLY THE ENTIRE WALL THICKNESS.  THE BOLT AND NUT HOLDING	 THE FLAP CABLES WERE WEARING INTO THE FORWARD LINE AS WAS THE PULLEY SEGMENT ON THE FLAP TORQUE TUBE EACH TIME THE FLAP	S WERE EXTENDED OR RETRACTED.		1	H	7	1 	3O				A21CE
1999012200098	19990122	00098	CE  	1999	1	22	99ZZZX297        	1	19981109	G	2750		CONTROL CABLE   			CESSNA	337   	337C        	2075712	CE  										TE FLAP	SEVERED         	A	P	A		L				ABORTED APPROACH        				F			FLT CONT AFFECTED         			AP	APPROACH       	1			GL	23	2655S					3370955				THE LEFT FLAP CONTROL CABLE WAS FOUND BADLY FRAYED AND SEVERED AT THE LEFT INBOARD BELLCRANK.  PHOTOS AT THE SCENE SHOW 	RT FLAPS FULL DOWN AND LOCKED.  LT FLAPS ARE NOT EXTENDED.  A FULL POWER 'GO AROUND' ATTEMPT RESULTED IN A 'NO CONTROL' 	SITUATION CAUSED BY A SPLIT FLAT CONDITION KNOWN AS ASYMMETRICAL FLAP HAZARD.  SUBMITTER STATED THE ANNUAL INSPECTION HA	D BEEN COMPLETED A FEW DAYS PRIOR.  AIRCRAFT WAS DESTROYED.			1	H	7	2 	3O			 	A6CE
1999012200099	19990122	00099	CE  	1999	1	22	99ZZZX298        	1	19981201	G	2510	05135733	COVER           			CESSNA	172   	172R        	2072401	CE  										COCKPIT	LOOSE           	B	L	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	426ER	415  				17280647				THE LT PROTECTIVE COVER CAME LOOSE AND PIVOTED FORWARD, TOWARD THE FIREWALL.  THIS PROTECTIVE COVER IS LOCATED ON THE BO	TTOM OF THE INSTRUMENT PANEL.  THE PILOT PULLED THE PANEL (COVER) BACK TO THE POSITION IT WAS SUPPOSED TO BE IN AND SHOR	TED OUT THE SWITCHES JUST ABOVE IT.  ALL AVIONICS WAS LOST EXCEPT FROM COMM 1 AND GPS.  PROTECTIVE COVER WAS RE-INSTALLE	D AND SECURED TO AIRCRAFT.			1	H	7	1 	3O			NT	3A12
1999012200100	19990122	00100	CE  	1999	1	22	99ZZZX299        	1	19981029	G	2460	MC012	MCU             	LAMAR       		CESSNA	172   	172R        	2072401	CE  										E/E BAY	MALFUNCTIONED   	B			N3XR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	441ER	104  			80115107	17280660				CIRCUIT PROTECTION FOR AVIONICS IS PROVIDED BY TWO 30-AMP AUTOMOTIVE TYPE SPADE FUSES PLUGGED INTO A 'FUSE PANEL'.  FUSE	 PANEL IS HOUSED IN A 'J' BOX CALLED THE 'MASTER CONTROL UNIT'.  PROBLEM IS SPECIFIC TO 'FUSE PANEL' BURNING METAL SPADE	 TERMINALS OF 30-AMP FUSE RENDERING AVIONICS INOPERABLE.  EXACT CAUSE IS NOT KNOWN,  SUBMITTER STATED REPLACING FUSE DOE	S NOT CORRECT PROBLEM.  ON A FLEET OF SIXTY LIKE AIRCRAFT, THIS PROBLEM IS OCCURRING SEVERAL TIMES A WEEK.			1	H	7	1 	3O			NT	3A12
1999010800013	19990108	00013	CE  	1999	1	8	99ZZZX3          	1	19981028	G	3230	12416186	SUPPORT         			CESSNA	210   	P210N       	2073454	CE  										LT AND RT MLG	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	5486W	2578 				P21000696				AIRPLANE HAD NO  GREEN LIGHT INDICATION FOR GEAR DOWN.  FOUND MAIN GEAR DOWNLOCK SUPPORT ASSEMBLY LOOSE.  THE LOOSE BOLT	S ALLOWED THE SHIM TO SHIFT OUT OF POSITION.  THE BOLTS WERE NOT SAFETIED.  SUBMITTER RECOMMENDED OTHER OPERATORS CHECK 	THEIR 210 NEXT TIME ON JACKS (GEAR INTRANSIT POSITION).  NOTE:  P210 OPERATORS ALLOW A CONSIDERABLE AMOUNT OF TIME TO DI	G THROUGH .50 INCH - .75 INCH OF PROSEAL AT PANEL LOCATED AT AFT DOOR POST BULKHEAD.  FACTORY QA COMMENTED BOLTS ARE ALW	AYS PROPERLY TORQUED AT SAFETY WHEEL.  ACFT ALWAYS QA INSPECTED IN FACTORY PER FACTORY SPECS.		1	H	7	1 	3O				3A21
1999010800038	19990108	00038	GL  	1999	1	8	99ZZZX30         	3	19981211	G	6114	C6447C23	HUB             			BEECH 	35    	H35         	1151520	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	6900V					D4955		676355		THE HUB WAS FOUND TO HAVE CORROSION IN THE RETENTION THREADS BEYOND ACCEPTABLE LIMITS.  SUBMITTER STATED THIS MAY HAVE B	EEN PREVENTED IF MAINTAINED ON THE RECOMMENDED TBO'S.					1	L	7	1 	3O				3A15    		5	C	P880
1999012200101	19990122	00101	EA  	1999	1	22	99ZZZX300        	2	19981201	G	7314	CA35318800	PUMP            			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	MISMANUFACTURED 	B			QFYR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NE	03	3437M				672	287890301				FAA-PMA'D PART OUT OF BOX FAILURE.  DEAD SHORT INTERNAL.  PUMP SUPPLIED BY:  PMA PRODUCTS, INC., LIBERTY, NC 27298.						1	L	7	1 	3O	3	O		2A13    	E286
1999012200102	19990122	00102	SO  	1999	1	22	99ZZZX301        	2	19980804	G	8530	652541	NUT             		6546451A    	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					NR 6 CYLINDER	CRACKED         	B			AW4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	9776G	27   				U20603828	564558			DURING INSPECTION OF ENGINE FOR OIL LEAK, THE LOWER FORWARD CYLINDER FLANGE ATTACH NUT (AT THRU-BOLT) WAS FOUND CRACKED 	AND LOOSE ON BOLT.  UNABLE TO DETERMINE CAUSE OF FAILURE.					1	H	7	1 	3O	3	O		A4CE    	E5CE
1999012200103	19990122	00103	CE  	1999	1	22	99ZZZX302        	1	19981211	G	7920	176060D0380F250	LINE            	STRATOFLEX  		CESSNA	421   	421         	2076010	CE  										ENGINE OIL	LEAKING         	H		A		O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			WP	05	789AC					4210012				PILOT REPORTED A SEVERE OIL LEAK ON THE LT ENGINE.  REMOVAL OF ENG COWLINGS REVEALED OIL LEAKING FROM INSIDE OF THE FIRE	 SLEEVE ON THE FORWARD END OF THE TURBOCHARGER OIL SUPPLY HOSE.  INSPECTION OF THE TURBO OIL SUPPLY HOSE REVEALED THE HO	SE WAS ROUTED IMPROPERLY AND CONTACTING THE TURBOCHARGER.  REMOVAL OF THE OIL SUPPLY HOSE REVEALED SEVERE HEAT DAMAGE OF	 THE FIRE SLEEVE AT THE POINT OF CONTACT. REMOVAL OF THE FIRE SLEEVE REVEALED SEVERE HEAT DAMAGE TO THE SUPPLY HOSE AT T	HE POINT OF CONTACT.  UPON FLEXING THE DAMAGED HOSE, HOSE BROKE CLEANLY INTO TWO SEPARATE PIECES.  THE DAMAGED HOSE WAS 	REPLACED AND RE-ROUTED TO ENSURE PROPER CLEARANCE WITH THE TURBOCHARGER.	1	L	7	2 	3O			RT	A7CE
1999082000089	19990820	00089	SW  	1999	8	20	99ZZZX3033       	1	19981023	G	6410	206016201131	BEARING         			BELL  	206   	206L3       	1182108	SW  										T/R BLADE	WORN            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17238	895  			CS3502	51492				BEARING WORN BEYOND LIMITS AT 894.6 HOURS SINCE NEW.  PAINT PEELING.						1	G	7	1 	3U				H2SW
1999082000091	19990820	00091	SW  	1999	8	20	99ZZZX3035       	1	19981029	G	7810	206064300005	STACK           			BELL  	206   	206L3       	1182108	SW  										EXHAUST	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17592	6219 			980547	51535				CRACK NEXT TO WELD ON AFT SIDE.						1	G	7	1 	3U				H2SW
1999082000096	19990820	00096	SW  	1999	8	20	99ZZZX3040       	1	19981026	G	7810	206064300005	STACK           			BELL  	206   	206L3       	1182108	SW  										EXHAUST	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	17237	6514 			980521	51478				EXHAUST STACK CRACKED AT AFT CENTER WELD.						1	G	7	1 	3U				H2SW
1999082000097	19990820	00097	SW  	1999	8	20	99ZZZX3041       	1	19980817	G	6320	206040032001	BEARING         			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2146F	844  			MB382	4073				OUTER RACE OF DUPLEX BEARING BREAKING DOWN.						1	G	7	1 	3U				H2SW
1999012200106	19990122	00106	SO  	1999	1	22	99ZZZX305        	2	19981223	G	8520	6419311075	BOLTS           								CONT  	O470  	O470U       	17026	SO  					CRANKCASE	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17		450  					286901R			UPON DISASSEMBLY OF C/CASE FOR PROPELLER STRIKE INSPECTION, MOST OF THE THRU-BOLT NUTS SEEMED TO BE OVERTORQUED.  MAJOR 	EFFORT WAS NEEDED TO BREAK THEM LOOSE AND SEVERAL FELT THEY WERE TWISTING AND THEN BROKE LOOSE WITH A LOUD CRACK.  SEVER	AL OF THEM, WHEN ROLLED ON A FLAT PLATE, WOBBLED LIKE THEY WERE BENT.  CORROSION ON THE THREADS WAS NOT A FACTOR.  TORQU	E LIMITS IN SB 96-7 SHOULD BE USED.  REPLACED ALL THRU-BOLTS.								3	O			E273
1999012200107	19990122	00107	SO  	1999	1	22	99ZZZX306        	2	19981223	G	8520	6309431050	BOLTS           								CONT  	O470  	O470U       	17026	SO  					CRANKCASE	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17		450  					286901R			UPON DISASSEMBLY OF C/CASE FOR PROPELLER STRIKE INSPECTION, MOST OF THE THRU-BOLT NUTS SEEMED TO BE OVERTORQUED.  MAJOR 	EFFORT WAS NEEDED TO BREAK THEM LOOSE AND SEVERAL FELT THEY WERE TWISTING AND THEN BROKE LOOSE WITH A LOUD CRACK.  SEVER	AL OF THEM, WHEN ROLLED ON A FLAT PLATE, WOBBLED LIKE THEY WERE BENT.  CORROSION ON THE THREADS WAS NOT A FACTOR.  TORQU	E LIMITS IN SB 96-7 SHOULD BE USED.  REPLACED ALL THRU-BOLTS.								3	O			E273
1999012200108	19990122	00108	SO  	1999	1	22	99ZZZX307        	2	19981223	G	8520	630943888	BOLTS           								CONT  	O470  	O470U       	17026	SO  					CRANKCASE	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	17		450  					286901R			UPON DISASSEMBLY OF C/CASE FOR PROPELLER STRIKE INSPECTION, MOST OF THE THRU-BOLT NUTS SEEMED TO BE OVERTORQUED.  MAJOR 	EFFORT WAS NEEDED TO BREAK THEM LOOSE AND SEVERAL FELT THEY WERE TWISTING AND THEN BROKE LOOSE WITH A LOUD CRACK.  SEVER	AL OF THEM, WHEN ROLLED ON A FLAT PLATE, WOBBLED LIKE THEY WERE BENT.  CORROSION ON THE THREADS WAS NOT A FACTOR.  TORQU	E LIMITS IN SB 96-7 SHOULD BE USED.  REPLACED ALL THRU-BOLTS.								3	O			E273
1999012200109	19990122	00109		1999	1	22	99ZZZX308        	4	19981028	G	3457	KLN89B	INDICATOR       	KING        		CESSNA	172   	172R        	2072401	CE  										GPS	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	101FV				6030	17280551				A DIODE INSIDE THE GPS HAD SHORTED OUT, BUT DUE TO THE MOUNTING TECHNIQUE OF THE BREAKER PANEL THE BREAKER DID NOT TRIP.	  THUS, THE GPS STILL HAD POWER, CONTINUING TO BURN THE DIODE.  THIS CAUSED SMOKE IN COCKPIT ALONG WITH THE ACCOMPANYING	 SMOKE SMELL.				1	H	7	1 	3O			NT	3A12
1999010800039	19990108	00039	GL  	1999	1	8	99ZZZX31         	3	19981211	G	6111	584B0	BLADE           		K84250YS    	BEECH 	35    	H35         	1151520	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	6900V					D4955		676355		THE BLADE WAS FOUND TO HAVE CORROSION BELOW THE PITCH LINE IN THE THREADS.  SUBMITTER STATED THIS MAY HAVE BEEN PREVENTE	D IF THE RECOMMENED TBO'S WERE FOLLOWED.					1	L	7	1 	3O				3A15    		5	C	P880
1999012200112	19990122	00112	GL  	1999	1	22	99ZZZX311        	1	19981215	G	2434	2224111000	BRACKET         			DIAMON	DA20  	DA20C1      	2990001	GL  										ALTERNATOR	BROKEN          	B			OG5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	21	236ND	17   				C0036				DURING ACCEPTANCE INSPECTION, ALTERNATOR BRACKET, P/N 22-2411-10-00, WAS FOUND BROKEN OFF AT THE TOP ALTERNATOR MOUNTING	 HOLE UNDERNEATH WELD.  LACK OF PENETRATION DURING WELDING MAY HAVE BEEN THE CAUSE.  PART REPLACED WITH NEW PART.  AIRCR	AFT RETURNED TO SERVICE.  MANUFACTURER NOTIFIED.				1	L	7	1 	3O			NT	TA4CH
1999082700866	19990827	00866	SW  	1999	8	27	99ZZZX3110       	1	19981122	G	2810	F391SMP	FUEL DRAIN      		220000161   	MOONEY	M20   	M20E        	5870212	SW  										LT WING	MISINSTALLED    	H	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	23	79340	200  				550				RUNNING FUEL LEAK AFER REPLACEMENT OF O-RING ON DRAIN VALVE.  ORIGINAL LEAKAGE WAS MINOR FROM AROUND ELONGATED RIVET HOL	E ON RETAINING NUT INSTALLATION.  HOSE FOR DRAIN VALVE WAS .50 INCH INSTEAD OF .4375 INCH AND NUT WAS OFFSET FROM HOLE B	Y .1250 INCH DUE TO MISALIGNMENT OF HOLE AND NUT.  SUBMITTER STATED THE INSTRUCTIONS OF MOONEY SB M20-188 WERE NOT ENETR	ED IN LOG BOOK.			1	L	7	1 	3O				2A3
1999012200321	19990122	00321	NM  	1999	1	22	99ZZZX312        	1	19981215	G	5315		FLOORBEAM       			BOEING	727   	727259      	138408J	NM  										BS 344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, COROSION WAS NOTED ON UPPER CHORD OF FLOORBEAM AT FS 344, LBL 60 - RBL 24.						2	L	7	3 	4F				A3WE
1999012200322	19990122	00322	NM  	1999	1	22	99ZZZX313        	1	19981124	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 1030-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 1030 - FS 1070, RBL 24.						2	L	7	3 	4F				A3WE
1999012200323	19990122	00323	NM  	1999	1	22	99ZZZX314        	1	19981124	G	5315		FLOORBEAM       			BOEING	727   	727259      	138408J	NM  										BS 1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON UPPER CAP OF FLOORBEAM FS 1050, LBL 5 - RBL 33.						2	L	7	3 	4F				A3WE
1999012200324	19990122	00324	NM  	1999	1	22	99ZZZX315        	1	19981215	G	5320		ANGLE           			BOEING	727   	727259      	138408J	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, COROSION WAS NOTED AT STA 1166 ON BLOCK H LOWER ATTACH ANGLE.						2	L	7	3 	4F				A3WE
1999012200325	19990122	00325	NM  	1999	1	22	99ZZZX316        	1	19981215	G	5320		WEB             			BOEING	727   	727259      	138408J	NM  										COCKPIT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON COCKPIT FLOOR WEB IN NUMEROUS AREAS.						2	L	7	3 	4F				A3WE
1999012200326	19990122	00326	NM  	1999	1	22	99ZZZX317        	1	19981124	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 380-480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 380 - FS 480, RBL 24.						2	L	7	3 	4F				A3WE
1999012200327	19990122	00327	NM  	1999	1	22	99ZZZX318        	1	19981215	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 1030-1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 1030 - FS 1070, RBL 44.						2	L	7	3 	4F				A3WE
1999012200328	19990122	00328	NM  	1999	1	22	99ZZZX319        	1	19981124	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 380-400	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 380 - FS 400, RBL 44.						2	L	7	3 	4F				A3WE
1999010800040	19990108	00040	GL  	1999	1	8	99ZZZX32         	3	19981211	G	6111	584B0	BLADE           			BEECH 	35    	H35         	1151520	CE  						MCAULY	2A36C	2A36C23     	GL  	PROPELLER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	6900V				C49319YS	D4955		676355		THE BLADE WAS FOUND TO HAVE CORROSION BELOW THE PITCH LINES IN THE THREADS.  SUBMITTER STATED THIS MAY HAVE BEEN PREVENT	ED IF THE RECOMMENDED TBO'S WERE FOLLOWED.					1	L	7	1 	3O				3A15    		5	C	P880
1999012200329	19990122	00329	NM  	1999	1	22	99ZZZX320        	1	19981124	G	3010		ANGLE           			BOEING	727   	727259      	138408J	NM  										ANTI ICE DUCT	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION NOTED ON RT WING ANTI-ICE DUCT IN LEADING EDGE AREA FSS 545 (DUCT SUPPORT ANGLES).						2	L	7	3 	4F				A3WE
1999012200330	19990122	00330	NM  	1999	1	22	99ZZZX321        	1	19981124	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1050-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON STR 27R, FS 1050 - FS 1130.						2	L	7	3 	4F				A3WE
1999090300770	19990903	00770	SW  	1999	9	3	99ZZZX3218       	1	19981228	G	6220	430010408101	BEARING         			BELL  	430   	430         	1182150	SW  										M/R LINK	WORN            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	338  			RE47	49037				MAIN ROTOR LINK HAS WORN BEARINGS.						1	G	7	2 	3U			RT	H9SW
1999090300771	19990903	00771	SW  	1999	9	3	99ZZZX3219       	1	19981228	G	6230	430010409105	BEARING         			BELL  	430   	430         	1182150	SW  										IDLER ASSEMBLY	WORD            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	338  			RE62	49037				IDLER ASSY HAS WORN BEARING.						1	G	7	2 	3U			RT	H9SW
1999012200331	19990122	00331	NM  	1999	1	22	99ZZZX322        	1	19981124	G	5320	65561841	FITTING         			BOEING	727   	727259      	138408J	NM  										BS 1010-1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON STR 27R STRINGER TEE FITTING FS 1010 - FS 1050.						2	L	7	3 	4F				A3WE
1999090300778	19990903	00778	SW  	1999	9	3	99ZZZX3226       	1	19981031	G	3340	01077050100	LIGHT           			BELL  	430   	430         	1182150	SW  										STROBE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	113  				49037				VIBRATION CAUSED BULB TO BREAK.						1	G	7	2 	3U			RT	H9SW
1999090300779	19990903	00779	SW  	1999	9	3	99ZZZX3227       	1	19981001	G	3340	01077050100	LIGHT           			BELL  	430   	430         	1182150	SW  										STROBE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	80   				49037				VIBRATION CAUSED BULB TO BREAK.						1	G	7	2 	3U			RT	H9SW
1999090300780	19990903	00780	SW  	1999	9	3	99ZZZX3228       	1	19981009	G	6710	PM212302	ICS SWITCH      			BELL  	430   	430         	1182150	SW  										CYCLIC STICK	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	110  				49037				ICS BUTTON HARD TO ACTUATE.  TRANSMISSION INTERMITENT.						1	G	7	2 	3U			RT	H9SW
1999090300781	19990903	00781	SW  	1999	9	3	99ZZZX3229       	1	19980820	G	3212	22036119102	COVER           			BELL  	430   	430         	1182150	SW  										FLOAT	TORN            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				DURING INSPECTION FOUND RIGHT FORWARD FLOAT COVER TORN DUE TO DEFECTIVE FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999012200332	19990122	00332	NM  	1999	1	22	99ZZZX323        	1	19981215	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 950-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK RT 24.75 FS 950 - FS 1030.						2	L	7	3 	4F				A3WE
1999090300782	19990903	00782	SW  	1999	9	3	99ZZZX3230       	1	19980820	G	3212	206373901105	VALVE           			BELL  	430   	430         	1182150	SW  										FLOAT	DAMAGED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   			217	49037				VALVE WAS ELECTRICALLY DISCONNECTED AND FLOATS INFLATED.  INSPECTION REVEALED FLOAT VALVE COULD NOT BE SAFETIED TO PREVE	NT MANUAL OPERATION.					1	G	7	2 	3U			RT	H9SW
1999090300783	19990903	00783	SW  	1999	9	3	99ZZZX3231       	1	19980820	G	3212	222036050104	FLOAT BAG       			BELL  	430   	430         	1182150	SW  										RT FLOAT	DAMAGED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOAT BAG DAMAGED DURING FLOAT INFLATION DUE TO DEFECTIVE FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999090300784	19990903	00784	SW  	1999	9	3	99ZZZX3232       	1	19980820	G	3212	222036050403	FLOAT BAG       			BELL  	430   	430         	1182150	SW  										LT FLOAT	DAMAGED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOAT BAG DAMAGED DURING FLOAT INFLATION DUE TO DEFECTIVE FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999090300785	19990903	00785	SW  	1999	9	3	99ZZZX3233       	1	19980820	G	7120	230031619101	BUSHING         			BELL  	430   	430         	1182150	SW  										RT MOUNT	MISSING         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				BUSHING (PN 20-057-6-30D) NOT INSTALLED.  REPLACED PER BELL HELICOPTER.						1	G	7	2 	3U			RT	H9SW
1999090300786	19990903	00786	SW  	1999	9	3	99ZZZX3234       	1	19980820	G	3212	222031979103	FLOAT BAG       			BELL  	430   	430         	1182150	SW  										LT FLOAT	DAMAGED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOAT BAG DAMAGED DURING FLOAT INFLATION DUE TO DEFECTIVE FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999090300787	19990903	00787	SW  	1999	9	3	99ZZZX3235       	1	19981016	G	6310	60002	TEMP STRIP      			BELL  	430   	430         	1182150	SW  										INPUT SHAFT	MISSING         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	141  				49037				FOUND TEMP STRIP MISSING FROM MDS AT 150-HOUR INSPECTION.						1	G	7	2 	3U			RT	H9SW
1999090300788	19990903	00788	SW  	1999	9	3	99ZZZX3236       	1	19981016	G	6310	60001	TEMP STRIP      			BELL  	430   	430         	1182150	SW  										INPUT SHAFT	MISSING         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	141  				49037				TEMP STRIP FOUND MISSING FROM MDS AT 150 HOUR INSPECTION.						1	G	7	2 	3U			RT	H9SW
1999090300789	19990903	00789	SW  	1999	9	3	99ZZZX3237       	1	19980820	G	3212	222031879104	FLOAT BAG       			BELL  	430   	430         	1182150	SW  										RT FLOAT	DAMAGED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOAT BAG DAMAGED DURING FLOAT INFLATION DUE TO DEFECTIVE FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999090300790	19990903	00790	SW  	1999	9	3	99ZZZX3238       	1	19980820	G	7120	230031620101	BUSHING         			BELL  	430   	430         	1182150	SW  										LT MOUNT	MISSING         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				BUSHING (20-057-6-301) NOT INSTALLED.  REPLACED PER BELL HELICOPTER.						1	G	7	2 	3U			RT	H9SW
1999090300791	19990903	00791	SW  	1999	9	3	99ZZZX3239       	1	19980820	G	6330	20057630D	BUSHING         			BELL  	430   	430         	1182150	SW  										ISOLATION MOUNT	MISSING         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOATING BUSHINGS 20-057-6-30D FOUND MISSING FROM ISOLATION MOUNT FORWARD MOUNT 430-010-211-101 TO MOUNT 230-010-319-101	 AND 230-010-620-101.					1	G	7	2 	3U			RT	H9SW
1999012200333	19990122	00333	NM  	1999	1	22	99ZZZX324        	1	19981124	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 970-1090	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 970 - FS 1090, LBL 24.						2	L	7	3 	4F				A3WE
1999090300792	19990903	00792	SW  	1999	9	3	99ZZZX3240       	1	19980820	G	3212	70055H000D130	LINE            			BELL  	430   	430         	1182150	SW  										FLOAT	KINKED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOAT LINE ON RIGHT REAR FLOAT FOUND KINKED WHEN FLOATS INFLATED DUE TO DEFECTIVE FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999090300793	19990903	00793	SW  	1999	9	3	99ZZZX3241       	1	19980820	G	3212	70055H000D130	LINE            			BELL  	430   	430         	1182150	SW  										FLOAT	KINKED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				FLOAT LINER ON LEFT FLOAT FOUND KINKED WHEN FLOATS INFLATED DUE TO DEFECTIVE FLOAT VALVES.						1	G	7	2 	3U			RT	H9SW
1999090300794	19990903	00794	SW  	1999	9	3	99ZZZX3242       	1	19980820	G	3212	222336101129	FLOAT BAG       		0128        	BELL  	430   	430         	1182150	SW  										FLOAT	TORN            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				LEFT REAR FLOAT BAG TORN WHEN FLOATS INFLATED DUE TO MALFUNCTIONING FLOAT VALVE.						1	G	7	2 	3U			RT	H9SW
1999090300795	19990903	00795	SW  	1999	9	3	99ZZZX3243       	1	19980829	G	6330	430010211101	ISOLATION MOUNT 			BELL  	430   	430         	1182150	SW  										TRANSMISSION	CHAFED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   			LK0008	49037				TRANSMISSION  MOUNT 230-031-619-101 CONTACTING AIRFRAME.  REPLACED ISOLATION MOUNT 430-010-211-101 WITH 430-010-211-105 	PER BELL HELICOPTER.					1	G	7	2 	3U			RT	H9SW
1999090300796	19990903	00796	SW  	1999	9	3	99ZZZX3244       	1	19980829	G	6330	430010211101	ISOLATION MOUNT 			BELL  	430   	430         	1182150	SW  										TRANSMISSION	CHAFED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   			LK0003	49037				TRANSMISSION MOUNT 230-031-620-101 CONTACTING AIRFRAME.  REPLACED ISOLATION MOUNT 430-010-211-101 WITH 430-010-211-105 P	ER BELL HELICOPTER.					1	G	7	2 	3U			RT	H9SW
1999012200334	19990122	00334	NM  	1999	1	22	99ZZZX325        	1	19981215	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON STR 30, STA 1166.						2	L	7	3 	4F				A3WE
1999090300807	19990903	00807	SW  	1999	9	3	99ZZZX3255       	1	19981030	G	2420	222375060115	VOLT REGULATOR  		97024       	BELL  	430   	430         	1182150	SW  										GENERATOR	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	184  				49037				GENERATOR WILL NOT COME ON LINE.						1	G	7	2 	3U			RT	H9SW
1999012200335	19990122	00335	NM  	1999	1	22	99ZZZX326        	1	19981215	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 328-480	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 328 - FS 480, LBL 24.						2	L	7	3 	4F				A3WE
1999090300812	19990903	00812		1999	9	3	99ZZZX3260       	4	19981030	G	3425	430375002105	EFIS TUBE       			BELL  	430   	430         	1182150	SW  										COCKPIT	MALFUNCTIONED   	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	184  			98020164	49037				THE LOWER EFIS TUBE TOOK APPROXIMATELY ONE HOUR TO COME ON-LINE AND THEN HAD HORIZONTAL LINES ACROSS THE SCREEN.  PILOT 	REPORTED THAT ON 2 OR 3 OTHER OCCASIONS.  THE TUBE HAD BEEN SLOW TO COME ON-LINE.					1	G	7	2 	3U			RT	H9SW
1999012200336	19990122	00336	NM  	1999	1	22	99ZZZX327        	1	19981215	G	5315		FLOORBEAM       			BOEING	727   	727259      	138408J	NM  										BS 1213	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON FLOORBEAM ASSY UPPER CHORD STA 1213 (RT).						2	L	7	3 	4F				A3WE
1999090300835	19990903	00835		1999	9	3	99ZZZX3272       	4	19981202	G	2210	60002600	GYRO            			BELL  	430   	430         	1182150	SW  										COCKPIT	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	267  			3246	49037				NR 2 AP CYCLED FROM 'FAILED' TO 'ON'.						1	G	7	2 	3U			RT	H9SW
1999012200337	19990122	00337	NM  	1999	1	22	99ZZZX328        	1	19981215	G	5315		FLOORBEAM       			BOEING	727   	727259      	138408J	NM  										BS 440	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON UPPER CHORD OF FLOORBEAM FS 440, LBL 24 - RBL 24.						2	L	7	3 	4F				A3WE
1999012200338	19990122	00338	NM  	1999	1	22	99ZZZX329        	1	19981215	G	5315		FLOORBEAM       			BOEING	727   	727259      	138408J	NM  										BS 1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON FLOORBEAM FS 1030 (BL ZERO - LBL 10).						2	L	7	3 	4F				A3WE
1999010800041	19990108	00041		1999	1	8	99ZZZX33         	1	19980212	G	3230		PIN             																	NLG	MISMANUFACTURED 	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99										UPON RECEIPT OF A FACTORY NEW NOSE GEAR ACTUATOR BEARING HOUSING WHICH IS MODIFIED FOR C/W SB 95-20 DOWNLOCK PIN  REPLAC	EMENT.  AFTER INSTALLING KIT SK210-155 PER SB 95-20, DISCOVERED THE DOWNLOCK PINS DID NOT PROTRUDE .325 INCH PLUS OR MIN	US .005 INCH FOR PROPER ALIGNMENT OF THE DOWNLOCK HOOKS.  INVESTIGATION BY CESSNA CONFIRMED IMPROPER ALIGNMENT AND DRILL	ING AT MFG.  BELIEVE AN EMERGENCY AD SHOULD BE ISSUED REQUIRING DOWNLOCK PIN MEASUREMENT FOR ALL NEW HOUSINGS OR NOSE GE	AR ACTUATORS THAT ARE IN SERVICE.
1999012200339	19990122	00339	NM  	1999	1	22	99ZZZX330        	1	19981215	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1010-1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON STR 28R, STA 1010 - STA 1050.						2	L	7	3 	4F				A3WE
1999091000028	19990910	00028		1999	9	10	99ZZZX3300       	1	19980903	G	6310	222044006109	SHAFT ASSY      																	TRANSMISSION	CORRODED        	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					A414					NEW PART DISASSEMBLED, FOUND CORRODED AT THE END OF SHAFT.  GEAR CORRODED UNDER PRIMER AND MISSING ONE CORK.
1999012200340	19990122	00340	NM  	1999	1	22	99ZZZX331        	1	19981215	G	5313		STRINGER        			BOEING	727   	727259      	138408J	NM  										BS 1010-1050	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON STR 28R, STA 1010 - STA 1050.						2	L	7	3 	4F				A3WE
1999012200341	19990122	00341	NM  	1999	1	22	99ZZZX332        	1	19981215	G	5320		WEB             			BOEING	727   	727259      	138408J	NM  										BS 1166	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON WEB STA 1166 BETWEEN STR 28R AND STR 29R.						2	L	7	3 	4F				A3WE
1999012200342	19990122	00342	NM  	1999	1	22	99ZZZX333        	1	19981124	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 1090-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 1090 - FS 1130, LBL 24.						2	L	7	3 	4F				A3WE
1999012200343	19990122	00343	NM  	1999	1	22	99ZZZX334        	1	19981215	G	5311		FRAME           			BOEING	727   	727259      	138408J	NM  										BS 1148	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON FRAME STA 1148, STR 28L - STR 28R.						2	L	7	3 	4F				A3WE
1999012200344	19990122	00344	NM  	1999	1	22	99ZZZX335        	1	19981215	G	5347		SEAT TRACK      			BOEING	727   	727259      	138408J	NM  										BS 950-1030	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK FS 950 - FS 1030, RT 45.5.						2	L	7	3 	4F				A3WE
1999091000154	19990910	00154	EU  	1999	9	10	99ZZZX3356       	1	19981007	G	6220	10513143	ROD END         			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	523  				7103				BEARING WORN.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999091000155	19990910	00155	EU  	1999	9	10	99ZZZX3357       	1	19981007	G	6220	10513144	ROD END         			BOLKMS	117   	BK117A3     	5626015	EU  										MAIN ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	523  				7103				BEARING WORN ON ROD END.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999091000159	19990910	00159	SW  	1999	9	10	99ZZZX3361       	1	19981215	G	6230	403375001105	BEARING         			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	228  			98030069	49037				MAST BEARING CHIP LIGHT WILL NOT EXTINGUISH.  REPLACED PER INSTRUCTIONS FROM BELL HELICOPTER.						1	G	7	2 	3U			RT	H9SW
1999091000160	19990910	00160	SW  	1999	9	10	99ZZZX3362       	1	19980924	G	6300	222044006109A	SHAFT           			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	DAMAGED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	604  			A317	49037				INPUT DRIVE SHAFT INSTALLED ON AIRCRAFT.  AIRCRAFT FLOWN 3.3 HOURS, TEMP PLATES CAME OFF.						1	G	7	2 	3U			RT	H9SW
1999091000161	19990910	00161	SW  	1999	9	10	99ZZZX3363       	1	19981107	G	6230	430375010103	BEARING         			BELL  	430   	430         	1182150	SW  										MAIN ROTOR	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	215  			143	49037				MAST CHIP (TRANSMISSION) LIGHT WOULD NOT EXTINGUISH.  REPLACED CDPU.						1	G	7	2 	3U			RT	H9SW
1999091000162	19990910	00162	SW  	1999	9	10	99ZZZX3364       	1	19980820	G	5320	222031663103	SHIELD          			BELL  	430   	430         	1182150	SW  										ENGINE BAY	BROKEN          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	30   				49037				SHIELD BROKEN AND REPLACED WHILE REPLACING RIGHT MOUNT 230-031619-101						1	G	7	2 	3U			RT	H9SW
1999091000166	19990910	00166	SW  	1999	9	10	99ZZZX3368       	1	19981223	G	7120	430310200107	MOUNT           			BELL  	430   	430         	1182150	SW  										ENGINE	CONTAMINATED    	B			AC2R	O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	03	430CH	324  			LK0106	49037				FLUID LEVEL LOW, DISCOLORED AND SEEMS CONTAMINATED.  AIRCRAFT HAS VIBRATION IN RIGHT HAND TURN.						1	G	7	2 	3U			RT	H9SW
1999012200572	19990122	00572		1999	1	22	99ZZZX337        	2	19980808	G	7200		ENGINE          			AMTR  		RV6         			LYC   		O360A1A     							NOSE	MISMANUFACTURED 	G				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			SO	11	245DF	73   				23315	L3519936A			THIS ENGINE WAS INSTALLED NEW ON A HOMEBUILT KIT VAN RV-6 AIRCRAFT.  DUIRNG CRUISE FLIGHT, THE PROPELLER BECAME LOOSE CA	USING A VIBRATION.  THE FRONT CRANKSHAFT COMPRESSION PLUG OPENED AND OIL WAS ALLOWED TO FLOW OUT AROUND THE BACK OF THE 	PROPELLER.  SUBMITTER STATED TEXTRON LYCOMING SI 1435 WAS NOT C/W WHICH WOULD HAVE ALLOWED OIL TO RETURN TO THE SUMP.							0
1999091000168	19990910	00168	SW  	1999	9	10	99ZZZX3370       	1	19981228	G	6500	430010450101	BUSHING         			BELL  	430   	430         	1182150	SW  										T/R DRIVE	WORN            	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	338  				49037				BUSHINGS ARE WORN.  REPLACED 2 EACH.						1	G	7	2 	3U			RT	H9SW
1999091000170	19990910	00170	SW  	1999	9	10	99ZZZX3372       	1	19981016	G	7110	50008RFS	RECEPTICAL      			BELL  	430   	430         	1182150	SW  										COWL	CRACKED         	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	141  				49037				RECEPTICAL FOUND CRACKED ON FORWARD COWLING.						1	G	7	2 	3U			RT	H9SW
1999012200573	19990122	00573	SO  	1999	1	22	99ZZZX338        	2	19981221	G	8530	643767	VALVE GUIDE     			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  					NR 4 CYLINDER	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	954CC	478  				18265290	813337R			DURING A ROUTINE 100-HOUR INSPECTION, THE NR 4 CYLINDER WAS FOUND TO HAVE LEAKAGE PAST THE EXHAUST VALVE.  FURTHER INVES	TIGATION REVEALED A WORN OUT EXHAUST VALVE GUIDE.  REPLACING THE GUIDE AND RE-FACING THE EXHAUST VALVE RESOLVED THE PROB	LEM.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR ASSEMBLY PROCESS FROM THE FACTORY.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1999012200574	19990122	00574	SO  	1999	1	22	99ZZZX339        	2	19981217	G	8530	654650	CYLINDER        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	952CC	468  				18263638	470757			DURING A ROUTINE 50 OIL CHANGE/COMPRESSION CHECK, THE NR 3 CYLINDER WAS FOUND TO HAVE LEAKAGE PAST THE EXHAUST AND PISTO	N RINGS.  THE REMOVED CYLINDER WAS FOUND TO HAVE A WORN OUT EXHAUST VALVE, EXHAUST VALVE GUIDE, AND CYLINDER BARREL (NO 	CHOKE).  THE CYLINDER ASSEMBLY WAS REPLACED WITH A NEW UNIT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS DEFECTIVE PARTS OR A	SSEMBLY PROCESS FROM THE FACTORY.			1	H	7	1 	3O	3	O	NT	TA13    	E273
1999010800042	19990108	00042	SO  	1999	1	8	99ZZZX34         	1	19980712	G	2121	C4140070101	FAN             			PIPER 	PA28  	PA28181     	7102807	SO  										E/E BAY	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4146R					2843160				COOLING FAN PIPER P/N 460-105 PRODUCED NOISE THAT INTERFERES WITH THE PROPER OPERATION OF THE MARKER BEACON RECEIVER IN 	THE ACFT.  THE PROBLEM SHOWS UP AS NOISE ON THE MARKER BEACON RECEIVER THAT LIGHTS THE IM LIGHT.  THIS NOISE IS ALSO PRE	SENT ON THE NAVIGATION RECEIVER, BUT DOES NOT EFFECT OPERATION.  RF FILTER NETWORK CONNECTED TO THE COOLING FAN POWER IN	PUT SHOULD CORRECT THE PROBLEM.  SUCH FILTERING NETWORK IS NOT CURRENTLY AVAILABLE OR AUTHORIZED FROM NEW PIPER AIRCRAFT	.		1	L	7	1 	3O				2A13
1999012200575	19990122	00575	NM  	1999	1	22	99ZZZX340        	1	19981216	G	5102	51518	PIN             			RAVEN 	S66   	S66A        	7480612	NM  										GONDOLA	FAILED          	B		A	XRCR	O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			WP	07	9108T	1200 				S66A3052				IMMEDIATELY AFTER TAKEOFF AT AN ALTITUDE OF TWO FEET, THE NR 4 ALUMINUN CONNECTOR PIN (PN 51518) SNAPPED IN HALF (COMPLE	TELY FAILED) SEPARATING THE GONDOLA FROM THE STRUCTURE AT NR 4 LOCATION AND SEVERELY BENDING THE REMAINING THREE CONNECT	OR PINS.  PILOT IMMEDIATELY DEFLATED THE ENVELOPE AND NO INJURY TO PERSONS OR FURTHER DAMAGE TO THE ACFT WAS SUSTAINED. 	 THE EVENT HAPPENED WHERE THE BALLOON SAFETY TIE-OFF LINE WAS ATTACHED - SUBMITTER STATED HAD THE TIE-OFF BEEN RELEASED,	 FAILURE COULD HAVE RESULTED IN INJURY OR FATILITY TO THE 6 OCCUPANTS.  NOTE:  THERE HAVE BEEN SEVERAL PAST FAILURES OF 	PN 51518.  ON ONE OCCASION, ALL 4 PINS FAILED DURING INFLATION.  INSPECT PINS AT ANNUAL INSPECTION WITH A 10X MAG GLASS.	1	B	0	0 					A15CE
1999012200578	19990122	00578		1999	1	22	99ZZZX343        	4	19981228	G	3416	A30	ENCODER         			AMTR  		LONGEZ      												ALTIMETER	MALFUNCTIONED   	B			FC6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	32618				22905	1120				ENCODING ERROR OVER 1,200 FEET.  REPLACED.									0
1999012200579	19990122	00579	SO  	1999	1	22	99ZZZX344        	1	19981205	G	3710	441CC7	VACUUM PUMP     	AIRBORNE    		PIPER 	PA23  	PA23250     	7102308	SO  										VACUUM SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	6944A	3636 	296  		9028J	277954109				PARTIAL VACUUM PUMP FAILURE UNDETECTED IN-FLIGHT OR WITH BOTH ENGINES RUNNING BECAUSE THE RED VACUUM INDICATOR BUTTON ON	 THE DUAL VACUUM GAUGE IS PULLED IN WITH MINIMAL SUCTION, POSSIBLY ABOUT 1 INCH HG.  THIS PROBLEM WAS DETECTED AFTER AN 	OIL CHANGE WHEN RUNNING UP ONE ENGINE AT A TIME.  THE VACUUM INDICATED AT FULL RPM WAS JUST OFF THE STOP.  (BELOW THE 3 	INCH MINIMUM OF THE GAUGE).  THE GYROS WOULD NOT ERECT AT THIS PRESSURE.  ALL DURING THIS TEST, THE RED VACUUM INDICATOR	 REMAINED IN.  REPAIR OF THE PUMP RESTORED NORMAL VACUUM PRESSURE.		1	L	7	2 	3O				1A10
1999012200580	19990122	00580	SO  	1999	1	22	99ZZZX345        	1	19981228	G	5320	79553000	FITTING         			PIPER 	PA28  	PA28181     	7102807	SO  										WINDSHIELD	CORRODED        	D	P			K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	5804F	3731 				287790134				LEAKY WINDSHIELD ALLOWED WATER TO ENTER FACTORY INSTALLED, OPEN CELL FOAM INSULATION, AND LAY IN CONTACT WITH STEEL FITT	INGS.  MINOR DAMAGE UNDER FITTINGS.  FITTINGS WERE REPLACED.  OPEN CELL FOAM WAS REMOVED.					1	L	7	1 	3O				2A13
1999091700552	19990917	00552	NE  	1999	9	17	99ZZZX3451       	2	19981109	G	7230	222025786101	DIFFUSER        			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					COMPRESSOR	BROKE           	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	218  				49037				DIFFUSER BROKEN OFF AT FLANGE MOUNT.  SUSPECT VIBRATION.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL
1999091700553	19990917	00553	NE  	1999	9	17	99ZZZX3452       	2	19981105	G	7261	23063144	FILTER          			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	112  				49037				BYPASS BUTTON POPPED.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL
1999091700554	19990917	00554	NE  	1999	9	17	99ZZZX3453       	2	19981006	G	7261	23063144	FILTER          			BELL  	430   	430         	1182150	SW  	ALLSN 	250C  	250C40B     	03032	NE  					ENGINE	FAILED          	B			AC2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	430CH	98   				49037				BYPASS BUTTON POPPED.						1	G	7	2 	3U	3	U	RT	H9SW    	E1GL
1999012200581	19990122	00581	SO  	1999	1	22	99ZZZX346        	1	19981228	G	5320	79553001	FITTING         			PIPER 	PA28  	PA28181     	7102807	SO  										WINDSHIELD	CORRODED        	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	99	5804F	3731 				287790134				LEAKY WINDSHIELD ALLOWED WATER TO ENTER FACTORY INSTALLED, OPEN CELL FOAM INSULATION, AND LAY IN CONTACT WITH STEEL FITT	INGS.  MINOR DAMAGE UNDER FITTINGS.  FITTINGS WERE REPLACED.  OPEN CELL FOAM WAS REMOVED.					1	L	7	1 	3O				2A13
1999012200582	19990122	00582	EU  	1999	1	22	99ZZZX347        	1	19981105	G	6420		BEARING         			AEROSP	SA316 	SA315B      	8680615	EU  										TAIL ROTOR	ROUGH           	B			FF6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	220SH					2466				PILOT REPORTED TAIL ROTOR PEDALS ARE STIFF AND NOTCHY.  MECHANIC REPORTED NOTCHED BEARINGS WHEN P/C LINK DISCONNECTED AN	D T/R BLADES ARE ROTATED.  REPLACED 3 EACH.  BEARING S/N'S A33795, A33783, AND A33812.					1	G	7	1 	4U				H1IN
1999012200583	19990122	00583		1999	1	22	99ZZZX348        	3	19981209	G	6112	9696000835	BOND ASSY       			BEECH 	58    	58          	1152740	CE  										PROPELLER DEICE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	58MW	3924 				TH863				BOND ASSEMBLY (DE-ICE FLUID LINE) WAS WORN THROUGH.  DAMAGED BY DE-ICE SLINGER RING.  SUBMITTER STATED WHEN INSTALLING P	ROPELLERS, BE SURE PROPER CLEARANCE EXISTS BETWEEN BOND AND SLINGER.					1	L	7	2 	3O				3A16
1999012200584	19990122	00584		1999	1	22	99ZZZX349        	4	19981228	G	3452		CONNECTOR       	NARCO       	AT50A       	PIPER 	PA22  	PA22160     	7102214	SO  										TRANSPONDER	FAILED          	B			FC6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	3670Z				35219	227408				LOSS OF B4 MODE C CODE LINE.  CONTACT PIN IN RACK LOST TENSION.  REPLACED ALL CONTACT PINS.						1	H	7	1 	3O				1A6
1999010800043	19990108	00043	SO  	1999	1	8	99ZZZX35         	1	19980712	G	2121		FAN             			PIPER 	PA28  	PA28181     	7102807	SO  										E/E BAY	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4145A					2843150				COOLING FAN, PIPER P/N 460-105, PRODUCES NOISE THAT INTERFERES WITH THE PROPER OPERATION OF THE MARKER BEACON RECEIVER I	N THE AIRCRAFT.  THE PROBLEM SHOWS UP AS NOISE ON THE MARKER BEACON RECEIVER THAT LIGHTS THE IM LIGHT.  THIS NOISE IS AL	SO PRESENT ON THE NAVIGATION RECEIVER, BUT DOES NOT EFFECT OPERATION.  RF FILTER NETWORK CONNECTED TO THE COOLING FAN PO	WER INPUT SHOULD CORRECT THE PROBLEM.  SUCH FILTERING NETWORK IS NOT CURRENTLY AVAILABLE OR AUTHORIZED FROM PIPER AIRCRA	FT.		1	L	7	1 	3O				2A13
1999012200585	19990122	00585	EA  	1999	1	22	99ZZZX350        	2	19981121	G	8500		CRANKCASE       			BNORM 	BN2MK3	BN2AMK3     	1520203	EU  	LYC   	O540  	O540E4C5    	41532	EA  					LEFT	CRACKED         	G				A				UNSCHED LANDING         				E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			SO	21	901VL	6099 	270  			1003	L1874140A			ON CRUISE FLIGHT, LEFT ENGINE STARTED TO VIBRATE AND LEAK OIL.  PILOT DECLARED EMERGENCY AND LANDED AT A MILITARY AIRPOR	T.  PRELIMINARY INSPECTION REVEALED LEFT ENGINE CRANKCASE CRACKED.  ENGINE CHANGE IN PROGRESS.  MORE DETAILS WILL BE SUB	MITTED AFTER ENGINE DISASSEMBLY.				1	H	7	3 	3O	3	O		A29EU   	E295
1999012200586	19990122	00586	SO  	1999	1	22	99ZZZX351        	1	19981201	G	2820		LINE            			PIPER 	PA34  	PA34200     	7103405	SO  										WING	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	01	10394					347250024				NOTED FUEL LAYING AROUND BOTTOM OF WING TANKS AND OCCASIONAL FUEL AROMA IN COCKPIT WHEN TANKS TOPPED OFF.  REMOVED FUEL 	TANKS, REPLACED FLEXIBLE FUEL VENT HOSES AND INSPECTED AND TREATED FOR CORROSION PER PIPER SB 1006.  SUBMITTER STATED TH	IS SB DOES NOT APPLY TO THE PA-34 SERIES AIRCRAFT.				1	L	7	2 	3O				A7SO
1999012200587	19990122	00587	CE  	1999	1	22	99ZZZX352        	1	19981221	G	2897	991008219	WIRE            	GULL        		CESSNA	310   	310R        	2074245	CE  										FUEL CELL	CHAFED          	B	L		YR4R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	4919A	4248 				310R1403				DURING ANNUAL INSPECTION, TOP INSPECTION PANEL ON THE RT WING AUXILIARY TANK WAS LEAKING FUEL.  UPON REMOVAL OF THE PANE	L TO REPLACE THE GASKET, NOTICED THE FUEL QUANTITY SENDING UNIT WIRES INSIDE THE FUEL TANK WERE EXCEPTIONALLY LONG.  UPO	N EXAMINATION OF THE WIRING, FOUND THE INSULATION HAD BEEN CHAFED OFF OF THE WIRES, AND BARE WIRE WAS SHOWING IN SEVERAL	 PLACES.  UPON INSPECTION OF THE LT AUXILIARY TANK, NOTICED THE WIRES WERE CHAFED IN SEVERAL PLACES AND BARE WIRE WAS SH	OWING THROUGH.  SENDING UNITS WERE REMOVED FROM BOTH THE LT AND RT FUEL AUXILIARY TANKS WHERE SEVERAL MORE CHAFED AREAS 	WERE FOUND.	1	L	7	2 	3O			 	3A10
1999012200590	19990122	00590	WP  	1999	1	22	99ZZZX354        	2	19981216	G	7200		ENGINE          			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					RIGHT	FAILED          	B			IZ2R	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SW	15	44MM					1526SA	P38080			DURING NORMAL CRUISE AT FL 220, THE RIGHT ENGINE WENT TO FEATHER.  UPON A NON-EVENTFUL LANDING, DETERMINED THE TURBINE H	AD UNCOUPLED FROM THE GEARBOX.  ENGINE TIME SINCE OVERHAUL 731.5 HOURS.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE
1999012200592	19990122	00592	EU  	1999	1	22	99ZZZX356        	1	19981112	G	3230	A23801102	SWITCH          	AEROSP      	MY20294106  	AMD   	FALC20	FALCON200   	2730150	EU  										RT MLG WW	DAMAGED         	A			H9WY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	1847B	7717 			M158	493				DURING POST-FLIGHT, THE RIGHT GEAR DOOR WAS FOUND DAMAGED.  ON INVESTIGATION, FORWARD DOOR LATCH MICROSWITCH, GEAR ACTUA	TOR MICROSWITCH, AND DOOR ACTUATOR MICROSWITCH WERE FOUND TO BE INTERMITTENT.  ALL DEFECTIVE PARTS WERE REPLACED AND FUN	CTIONAL CHECK WAS CARRIED OUT, FOUND SERVICEABLE.  AICRAFT WAS RELEASED TO SERVICE.  SUBMITTER RECOMMENDATIONS:  CHECK A	LL MICROSWITCHES ON LANDING GEAR SYSTEM AT EVERY SCHEDULED INSPECTION.			2	L	7	2 	4F			RT	A7EU
1999012200593	19990122	00593	EU  	1999	1	22	99ZZZX357        	1	19981112	G	3230	A23802102	SWITCH          	AEROSP      	MY20294106  	AMD   	FALC20	FALCON200   	2730150	EU  										RT MLG WW	DAMAGED         	A			H9WY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	1847B	7717 			M2638	493				DURING POST-FLIGHT, THE RIGHT GEAR DOOR WAS FOUND DAMAGED.  ON INVESTIGATION, FORWARD DOOR LATCH MICROSWITCH, GEAR ACTUA	TOR MICROSWITCH, AND DOOR ACTUATOR MICROSWITCH WERE FOUND TO BE INTERMITTENT.  ALL DEFECTIVE PARTS WERE REPLACED AND FUN	CTIONAL CHECK WAS CARRIED OUT, FOUND SERVICEABLE.  AICRAFT WAS RELEASED TO SERVICE.  SUBMITTER RECOMMENDATIONS:  CHECK A	LL MICROSWITCHES ON LANDING GEAR SYSTEM AT EVERY SCHEDULED INSPECTION.			2	L	7	2 	4F			RT	A7EU
1999012200594	19990122	00594	EU  	1999	1	22	99ZZZX358        	1	19981112	G	3230	VTS4424	SWITCH          	AEROSP      	MY20294106  	AMD   	FALC20	FALCON200   	2730150	EU  										RT MLG WW	DAMAGED         	A			H9WY	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	33	1847B	7717 			1826	493				DURING POST-FLIGHT, THE RIGHT GEAR DOOR WAS FOUND DAMAGED.  ON INVESTIGATION, FORWARD DOOR LATCH MICROSWITCH, GEAR ACTUA	TOR MICROSWITCH, AND DOOR ACTUATOR MICROSWITCH WERE FOUND TO BE INTERMITTENT.  ALL DEFECTIVE PARTS WERE REPLACED AND FUN	CTIONAL CHECK WAS CARRIED OUT, FOUND SERVICEABLE.  AICRAFT WAS RELEASED TO SERVICE.  SUBMITTER RECOMMENDATIONS:  CHECK A	LL MICROSWITCHES ON LANDING GEAR SYSTEM AT EVERY SCHEDULED INSPECTION.			2	L	7	2 	4F			RT	A7EU
1999012200595	19990122	00595	NE  	1999	1	22	99ZZZX359        	3	19981222	G	6110	7757571	BEARING         	HAMSTD      	6044T35P02  	SAAB  	SF340 	SF340A      	7850100	EU  						ROTOL	R320	R3204123F1  	NE  	PROPELLER SHAFT	SPALLED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		27494			5270					DURING DISASSEMBLY OF GEARBOX, THE FORWARD ROLLER BEARING WAS FOUND SPALLED AND CRACKED.  NO OTHER DISCREPANCIES REQUIRI	NG AN M OR D WERE NOTED.  HSS SO NR 21918950.  CUSTOMER:  SKYWAYS A/L.					2	L	7	2 	4T			RT	A52EU   		6	C	P5NE
1999010800044	19990108	00044	SO  	1999	1	8	99ZZZX36         	1	19980712	G	2121		FAN             			PIPER 	PA28  	PA28181     	7102807	SO  										E/E BAY	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	19	4149A					2843189				COOLING FAN, PIPER P/N 460-105, PRODUCES NOISE THAT INTERFERES WITH THE PROPER OPERATION OF THE MARKER BEACON RECEIVER I	N THE AIRCRAFT.  THE PROBLEM SHOWS UP AS NOISE ON THE MARKER BEACON RECEIVER THAT LIGHTS THE IM LIGHT.  THIS NOISE IS AL	SO PRESENT ON THE NAVIGATION RECEIVER, BUT DOES NOT EFFECT OPERATION.  RF FILTER NETWORK CONNECTED TO THE COOLING FAN PO	WER INPUT SHOULD CORRECT THE PROBLEM.  SUCH FILTERING NETWORK IS NOT CURRENTLY AVAILABLE OR AUTHORIZED FROM NEW PIPER AI	RCRAFT.		1	L	7	1 	3O				2A13
1999012200596	19990122	00596	CE  	1999	1	22	99ZZZX360        	1	19981222	G	7603	556580315	SPRING          			CESSNA	500   	550         	2076604	CE  										THROTTLE	BROKE           	H				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	84EA	6723 				5500484				PILOT REPORTED HE HEARD A 'POP' DURING ENGINE SHUT DOWN AND LEFT THROTTLE TRIGGER LOST TENSION.  FOUND SPRING BROKEN AND	 REPLACED UNIT.  FAILURE OF THIS SPRING COULD ALLOW THROTTLE TO MAKE A 'CUT-OFF' INADVERTENTLY INSTEAD AT IDLE.					1	L	7	2 	4F				A22CE
1999012200598	19990122	00598	SW  	1999	1	22	99ZZZX362        	1	19981223	G	7931	407375005101	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	DAMAGED         	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	10EW	8    			0344	53262				INDICATOR DAMAGED.  REPLACED WITH NEW GAUGE FROM BELL HELICOPTER.						1	G	7	1 	3U			O	H2SW
1999012200599	19990122	00599	NM  	1999	1	22	99ZZZX363        	1	19981113	G	6710	A1217	TUBE            			ROBSIN	R22   	R22BETA     		NM  										CYCLIC	WORN            	B		A	DDER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8363D	57   				2745				PUSH/PULL TUBES FOUND WEARING EXCESSIVELY AT UPPER FRAME FORWARD TWO BOLTHEADS AT THE HORIZONTAL FIREWALL.  TUBES WERE W	ORN WAY BEYOND TOLERANCE LIMITS ON AN AIRFRAME WITH ONLY 57 HOURS TOTAL TIME.  (ONE YEAR OLD).					1	G	7	1 	3O				H10WE
1999012200600	19990122	00600	WP  	1999	1	22	99ZZZX364        	1	19980713	G	6410	369A17267	BEARING         			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	G		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	58377	596  				1290646D				TAIL ROTOR BLADE CONICAL BEARINGS WERE INSPECTED 96 HOURS PRIOR TO FAILURE WITH NO DEFECTS NOTED.  BEARING WEAR AND FAIL	URE CAUSED TAIL ROTOR DRIVESHAFT TO FLEX AND BOUNCE UNTIL IT BROKE IN HALF SEVERING THE TAIL BOOM.  FORTUNATELY, THE AIR	CRAFT WAS ON THE GROUND.  SUBMITTER RECOMMENDED A THOROUGH INSPECTION AT 100-HOUR INSPECTIONS AND SPECIAL DETAIL TO TAIL	 ROTOR DURING PRE-FLIGHT INSPECTIONS.			1	G	7	1 	3U				H3WE
1999012200735	19990122	00735	CE  	1999	1	22	99ZZZX366        	1	19981207	G	3230	51420025	DRAG BRACE      			CESSNA	414   	414A        	2075907	CE  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	37150	4737 				414A0251				COMPLYING WITH CESSNA SB MFB 91-11, DRAG BRACE INSPECTION.  FOUND BRACE CRACKED AT ACTUATOR ATTACH POINT.  INSTALLED NEW	 STYLE DRAG BRACE, P/N 5142002-5.					1	L	7	2 	3O				A7CE
1999012200736	19990122	00736	EA  	1999	1	22	99ZZZX367        	2	19981221	G	8530		VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 4 CYLINDER	FAILED          	B				O				OTHER                   				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			EA	21	75709					17267890	L231276			ENGINE STOPPED IN-FLIGHT.  FOUND NR 4 CYLINDER INTAKE VALVE BROKEN, INTAKE VALVE PART NUMBER UNKNOWN.  ENGINE TSMOH:  11	7.9 HOURS.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1999012200737	19990122	00737	NE  	1999	1	22	99ZZZX368        	3	19981231	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3473 					HJ717		NR 3 BLADE EROSION SHIELD DEBONDED.  DEBOND AT BUTT END OF BLADE ABOUT 5 SQUARE INCHES.  REPAIRED IAW MFG CMM.																5	C	P10NE
1999012200738	19990122	00738	NE  	1999	1	22	99ZZZX369        	3	19981231	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			861  					HJ872		NR 2 BLADE EROSION SHIELD DEBONDED.  DEBOND AT BUTT END OF BLADE ABOUT 3 SQUARE INCHES.  REPAIRED AND INSTALLED NEW DEIC	E BOOT IAW MFG CMM.															5	C	P10NE
1999010800045	19990108	00045	SW  	1999	1	8	99ZZZX37         	1	19981020	G	6220	222310126101	BEARING         		22201210110 	BELL  	230   	230         	1182149	SW  										M/R HEAD	DELAMINATED     	B	P	A	TU3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	303PS	1274 			0074	23016				PILOT REQUESTED A FLIGHT TRACK CHECK OF THE MAIN ROTOR SYSTEM DUE TO A CHANGE IN VIBRATION LEVELS WHICH HAD CHANGED FROM	 LAST FLIGHT.  THE TRIM TABS WERE CHECKED WITH THE RECORD MADE FROM THE LAST TRACKING FLIGHTS WITH ONLY A MINOR CHANGE. 	 THE BLADE TRACKING EQUIP INSTALLED AND HELICOPTER FLOWN.  THERE WERE SEVERAL READINGS OBTAINED FROM THIS FLIGHT AND THE	Y WERE NOT CONSISTENT.  INSP FOUND BOTH FEATHERING BEARINGS DELAMINATED AND THE BEARING INNER MEMBERS SEPARATED ON THE R	ED BLADE.  BEARINGS REPLACED PER MFG'S COMPONENT O/H AND RM.  HELICOPTER TRACKED AND BALANCED WITHOUT ANY  PROBLEMS AND 	RELEASED TO SERIVCE.  LAST INSPECTION 67.2 HRS AND 5 MONTHS PRIOR, FOUND NO DEFECTS WITH THE BEARINGS.	1	G	7	2 	3U			NC	H9SW
1999012200739	19990122	00739	NE  	1999	1	22	99ZZZX370        	3	19981217	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1125 					HJ140A		NR 4 BLADE EROSION SHIELD DEBONDED.  DEBONDED IN AREA OF DEICE BOOT ON BLADE FACE, THE LENGTH OF DEICE BOOT, ABOUT .50 I	NCH UP FROM TRAILING EDGE.  REPAIRED IAW MFG CMM.  INSTALLED NEW DEICE BOOT.															5	C	P10NE
1999012200740	19990122	00740	NE  	1999	1	22	99ZZZX371        	3	19981224	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1102 					HJ621		NR 1 BLADE EROSION SHIELD DEBONDED.  DEBOND AREA STARTING AT BLADE BUTT END GOING ABOUT 4 INCHES OUTBOARD ON BLADE FACE.	  REPAIRED AND INSTALLED NEW DEICE BOOT IAW MFG CMM.															5	C	P10NE
1999012200741	19990122	00741	NE  	1999	1	22	99ZZZX372        	3	19981219	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	CRACKED         	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1251 					HJ630		NR 3 BLADE HAS 7 CRACKS IN THE EROSION SHIELD.  REPLACED EROSION SHIELD AND OVERHAULED NR 3 BLADE, S/N 392.																5	C	P10NE
1999012200742	19990122	00742	NE  	1999	1	22	99ZZZX373        	3	19981223	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1447 					HJ593		EROSION SHIELD DEBONDED ON NR 3 BLADE.  DEBOND WAS 2 SQUARE INCHES UNDER INBOARD HALF OF DEICE BOOT.  REPAIRED DEBOND, S	ET PRELOAD, RE-ASSEMBLED PROPELLER IAW MFG CMM.															5	C	P10NE
1999012200743	19990122	00743	SO  	1999	1	22	99ZZZX374        	1	19981229	G	2823	1H654	VALVE SHAFT     		99321       	PIPER 	PA32  	PA32300     	7103212	SO  										FUEL SELECTOR	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	1132Q	5887 			0048	327740041				FUEL SELECTOR HANDLE WAS FOUND TO HAVE EXCESS PLAY BETWEEN TANK DETENTS.  UPON DISASSEMBLY OF FUEL SELECTOR VALVE, FOUND	 BOTH SPIRAL PINS SECURING ACTUATOR ARM TO VALVE SHAFT HAD WORN APPROXIMATLEY 80 PERCENT THROUGH.  A SERVICEABLE SHAFT A	RM ASSEMBLY WAS USED TO MAKE REPAIR.  THIS VALVE IS DIFFERENT MODEL THAN SPECIFIED IN AD 70-22-02, BUT THE FAILURE MODE 	IS SIMILAR.			1	L	7	1 	3O				A3SO
1999012200744	19990122	00744	EA  	1999	1	22	99ZZZX375        	2	19980108	G	8530		SHAFT           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  					ENGINE	WRONG PART      	B			BNZR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	19	9988B					172RG1108	L2810936A			FOUND ENGINE OVERHAULED WITH INCORRECT ROCKER SHAFTS INSTALLED ON ALL CYLINDERS.  NOTICED SHAFTS WERE DAMAGING ROCKER CO	VERS.  UPON FURTHER INSPECTION, DETERMINED THE ROCKER SHAFTS WERE NOT THE CORRECT PART NUMBER, WERE TOO LONG, AND DID NO	T CONTAIN THE PLASTIC END CAPS.  ENGINE HAS 1,174.3 TSMOH HOURS.				1	H	7	1 	3O	3	O		3A17    	E286
1999012200745	19990122	00745	EA  	1999	1	22	99ZZZX376        	2	19981207	G	8530	SL12596	BOLT            			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	LTIO540F2BD 	41533	EA  					RT ENGINE	FAILED          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	24MG	447  				317512049	RL143668A			PILOT REPORTED RT ENGINE RUNS ROUGH.  FOUND NO COMPRESSION NR 6 CYLINDER.  FOUND METAL IN MAIN OIL SCREEN.  FOUND NR 6 R	OD BOLT BROKEN AND CONNECTING ROD BROKEN LOOSE FROM CRANKSHAFT.  MAJOR DAMAGE TO CRANKCASE, CRANKSHAFT, ROD, AND CYLINDE	RS.  SUBMITTER SUSPECTED IMPROPER HEAT TREATMENT OF ROD BOLT.  BOLT TO BE SENT TO THE MANUFACTURER FOR FURTHER TESTING.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1999012200746	19990122	00746		1999	1	22	99ZZZX377        	4	19980104	G	2562	300011	ELT             	POINTER     		CESSNA	172   	172R        	2072401	CE  										CABIN	MALFUNCTIONED   	B			EIPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	9529W				326501	17280470				REMOTE ELT SWITCH DID NOT ACTUATE ELT.  SUBMITTER TALKED WITH FACTORY.  FOUND CESSNA USED CIRCUIT TESTER AND SHORTED INT	ERNAL FUSES IN ELT.  TESTED ELT AND SWITCH WIRING PER FACTORY.  SENT IN ELT'S TO FACTORY TO HAVE HIGHER AMP FUSES INSTAL	LED.				1	H	7	1 	3O			NT	3A12
1999012200748	19990122	00748	SO  	1999	1	22	99ZZZX379        	1	19981231	G	2560	AK450	ELT             	AMERIKING   		PIPER 	PA31  	PA31P       	7103120	SO  										CABIN	FAILED          	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	252MA	630  			4505079	31P33				UNIT INSTALLED 12-96.  NO OUTPUT SIGNAL DURING TEST PER FAR 91-207D.  SUBMITTER STATED THIS IS THE FOURTH UNIT OF THIS M	ANUFACTURER TO FAIL SHORTLY AFTER INSTALLATION.					1	L	7	2 	3O				A8EA
1999010800046	19990108	00046	SW  	1999	1	8	99ZZZX38         	1	19981020	G	6220	222310125103	BEARING         		22201210110 	BELL  	230   	230         	1182149	SW  										M/R HUB ASSY	DELAMINATED     	B	P	A	TU3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	303PS	1274 			LK0008	23016				PILOT REQUESTED A FLIGHT TRACK CHECK OF THE MAIN ROTOR SYSTEM DUE TO A CHANGE IN VIBRATION LEVELS WHICH HAD CHANGED FROM	 LAST FLIGHT.  THE TRIM TABS WERE CHECKED WITH THE RECORD MADE FROM THE LAST TRACKING FLIGHTS WITH ONLY A MINOR CHANGE. 	 THE BLADE TRACKING EQUIP INSTALLED AND HELICOPTER FLOWN.  THERE WERE SEVERAL READINGS OBTAINED FROM THIS FLIGHT AND THE	Y WERE NOT CONSISTENT.  INSP FOUND BOTH FEATHERING BEARINGS DELAMINATED AND THE BEARING INNER MEMBERS SEPARATED ON THE R	ED BLADE.  BEARINGS REPLACED PER MFG'S COMPONENT O/H AND RM.  HELICOPTER TRACKED AND BALANCED WITHOUT ANY  PROBLEMS AND 	RELEASED TO SERIVCE.  LAST INSPECTION 67.2 HRS AND 5 MONTHS PRIOR, FOUND NO DEFECTS WITH THE BEARINGS.	1	G	7	2 	3U			NC	H9SW
1999012200749	19990122	00749	CE  	1999	1	22	99ZZZX380        	1	19981123	G	5752		BALL CARRIAGE   		CL3010010702	CESSNA	210   	210J        	2073439	CE  										FLAP ACTUATOR	LOOSE           	D				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			GL	23		2700 								DURING APPROACH TO LANDING, THE FLAPS SUDDENLY RETRACTED.  INVESTIGATION REVEALED THE CABLE DRIVE ASSY TO WHICH THE CABL	ES ARE ATTACHED SEPARATED FROM THE FLAP ACTUATOR ASSY.  THE CABLE DRIVE ASSY IS ATTACHED TO THE FLAP ACTUATOR BY THREADS	 INTERNAL TO THE CABLE DRIVE ASSY AND EXTERNAL TO THE BALL CARRIAGE THAT RUNS ON THE JACK SCREW OF THE ACTUATOR.  THIS C	ONNECTION IS KEPT FROM UNSCREWING BY ONE SET SCREW THAT SHOULD BE LOC-TITED IN PLACE.  SUBMITTER STATED IT APPEARS AS IF	 THIS SET SCREW WAS NOT LOC-TITED IN PLACE, LOOSENED, AND ALLOWED THE BALL CARRIAGE TO UNSCREW FROM THE CABLE DRIVE ASSY	.	1	H	7	1 	3O				3A21
1999012200751	19990122	00751	CE  	1999	1	22	99ZZZX382        	1	19981222	G	7500		LEVER           			BEECH 	100   	B100        	1152919	CE  										COCKPIT	JAMMED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	15	8514B					BE6				DURING PRE-FLIGHT, FOUND RIGHT CONDITION LEVER COULD NOT BE PLACED INTO EMERGENCY FEATHER POSITION.  LEVER WOULD JAM ABO	UT HALF WAY TO STOP POSITION.  ENGINE CONTROL RE-RIGGED TO PROVIDE CONDITION LEVER FULL TRAVEL.  SUBMITTER SUGGESTED A F	EATHER VALVE CHECK BE ACCOMPLISHED PRIOR TO FLIGHT FOR THESE AIRCRAFT.				1	L	7	2 	4T				A14CE
1999012200753	19990122	00753	EA  	1999	1	22	99ZZZX384        	2	19981221	G	7210	3016923	HOUSING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					GEARBOX	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	22071	8933 	8303 			BB111	PCE80412			DURING RE-ASSEMBLY OF THE REDUCTION GEARBOX AFTER LIGHTNING STRIKE INSPECTION, FOUND THE PROPELLER OIL TRANSFER HOUSING 	WAS DAMAGED.  THE CHIP DETECT LIGHT CAME ON DURING FIRST FLIGHT.  REMOVED GEARBOX, INSTALLED NEW HOUSING.  PEFORMED IAW 	MM AND SUBMITTER STATED NOT TO USE EXCESSIVE FORCE.				1	L	7	2 	4T	4	T		A24CE   	E4EA
1999012900053	19990129	00053	CE  	1999	1	29	99ZZZX387        	1	19981130	G	5541	33630000601	SPAR            			BEECH 	33    	35B33       	1151406	CE  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	727NG	4049 				CD689				WHILE COMPLYING WITH AD 93-24-03, FOUND SMALL CRACK UNDER UPPER RUDDER HINGE BRACKET.  INSTALLED GENERAL FORMING DW-1 AN	D DW-2 BRACKETS PER STC SA00044LA.  CRACK WAS NOT VISIBLE UNTIL DYE PENETRANT INSPECTION PERFORMED.					1	L	7	1 	3O				3A15
1999012900054	19990129	00054	SW  	1999	1	29	99ZZZX388        	1	19981231	G	2421	51539002N	CONTROLLER      			BELL  	412   	412EP       	1182205	SW  										AC GENERATOR	FAILED          	B			GS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	44454	11   			97488	36210				CONTROLLER REPLACED WITH NEW FROM BELL HELICOPTER.						1	G	7	2 	4U				H4SW
1999010800047	19990108	00047	NE  	1999	1	8	99ZZZX39         	1	19980326	G	6210	7615009100052	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547K	5662 	302  		A08601722	760085				DISCOVERED DURING DAILY INSPECTION, TRIM TAB DEBONDED AND WASHED OUT.						1	G	7	2 	3U				H1NE
1999012900057	19990129	00057	EU  	1999	1	29	99ZZZX391        	1	19981222	G	3340	3011913	STROBE          	GRIMES      		AMD   	FALC50	FALCON50MYST	2730106	EU  										WING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	280BG	5373 			255	109				STROBE LIGHT WAS INOPERABLE.  DISCOVERED STROBE FLASH TUBE HAD ARCHED TO CASE AT END MOUNT.  SUBMITTER STATED THIS COULD	 BECOME VERY HAZARDOUS IF ANY FUEL VAPOR SHOULD BE IN WING.  PART IS OK FOR INSPECTION, BUT A CLOSER LOOK DURING ANY INS	PECTION WOULD BE WISE.				2	L	7	3 	4F				A46EU
1999012900058	19990129	00058	EU  	1999	1	29	99ZZZX392        	1	19981222	G	3340	3011913	STROBE          	GRIMES      		AMD   	FALC50	FALCON50MYST	2730106	EU  										WING	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	280BG	5373 			256	109				STROBE LIGHT WAS INOPERABLE.  DISCOVERED STROBE FLASH TUBE HAD ARCHED TO CASE AT END MOUNT.  SUBMITTER STATED THIS COULD	 BECOME VERY HAZARDOUS IF ANY FUEL VAPOR SHOULD BE IN WING.  PART IS OK FOR INSPECTION, BUT A CLOSER LOOK DURING ANY INS	PECTION WOULD BE WISE.				2	L	7	3 	4F				A46EU
1999012900060	19990129	00060	NM  	1999	1	29	99ZZZX394        	1	19981215	G	5313		STRINGER        			BOEING	727   	72759       		NM  										BS 950-1009	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	203AV					22474				DURING A C-CHECK, CORROSION WAS NOTED ON STRINGER 30, STA 950 - STA 1009.						2	L	7	3 	4F				A3WE
1999020600001	19990206	00001	EU  	1999	2	6	99ZZZX395        	1	19981216	G	2750		SWITCH          		C13606645   	PIAGIO	P180  	P180        	6960204	EU  										TE FLAP	MALFUNCTIONED   	B			CB5Y	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	35	220TW	1134 			1051	1018				FLAPS 'LOCKED OUT' IN THE MID-POSITION WHILE MOVING FROM THE FULL DOWN TO UP POSITION.  THE MALFUNCTION WAS DUE TO A HIG	H RESISTANCE IN THE INTERNAL MICROSWITCHES OF THE FLAP DRIVE UNIT.  THE AIRCRAFT MANUFACTURER IS AWARE OF THE PROBLEM. T	HE FLAP DRIVE UNIT WAS REPLACED BY AN IMPROVED VERSION.  P/N C136066-45, S/N 1051 REMOVED.  P/N C152550-1, S/N 1007 FITT	ED.  FULL FUNCTIONAL CHECKS CHECK OUT, AIRCRAFT FLOWN.  NO FURTHER REPORTED DEFECTS.			1	H	7	2 	3O			RT	A59EU
1999012900061	19990129	00061	CE  	1999	1	29	99ZZZX396        	1	19981224	G	2434		WIRE            			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    	 	EA  					ALTERNATOR	BROKEN          	B	P		N3XR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	15	420ER	256  				17280634	L2780851A			LOW VOLTAGE LIGHT CAME ON SEVERAL TIMES DURING FLIGHT.  PERFORMED ENGINE RUN-UP FOR OPERATIONAL CHECK OF ALTERNATOR.  AL	TERNATOR CHECKS GOOD.   BATTERY AND GROUND ALTERNATOR TERMINALS WERE FOUND BROKEN.  THESE WIRE TERMINALS APPEAR TO BE TH	IN AND ARE BREAKING JUST IN FRONT OF THE CRIMP.  REPLACED WIRE TERMINALS TO ALTERNATOR AND OPER CHECK GOOD.  SE78-38 APP	LIED TO 1979 VINTAGE C172 PRESCRIBED A PROCEDURE TO ISOLATE AND SECURE ALTERNATOR WIRES TO AFT FRAME OF ALTERNATOR IN SE	VERAL PLACES AND ELIMINATED WIRE TERMINAL BREAKAGE.  SUGGEST S/N AND MODEL APPLICABILITY BE REVISED TO INCLUDE RECENT PR	ODUCTION ACFT WHICH WOULD ELIMINATE ELEC SYS MALFUNCTION AND/OR FAILURE IN 53 C172R ACFT.	1	H	7	1 	3O	3	O	NT	3A12    	1E10
1999012900062	19990129	00062	CE  	1999	1	29	99ZZZX397        	1	19981201	G	7160	17520789	SEAL            			CESSNA	177   	177B        	2073708	CE  										AIR BOX	TORN            	B	P		BD6R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	177A					17702284				THE RUBBER SEAL AROUND THE EDGE OF THE VALVE RIPPED AND LOOKED LIKE IT WOULD HAVE BEEN SUCKED INTO THE ENGINE IN A COUPL	E OR MORE HOURS.  SUBMITTER STATED THE RUBBER SEAL LOOKED LIKE IT WAS MADE FROM THE WRONG MATERIAL .  TT ON PART, 8 HOUR	S.				1	H	7	1 	3O				A13CE
1999012900063	19990129	00063	EA  	1999	1	29	99ZZZX398        	2	19981228	G	8530	LW11775	PLUG            		LW14077     	CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					NR 4 CYLINDER	WORN            	B				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			SO	11	476ER	319  				17280621	L2782851A			DURING A NIGHT TRAINING FLIGHT, THE CREW NOTICED AN ENGINE VIBRATION THAT BECAME VIOLENT OVER A SHORT PERIOD OF TIME.  D	URING LANDING, THE OIL PRESSURE WENT TO ZERO PSI.  THE NR 4 PISTON WAS FOUND DESTROYED.  THE PISTON PIN PLUGS (LYC P/N L	W-11775) WERE WORN SO SEVERELY THAT ALL OF THEM WERE CONSUMED AND IN THE FILTER.  THE AIRCRAFT IN THE FLEET WERE INSPECT	ED AND ALL THE PLUGS WERE WORN SEVERELY.  ALL WERE REPLACED PER LYC SB 12678.			1	H	7	1 	3O	3	O	NT	3A12    	1E10
1999012900064	19990129	00064	CE  	1999	1	29	99ZZZX399        	1	19981130	G	5311		FRAME           			CESSNA	172   	172N        	2072434	CE  										FUSELAGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	739ZC	5501 				17270928				CRACK WAS FOUND ON LEFT FORWARD DOOR POST BULKHEAD AT LOWER DOOR HINGE ATTACH POINT.  REMOVAL OF INTERIOR SIDE PANEL ALL	OWS EASY INSPECTION.  A 4130 STEEL DOUBLER WAS FABRICATED AND INSTALLED BY OUTSIDE REPAIR STATION.					1	H	7	1 	3O			NT	3A12
1999010800048	19990108	00048	SW  	1999	1	8	99ZZZX40         	1	19980330	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417AL					53054				DURING C/W 25-HOUR AD 97-24-17, PART A, B, AND E, FOUND ONE LAMINATE ON AFT SIDE OF NR 7 DISK PACK, P/N 406-040-340-101,	 CRACKED.					1	G	7	1 	3U			O	H2SW
1999012900065	19990129	00065	CE  	1999	1	29	99ZZZX400        	1	19981130	G	5311		FRAME           			CESSNA	172   	172N        	2072434	CE  										FUSELAGE	CRACKED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5435E	5562 				17271863				A CRACK WAS FOUND ON LEFT FORWARD DOOR POST BULKHEAD AT LOWER DOOR HINGE ATTACH POINT.  REMOVAL OF INTERIOR SIDE PANEL A	LOWS EASY INSPECTION.  A 4130 STEEL DOUBLER WAS FABRICATED AND INSTALLED BY OUTSIDE REPAIR STATION.					1	H	7	1 	3O			NT	3A12
1999012900066	19990129	00066	CE  	1999	1	29	99ZZZX401        	1	19981130	G	5311		FRAME           			CESSNA	172   	172N        	2072434	CE  										FUSELAGE	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5344D	7646 				17272532				A CRACK WAS FOUND ON LEFT FORWARD DOOR POST BULKHEAD AT LOWER DOOR HINGE ATTACH POINT.  REMOVAL OF INTERIOR SIDE PANEL A	LLOWS EASY INSPECTION.  A 4130 STEEL DOUBLER WAS FABRICATED BY OUTSIDE REPAIR STATION.					1	H	7	1 	3O			NT	3A12
1999012900085	19990129	00085	SW  	1999	1	29	99ZZZX404        	1	19981210	G	2912	0113245	FRAME           			BELL  	206   	206B        	1181511	SW  										HYDRAULIC FILTER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5008K	2021 				2524				SHOP INSPECTION FOR REPAIR OF LEAKING SHAFT SEALS.  FOUND RUST COATING ON FILTER FRAME.						1	G	7	1 	3U				H2SW
1999012900086	19990129	00086	SW  	1999	1	29	99ZZZX405        	1	19981210	G	2912	0113245	FRAME           			BELL  	206   	206B        	1181511	SW  										HYDRAULIC FILTER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42AL	993  				918				SHOP INSPECTION FOR REPAIR OF LEAKING SHAFT SEALS.  FOUND RUST COATING ON FILTER FRAME.						1	G	7	1 	3U				H2SW
1999012900087	19990129	00087	SW  	1999	1	29	99ZZZX406        	1	19981210	G	2912	0113245	FRAME           			BELL  	206   	206B        	1181511	SW  										HYDRAULIC FILTER	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3912Q	994  				3271				SHOP INSPECTION OF PUMP FOR REPAIR DUE TO LEAKING SHAFT SEALS.  FOUND RUST COATING ON FILTER FRAME.						1	G	7	1 	3U				H2SW
1999012900088	19990129	00088	SW  	1999	1	29	99ZZZX407        	1	19981228	G	5512	407023800126	ANGLE           		407023800101	BELL  	407   	407         		SW  										HORIZ STABILIZER	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	547AL	1340 				53240				DURING DAILY INSPECTION, FOUND CRACK IN BEND RADIUS.						1	G	7	1 	3U			O	H2SW
1999012900089	19990129	00089	GL  	1999	1	29	99ZZZX408        	2	19981222	G	7210	6889326	BEARING         		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	537AL	496  			MPO5309	53230				UPON INSPECTION OF BEARING (AFT) PTO GEAR FOUND WITH EXCESSIVE GALLING ON ONE BALL BEARING.  SUBMITTER STATED POSSIBLE C	AUSE FOR BEARING GALLING UNKNOWN.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999010800049	19990108	00049	EU  	1999	1	8	99ZZZX41         	1	19980303	G	6520	4619211901	CASE            		4619003003  	BOLKMS	105   	BO105C      	5626005	EU  										T/R GEARBOX	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	501AL	4587 	35   		11389	S58				GEARBOX SENT TO OVERHAUL SHOP FOR OIL LEAK.  FOUND TO BE LEAKING THROUGH CRACK.  CRACKED AT MOUNTING STUD BOSS.						1	G	7	2 	3U				H3EU
1999012900092	19990129	00092	GL  	1999	1	29	99ZZZX411        	2	19981211	G	7210	6889191	JOURNAL         		26063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	537AL	496  			CAG47251	53230	CAE847251			UPON DISASSEMBLY OF GEARBOX, TORQUE METER SUPPORT JOURNAL WAS FOUND TO HAVE MAGNESIUM SLIVERS IN JOURNAL BORE.  UPON FIN	DING MAGNESIUM SLIVERS IN TORQUE METER JOURNAL BORE, MEASURED JOURNAL AND FOUND IT TO BE OVER MFG SPECS 2.485 INCHES (MF	G MAX LIMIT 2.480 INCHES).  ALLISON INSTALLED THE OVERSIZE JOURNAL BY HAMMERING IN COVER CAUSING SLIVERS.  THESE SLIVERS	 COULD ALSO HAVE CAUSED DAMAGE TO THE OTHER GEARBOX PARTS.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999012900097	19990129	00097	GL  	1999	1	29	99ZZZX414        	2	19981223	G	7532	MS2007317	BOLT            		23005366    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					BLEED VALVE	STRETCHED       	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	537AL	496  			FF57528	53230				UPON DISASSEMBLY OF ENGINE FOR METAL, CHECKED BOLT TIGHTNESS BY MOVING COVER AND BODY ASSY.  ACTUAL TORQUE ON BOLTS WAS 	ONLY 15 INCHES/POUNDS.  THREE EACH BLEED VALVE COVER BOLTS WERE NOT TORQUED TO SPECS FROM FACTORY OR BOLTS ARE STRETCHIN	G AFTER ASSEMBLY AND TORQUING.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999012900098	19990129	00098	GL  	1999	1	29	99ZZZX415        	2	19981218	G	7210	6893673	GEAR            		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	537AL	496  			NN144758	53230	CAE847251			ENGINE WAS REMOVED FOR METAL CHIPS ON UPPER AND LOWER CHIP PLUGS.  UPON INSPECTION OF GEARBOX PARTS, FOUND PINION GEAR G	ALLING AND TORQUE METER GEAR SPALLING.  NOTE:  METAL CONTAMINATION CAUSED DAMAGE TO OTHER PARTS IN GEARBOX.  SUBMITTER S	UGGESTED IMPROPER MESHING BETWEEN TORQUE METER GEAR AND PINION GEAR WERE THE CAUSE FOR GALLING AND SPALLING OF GEARS.				1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999012900099	19990129	00099	GL  	1999	1	29	99ZZZX416        	2	19981222	G	7210	23004230	LINE            		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	CLOGGED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	537AL	496  			CAG47251	53230	CAE847251			UPON DISASSEMBLY OF GEARBOX, FOUND EXCESSIVE AMOUNTS OF SPLIT LINE SEALANT ON SPLIT LINE.  NOTE:  BEFORE DISASSEMBLY, FO	UND ALOT OF SEALANT ALONG SPLIT LINE, OUTSIDE OF GEARBOX.  UPON INSPECTION OF GEARBOX PARTS, FOUND SCAVENGE OIL TRANSFER	 TUBE NR 23004230 BLOCKED WITH SPLIT LINE SEALANT.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS EXCESSIVE AMOUNT OF SEALANT ON	 SPLIT LINE CAUSING SEALANT TO BEAD UP ALONG SPLIT LINE.  THE BEAD OF SEALANT BROKE OFF AND BLOCKED OIL PASSAGE.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999012900067	19990129	00067	WP  	1999	1	29	99ZZZX417        	1	19981222	G	5720		DOUBLER         			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  										WING	CRACKED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	141JR					19366				A PREVIOUSLY INSTALLED REPAIR DOUBLER CRACKED AT THE LOWER BOLT OF THE RIGHT DRAG STRUT ATTACH FITTING.  CRACK APPEARS T	O BE FROM IMPROPER INSTALLATION OF REPAIR DOUBLER.					2	L	7	2 	4R				A669
1999012900069	19990129	00069	EU  	1999	1	29	99ZZZX419        	1	19981230	G	2520	3410	PAN             			AIRBUS	320   	A320232     	3930326	EU  										PASSENGER SEAT	CRACKED         	D		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	406UA					454				DURING THE FIRST HEAVY MAINTENANCE VISIT (HMU-1) VIRTUALLY 100 PERCENT OF THE COACH SEATS IN THE PASSENGER CABIN WERE FO	UND TO HAVE SEAT PANS THAT WERE CRACKED AT THE FORWARD ATTACHMENT HOLES FOR THE SEAT PANS.  THESE ARE RECARO 720 SERIES 	SEATS INSTALLED IN A-320-232 AIRCRAFT.  THE SEAT MFG DESIGNATES THE SEAT PAN AS PRIMARY STRUCTURE FOR THE SEAT.  SUBMITT	ER STATED AN AD SHOULD BE ISSUED TO INSPECT THESE SEAT PANS FOR CRACKS EACH 90 DAYS AND FOR REMOVAL FROM SERVICE OF ANY 	PANS THAT ARE CRACKED.  THESE PANS ARE BEING REPLACED WITH NEW SEAT PANS THAT HAVE SAME DESIGN FLAWS WHICH WILL CRACK IN	 SERVICE.  THERE ARE 132 SEAT PANS ON THE ACFT.  THIS IS THE 6TH A-320 TO SHOW 100 PERCENT FAILURE OF THESE SEAT PANS.	2	L	7	2 	4F			RT	A28NM
1999012900070	19990129	00070	EA  	1999	1	29	99ZZZX420        	2	19981111	G	8500	61510	ENGINE          			CESSNA	177   	177RG       	2073709	CE  	LYC   	O320  	O320B3B     	41508	EA  					NOSE	MISOVERHAULED   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	09										MISISNG OIL RESTRICTOR ORFICE AND LOW OIL PRESSURE.  FACTORY OVERHAULED ENGINE FROM AVCO-LYCOMING WOULD NOT MAKE PROPER 	OIL PRESSURE AFTER INSTALLATION.  PROPELLER WOULD NOT RESPOND TO PITCH CHANGES.  AFTER SENDING PROPELLER AND GOVERNOR TO	 PROP SHOP, DISCOVERED THE OIL RESTRICTOR ORFICE WAS NOT INSTALLED IN THE NEW REPLACEMENT ENGINE.  AFTER THE PLUG WAS IN	STALLED, THE OIL PRESSURE WAS RED LINED AND WOULD NOT COME DOWN.  HAD WRONG OIL PRESSURE REGULATOR SPRING INSTALLED ALSO	.  ONE FOR FIXED PITCH PROP ENGINE.  SUBMITTER RECOMMENDED COMPARING NEW ENGINE TO OLD ENGINE BEFORE INSTALLATION.		1	H	7	1 	3O	3	O		A20CE   	E274
1999012900071	19990129	00071	SO  	1999	1	29	99ZZZX421        	1	19981201	G	5753		SPAR            			PIPER 	PA22  	PA22108     	7102204	SO  										TE FLAP	CORRODED        	D	L			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07										CORROSION ON AILERON AND FLAP SPARS.						1	H	7	1 	3O				1A6
1999012900072	19990129	00072	EU  	1999	1	29	99ZZZX422        	1	19981015	G	3411		LINE            			HWKSLY	DH125 	DH1251A     	4230106	EU  										PITOT	CLOGGED         	H				D				RETURN TO BLOCK         				O			OTHER                     			NR	NOT REPORTED   	1			WP	05	125BH					25027				ABNORMAL READING ON COPILOT'S ALTIMETER (DIFFERENCE = 1 THOUSAND FEET).  AFTER LANDING, STALL SYSTEM WAS CHECKED AND FOU	ND ALL 20 STATIC LINES IN AIRCRAFT EITHER PARTIALLY PLUGGED OR, IN THIS CASE, ONE LINE ALMOST COMPLETELY PLUGGED.  FOUND	 APPROXIMATELY 50 BOUGAINVILLEA LEAVES IN SYSTEM ALL CURLED UP AND WELL UP INTO THE LINES.  ANOTHER AIRCRAFT FOUND WITH 	SAME LEAVES IN IT.  THE LEAVES ARE PULLED INTO THE SYSTEM BY A SMALL WASP.  THERE WAS YELLOW POLLEN AROUND THE STATIC PO	RT HOLES.  IN SMALLER AIRCRAFT, THIS COULD BE A PROBLEM IN THE PITOT HEADS.  SUBMITTER STATED ALL PILOTS SHOULD BE NOTIF	IED OF THE PROBLEM ESPECIALLY IN SOUTHERN CALIFORNIA AREA.	2	L	7	2 	4J				A3EU
1999012900073	19990129	00073	SO  	1999	1	29	99ZZZX423        	2	19981201	G	7414	S4RN25	WASHER          			CESSNA	140   	140         	2071602	CE  	CONT  	O200  	O200A       	17020	SO  					MAGNETO	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	89513					8549				UPON MAGNETO AD NOTE INSPECTION NOTED:  SCREW RETAINING CAM LOOSE ON ROTATING MAGNET.  WASHER UNDER SCREW HAD ALMOST WOR	N AWAY SCREW HEAD.  INSTALLED NEW SCREW AND WASHER.					1	H	7	1 	3O	3	O	NC	A768    	E252
1999012900074	19990129	00074	EU  	1999	1	29	99ZZZX424        	1	19981006	G	3610	ACM28786	FILTER ASSY     	DUNLOP      		FOKKER	F27   	F27MK400    	4990626	EU  										PNEUMATIC SYSTEM	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05		7384 								3,400 PSI WORKING PRESSSURE AIR CAUSED THE PERFORATED PLATE TO CONFORM TO THE SHAPE OF THE CONCAVE OUTLET COVER AND THEN	 BREAK BETWEEN PERFORATIONS IN THE CENTER OF THE PLATE.  THE FELT FILTER THEN EXTRUDED THROUGH THE BREAK IN THE PERFORAT	ED PLATE AND INTO THE OUTLET PASSAGE OF THE OUTLET COVER REDUCING THE FILTER ASSY'S FLOW CAPACITY.  THE PERFORATED PLATE	 IS UNSUPPORTED IN THE CENTER AND IS UNABLE TO WITHSTAND PRESSURE CREATED WHEN FELT FILTER IS PARTIALLY CLOGGED OR COATE	D WITH ICE.  SUBMITTER SUGGESTED PERFORATED PLATE BE MADE STRONGER AND/OR SUPPORTED BY (PERFORATED) SUPPORT COLUMN AROUN	D THE FILTER OUTLET PASSAGE.	2	H	7	2 	4T				A817
1999012900075	19990129	00075	NM  	1999	1	29	99ZZZX425        	1	19980422	G	3230	654458211	HOUSING         		65445815    	BOEING	737   	737*        		NM  										HYD MOD PACKAGE	CRACKED         	B			C8ER	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	01										SHUT-OFF VALVE MODULAR PACKAGE ASSY, P/N 65-44581-5, RECEIVED FOR O/H.  UNIT REMOVED BECAUSE VALVE WAS LEAKING.   AFTER 	REMOVAL OF TWO SHUT-OFF VALVES, A 1.75 INCH CRACK WAS FOUND IN HOUSING, P/N 65-44582-11.  THE CRACK PROGRESSED FAR ENOUG	H TO ALLOW FLUID TO LEAK FROM THE TOP OF THE VALVES.  CRACK IS 1.75 INCHES LONG AND GOES COMPLETELY THROUGH THE .50 INCH	 THICK INTERNAL WALL OF THE HOUSING BETWEEN THE SHUT-OFF VALVES.  COMPONENT IS NOT SUBJECTED TO EXTERNAL LOADS AND CRACK	 DOES NOT START AT A STRESS RISER.  SUBMITTER STATED THIS IS SECOND HOUSING FOUND CRACKED IN THIS AREA.  FIRST CRACK SHO	RTER AND WAS A STRAIGHT LINE.  THIS CRACK IS JAGGED AND APPEARS TO FOLLOW THE GRAIN STRUCTURE.  REF:  OHM CH 32-43-22.	2	L	7	2 	4F			RT	A16WE
1999012900079	19990129	00079	CE  	1999	1	29	99ZZZX429        	1	19980511	G	3242		BRAKE           	CLEVELAND   		CESSNA	441   	441         	2076020	CE  										MLG	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	413PC					4410240				WHEN THE LEFT AND RIGHT MAIN LANDING GEAR IS RETRACTED, THE BRAKE ASSY, P/N 30-143, MAKES HOLES IN THE UPPER WING SKIN H	ONEYCOMB, P/N 5722311.  AT THE SAME TIME, THE BRAKE PISTONS ARE PUSHED INTO THE BRAKE HOUSING ALLOWING ENOUGH SPACE FOR 	THE BRAKE PADS, P/N 066-07300, TO FALL OUT IN-FLIGHT.  THE BRAKE ASSEMBLES ARE INSTALLED ON THE CESSNA 441 UNDER STC NR 	SA644GL.			1	L	7	2 	3T			RT	A28CE
1999010800051	19990108	00051	SW  	1999	1	8	99ZZZX43         	1	19981209	G	6210	206015001107	BLADE           			BELL  	206   	206L4       	1182110	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	171AL	1189 			A2216	52064				DISCOVERED DURING DAILY INPSECTION, HEAVY CORROSION ALONG TRAILING EDGE (APPEARS TO BE INTERGRANNULAR CORROSION IN TRAIL	ING EDGE EXTRUSION).					1	G	7	1 	3U			NC	H2SW
1999012900080	19990129	00080	CE  	1999	1	29	99ZZZX430        	1	19980511	G	3242		BRAKE           	CLEVELAND   		CESSNA	441   	441         	2076020	CE  										MLG	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	441BL					4410080				WHEN THE LEFT AND RIGHT MAIN LANDING GEARS ARE RETRACTED, THE BRAKE ASSY, P/N 30-143, MAKES HOLES IN THE UPPER WING SKIN	 HONEY COMB, P/N 572231-1.  AT THE SAME TIME, THE BRAKE PISTONS ARE PUSHED INTO THE BRAKE HOUSING ALLOWING ENOUGH SPACE 	FOR THE BRAKE PADS, P/N 066-07300, TO FALL OUT IN-FLIGHT.  THESE BRAKE ASSEMBLIES ARE INSTALLED ON THE CESSNA 441 UNDER 	STC NR SA644GL.			1	L	7	2 	3T			RT	A28CE
1999012900081	19990129	00081	CE  	1999	1	29	99ZZZX431        	1	19981101	G	3246		WHEEL           	MCAULY      		CESSNA	210   	210L        	2073448	CE  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	444CL	2669 				21060910				MAIN WHEELS REMOVED DURING ANNUAL INSPECTION, FOUND ALL BOLT HOLES IN HUBS CRACKED.  PREVIOUS WHEELS HAVE AD 74-13 6 ASS	OC WITH THEM.  AD REQUIRES THE SERIES OF ATTACH HOLES IN THE HUBS ENLARGED FROM .25 INCH FASTENER TO .3125 INCH FASTENER	 BY OVERSIZING THE HOLES AND TAPING.  WHEELS ADDRESSED IN THIS REPORT ARE NOT SUBJECT IN THE BODY OF THIS AD, YET HAVE B	EEN MODIFIED TO THE LARGER BOLT HOLES.  MODIFICATION LEAVES MINIMAL WALL THICKNESS BETWEEN THE HOLE AND OUTER DIA OF HUB	 EDGE.  SUBMITTER STATED MINIMAL THICKNESS COMBINED WITH NUMEROUS CYCLES OF BOLT REMOVAL AND INSTALLATION INITIATED THES	E CRACKS.  RECOMMEND ALL MCCAULEY WHEELS OF THIS SERIES MODIFIED TO .3125 INCH BOLT STYLE BE INSPECTED FOR CRACKS.	1	H	7	1 	3O				3A21
1999010800052	19990108	00052	SW  	1999	1	8	99ZZZX44         	1	19981209	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	367AL	1780 			A2437	51443				DISCOVERED DURING DAILY INSPECTION, HEAVY CORROSION ALONG TRAILING EDGE (APPEARS TO BE INTERGRANNULAR CORROSION IN TRAIL	ING EDGE EXTRUSION).					1	G	7	1 	3U				H2SW
1999012900717	19990129	00717	NM  	1999	1	29	99ZZZX442        	1	19981204	G	5320		WEB             			BOEING	727   	727227      	1384078	NM  										BS 1110-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	70755					21366				DURING A C-CHECK, CORROSION WAS NOTED AT FS 1110 - FS 1130 UNDERSIDE OF CUSP WEB RBL 64.						2	L	7	3 	4F				A3WE
1999010800053	19990108	00053	SW  	1999	1	8	99ZZZX45         	1	19981209	G	6210	206015001107	BLADE           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	365AL	648  			A2523	51376				DISCOVERED DURING DAILY INSPECTION, HEAVY CORROSION ALONG T/R, (APPEARS TO BE INTERGRANNULAR CORROSION IN TRAILING EDGE 	EXTRUSION).					1	G	7	1 	3U				H2SW
1999010800054	19990108	00054	SW  	1999	1	8	99ZZZX46         	1	19981209	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1067D	727  			A2760	45435				DISCOVERED DURING DAILY INSPECTION, HEAVY CORROSION ALONG TRAILING EDGE (APPEARS TO BE INTERGRANNULAR CORROSION IN TRAIL	ING EDGE EXTRUSION).					1	G	7	1 	3U				H2SW
1999123100327	19991231	00327	CE  	1999	12	31	99ZZZX4678       	1	19980920	G	2731		PUSH RODS       			CESSNA	310   	310K        	2074228	CE  										ELEVATOR	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	711CG	2000 				310K0015				DURING POST-CRASH EXAMINATION OF THE CONTROL SYSTEM, THE TYPICAL AILERON, ELEVATOR, AND RUDDER TRIM TAB ACTUATING RODS W	ERE FOUND INTERNALLY RUSTED AND CORRODED.  THE TUBES HAVE ROD/FORKS ON EACH END AND APPEAR HOLLOW OR OPEN THROUGH THE FO	RKED END ALLOWING WATER TO ENTER THE TUBES.  NO INTERIOR PROTECTION WAS FOUND.				1	L	7	2 	3O				3A10
1999010800055	19990108	00055	NE  	1999	1	8	99ZZZX47         	1	19980727	G	6210	7615009100051	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	DEBONDED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	712AL	7639 			A08601424	760280				DISCOVERED DURING 500-HOUR INPSECTION, TIP RIB STRAP DEBONDED, (RECURRING PROBLEM).  TIP RIB STRAPS REPLACED BY C.T.I. 0	4-04-97, TT:  6,245.1 HOURS. 05-19-97, TT:  6,340.1 HOURS, AND 12-23-97, TT:  7,207.8 HOURS.					1	G	7	2 	3U				H1NE
1999020500017	19990205	00017	NM  	1999	2	5	99ZZZX471        	1	19981204	G	5330		SKIN            			BOEING	727   	7272B7      	138407L	NM  										BS 680	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	907PG					22164				DURING A C-CHECK, CORROSION WAS NOTED ON SKIN UNDER LEVELING COMPOUND AFT OF STA 680 BETWEEN S28R AND S28L.						2	L	7	3 	4F				A3WE
1999020500018	19990205	00018	NM  	1999	2	5	99ZZZX472        	1	19981214	G	5311		FRAME           			BOEING	727   	7272B7      	138407L	NM  										BS 740-870	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	907PG					22164				DURING A C-CHECK, CORROSION WAS NOTED ON AFT FRAME OF FORWARD ADF LOOP ANTENNA DELTA KEEL BEAM AREA FS 740 - FS 840 (BL 	ZERO).					2	L	7	3 	4F				A3WE
1999020500019	19990205	00019	NM  	1999	2	5	99ZZZX473        	1	19981204	G	5311		FRAME           			BOEING	727   	7272B7      	138407L	NM  										STA 560	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	907PG					22164				DURING A C-CHECK, CORROSION WAS NOTED ON FRAME AT FS 560 UNDER TRANS PANEL AT S26R.						2	L	7	3 	4F				A3WE
1999020500020	19990205	00020	NM  	1999	2	5	99ZZZX474        	1	19981207	G	5330		SKIN            			BOEING	727   	7272B7      	138407L	NM  										BS 500	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION ON SKIN BULGE AT BS 500 AT AREA BETWEEN STR 26 - STR 27R.						2	L	7	3 	4F				A3WE
1999020500021	19990205	00021	NM  	1999	2	5	99ZZZX475        	1	19981204	G	5320		ANGLE           			BOEING	727   	7272B7      	138407L	NM  										FUSELAGE	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED IN AFT AIR STAIRS, RT SUPPORT ARM CASTING.  (THE ZEE ANGLES WERE CORRODED).						2	L	7	3 	4F				A3WE
1999020500022	19990205	00022	NM  	1999	2	5	99ZZZX476        	1	19981207	G	5320		BRACKET         			BOEING	727   	7272B7      	138407L	NM  										BS 1070	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON FLOOR TRACK BRACKET BS 1070 LBL 50.						2	L	7	3 	4F				A3WE
1999020500023	19990205	00023	NM  	1999	2	5	99ZZZX477        	1	19981207	G	5311		FRAME           			BOEING	727   	7272B7      	138407L	NM  										STA 720A	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED IN FORWARD BAGGAGE PIT STA 720A BETWEEN S28L AND S27L.						2	L	7	3 	4F				A3WE
1999020500024	19990205	00024	NM  	1999	2	5	99ZZZX478        	1	19981204	G	5320		PLATE           			BOEING	727   	7272B7      	138407L	NM  										LAVATORY	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON FORWARD LAVATORY FLOOR PLATE IN SEVERAL PLACES.						2	L	7	3 	4F				A3WE
1999020500025	19990205	00025	NM  	1999	2	5	99ZZZX479        	1	19981207	G	5315		FLOORBEAM       			BOEING	727   	7272B7      	138407L	NM  										STA 344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DUIRNG A C-CHECK, CORROSION WAS NOTED ON TOP CHORD OF FLOOR BEAM, STA 344 - LBL 44 TO RBL 12.						2	L	7	3 	4F				A3WE
1999020500026	19990205	00026	NM  	1999	2	5	99ZZZX480        	1	19981204	G	5347		SEAT TRACK      			BOEING	727   	7272B7      	138407L	NM  										BS 344-380	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK STA 344 - STA 380, LBL 24.						2	L	7	3 	4F				A3WE
1999020500027	19990205	00027	NM  	1999	2	5	99ZZZX481        	1	19981207	G	5347		SEAT TRACK      			BOEING	727   	7272B7      	138407L	NM  										BS 344	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK STA 344, APPROXIMATELY LBL 42.						2	L	7	3 	4F				A3WE
1999020500028	19990205	00028	NM  	1999	2	5	99ZZZX482        	1	19981207	G	5315		FLOORBEAM       			BOEING	727   	7272B7      	138407L	NM  										BS 380	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON TOP CHORD OF FLOORBEAM, STA 380, RBL 55.						2	L	7	3 	4F				A3WE
1999020500029	19990205	00029	NM  	1999	2	5	99ZZZX483        	1	19981207	G	5347		SEAT TRACK      			BOEING	727   	7272B7      	138407L	NM  										BS 1110-1130	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON SEAT TRACK STA 1110 - STA 1130, RBL 25.						2	L	7	3 	4F				A3WE
1999020500030	19990205	00030	NM  	1999	2	5	99ZZZX484        	1	19981204	G	5311		FRAME           			BOEING	727   	7272B7      	138407L	NM  										BS 950	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON FRAME AND WEB OF FLOORBEAM FS 950 BETWEEN LBL 45.50 TO FUSELAGE.						2	L	7	3 	4F				A3WE
1999020500033	19990205	00033	GL  	1999	2	5	99ZZZX487        	2	19981130	G	7210	6893673	GEAR            		23063393    	BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					GEARBOX	MAKING METAL    	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467AL	1995 			NN144864	53190	CAE847188			ENGINE WAS REMOVED FOR TIME CHANGE TURBINE AND COMPRESSOR.  UPON INSPECTION OF CHIP PLUGS, FOUND METAL CHIPS.  DISASSEMB	LED AND FOUND TORQUE METER GEAR AND PINION GEAR GALLING CAUSING SOME METAL CONTAMINATION DAMAGE TO THE PARTS.  IMPROPER 	MESHING BETWEEN TORQUE METER GEAR AND PINION GEAR WAS CAUSE FOR GALLING.  SECONDARY DAMAGE:  PINION GEAR PN 6893672, SN 	NN76158. TT: 1,994.7 HOURS.			1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1999020500035	19990205	00035		1999	2	5	99ZZZX489        	1	19981230	G	2560	15D22129	EVACUATION SLIDE	AIRCRUISERS 																FUSELAGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					7028466					DURING OVERHAUL INSPECTION OF UNIT, THE INFLATION HOSE WAS FOUND DISCONNECTED FROM CYLINDER.  THE HALF-TIE RESTRAINT (SE	CONDARY RESTRAINT) WAS 2 STRANDS OF COTTON THREAD.  MAINTENANCE MANUAL REQUIRES 12-PLY CORD 276 T/IVA.  THE INFLATION VA	LVE WAS LEFT OPEN.  UNIT WAS OVERHAULED 2.5 YEARS AGO.
1999010800057	19990108	00057	SW  	1999	1	8	99ZZZX49         	1	19981203	G	6320	6893672	GEAR            		23063393    	BELL  	407   	407         		SW  										GEARBOX	GALLED          	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	477AL	649  			NN76905	53203				DISASSEMBLED, CLEANED AND INSPECTED AND FOUND EXCESSIVE GALLING ON PINION AND T/M GEARS.  PINION GEAR HAD EXCESSIVE GALL	ING ON GEAR TEETH POSSIBLY DUE TO IMPROPER MESHING OF T/M AND PINION GEARS.  SECONDARY DAMAGE:  T/M GEAR P/N 6893673 S/N	 NN145514, TT:  648.9 HOURS - GALLING ON GEAR TEETH.				1	G	7	1 	3U			O	H2SW
1999020500036	19990205	00036		1999	2	5	99ZZZX490        	1	19981230	G	2560	15022129	EVACUATION SLIDE	AIRCRUISERS 																FUSELAGE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19					7364666					DURING OVERHAUL INSPECTION, THE INFLATION HOSE WAS FOUND DISCONNECTED FROM CYLINDER ASSEMBLY.  THE SECONDARY RESTRAINT (	TIE-BACK) USED WAS 2 STRANDS OF COTTON THREAD.  MANUFACTURER'S MM REQUIRES USE OF 12-PLY CORD, 276 T/IVA.  UNIT WAS LAST	 OVERHAULED 2.5 YEARS AGO.
1999020500087	19990205	00087	SO  	1999	2	5	99ZZZX491        	2	19981025	G	8530		CYLINDER        			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					ENGINE	CRACKED         	B			ISOR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	05	5453V	1852 				R1722299	355310			DURING INSPECTION FOR AN OIL LEAK, FOUND THE ENGINE CYLINDER HEAD CRACKED BEHIND THE ROCKER COVER AREA AND EXTENDING BEH	IND THE INTAKE VALVE SPRAY.  ONE DAY LATER, FOUND SIMILAR CRACK ON A DIFFERENT AIRPLANE WITH THE SAME MODEL ENGINE.  AFT	ER CLOSE INSPECTION, UNABLE TO DETERMINE REASON.  FIRST AIRCRAFT CESSNA R172K, ENGINE IO360K, S/N 355310.  SECOND AICRAF	T PIPER PA34200T, ENGINE LTSIO360E, S/N 306232.			1	H	7	1 	3O	3	O		3A17    	E1CE
1999020500090	19990205	00090	CE  	1999	2	5	99ZZZX494        	1	19980106	G	2842	S33312	TRANSMITTER     			CESSNA	172   	172R        	2072401	CE  										LT WING FUEL	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	426ER	441  				17280647				DURING A POST INSPECTION RUN-UP, THE LEFT FUEL GAUGE NEEDLE WAS READING ERRATIC (FULL TO ZERO).  INSPECTION OF THE FUEL 	INDICATION SYSTEM FOUND THE LEFT FUEL TANK SENDER BAD.					1	H	7	1 	3O			NT	3A12
1999010800015	19990108	00015	CE  	1999	1	8	99ZZZX5          	1	19980622	G	5510	2332000	STRINGER        			LEAR  	24    	24          	5170302	CE  										HORIZONTAL STAB	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	241JA	12608				131				DISCOVERED SEVERAL SMALL CRACKS INSIDE HORIZONTAL STABILIZER LOCATED AT LEFT AND RIGHT BL 19.40.  CRACKS WERE NOTED DURI	NG SCHEDULED INSPECTION OF THE AREA.  A REPAIR WAS PERFORMED BY AN FAA CERTIFIED REPAIR STATION, FOLLOWING N.D.T. CONFIR	MATION OF THE CRACKS.  CRACKS WERE IN THE BULB STRINGER AT THE RIB LOCATED RT BL 19.40				2	L	7	2 	4J				A10CE
1999020500096	19990205	00096	SO  	1999	2	5	99ZZZX500        	1	19980107	G	5513	6358500	TRIM TAB        			PIPER 	PA28  	PA28236     	7102815	SO  										RT/LT STABILATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	236WH	2000 				288511012				DURING ANNUAL INSPECTION, FOUND TRIM TAB CRACKED APPROXIMATELY 60 PERCENT AROUND BASE OF ATTACH ARM, P/N 65248-000.  DAM	AGE EXTENDED THROUGH INBOARD RIB, P/N 63887-01.  SUBMITTER RECOMMENDED CLOSER PRE-FLIGHT AND MAINTENANCE INSPECTION OF T	HIS AREA AS IT CAN ONLY BE SEEN BY LOOKING UNDER STABILATOR.				1	L	7	1 	3O				2A13
1999020500097	19990205	00097	SO  	1999	2	5	99ZZZX501        	1	19980107	G	5513	6358501	TRIM TAB        			PIPER 	PA28  	PA28236     	7102815	SO  										RT/LT STABILATOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	236WH	2000 				288511012				DURING ANNUAL INSPECTION, FOUND TRIM TAB CRACKED APPROXIMATELY 60 PERCENT AROUND BASE OF ATTACH ARM, P/N 65248-000.  DAM	AGE EXTENDED THROUGH INBOARD RIB, P/N 63887-01.  SUBMITTER RECOMMENDED CLOSER PRE-FLIGHT AND MAINTENANCE INSPECTION OF T	HIS AREA AS IT CAN ONLY BE SEEN BY LOOKING UNDER STABILATOR.				1	L	7	1 	3O				2A13
1999020500098	19990205	00098	CE  	1999	2	5	99ZZZX502        	1	19981228	G	1220	15W50	OIL             			CESSNA	172   	172R        	2072401	CE  										ENGINE	MISMANUFACTURED 	B			DYCR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	07	173QS	297  				17280460				DID ROUTINE OIL CHANGE AT 100-HOUR/ANNUAL INSPECTION.  ALL NORMAL UNTIL RUN-UP AT COMPLIANCE OF INSPECTION.  LOW OIL PRE	SSURE AT ALL POWER SETTINGS.  SPSI AT IDLE.  TROUBLESHOT SITUATION AND FOUND BAD OIL FROM 2 EACH 1-GALLON JUGS (WERE SEA	LED) FROM OIL INVENTORY.  DRAINED OIL.  REMOVED FILTER AND INSTALLED NEW OIL.  OPS CHECKED NORMAL.  SUBMITTER SUGGESTED 	GOOD RUN-UP/WARM-UP AND DOUBLE CHECK OIL PRESSURE.			1	H	7	1 	3O			NT	3A12
1999020500099	19990205	00099	EU  	1999	2	5	99ZZZX503        	1	19980924	G	3060	XA95110033	SEAL            			BRAERO	DH125 	BAE125800A  	1500285	EU  										PUMP	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	25	270HC		3    			258020				AFTER 3.4 HOURS TSO, PUMP BEGAN LEAKING FROM SHAFT SEAL.  THIS WAS THE THIRD PUMP INSTALLED IN LAST 12 MONTHS.  PART S/N	 L167-B6.					2	L	7	2 	4F			RT	A3EU
1999020500100	19990205	00100	EU  	1999	2	5	99ZZZX504        	1	19980929	G	3060	XA9511E0033	PUMP            			BRAERO	DH125 	BAE125800A  	1500285	EU  										PROP DEICE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	25	270HC		275  			258020				AFTER 11 MONTHS, PUMP BEGAN TO LEAK FROM SHAFT SEAL.  SUBMITTER STATED THIS WAS THE FIRST PUMP TO LEAK IN 12 MONTHS OF T	HREE TOTAL TO LEAK.					2	L	7	2 	4F			RT	A3EU
1999020500101	19990205	00101	EU  	1999	2	5	99ZZZX505        	1	19980929	G	3060	XA9511E0033	PUMP            			BRAERO	DH125 	BAE125800A  	1500285	EU  										PROP DEICE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	25	270HC		6    		67285	258020				AFTER 6 HOURS TSO, PUMP BEGAN TO LEAK FROM SEAL BETWEEN MOTOR AND PUMP.						2	L	7	2 	4F			RT	A3EU
1999020500102	19990205	00102	SO  	1999	2	5	99ZZZX506        	1	19981210	G	3260	12H214	SWITCH          		4550402     	PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	FAILED          	G				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			GL	15	74972				P31350256	317305123				UPON GEAR EXTENSION FOR LANDING, RIGHT MAIN GEAR LIGHT DID NOT ILLUMINATE.  CYCLED GEAR, NO HELP.  FLY-BY TOWER AND GEAR	 APPEARED TO BE DOWN AND LOCKED.  LANDED WITHOUT INCIDENT.  DOWNLOCK SWITCH REPLACED AND GEAR RETRACTION ACCOMPLISHED. S	UBMITTER RECOMMENDED REPLACING THE GEAR SWITCHES EVERY TWO YEARS AND SIMULTANEOUSLY WITH GEAR REPLACEMENT.				1	L	7	2 	3O				A20SO
1999020500103	19990205	00103	GL  	1999	2	5	99ZZZX507        	3	19980728	G	6114		HUB             			CESSNA	185   	A185E       	2072818	CE  						MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07								744955		HUB WAS SUBMITTED FOR OVERHAUL FROM CUSTOMER SUPPLIED SOURCE.  HUB CONTAINED CRACKS IN BOTH BLADE RETENTION SOCKETS.  CR	ACKS WERE DETECTED USING EDDY CURRENT METHOD.					1	H	7	1 	3O				3A24    		5	C	P3EA
1999020500104	19990205	00104	SO  	1999	2	5	99ZZZX508        	1	19981001	G	7922	SL53E	VERNATHERM      	SUPAIRPART  		PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	FAILED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	626JD	1    			19600	32R7680084				NEW VERNATHERM INSTALLED IN PA32R300 LYC IO540K1A5.  COULD NOT CONTROL OIL TEMPERATURE.  REPLACED PART, CORRECTED CONDIT	ION.					1	L	7	1 	3O	3	O		A3SO    	1E4
1999020500489	19990205	00489	GL  	1999	2	5	99ZZZX512        	3	19980930	G	6114		HUB             			CESSNA	411   	411A        	2075904	CE  						MCAULY	3AF34C	3AF34C74    	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	210Z					4110292		751006		CRACK WAS FOUND DURING PENETRANT INSPECTION ON OUTSIDE OF NR 1 SOCKET.  PROPELLER WAS BEING INSPECTED PER S/N 93-112 AD 	95-24-11.					1	L	7	2 	3O				A7CE    		5	C	P22EA
1999020500492	19990205	00492	SW  	1999	2	5	99ZZZX515        	1	19981103	G	6220	407010103101	PITCH HORN      		407010100111	BELL  	407   	407         		SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	1252 			A838	53172				DISSIMILAR METAL CAUSED CORROSION UNDER BUMPER PLATE AND  DOWEL PIN HOLES.						1	G	7	1 	3U			O	H2SW
1999020500493	19990205	00493	SW  	1999	2	5	99ZZZX516        	1	19981103	G	6220	407010103101	PITCH HORN      		407010100111	BELL  	407   	407         		SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	1252 			A840	53172				DISSIMILAR METAL CAUSED CORROSION UNDER BUMPER PLATE AND  DOWEL PIN HOLES.						1	G	7	1 	3U			O	H2SW
1999020500494	19990205	00494	SW  	1999	2	5	99ZZZX517        	1	19981103	G	6220	407010103101	PITCH HORN      		407010100111	BELL  	407   	407         		SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	1252 			A842	53172				DISSIMILAR METAL CAUSED CORROSION UNDER BUMPER PLATE AND  DOWEL PIN HOLES.						1	G	7	1 	3U			O	H2SW
1999020500495	19990205	00495	SW  	1999	2	5	99ZZZX518        	1	19981103	G	6220	407010103101	PITCH HORN      		407010100111	BELL  	407   	407         		SW  										MAIN ROTOR	CORRODED        	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL	1252 			A836	53172				DISSIMILAR METAL CAUSED CORROSION UNDER BUMPER PLATE AND  DOWEL PIN HOLES.						1	G	7	1 	3U			O	H2SW
1999010800088	19990108	00088	SO  	1999	1	8	99ZZZX52         	2	19980921	G	7261	632623A23	PUMP            		632623A22   						CONT  	O520  	GTSIO520L   	17032	SO  					OIL SYSTEM	MISMANUFACTURED 	D		A		K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			WP	07							604451			NEW TCM OIL PUMP HOUSING WAS PURCHASED FORM LOCAL AVIALL DISTRIBUTION BRANCH.  UPON VISUAL INSPECTION OF PART PRIOR TO A	SSY AND DIMENSIONAL CHECKS, NOTED THE CHAMBER DEPTH WAS BELOW MINIMUM SPECS PER MANUAL.  FURTHER INVESTIGATION REVEALED 	MACHINING STEP WAS NOT CLEANED UP IN THE RADIUS.  THIS CAUSES THE GEARS TO SIT UP HIGHER IN THE CHAMBER BORE AND WHEN TH	E SCAVENGE PUMP HOUSING IS INSTALLED OVER THE TOP, THERE IS NO END CLEARANCE CAUSING GEARS TO BIND UP.  SUBMITTER RECOMM	ENDED COMPLETE VISUAL AND DIMENSIONAL CHECK ON ALL HOUSINGS PRIOR TO ASSY.  (THIS IS THE SECOND HOUSING FOUND, WITH THES	E CIRCUMSTANCES).						3	O			E7CE
1999020500499	19990205	00499	CE  	1999	2	5	99ZZZX522        	1	19981231	G	5510		BOLTS           			CESSNA	188   	T188C       	2073012	CE  										HORIZ STABILIZER	LOOSE           	H		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	11	2034J	3122 				T18803339T				DURING ANNUAL INSPECTION, HORIZONTAL STABILIZER WAS FOUND LOOSE.  REAR ATTACH BOLTS HAD LOOSENED.  THIS IS SECOND AIRCRA	FT.  SUBMITTER RECOMMENDS EXTRA CARE DURING INSPECTIONS.					1	L	7	1 	3O				A9CE
1999020500501	19990205	00501	EU  	1999	2	5	99ZZZX524        	1	19980508	G	5520	TB1027088001	SUPPORT         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										ELEVATOR	CRACKED         	B		A	FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	20TK	3005 				748				REMOVED LEFT AND RIGHT ELEVATOR AND RUDDER CONTROL SUPPORT BELLCRANKS DUE TO WORN BELLCRANKS CAUSING PLAY IN CONTROLS. U	PON REMOVAL OF THE PARTS AND A THOROUGH INSPECTION, CRACKS WERE NOTED IN THE FOUR CORNERS OF THE ATTACH POINTS, THAT ATT	ACH THE SUPPORTS TO THE REAR BULKHEAD.  NOTE:  CRACKS WERE NOT VISUAL WITH BELLCRANKS INSTALLED.  SUBMITTER SUGGESTED RE	MOVING BELLCRANKS PERIODICALLY TO INSPECT.			1	L	7	1 	3O			NT	A51EU
1999020500502	19990205	00502	EU  	1999	2	5	99ZZZX525        	1	19980508	G	5520	TB1027088002	SUPPORT         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										ELEVATOR	CRACKED         	B			FGQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	01	20TK	3005 				748				REMOVED LEFT AND RIGHT ELEVATOR AND RUDDER CONTROL SUPPORT BELLCRANKS DUE TO WORN BELLCRANKS CAUSING PLAY IN CONTROLS. U	PON REMOVAL OF THE PARTS AND A THOROUGH INSPECTION, CRACKS WERE NOTED IN THE FOUR CORNERS OF THE ATTACH POINTS, THAT ATT	ACH THE SUPPORTS TO THE REAR BULKHEAD.  NOTE:  CRACKS WERE NOT VISUAL WITH BELLCRANKS INSTALLED.  SUBMITTER SUGGESTED RE	MOVING BELLCRANKS PERIODICALLY TO INSPECT.			1	L	7	1 	3O			NT	A51EU
1999020500504	19990205	00504		1999	2	5	99ZZZX527        	1	19981209	G	3242	66003309	BRAKE           		9543992     															MLG	MISMANUFACTURED 	B			JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09										ORDERED AND RECEIVED FROM LEARJET, ROTATING DISC, P/N 943992.  THE KEY SLOTS WERE BEVELED.  BOMBARDIER LEARJET AND AIRCR	AFT BRAKING SYSTEMS WERE CALLED AND WERE INFORMED THE KEY SLOTS SHOULD NOT BE BEVELED, BUT SQUARE.
1999010800089	19990108	00089	EU  	1999	1	8	99ZZZX53         	1	19980930	G	2130		LINE            			AMD   	FALC10	FALCON10    	2730101	EU  										CABIN AIR	CRACKED         	H				A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			GL	07	256W					151				SMALL CRACK DEVELOPED IN-FLIGHT ON ALUMINUM LINE, P/N F10 22157, BETWEEN TEE AND RIGHT HAND OUTFLOW VALVE IN MANUAL CONT	ROL SYSTEM.  ALLOWED CABIN AIR PRESSURE IN-FLIGHT (ACFT AT 18,000 FEET) INTO LINE RESULTING IN THE CLOSING OF BOTH OUTFL	OW VALVES.  CABIN PRESSURE BEGAN TO INCREASE.  CREW LOST CONTROL OF PRESSURIZATION IN NORMAL, EMERGENCY (MANUAL), AND CA	BIN DUMP.  CABIN NEVER REACHED THE OVER-PRESSURE LIMIT AS CREW TURNED OFF CABIN AIR TO CONTROL CABIN.  AIRCRAFT RETURNED	 TO BASE AND CABIN LEAK RATE ALLOWED FOR AN UNPRESSURIZED LANDING.		2	L	7	2 	4F				A33EU
1999020500509	19990205	00509	CE  	1999	2	5	99ZZZX532        	1	19981210	G	3110		INSULATION      			CESSNA	182   	R182        	2072734	CE  										INSTRUMENT PANEL	DETERIORATED    	B			EHHR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	17	17059	7800 			07134829	R18201915				FOAM INSULATION ON UNDERSIDE OF INSTRUMENT PANEL GLARESHIELD DRIED OUT FROM AGE FLAKING POWDERY MATERIAL FALLING DOWN ON	 INSTRUMENTS.  ENGINE INSTRUMENT CLUSTER NOT SEALED AND HAS BEEN CAUSING ENGINE INSTRUMENTS TO BECOME ERRATIC.  HAD TO C	HANGE FUEL QUANTITY GAUGES BECAUSE OF THIS PROBLEM.  REMOVED INSULATION AND SEALED ENGINE INSTRUMENT CLUSTER.				1	H	7	1 	3O			RT	3A13
1999020500513	19990205	00513	SO  	1999	2	5	99ZZZX536        	2	19981222	G	7260		T DRIVE         			BEECH 	35    	C35BEECH    	1151508	CE  	CONT  	E225  	E2258       	17015	SO  					ACCESSORY DRIVE	LEAKING         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	01	8945A	940  	9    			D2699	363830R			ENGINE T-DRIVE (THIS UNIT MOUNTS THE ENGINE FUEL PUMP AND PROP GOVERNOR ONTO A SINGLE ACCESSORY PAD) DEVELOPED A LEAK. U	NIT  REMOVED AND SENT FOR OVERHAUL.  UNIT WAS CERTIFIED AND RE-INSTALLED ONLY TO FIND THE GOVERNOR DRIVE GEAR TO BE THE 	WRONG ONE.  UNIT REWORKED AND RETURNED.  UNIT RE-INSTALLED AND OPS CHECKED GOOD.  8.37 HOURS LATER, A GEAR HOWL WAS NOTE	D ON GROUND RUN.  T-DRIVE REMOVED AND INSPECTED.   GOVERNOR DRIVE BEARINGS HAD DISINTEGRATED CAUSING METAL TO BE SPREAD 	THROUGHOUT THE ENGINE OIL SYS.  SUBMITTER SUGGESTED CAUSE AS INCORRECT OVERHAUL PROCEDURES USED TO ASSEMBLE UNIT.		1	L	7	1 	3O	3	O		A777    	E267
1999020500514	19990205	00514	CE  	1999	2	5	99ZZZX537        	1	19981128	G	3230	35380094	MOTOR           			BEECH 	35    	V35B        	1151548	CE  										MLG	FAILED          	D				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SO	05	449T				6753	D9153				LANDING GEAR MOTOR FAILED RESULTING IN SMOKE IN THE COCKPIT.  REMOVED LANDING GEAR MOTOR, DISASSEMBLED, FOUND BRUSHES IN	 GOOD CONDITION.  FOUND ARMATURE BURNT AND FIELD COIL ASSEMBLY BURNT.  BEARINGS WERE FOUND TO BE IN GOOD CONDITION.  SUB	MITTER SUGGESTED A POSSIBLE CAUSE AS FAILURE OR INTERNAL SHORTED ARMATURE.				1	L	7	1 	3O				3A15
1999010800090	19990108	00090	GL  	1999	1	8	99ZZZX54         	2	19981008	G	7321	55629	FCU             			CESSNA	525   	525         	2076601	CE  	WILINT	FJ44  	FJ44        	66000	GL  					LT ENGINE	MALFUNCTIONED   	B			NE3R	O				OTHER                   				X			ENGINE FLAMEOUT           			AP	APPROACH       	1			WP	25	525J	343  			RF11534086	5250184	1379			OPERATOR REPORTED DURING DESCENT FROM FL 410 WHEN POWER LEVERS WERE RETARDED, LEFT ENGINE ROLLED BACK AND FLAMED OUT.  A	 SUBSEQUENT AIR-START WAS NOT ATTEMPTED.  OPERATOR DESCENDED AND LANDED AT DESTINATION AIRPORT.  TROUBLESHOOTING OF DISC	REPANCY PER MM REVEALED NO ABNORMALITIES.  WILLIAMS/ROLLS WAS CONTACTED AND RECOMMENED REMOVAL OF FUEL CONTROL UNIT FOR 	EVALUATION.   INSTALLED REPLACEMENT FUEL CONTROL UNIT AND CHECKED FUEL NOZZLE FLOW PER SUGGESTION FROM WILLIAMS/ROLLS. N	OTE:  WAITING FOR FUEL CONTROL UNIT EVALUATION.		1	L	7	2 	4F	4	F	RT	A1WI    	E3GL
1999020500518	19990205	00518	EA  	1999	2	5	99ZZZX541        	1	19980518	G	2730	72760182001	ROD             			DHAV  	DHC7  	DHC7102     	2802708	EA  										ELEVATOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	176RA					76				DURING MAINTENANCE FOUND PUSH ROD CRACKED.  MATERIAL IS PUSHED IN AN OUTWARD DIRECTION, INSPECTED AND FOUND WRONG PART N	UMBER ROD END BEARING INSTALLED AT TOP OF ROD.  ROD END BEARING HAS SLOT CUT IN THREADS.  SUBMITTER SUSPECTS WATER ENTER	ED INTERIOR OF TUBE THROUGH SLOT, FROZE, AND CRACKED PUSH ROD.				2	H	7	4 	4T				A20EA
1999020500519	19990205	00519	SO  	1999	2	5	99ZZZX542        	1	19981210	G	5753		WING FLAP       			PIPER 	PA23  	PA23        	7102302	SO  										T/E FLAP	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	3028P					23939				AIRCRAFT REMOVED FROM STORAGE.  ANNUAL INSPECTION FOUND THE FOLLOWING:  GRASPING TRAILING EDGE OF LEFT FLAP, NO CLUNKING	 SOUND OF HINGES, RATHER, MUSHY FEELING.  FLAP SPAR AND DOUBLER CRACKED ALONG UPPER AND LOWER HINGE MOUNTING BOLTS.  NO 	APPARENT DAMAGE WHICH WOULD CAUSE INBOARD HINGE ACTUATOR MOUNTING FAILURE.  NORMAL USE.				1	L	7	2 	3O				1A10
1999020500520	19990205	00520	CE  	1999	2	5	99ZZZX543        	1	19980320	G	7600	016A43015261	CONTROL CABLE   			MTSBSI	MU2   	MU2B26      	5780408	CE  										RT ENGINE	FRAYED          	B			FJTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	475CA	2536 				319				DURING 500-HOUR MANUFACTURER'S INSPECTION, FOUND RIGHT ENGINE POWER LEVER CABLE FRAYED AT LOWER AFT PULLEY CLUSTER AT FS	 5300.					1	H	7	2 	3T			RT	A10SW
1999020500523	19990205	00523	NM  	1999	2	5	99ZZZX546        	1	19980119	G	5522		SKIN            			DOUG  	MD11  	MD11        	3023602	NM  										ELEVATOR	DELAMINATED     	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	273WA					48519				LEFT AND RIGHT DETACHABLE INBOARD ELEVATORS T/E DELAMINATED.  APPLIED HOT BEND LAY-UP REPAIRS IAW MD-11 SRM 55-99-00, SH	EET 3 FIG 1 AND SHEET 4 FIG 2.					2	L	7	3 	4F			RT	A22WE
1999020500524	19990205	00524	NM  	1999	2	5	99ZZZX547        	1	19980119	G	5753		SKIN            			DOUG  	MD11  	MD11        	3023602	NM  										TE FLAP	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	07	273WA					48519				LEFT INBOARD FLAP UPPER SKIN DAMAGED.  TRIMMED OUT DAMAGED AREA, FABRICATED AND INSTALLED FILLER AND DOUBLER IAW MD-11 S	RM 51-71-00, PAGES 68-70, AND SRM 53-20-00.					2	L	7	3 	4F			RT	A22WE
1999020500526	19990205	00526	SO  	1999	2	5	99ZZZX549        	1	19980107	G	2720	40040007	TORQUE TUBE     		51094000    	PIPER 	PA31T 	PA31T       	7103124	SO  										RUDDER	CORRODED        	B		A	SO5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	29CA	4269 				31T7800076				FORWARD DRAIN HOLE IN RUDDER CLOGS AND RUDDER FILLS UP SEVERAL INCHES WITH WATER.  ONLY SIGN OF POSSIBLE INTERNAL DAMAGE	 IS SOME RUST STARTING TO LEAK OUT OF RUDDER SEAMS.  REMEDY - DRILL LARGER DRAIN HOLES AND ADD ONE JUST AFT OF TORQUE TU	BE PLATE.				1	L	7	2 	3T				A8EA
1999010800091	19990108	00091	EU  	1999	1	8	99ZZZX55         	1	19981203	G	2520	3410	SEAT            			AIRBUS	320   	A320232     	3930326	EU  										CABIN	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	405UA					452				DURING THE FIRST HEAVY MAINTENANCE VISIT (HMV-1) FOR THIS AIRCRAFT, VIRTUALLY 100 PERCENT OF THE COACH PASSENGER SEAT PA	NS WERE FOUND CRACKED.  THESE SEAT PANS ARE INSTALLED ON RECARO MODEL 3410, 720 SERIES SEATS INSTALLED IN A-320-232 AIRC	RAFT.  THESE CRACKS ARE OCCURRING AT THE FORWARD EDGE OF THE SEAT PAN ADJACENT TO THE MOUNTING HOLES WHERE THE PAN IS AT	TACHED TO THE SEAT FRAME.  THE SEAT MANUFACTURER DESIGNATES THE SEAT PAN TO BE PRIMARY STRUCTURE.			2	L	7	2 	4F			RT	A28NM
1999020500527	19990205	00527	NM  	1999	2	5	99ZZZX550        	1	19980601	G	5347	BAC1520	SEAT TRACK      			BOEING	747   	747422      	1384935	NM  										BS 998-1000	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	09	180UA					25224				MAIN DECK SEAT TRACK UPPER T-CAP BROKEN AT LBL 98.58 BETWEEN STATIONS 998 AND 1000.  CIRCUMSTANCES UNKNOWN.  REPAIRED PE	R MOBILE AEROSPACE ENGINEERING.  E.A. NR 47-5346-13-AB341 - 5-28-98.  ACFT TT:  33,618.54 HOURS.  CYCLES:  4,064.					2	L	7	4 	4F			RT	A20WE
1999020500528	19990205	00528	EA  	1999	2	5	99ZZZX551        	2	19980625	G	7532	3N254	VALVE           		310687001   	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  					RT ENGINE	BROKEN          	D				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			GL	13	124CA		4959 		3N254	SH3652	97192			ON DESCENT, RIGHT ENGINE BEGAN TO SURGE WITH POWER LEVER MOVEMENTS.  SHUT DOWN ENGINE FOR PRECAUTIONARY MEASURES AND LAN	DED ON ONE ENGINE.  REMOVED AND REPLACED BLEED VALVE.  OPS CHECK OK.					2	H	7	2 	4T	4	T		A41EU   	E4EA
1999020500529	19990205	00529	NM  	1999	2	5	99ZZZX552        	1	19980614	G	3222		STRUT           			BOEING	747   	747*        		NM  										NLG	FAILED          	H				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			EU	01										NOSE GEAR FAILURE ON SINGAPORE AIRLINES AIRCRAFT, WHILE ON TOW AT ISTANBUL ATATURK AIRPORT.  THE NOSE OLEO COLLAPSED.  O	N INSPECTION, A CIRCUMFERENCIAL CRACK APPEARED.  THIS FAILURE CAUSED LOSS OF OLEO OIL.   SINGAPORE AIRLINES ENFORCED THA	T WORKING PARTY WOULD BE REQUIRED.				2	L	7	4 	4F			RT	A20WE
1999020500530	19990205	00530		1999	2	5	99ZZZX553        	4	19980301	G	3442	40007633101	RADAR           	BENDIX      		STBROS	SD3   	SD330       	8100602	EU  										COCKPIT	MALFUNCTIONED   	D				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			GL	13	167RC				5576	SH3038				AFTER TAKEOFF, CREW NOTICED A SMOKE SMELL.  THEY RETURNED TO AIRPORT TO INVESTIGATE.  FOUND THE RADAR RT HAD OVERHEATED.	  MEL'D RADAR AND CONTINUED FLIGHT.					2	H	7	2 	4T				A41EU
1999020500533	19990205	00533	CE  	1999	2	5	99ZZZX556        	1	19981222	G	5512		SKIN            		11562001027 	BEECH 	99    	99          	1154002	CE  										HORIZ STABILIZER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	118SF	10930				U32				DURING A ROUTINE INSPECTION, CRACKS WERE DISCOVERED IN THE TOP SKIN AND RIB AT STA 76 OF THE LEFT HORIZONTAL STABILIZER.	  THE CRACK RAN FOR SEVERAL INCHES FORWARD AND AFT OF THE FORWARD J-CHANNEL.  SI NR 0131-130, HAD BEEN PREVIOUSLY CW.  S	UBMITTER STATED POSSIBLE CAUSE AS VIBRATION DUE TO SLIP STREAM.				1	L	7	2 	3T				A14CE
1999020500534	19990205	00534	CE  	1999	2	5	99ZZZX557        	1	19981222	G	5512		SKIN            		11562001027 	BEECH 	99    	99          	1154002	CE  										HORIZ STABILIZER	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	118SF	10930				U32				DURING A ROUTINE INSPECTION, CRACKS WERE DISCOVERED IN THE TOP SKIN OF THE LEFT HORIZONTAL STABILIZER BEGINNING UNDER TH	E DE-ICE BOOT TRAVELING AFT ALONG THE ROW OF RIVETS AT STA 87 TO THE FORWRD J-CHANNEL.  SI NR 0131-130 HAD BEEN PREVIOUS	LY C/W.  SUBMITTER SUGGESTED POSSIBLE CAUSE AS VIBRATION DUE TO SLIP STREAM.				1	L	7	2 	3T				A14CE
1999020500535	19990205	00535	NE  	1999	2	5	99ZZZX558        	2	19980818	G	7250	754380	BEARING         			BOEING	747   	747*        		NM  	PWA   	JT9   	JT9D7A      	52054	NE  					NR 2	SPALLED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99		367  			ACWKAH0849		663036			THE ENGINE WAS REMOVED FROM SERVICE 367 HOURS/155 CYCLES SINCE HEAVY REPAIR DUE TO METAL BEING PICKED UP ON THE MAGNETIC	 CHIP DETECTOR (ANGLE GEARBOX).  THIS METAL IDENTIFIED AS BEING BEARING CAGE MATERIAL.  STRIP OF THE BEARING WAS FOUND W	ITH HEAVY WEAR IN ALL CAGE POCKETS AND SPALLING/PITTING IN 70 PERCENT OF POCKETS.  THIS BEARING IS OF THE TYPE THAT HAVE	 TEN DIGIT SERIAL NUMBERS THAT WERE INTRODUCED IN SEPT 97.			2	L	7	4 	4F	4	F	RT	A20WE   	E20EA
1999020500536	19990205	00536	NE  	1999	2	5	99ZZZX559        	2	19980408	G	7260	385384	GEARSHAFT       								PWA   	JT3D  	JT3D*       	52039	NE  					GEARBOX	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					209					CHROME PLATE REMOVED FROM SEAL FACE (INDEX 27) AND BASE METAL FOUND TO BE CRACKED IN SEVERAL PLACES.  FMPI FOUND THE PRO	BLEM.  CAUSE UNKNOWN.										4	F			1E8
1999010800092	19990108	00092	NM  	1999	1	8	99ZZZX56         	1	19981130	G	5350	655518668	RADOME          			BOEING	727   	727251      	138408H	NM  										NOSE	CONTAMINATED    	B	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	25	275US				04	21154				VERY LOW RADAR TRANSMISSION THROUGH RADOME (27.7 PERCENT IN NOSE).  MINIMUM SPEC IS 82 PERCENT.  RADAR RANGE WILL BE DIM	INISHED.					2	L	7	3 	4F				A3WE
1999020500537	19990205	00537	NE  	1999	2	5	99ZZZX560        	2	19980905	G	7250	50B050	SEAT            								PWA   	4460  	PW4460      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					C7129					CRACKS IN CHROME SEAL FACE SEEM TO BE TRANSFERRING INTO BASE MATERIAL.											4	F			E24NE
1999020500538	19990205	00538	NE  	1999	2	5	99ZZZX561        	2	19980906	G	7250	50B050	SEAT            								PWA   	4460  	PW4460      		NE  					NR 1 BEARING	CRACKED         	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					B2099					SAME AS SEVERAL OTHERS OF SAME PART NUMBER.  CRACKS IN CHROME SEAL FACE APPEAR TO BE TRANSFERRING INTO BASE MATERIAL.											4	F			E24NE
1999010800093	19990108	00093	CE  	1999	1	8	99ZZZX57         	1	19981208	G	2752		ACTUATOR        			BEECH 	90    	65A90       	1152908	CE  										TE FLAP	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	23	5Y	9800 				LJ272				DURING ROUTINE PHASE INSPECTION, FOUND 3 OF THE 4 FLAP ACTUATORS WERE INSTALLED WITH THE VENT HOLE DOWN.  SUBMITTER STAT	ED IT IS VERY IMPORTANT TO INSTALL ACTUATORS IAW BEECH MM WHICH CALLS FOR VENT FHOLE TO BE POSITIONED UP TO PREVENT LUBR	ICANT LOSS.  ACTUATOR P/N'S 50-521198-3, 50-521198-4, 50-521152-1, AND 50-521152-2.				1	L	7	2 	3T				3A20
1999021900017	19990219	00017	SO  	1999	2	19	99ZZZX577        	2	19980206	G	8520	1H2418	MANIFOLD        			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520BE   	17040	SO  					ENGINE	WORN            	B			LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	1228	1214 				4608092				AS PART OF INSPECTION, DEICE CONTROL AND MANIFOLD ARE CHECKED.  FOUND MANIFOLD NOT OPERATING CORRECTLY.  INTERNAL CHECK 	VALVES NOT SEALING WHEN AIR BLOWN IN ONE INLET AT A TIME.  THIS COULD HAVE AN EFFORT ON BOOT OPERATION IF ONE VACUUM PUM	P FAILED BY ALLOWING SOME PRESSURE TO RUN BACK THROUGH INOPERATIVE PUMP.  AIRBORNE PRODUCT REF MEMO NR 39 RECOMMENDS REP	LACEMENT AFTER 10 YEARS.  PART REPLACED ON THIS AIRCRAFT WAS 10 YEARS OLD.			1	L	7	1 	3O	3	O	RT	A25SO   	E8CE
1999021900019	19990219	00019	CE  	1999	2	19	99ZZZX579        	1	19980101	G	5740		BOLT            			BEECH 	200   	200BEECH    	1152920	CE  										WING	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	23	15NG					BB666				8727 AACT 20,988 TL.  FIRST FIVE YEAR WING BOLT INSPECTION AFTER REPLACEMENT.  THE LEFT AND RIGHT LOWER FORWARD WING (IN	CONEL) BOLTS WERE FOUND CRACKED USING DIE PENETRANT.  ONE BOLT WAS VERIFIED TO BE CRACKED USING A MICROSCOPE.  ONE BOLT 	WAS VERIFIED TO BE CRACKED USING DIE A MICROSCOPE.  ONE UPPER FORWARD STEEL BOLT WAS SUSPECTED TO BE CRACKED USING DIE P	EN.  INCONEL BOLT TIME IN SERVICE 5 YEARS.  1,882 HOURS, 3,418 CYCLES.			1	L	7	2 	4T				A24CE
1999010800094	19990108	00094	CE  	1999	1	8	99ZZZX58         	1	19981017	G	2820		CONNECTOR       			LEAR  	35    	31A         	5170531	CE  										RT ENGINE	LOOSE           	D				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			EA	35	770CC					058				A 'WIGGINS' CONNECTOR IN THE RIGHT ENGINE FUEL FEED, FORWARD AND ADJACENT TO THE RIGHT BATTERY TRAY BECAME DISLODGED CAU	SING THE RIGHT ENGINE TO FLAME OUT.  THE CONNECTOR WAS REFITTED AND WIRE LOCKED (AN OPTION IN LEAR JET SIL 28-004).  NO 	LEAKS APPARENT IN SUBSEQUENT GROUND RUN.  CAUSE UNKNOWN.  SUBMITTER SUGGESTED WIRE LOCKING OF 'WIGGINS' CONNECTORS IN FU	EL SYSTEMS BE MANDATORY.			2	L	7	2 	4F			RT	A10CE
1999021900020	19990219	00020	SO  	1999	2	19	99ZZZX580        	2	19980506	G	8530	TM6413705	VALVE           			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					CYLINDER	FAILED          	B			AW1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	178JA	103  				347770193	265593R			INTAKE VALVE SEAT CAME LOOSE, STUCK UNDER VALVE.  CYLINDER CERMINIL STEEL (EC) ENG T.W. SMITH OVERHAULED.  PART TIME 102	.8 HRS.  AIRCRAFT LANDED  RESTARTED, WOULD NOT DEVELOP POWER.					1	L	7	2 	3O	3	O		A7SO    	E9CE
1999021900024	19990219	00024	EA  	1999	2	19	99ZZZX584        	2	19980227	G	8530		STUD            			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1A5   	41532	EA  					NR 2 CYLINDER	BROKEN          	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	615MT	4493 	907  			500B9112	L20548			LEFT ENGINE NR 2 CYLINDER BROKE 6 OF THE 8 STUDS HOLDING IT TO THE CRANKCASE.  THIS RESULTED IN OIL LEAK AND CYLINDER FL	ANGE AND SKIRT BREAKING.  TWO REMAINING STUDS AND NUTS WERE STILL SECURE.  AFTER LOSS OF OIL, OIL PRESSURE DROPPED.  ENG	INE WAS CAGED AND A SAFE LANDING WAS MADE ON REMAINING ENGINE.  ENGINE WAS REMOVED FOR TEARDOWN.				1	H	7	2 	3O	3	O		6A1     	1E4
1999021900025	19990219	00025	GL  	1999	2	19	99ZZZX585        	1	19981124	G	3222	2032200016	FORK            			DIAMON	DA20  	DA20A1      	2990000	GL  	PWA   	R985  	R985AN14B   	52008	NE  					NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	53HA	1599 				10055	P227432			AFTER THE FAILURE OF THE NOSE GEAR FORKS ON DA-20-A1, ELECTED TO PERFORM AN INSPECTION ON LIKE AIRCRAFT.  CLEANED PART A	ND PERFORMED A DYE PENETRANT INSPECTION ON THE SECOND AIRCRAFT.  THREE CRACKS WERE FOUND AT THE LOCATION NEAR THE THROUG	H-BOLT THAT HOLDS THE NOSE GEAR.  THE LOCATION OF THE CRACKS ARE THE SAME AS WHERE THE FIRST AIRCRAFT'S GEAR FORKS BROKE	.  CRACKS ARE APPEARING AT THE SMALL OF THE METAL (NARROWEST POINT).			1	L	7	1 	3O	3	R	NT	TA4CH   	5E1
1999021900026	19990219	00026	GL  	1999	2	19	99ZZZX586        	1	19981124	G	3222	2032200015	FORK            			DIAMON	DA20  	DA20A1      	2990000	GL  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	21	53HA	1599 				10055				AFTER THE FAILURE OF THE NOSE GEAR FORKS ON DA-20-A1, ELECTED TO PERFORM AN INSPECTION ON LIKE AIRCRAFT.  CLEANED PART A	ND PERFORMED A DYE PENETRANT INSPECTION ON THE SECOND AIRCRAFT.  THREE CRACKS WERE FOUND AT THE LOCATION NEAR THE THROUG	H-BOLT THAT HOLDS THE NOSE GEAR.  THE LOCATION OF THE CRACKS ARE THE SAME AS WHERE THE FIRST AIRCRAFT'S GEAR FORKS BROKE	.  CRACKS ARE APPEARING AT THE SMALL OF THE METAL (NARROWEST POINT).			1	L	7	1 	3O			NT	TA4CH
1999021900027	19990219	00027	EA  	1999	2	19	99ZZZX587        	2	19980710	G	7414	S4LN1209	MAGNETO         	ELECTROSYS  		CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AL	05	39799	50   			A267299	363	L1073951			MAGNETO FAILED IN-FLIGHT.  TROUBLESHOOTING REVEALED DISTRIBUTOR GEAR NOT TURNING.  PAPER SHIM NEXT TO COIL HAD MIGRATED 	TOWARD GEAR AND CAUSED CATASTROPHIC FAILURE OF GEAR TEETH.  ENGINE AND MAGS 50 HOURS SINCE OVERHAUL.					1	H	7	1 	3O	3	O		1A13    	1E10
1999021900028	19990219	00028	SO  	1999	2	19	99ZZZX588        	2	19980516	G	7314	AC631391	PUMP            			UNIVAR	415   	415C        	0420302	NM  	CONT  	A75   	C7512       	17005	SO  					FUEL SYSTEM	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	3230H					3855	1472612			ENGINE DRIVEN FUEL TRANSFER PUMP FAILED.  FUEL NOT TRANSFERRED TO HEADER FUEL TANK.  GRAVITY FEED OF FUEL TO CARBURETOR.	  NOTE:  ONE WAFER VALVE STUCK CLOSED.  SPRING AND WAFER VALVE WAS LOCATED NEXT TO DIAPHRAGM.					1	L	7	1 	3O	3	O		A718    	E233
1999021900029	19990219	00029	EA  	1999	2	19	99ZZZX589        	2	19980720	G	8530	73457	PUSH ROD        			MOONEY	M20   	M20E        	5870212	SW  	LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	2585W		125  			940	L1915751A			THIS ENGINE WAS DISASSEMBLED FOR REPLACEMENT OF 4 CYLINDERS DUE TO LOW COMPRESSION.  IT HAD 125 HOURS SMOH BY LYCOMING. 	 THE NR 1 ROCKER ARMS WERE FOUND SWITCHED.  THE EXHAUST ROCKER IN THE INTAKE POSITION DID NOT DAMAGE, HOWEVER, THE INTAK	E ROCKER WORE THE PUSH ROD SEVERELY ON THE EXHAUST SIDE FROM CONTACT ABOUT .50 INCH FROM THE END.  THE WALL OF THE PUSH 	ROD WAS NEARLY WORN THROUGH.  THE INTAKE ROCKER HAS A RAISED AREA ON THE BODY TO PREVENT THIS MISTAKE, BUT THESE CYLINDE	RS ARE MACHINED DEEPLY ENOUGH TO ALLOW THE INTAKE ROCKER TO FIT IN THE EXHAUST POSITION.		1	L	7	1 	3O	3	O		2A3     	1E10
1999010800095	19990108	00095	EU  	1999	1	8	99ZZZX59         	1	19980515	G	5210	33304603	DOOR JAMB       			ISRAEL	1124  	1124A       	4500103	EU  										BS 93	CRACKED         	B	S		CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	365CX	4254 				425				DURING INSPECTION, FOUND CABIN DOOR LOWER DOOR JAMB CRACKED AT LOCATION WHERE DOOR STEP ASSY FORWARD STOP CONTACTS DOOR 	JAMB ANGLE, P/N 333046-03.  DOOR JAMB ANGLE SHOULD BE REINFORCED WHERE STEP ASSY STOP CONTACTS AREA.					2	M	7	2 	4F				A2SW
1999021900030	19990219	00030	CE  	1999	2	19	99ZZZX590        	1	19980217	G	2913		PUMP            	PRESTOLITE  		BEECH 	23    	B24R        	1151253	CE  										HYDRAULIC SYSTEM	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	99	22PA	3098 				MC223				NOSE GEAR FAILED TO RETRACT COMPLETELY.  GEAR WOULD NOT EXTEND OR RETRACT WITH ELECTRO HYDRAULIC SYSTEM.  GEAR EXTENDED 	WITH EMERGENCY EXTENSION SYSTEM.  HYDRAULIC PUMP ASSY MOTOR INOPERATIVE.  SUBMITTER SUGGESTED CLOSER INSPECTION OF BRUSH	ES AT ANNUAL INSPECTION.				1	L	7	1 	3O				A1CE
1999021900031	19990219	00031	EU  	1999	2	19	99ZZZX591        	2	19980706	G	7314	996592	PUMP            			DIAMON	DA20  	DA20A1      		GL  	ROTAX 	912   	ROTAX912    	55555	EU  					FUEL SYSTEM	FAILED          	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			NM	11	25UV	1580 	1200 		9G0116	10262	4412692			DISCOVERED FUEL STAINS BELOW PUMP (ENGINE DRIVEN) ON ROUTINE INSPECTION.  FUEL LEAKAGE WAS NOTED WITH ELECTRIC PUMP PRES	SURIZING SYSTEM.  LEAKAGE WAS AT WEEP HOLES IN THE PUMP BODY.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
1999021900032	19990219	00032	EA  	1999	2	19	99ZZZX592        	2	19981124	G	7414	D4LN2021	MAGNETO         			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					ENGINE	WORN            	G				A				UNSCHED LANDING         				O			OTHER                     			NR	NOT REPORTED   	1			SO	13	201QG	421  				240340	R3011579			THE AIRCRAFT WAS FORCED TO MAKE AN OFF-AIRPORT GEAR UP LANDING IN A FIELD DUE TO A LOSS OF ENGINE POWER.  SUBSEQUENT INV	ESTIGATION REVEALED THE ENGINE MAGNETO HAD EXCESSIVE WEAR ON THE CAM.  THIS CAUSED IMPROPER POINT GAP CAUSING MAGNETO TO	 MALFUNCTION AND CREATE THE LOSS OF ENGINE POWER.				1	L	7	1 	3O	3	O		2A3     	1E10
1999021900033	19990219	00033	GL  	1999	2	19	99ZZZX593        	1	19980801	G	3230	2032200016	FORK            			DIAMON	DA20  	DA20A1      		GL  										NLG	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	198DA	1195 				10058				NOSE GEAR FORKS FOUND TO BE CRACKED.  BOTH SIDES, 25 PERCENT REMAINING.  CRACKS OBSCURED BY PAINT AND WHEEL PART. VISUAL	 INSPECTION AT PRE-FLIGHT.					1	L	7	1 	3O			NT	TA4CH
1999021900035	19990219	00035	SO  	1999	2	19	99ZZZX595        	2	19980707	G	8530	649805	PISTON          			CESSNA	414   	414A        	2075907	CE  	CONT  	O550  	TSIO550A    	41516	SO  					NR 4 CYLINDER	CRACKED         	H				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			SW	07	12455					414A1207	800532			DURING FLIGHT, THE RIGHT ENGINE BEGAN TO RUN ROUGH AND LOST OIL PRESSURE.  THE PILOT SECURED THE ENGINE AND MADE A SAFE 	SINGLE-ENGINE LANDING.  AN INVESTIGATION REVEALED A CRACK IN THE PISTON.  THIS CRACK STARTED FROM THE OIL CONTROL RING L	ANDING THROUGH THE CENTER OF THE PISTON AND A HOLE WAS NOTED IN THE TOP OF THE PISTON.  NO OVERHEATING OR ABNORMAL WEAR 	WAS NOTED.  SUBMITTER STATED CAUSE UNKNOWN.			1	L	7	2 	3O	3	O		A7CE    	E5SO
1999021900036	19990219	00036	CE  	1999	2	19	99ZZZX596        	1	19980720	G	2912	AN62342	FILTER          			CESSNA	441   	441         	2076020	CE  										HYDRAULIC SYSTEM	FAILED          	H				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			NM	10	441AG	3280 				4410327				SHORTY AFTER TAKEOFF, AFTER THE LANDING GEAR AND FLAPS WERE RETRACTED, THE RT HYDRAULIC LOW FLOW LIGHT ILLUMINATED.  FOL	LOWED SHORTLY BY THE LEFT HYDRAULIC LOW FLOW LIGHT ILLUMINATING.  HYD FLUID WAS OBSERVED COMING FROM THE RT ENGINE COWLI	NG.  THE LANDING GEAR WAS BLOWN DOWN AND A SAFE LANDING MADE WITHOUT INCIDENT.  A POST-FLIGHT INSPECTION REVEALED THE RT	 HAND HYD FILTER BOWL WAS SPLIT ABOUT 1/2 OF ITS CIRCUMFERENCE BETWEEN THE THREADS.  POSSIBLE CAUSES COULD BE A CASTING 	FLAW OR OVERTIGHTENING OF THE FILTER BOWL.  RECOMMEND REPLACING THE PUROLATOR FILTER ASSY WITH THE FAUCET ASSY (SAME PAR	T NUMBER).	1	L	7	2 	3T			RT	A28CE
1999021900037	19990219	00037		1999	2	19	99ZZZX597        	2	19980420	G	8530	71166	CYLINDER        			BEECH 	18    	G18S        	1151010	CE  										EXHAUST	BROKEN          	D				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			GL	13	9669R		14350			BA495				PILOT FELT DIFFFERENT VIBRATION ON A SHORT PART 91 FLIGHT.  A COLD CYLINDER CHECK WAS DONE, AND NR 8 FOUND TO BE COLD. R	EMOVED CYLINDER AND FOUND PART OF VALVE FACE BROKEN OFF.  POSSIBLY DUE FROM OLD AGE.  CHANGED CYLINDER AND PISTON.					1	L	7	2 	3R				A765
1999021900038	19990219	00038		1999	2	19	99ZZZX598        	1	19981005	G	2435	23085001	STARTER         	LUCAS       																STARTER/GEN	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05		5142 	1    							THE STARTER/GENERATOR WAS RETURNED TO THIS LOCATION AFTER 0.6 HOURS OF OPERATION.  INSPECTION REVEALED THE COMMUTATOR HA	D COME APART AND AS A RESULT RIPPED OPEN THE BRUSH INSPECTION COVER AND SEVERELY DAMAGED THE COMMUTATOR END BELL AND BRU	SH HOLDERS.  CLOSER INSPECTION SHOWED THE INDICATION OF A CRACK ON THE INTERNAL SHOULDER OF THE OUTBOARD COMMUTATOR BAR 	RETENTION WEDGE AT THE TRANSITION OF THE SLEEVE AND END PIECE.  THE UNIT HAS BEEN RETURNED TO THE OEM FOR ENGINEERING EV	ALUATION.
1999021900039	19990219	00039	SO  	1999	2	19	99ZZZX599        	2	19980306	G	8530	637837	VALVE SPRING    			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 1 CYLINDER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	190MG	145  				414A0639	514952			UPON REMOVAL OF CYLINDER NR 1, THE INNER VALVE SPRING P/N 631521 AND OUTER VALVE SPRING P/N 637837 WERE FOUND BROKEN.  T	HE OUTER VALVE SPRING P/N 637837 ON CYLINDER NR 3 WAS FOUND BROKEN.  CAUSE IS UNKNOWN.  OWNER COMPLAINED OF EXCESSIVE EN	GINE VIBRATION.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1999010800016	19990108	00016	NE  	1999	1	8	99ZZZX6          	2	19981207	G	7421	FHE2464	IGNITER         			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ENGINE	DAMAGED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	31RC				9762031	5600023	108043			DURING PHASE B INSPECTION, FOUND LEFT ENGINE INBOARD IGNITER CENTER ELECTRODE LOOSE IN IGNITER BODY.  ELECTRODE IS FREE 	TO MOVE IN AND OUT IGNITER BODY APROXIMATELY .3125 INCH.  IGNITER HAS NORMAL WEAR AND NO OTHER APPARENT DAMAGE.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA
1999010800096	19990108	00096	WP  	1999	1	8	99ZZZX60         	2	19981015	G	7250		BLADE           			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R    	01518	WP  					RT ENGINE	DAMAGED         	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	38PA					NA0208				DURING INSPECTION FOUND NUMEROUS FAN BLADES DAMAGED ON RIGHT ENGINE.  FOUND RIVET MISSING AT 6 O'CLOCK POSITION ON ENGIN	E INLET LIP AND THREE LOOSE RIVETS.  SUSPECT INCORRECT INSTALLATION PROCEDURES USED FOR BLIND RIVETS DURING REPAIR.  ENG	INE INLETS WITH BLIND RIVETS SHOULD BE MORE FREQUENTLY INSPECTED.				2	L	7	2 	4F	4	F		A3EU    	E6WE
1999021900040	19990219	00040	SO  	1999	2	19	99ZZZX600        	2	19980306	G	8530	631521	VALVE SPRING    			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					NR 3 CYLINDER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	190MG	145  				414A0639	514952			UPON REMOVAL OF CYLINDER NR 1, THE INNER VALVE SPRING P/N 631521 AND OUTER VALVE SPRING P/N 637837 WERE FOUND BROKEN.  T	HE OUTER VALVE SPRING P/N 637837 ON CYLINDER NR 3 WAS FOUND BROKEN.  CAUSE IS UNKNOWN.  OWNER COMPLALINED OF EXCESSIVE E	NGINE VIBRATION.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1999021900237	19990219	00237	SW  	1999	2	19	99ZZZX602        	1	19981014	G	2820		LINE            			AIRTRC	AT500 	AT502B      	0390307	SW  										FUEL SYSTEM	LEAKING         	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	6108L	2600 				502B0289				IN-FLIGHT LOSS OF FUEL FLOW RESULTING IN ENGINE FAILURE.  EMERGENCY LANDING AT NEARBY AIRPORT.  INSPECTION REVEALED CHAF	ED THROUGH FUEL LINE (ALUMINUM).  FUEL SELECTOR TO FIREWALL.  FUEL LINE CHAFED THROUGH DUE TO CONTACT WITH DEFROSTER SCA	T HOSE.  SUBMITTER SUGGESTED INSPECTION AND/OR REPLACEMENT WITH A SHIELDED FUEL LINE.				1	L	7	1 	3T			NC	A17SW
1999021900238	19990219	00238	CE  	1999	2	19	99ZZZX603        	1	19980108	G	7160	NH3000XXX10	CHANNEL         			CESSNA	500   	560CESSNA   	2076750	CE  										ENGINE INLET	MISMANUFACTURED 	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	07	393QS	77   				5600393				CESSNA SB 560-54-03 COMPLETED 12-14-98.  SB INCORPORATES VAPOR BARRIER/VIBRATION DAMPENING CHANNEL AROUND ENGINE INLET D	UCT.  FOUND CHANNELS MELTED AFTER 77.1 HOURS TIS.  SUBMITTER RECOMMENDED CHANNELS BE MANUFACTURED FROM MATERIAL WITH A H	IGHER TOLERANCE FOR HEAT.				2	L	7	2 	4F			RT	A22CE
1999021900239	19990219	00239	CE  	1999	2	19	99ZZZX604        	1	19980423	G	5753	262501570	RIB             			LEAR  	60    	60LEAR      	5170707	CE  										TE FLAP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17	600L	2395 				020				DURING 2400 HOUR INSPECTION, CRACK FOUND IN RIB ON LEFT FLAP.  ALSO, A NEARBY Y-FITTING HAD A PULLED RIVET.  FLAP HAD TO	 BE RETURNED TO LEARJET FOR REPAIR.					2	L	7	2 	4F			RT	A10CE
1999021900240	19990219	00240	EU  	1999	2	19	99ZZZX605        	1	19980311	G	7920	SD3790029XB	FITTING         			STBROS	SD3   	SD330       	8100602	EU  										LT ENGINE	STRIPPED        	D				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			GL	13	938MA					SH3046				WHILE CLIMBING OFF OF CWA, THE CREW NOTICED FLUCTUATION ON THE LEFT OIL PRESSURE.  APPROXIMATELY 15 SECONDS LATER, OIL P	RESSURE WAS DROPPING ON THAT SIDE AND TORQUE WAS REDUCED.   VISUAL INSPECTION SHOWED OIL EXTRACTING FROM THE DRAINS OF T	HE LEFT ENGINE.  OIL PRESSURE AT THIS POINT WAS APPROX 80 PSI.  CREW THEN PROCEEDED TO SHUT DOWN THE ENGINE.  RETURNED F	OR LANDING AT CWA AIRPORT.  THE OIL FITTING FOR THE TORQUE TRANSMITTER WAS TIGHTENED AND SAFETY WIRED.			2	H	7	2 	4T				A41EU
1999021900241	19990219	00241	EA  	1999	2	19	99ZZZX606        	2	19980313	G	7250		TURBINE SECTION 			STBROS	SD3   	SD330       	8100602	EU  	PWA   	PT6   	PT6A45      	52043	EA  					LT ENGINE	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			GL	13	938MA		2067 			SH3046	84101			A RECURRENCE OF THE LEAKING OIL ON THE LEFT POWER SECTION, PAGE 84101.  THE REPAIR DID NOT HOLD.  THE POWER SECTION WAS 	REMOVED AND REPLACED.  RUN AND LEAK CHECKED GOOD.					2	H	7	2 	4T	4	T		A41EU   	E4EA
1999021900242	19990219	00242	NM  	1999	2	19	99ZZZX607        	1	19981228	G	5313		STRINGER        			BOEING	727   	7272B7      	138407L	NM  										BS 1183	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED JUST FORWARD OF STA 1183 ON STR 22L.						2	L	7	3 	4F				A3WE
1999021900243	19990219	00243	NM  	1999	2	19	99ZZZX608        	1	19981228	G	5311		FRAME           			BOEING	727   	7272B7      	138407L	NM  										BS 1223	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED AT STA 1223 BELOW NR 12 STEP AFT AIRSTAIRS LBL 22.  T-CHORD HAS CORROSION ON LOWER	 SURFACE.					2	L	7	3 	4F				A3WE
1999021900244	19990219	00244	NM  	1999	2	19	99ZZZX609        	1	19981228	G	5320		SPLICE          			BOEING	727   	7272B7      	138407L	NM  										BS 1223	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED AT STA 1223 RBL 25 LOWER SURFACE OF SPLICE ANGLE BELOW AFT AIRSTAIRS STEP NR 12.						2	L	7	3 	4F				A3WE
1999010800097	19990108	00097	EU  	1999	1	8	99ZZZX61         	1	19981031	G	2910	326705	VALVE           			AIRBUS	320   	A320214     		EU  										HYDRAULIC SYSTEM	FAILED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EU	01	716AW					716				CHECK VALVE FAILED CAUSING AC PUMP (YELLOW SYSTEM) TO BE BACK DRIVEN BY N2 ENGINE EDP.  CHECK VALVE FIN 8083.  NOTE:  FA	ILED CHECK VALVE WAS DISCOVERED AFTER SECOND PUMP REPLACEMENT.					2	L	7	2 	4F			RT	A28NM
1999021900246	19990219	00246	NE  	1999	2	19	99ZZZX611        	2	19980713	G	7200		IDG             	SUNDSTRANDAI		BOEING	767   	767259      	1385136	NM  	PWA   	4056  	PW4056      	 	NE  					LEFT	MALFUNCTIONED   	W			ANCF	A				UNSCHED LANDING         				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SO	23	986AN	26496	4446 		G0450	24835	724605			BOG/APR - FLT 014 - AIR TURN BACK.  EICAS MSG LT GENERATOR DRIVE AND IDG TEMP SENSOR AND DRIVE WARNING LIGHT FLICKERS. I	DG WAS DISCONNECTED.  LT IDG WAS REPLACED.  TEST ACCORDING MM 24-20-00 WITH ENGINE RUN-UP OK.					2	L	7	2 	4F	4	F	RT	A1NM    	E24NE
1999021900248	19990219	00248	NE  	1999	2	19	99ZZZX613        	2	19981102	G	7250	2A2833	SEAL            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							0170			PART REJECTED AT FPI DUE TO CRACKS IN 2 PLACES ON TOP SURFACE:  CRACK 'A' = 2 INDICATIONS 0.015 INCH AND 0.020 INCH.  CR	ACK 'B' = 1 INDICATION 0.250 INCH.  JOB FOR:  WESTFIELD GAGE (P.O. NR 97553).										4	F			E311NE
1999021900249	19990219	00249	NE  	1999	2	19	99ZZZX614        	2	19980625	G	7250	50B050	SEAT            								PWA   	4460  	PW4460      		NE  					NR 1 BEARING	CRACKED         	B			WWFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17					C3618					THIS IS A CHROME FACED SEAL.  AFTER REMOVING CHROME, CRACKS ARE FOUND IN THE BASE METAL.  USUALLY, LIGHT MACHINING WILL 	REMOVE THE INDICATION, BUT THIS CONDITION GETS WORSE OVERALL AND SUBMITTER STATED THE CRACKS ON THIS PART CANNOT BE REMO	VED.									4	F			E24NE
1999021900250	19990219	00250	NE  	1999	2	19	99ZZZX615        	2	19981215	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							25212			PART REJECTED DUE TO CRACK .190 INCH LONG AND LINEAR INDICATION .375 INCH LONG.  JOB FOR:  WESTFIELD GAGE P.O NR 98832.											4	F			E311NE
1999021900251	19990219	00251	NE  	1999	2	19	99ZZZX616        	2	19980812	G	7250	2A0851	SEAT            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							0136			PART WAS REJECTED DUE TO 0.125 INCH CRACK ON TOP SURFACE.  JOB FOR:  WESTFIELD GAGE.											4	F			E311NE
1999021900252	19990219	00252	NE  	1999	2	19	99ZZZX617        	2	19980708	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							0103			CRACKS - 2 PLACES ON TOP SURFACE, AS MARKED 0.250 INCH AND 0.450 INCH.											4	F			E311NE
1999021900253	19990219	00253	NE  	1999	2	19	99ZZZX618        	2	19980904	G	7250	2A0851	SEAL            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							0047			PART REJECTED DUE TO CRACKS - 2 PLACES ON TOP FACE 0.750 INCH AND 1.500 INCH LONG (CRACKS VERIFIED BY MICROSCOPE).											4	F			E311NE
1999021900254	19990219	00254	NE  	1999	2	19	99ZZZX619        	2	19980101	G	7250	2A0851	HOUSING         								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	FAILED          	B			WNFR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					0047					THIS IS A TITANIUM HOUSING WHICH HAS FAILED FPI INSPECTION.  PART IS CRACKED IN TWO LOCATIONS.  PART IS SCRAP.											4	F			E311NE
1999010800098	19990108	00098	EU  	1999	1	8	99ZZZX62         	1	19981109	G	2810		FUEL TANK       			BAC   	146   	AVRO146RJ100	1500096	EU  										CENTER	LEAKING         	B			MU1Z	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	23	506MM					E3244				DURING A C-3 CHECK PERFORMED 11-9-98, FUEL LEAK WAS FOUND IN THE CENTRAL FUEL TANK.  SUBMITTER STATED THE POSSIBLE CAUSE	 FOR THIS DEFECT IS FATIGUE OF THE JOINT AND THE TANK STRUCTURE.  THE CORRECTIVE ACTION IS BEING COORDINATED WITH MANUFA	CTURER, AND INVOLVES SEALANT APPLICATION AND TANK STRUCTURE REPAIR.  IT IS RECOMMENDED TO INSPECT THIS AREA FOR DAMAGE.				2	H	7	4 	4F			RT	A49EU
1999021900255	19990219	00255	NE  	1999	2	19	99ZZZX620        	2	19981102	G	7250	2A0847	SEAL            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							0193			PART REJECTED AT FPI DUE TO CRACK 0.500 INCH LONG ON SMALL OUTSIDE DIAMETER BEND RADIUS.  JOB FOR:  WESTFIELD GAGE P.O. 	97541.										4	F			E311NE
1999021900256	19990219	00256	NE  	1999	2	19	99ZZZX621        	2	19980408	G	7250	2A0847	SEAL            								IAE   	V2500 	V2500A1     		NE  					NR 4 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03							0294			PART WAS REJECTED DUE TO NUMEROUS CRACKS ON INNER DIAMETER SURFACE.											4	F			E311NE
1999021900257	19990219	00257	NE  	1999	2	19	99ZZZX622        	2	19980408	G	7250	583705	NUT             								PWA   	JT9   	JT9*        	52054	NE  					NR 2 BEARING	CRACKED         	B			KB1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03										PART WAS REJECTED FOR BACK-TO-BACK CRACKS .090 INCH/.125 INCH ON RIM, AS MARKED.											4	F			E20EA
1999021900258	19990219	00258	EU  	1999	2	19	99ZZZX623        	1	19980704	G	2731		TAB             			BAC   	146   	AVRO146RJ100	1500096	EU  	LYC   	LF507 	LF5071F     		NE  					ELEVATOR	MALFUNCTIONED   	A			SADF	A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			SO	23	505MM					E3242				CLO/ADZ - FLT 176 - FLIGHT DIVERSION TO PTY.  AT 22,000 FT ASL WITH 86,000 POUNDS GW, THE AIRCRAFT PRESENTED PITCH OSCIL	LATION WITH ALL AIRFRAME PROTECTION SELECTED ON.  THE CHECK LIST WAS DONE AND WAS REQ LOW LEVEL FLIGHT.  VISUALLY INSPEC	TED AND OPERATIONALLY CHECKED ON GROUND CONTROL SURFACES AND WERE FOUND IN NORMAL CONDITIONS.  CHECKED ENGINES INLET AND	 EXHAUST, WING AND TAIL FINDING NORMAL.			2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1999021900260	19990219	00260	SO  	1999	2	19	99ZZZX625        	2	19980707	G	8520	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O550  	IO550A      		SO  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	98904	1071 				310R1240	280460R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION, DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E3SO
1999021900261	19990219	00261	SO  	1999	2	19	99ZZZX626        	2	19980707	G	8520	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O550  	IO550A      		SO  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	98904	351  				310R1240	280448R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION, DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E3SO
1999021900262	19990219	00262	EU  	1999	2	19	99ZZZX627        	1	19980318	G	3222	124500	NOSE STRUT      			HOACAU	DV20  	DV20        	4170001	EU  										NLG	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	28	96DV	1200 				20096				PILOT SQUAWKED NOSE GEAR SHIMMY.  UPON INSPECTION, FOUND CRACK AT HUB WELD ALMOST THROUGH ENTIRE STRUT.  CRACK WAS JUST 	ABOVE WELD.  SUBMITTER STATED NUT ON FORK PIVOT SHOULD BE INSTALLED WITH COTTER PIN.  NOSE WHEEL TAPPET CRACKED.  SUBMIT	TER CALLED ISSUER OF AD.				1	L	7	1 	3O				A74EU
1999010800099	19990108	00099	CE  	1999	1	8	99ZZZX63         	1	19981113	G	2910	605700311	LINE            			LEAR  	60    	60LEAR      	5170707	CE  										NR 2 ENGINE	LEAKING         	D				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CE	03	8270	1616 				063				IN-FLIGHT, NOTED LINE DEVELOPED LEAK DEPLETING MAIN HYDRAULIC SYSTEM FLUID.  LEFT THEN RIGHT LOW HYDRAULIC PRESSURE LIGH	TS CAME ON.  CREW USED ABNORMAL PROCEDURES CHECK LIST, REQUESTED EMERGENCY LANDING AND LANDED SAFELY WITHOUT ANY FURTHER	 PROBLEMS.				2	L	7	2 	4F			RT	A10CE
1999021900265	19990219	00265	EA  	1999	2	19	99ZZZX630        	2	19981207	G	7414	4370	BUSHING         	SLICK       	K3822       	PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320B2B     	41508	EA  					MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	82530	294  			98011710	187809087	RL846139A			ENGINE IS FACTORY REMANUFACTURED 2-11-98.  MAGNETO GOOD, PREVIOUSLY WOULD NOT START, NEXT FLIGHT.  BRASS BUSHING IS DIST	RIBUTOR BLOCK WORN BADLY.					1	H	7	1 	3O	3	O		1A2     	E274
1999021900266	19990219	00266	EA  	1999	2	19	99ZZZX631        	2	19981207	G	7414	4373	BUSHING         	SLICK       	K3822       	PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320B2B     	41508	EA  					MAGNETO	WORN            	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	82530	294  			98010938	187809187	RL846139A			ENGINE IS FACTORY REMANUFACTURED 2-11-98.  MAGNETO DROP GOOD PREVIOUSLY.  WOULD NOT START, NEXT FLIGHT.  BRASS BUSHING I	N DISTRIBUTOR BLOCK WORN BADLY.					1	H	7	1 	3O	3	O		1A2     	E274
1999021900267	19990219	00267	EA  	1999	2	19	99ZZZX632        	2	19980609	G	7322	MA3A	FLOAT           	PRECISION   		CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					CARBURETOR	STUCK           	D				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			EA	21	757EK	1201 			CR27451	15279679				AIRCRAFT IS USED FOR FLIGHT TRAINING.  PILOT  INDUCED POWER ON STALL.  AT THIS TIME, AIRCRAFT BEGAN RUNNING ROUGH DUE TO	 AN EXCESSIVE RICH MIXTURE.  AFTER AN EMERGENCY LANDING WAS MADE, THE PILOT TAPPED ON THE CARBURETOR WITH A HAMMER HANDL	E, AND RE-STARTED THE AIRCRAFT.  ENGINE THEN RAN NORMAL, INDICATING THE FLOAT WAS STUCK.  THE CARBURETOR WAS REMOVED AND	 REPLACED WITH A P/N 10-5199, S/N CR1699.  OPS CHECKED OK.  TO PREVENT THESE OCCURRENCES, SUBMITTER RECOMMMENDED OVERHAU	L TIME SHOULD BE OBSERVED.		1	H	7	1 	3O	3	O	NT	3A19    	E223
1999021900268	19990219	00268	CE  	1999	2	19	99ZZZX633        	1	19981109	G	3233	98820151	ACTUATOR        			CESSNA	182   	R182        	2072734	CE  										MLG	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	7568T	4975 				R1820039				DURING AN ANNUAL INSPECTION, BRAKE FLUID WAS FOUND LEAKING NEAR A SWIVEL FITTING AT THE RT MAIN GEAR ACTUATOR.  FURTHER 	INVESTIGATION REVEALED TWO OF THE THREE BOLTS SECURING THE ACTUATOR WERE SHEARED OFF INSIDE THE MAIN GEAR SUPPORT, AND B	EING HELD FLUSH IN PLACE BY THE SAFETY WIRE.  THE LT ACTUATOR ALSO HAD ONE BOLT SHEARED POSSIBLY CONTRIBUTING FACTOR IS 	THE GREAT AMOUNT OF TORQUE PLACED ON THE ACTUATORS WHEN THE GEAR REACHES BOTH THE UP AND DOWN STOPS.  SUBMITTER SUGGESTS	 REMOVING AND INSPECTING THESE BOLTS EVERY 2 YEARS OR 250 HOURS.		1	H	7	1 	3O			RT	3A13
1999021900269	19990219	00269	CE  	1999	2	19	99ZZZX634        	1	19981216	G	3260	MS250413330	LIGHT           			BEECH 	76    	76          	1153005	CE  										COCKPIT	INTERMITTENT    	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	21	18122					ME417				NOSE GEAR DOWN LIGHT INTERMITTENT.  TROUBLESHOT SYSTEM.  REPLACED LIGHT ASSEMBLY.  PROBLEM RECURRED.  CONTINUED TROUBLES	HOOTING.   SWAPPED LIGHT ASSEMBLY WITH RT MAIN.  PROBLEM WENT WITH LIGHT ASSY.  REPLACED RT MAIN LIGHT ASSY WITH NEW.  P	ROBLEM RECURRED ON RT MAIN.  REPLACED WITH SERVICEABLE LIGHT ASSY.  OPS CHECK OK.  TROUBLESHOOTING IS VERY COSTLY WHEN N	EW REPLACEMENT PARTS ARE DEFECTIVE.			1	L	7	2 	3O				A29CE
1999021900270	19990219	00270	EA  	1999	2	19	99ZZZX635        	2	19981119	G	8520	LW1328Z	CRANKCASE       			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	13	4905H	3233 	1135 		L1357115	15284013	L1357115			DURING 50 HOUR INSPECTION, AN APPARENT OIL LEAK WAS FOUND ON THE TOP LEFT OF ENGINE CASE.  PERFORMED DYE PENETRANT TEST.	  FOUND CRACK IN CASE ABOVE NR 2 CYLINDER ALONG THE EXHAUST LIFTER BOSS.  CRACK WAS APPROXIMATELY 4 INCHES LONG.  NO APP	ARENT REASON FOR DEFECT.				1	H	7	1 	3O	3	O	NT	3A19    	E223
1999021900271	19990219	00271	EA  	1999	2	19	99ZZZX636        	2	19980127	G	7310	LW120980140	LINE            			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  					FUEL SYSTEM	BROKEN          	H				A				UNSCHED LANDING         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		NR	NOT REPORTED   	1			SW	99	190ER	593  				24170614				THE PILOT REPORTED A ROUGH ENGINE THAT RESULTED IN A PRECAUTIONARY LANDING.  THE INITIAL INSPECTION REVEALED THE NR 1 CY	LINDER FUEL INJECTOR LINE WAS BROKEN IN TWO AT THE NOZZLE END.  THE FLIGHT SCHOOL OPERATES A FLEET OF 8 M20J AIRCRAFT. A	D 93-02-05 IS ALWAYS C/W AT EACH 100-HOUR INSPECTION.  THIS IS A COMMON FAILURE, AND VERY DANGEROUS.				1	L	7	1 	3O	3	O		2A3     	1E10
1999021900272	19990219	00272	SO  	1999	2	19	99ZZZX637        	2	19980129	G	8530	SA62488	LIFTER          			CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	IO470R      	17026	SO  					NR 3 ENGINE	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	1935V	10   				18256760	763141F4			THREE INTAKE LIFTERS WENT FLAT.  NR 3 WOULD NOT PUMP UP CAUSING SERIOUS VIBRATION.  THE OTHER TWO DID EVENTUALLY PUMP UP	.  REPLACED ALL LIFTERS.  TIME ON ORIGINAL PART, 10 HOURS.  LIFTERS WERE FROM SUPERIOR AIRPARTS, INC.					1	H	7	1 	3O	3	O	NT	3A13    	3E1
1999021900273	19990219	00273		1999	2	19	99ZZZX638        	4	19980801	G	8300	887270	CLUTCH          			DIAMON	DA20  	DA20A1      		GL  										GEARBOX	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	198DA	296  			11900	10058				EXCESSIVE VIBRATION AND ROUGH RUNNING ENGINE WAS EVENTUALLY TRACKED DOWN TO REDUCTION GEARBOX CLUTCH FAILURE.  CLOSE INS	PECTION OF GEARBOX CLUTCH PER MM AT FREQUENT INTERVALS.					1	L	7	1 	3O			NT	TA4CH
1999021900274	19990219	00274	SO  	1999	2	19	99ZZZX639        	2	19980707	G	8530	6428488	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1203W	293  				310R2103	811593R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION, DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E5CE
1999010800100	19990108	00100	EA  	1999	1	8	99ZZZX64         	2	19980903	G	7412	103815504	EXCITER         			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					RT ENGINE	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	13		1    			866221C					UNIT RECEIVED AS OVERHAULED UNIT AND WAS INSTALLED ON RT ENGINE OF C-90 KING AIR.  UNIT FAILED AFTER ONE START.  FAULTY 	SOLDERING ON EXTERIOR OF CASE.  TAGS ON THE EXTERIOR OF THE UNIT DRAW A QUESTION AS TO ITS ORIGIN AND SERVICEABILITY.					1	L	7	2 	3T	4	T		3A20    	E4EA
1999021900275	19990219	00275	SO  	1999	2	19	99ZZZX640        	2	19980707	G	8530	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1203W	293  				310R2103	811593R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION, DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E5CE
1999021900276	19990219	00276	SO  	1999	2	19	99ZZZX641        	2	19980707	G	8530	6428488	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1545G	1198 				310R1220	270995R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION, DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E5CE
1999021900277	19990219	00277	SO  	1999	2	19	99ZZZX642        	2	19980707	G	8530	646277	LIFTER          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					ENGINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1545G	1198 				310R1220	270995R			ENGINE REMOVED FROM SERVICE DUE TO METAL CONTAMINATION, DUE TO PREMATURE FAILURE OF TAPPET BODIES.						1	L	7	2 	3O	3	O		3A10    	E5CE
1999021900278	19990219	00278	CE  	1999	2	19	99ZZZX643        	1	19980217	G	3250	HM4U	ROD END         			BEECH 	23    	B24R        	1151253	CE  										NLG STEERING	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	01	22PA	3098 				MC223				NOSE WHEEL NOT CENTERED.  NOSE STEERING WOULD NOT RESPOND.  FOUND FORWARD NOSE STEERING ROD END BROKEN JUST OUTSIDE OF L	OCK NUT.  CAUSE KNOWN.					1	L	7	1 	3O				A1CE
1999021900284	19990219	00284	SW  	1999	2	19	99ZZZX649        	1	19980614	G	7810	40B21089	EXHAUST PIPE    			MOONEY	M20   	M20M        	5870222	SW  										ENGINE	CRACKED         	B			OVTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	424AT	115  				270240				EXHAUST PIPE CRACKED AT THE WELD.  APPROXIMATELY A 1 INCH CRACK.  THIS CRACK HAS BEEN NOTED ON SEVERAL OTHER AIRCRAFT OF	 THE SAME MODEL IN EXACTLY THE SAME SPOT.					1	L	7	1 	3O			RT	2A3
1999010800101	19990108	00101	SO  	1999	1	8	99ZZZX65         	1	19981201	G	2840	7936500	INDICATOR       			PIPER 	PA32  	PA32300     	7103212	SO  										COCKPIT	FAILED          	G				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			SW	99	5242S					3240930				WIRE WOUND COIL IN INDICATOR SHORTED AND BURNED CAUSING SMOKE IN THE COCKPIT.						1	L	7	1 	3O				A3SO
1999021900286	19990219	00286	SO  	1999	2	19	99ZZZX651        	2	19980824	G	8520	641931	BOLT            			CESSNA	182   	182R        	2072731	CE  	CONT  	O470  	O470U       	17026	SO  					ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	5080Y					18267875	809994R			NR 2 MAIN JOURNAL THROUGH-BOLT WAS BROKEN AT TOP OF NR 2 CYLINDER.  NO OTHER DEFECT NOTED.  PILOT DID NOT STATE ABOUT AN	YTHING TO CAUSE THIS, ALL OTHER ASSOCIATED ATTACH POINTS INSPECTED OK.  ENGINE ONLY HAS 146.6 TSMOH AT FACTORY.  PER SB 	97-6, THROUGH-BOLTS ARE NOW REPLACED WITH NEW.				1	L	7	1 	3O	3	O	NT	3A13    	E273
1999021900541	19990219	00541	CE  	1999	2	19	99ZZZX654        	1	19980113	G	8120	HRJ0193	CLAMP           			BEECH 	35    	S35         	1151532	CE  										TURBOCHARGER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	7WA					D7668				AIRCRAFT WAS MODIFIED UNDER STC SA2556 TO INSTALL TSIO-520 ENGINE.  EXHAUST CLAMP TO LEFT TURBOCHARGER FAILED DUE TO COR	ROSION ALLOWING HOT EXHAUST GASSES TO MELT ALL ELECTRICAL WIRING AND VOLTAGE REGULATOR ON LEFT SIDE OF FIREWALL.  THIS B	YPASSED MASTER SWITCH SO POWER COULD NOT BE SHUT DOWN WHICH DID FURTHER DAMAGE TO ELECTRICAL SYSTEM.  SUBMITTER STATED C	AUSED BY CLAMP FAILURE, NEEDS BETTER INSPECTION OF TURBOS AND EXHAUST.			1	L	7	1 	3O				3A15
1999021900542	19990219	00542	CE  	1999	2	19	99ZZZX655        	1	19980828	G	3230	51410061	PIN             			CESSNA	402   	402C        	207590R	CE  										TORQUE LINK	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7011X					402C0255				P/N'S AFFECTED:  514106-1 SHAFT; NAS561P5-18 PIN-SPRINGS TO HOLD 5141005-9 LINK ASSY.  SAFETY PIN (NAS561P5-18) AND SAFE	TY WIRE (PER MM) THAT WAS TO SECURE PIN TO THE SHAFT (5141006-1) AND EXTERNAL APPEARANCE SHOWED NO DEFECTS.  THE SAFETY 	WIRE REMAINED IN PLACE.  WHILE IN FLIGHT WITH NO PRESSURE, PIN MOVED INBD OF THE MLG.  UPON LANDING, OTBD SIDE OF THE LI	NK ASSY PULLED AWAY FROM MLG AND CAUSED WHEEL ASSY TO ROTATE PLUS OR MINUS 90 DEGREES TO DIRECTION OF FLIGHT.  PILOT ABL	E TO MAKE AN ABORTED LANDING AND RETURNED TO BASE AIRPORT.  LANDED WITHOUT MAJOR DAMAGE.  PARTS REPLACED:  TORQUE LINK A	SSY, PINS ON BUSHING.  POSSIBLE CAUSE WHY PIN FAILED, FROZEN BUSHING, BUT ALLOWED PIN TO EXIT.  LAST AAIP INSP FOR MLG	1	L	7	2 	3O				A7CE
1999021900543	19990219	00543	NM  	1999	2	19	99ZZZX656        	1	19980401	G	2752	6740100	ACTUATOR        	EEMCO       		ISRAEL	1125  	1125        		NM  										FLAP	FAILED          	H				O				OTHER                   				F			FLT CONT AFFECTED         			DE	DESCENT        	1			WP	15	279DS		10   		453	040				ON DESCENT FROM A LONG HIGH ALTITUDE FLIGHT, FLAPS DID NOT RESPOND TO DOWN COMMAND.  ON THE GROUND AFTER APPROX 20 MINUT	ES, THE CURRENT LIMITER WAS RESET AND FLAPS WORKED AS COMMANDED.  UPON RETURNING HOME, ALL FLAP ACTUATORS WERE COOLED TO	 TEMPERATURES BELOW FREEZING AND ABOVE CRUISE.  ONE ACTUATOR FAILED; THIS ACTUATOR HAD LESS THAN 10 FLIGHT HRS BETWEEN O	/H AND FAILURE.  FURTHER INSPECTION OF FAILED ACTUATOR SHOWED A SEAL BETWEEN THE JACKSCREW AND GEARBOX DID NOT SEAL.  SU	BMITTER SUSPECTED THIS SEAL FAILURE ALLOWED JACKSCREW LUBRICANT INTO GEARBOX DURING OVERHAUL AND RECOMMENDED LUBRICATION	 PROCEDURES GIVEN IN AIRCRAFT MM BE FOLLOWED DURING OVERHAUL.	2	L	7	2 	4F			RT	A16NM
1999021900544	19990219	00544	NE  	1999	2	19	99ZZZX657        	2	19980423	G	7200		CONTROLLER      	HAMSTD      		BOEING	767   	767383      	1385214	NM  	PWA   	4060  	PW4060      	52119	NE  					LT ENGINE	MALFUNCTIONED   	W			ANCF	C				ABORTED TAKEOFF         				J			WARNING INDICATION        			TO	TAKEOFF        	1			SO	23	984AN				880622		724152			JFK/BOG - FLT 021 - EICAS MESSAGE.  LEFT ENGINE, HPSOV DISPLAYED LEFT ENGINE BLEED LGT ILLUMINATED STEADY AT HIGH THRUST	.  DUCT PRESSURE NOT CHECKED.  TAKEOFF WAS REJECTED AT 90 KNOTS.  PERFORMED TROUBLESHOOTING ACCORDING TO 36-10-00 PG 127	.  HI PRESS VALVE FAILS TO CLOSE.  HI STAGE BLEED VALVE CLOSED AND LOCKED PER MEL 36-11-2 CAT C.				2	L	7	2 	4F	4	F	RT	A1NM    	E24NE
1999010800102	19990108	00102	SO  	1999	1	8	99ZZZX66         	1	19981217	G	3213		MLG             			PIPER 	PA32  	PA32300     	7103212	SO  										RIGHT	SEPARATED       	G				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			GL	15	32037					327540009				THE RT MAIN LANDING GEAR LOWER STRUT AND WHEEL CAME OFF DURING TAKEOFF.  THE AIRCRAFT LANDED, MINOR DAMAGE.  EXAMINATION	 OF THE UPPER STRUT AND UPPER HALF OF THE TORQUE LINK DOES NOT INDICATE COMPONENT FAILURE.					1	L	7	1 	3O				A3SO
1999021900547	19990219	00547	EU  	1999	2	19	99ZZZX660        	1	19981102	G	2810	257PT51	FUEL TANK       			BRAERO	DH125 	HS125700A   	4230170	EU  										FUSELAGE	CHAFED          	B			UVVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	5511A	8846 			OHB113	NA0279				UPON INSPECTION OF VENTRAL TANK AFTER REMOVAL FROM AIRCRAFT, SEVERAL AREAS OF SIDE WALLS WERE FOUND SCORED AND CHAFED IN	 RADIUS.  SAID AREAS APPEAR TO HAVE BEEN SCORED DURING PREVIOUS REMOVAL PROCEDURES USING SHARP INSTRUMENT TO CUT BEAD SE	ALING.  THE SIDE WALLS HAVE BEEN DEEMED UNAIRWORTHY BY THE RAYTHEON REPAIR DESIGN OFFICE AND ARE BEING REPLACED.  PROPER	 TECHNIQUES USING APPROVED TOOLING TO REMOVE SEALANT RECOMMENDED.			2	L	7	2 	4F				A3EU
1999021900548	19990219	00548	EU  	1999	2	19	99ZZZX661        	1	19981102	G	2810	25PT3A	FUEL TANK       			HWKSLY	DH125 	DH125400A   	4230140	EU  										FUSELAGE	CHAFED          	B			UVVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	730TS	12404			DH364	NA0730				UPON INSPECTION OF VENTRAL TANK AFTER REMOVAL FOR AIRCRAFT, SEVERAL AREAS OF SIDEWALLS WERE FOUND SCORED AND CHAFED IN R	ADIUS.  SAID AREAS APPEAR TO HAVE BEEN SCORED DURING PREVIOUS REMOVAL PROCEDURES USING SHARP INSTRUMENT TO CUT BEAD SEAL	ING.  THE SIDE WALLS HAVE BEEN DEEMED UNAIRWORTHY BY THE RAYTHEON REPAIR/DESIGN OFFICE AND ARE BEING REPLACED.  PROPER T	ECHNIQUES USING APPROVED TOOLING TO REMOVE SEALANT RECOMMENDED.			2	L	7	2 	4J				A3EU
1999021900549	19990219	00549	NM  	1999	2	19	99ZZZX662        	1	19980608	G	5320	BACB30MT18T68	BOLT            			BOEING	737   	737291      	138448W	NM  										BS 695	BROKEN          	B			OMJR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	19	7375F					20363				DURING ACCOMPLISHMENT OF BOEING 737 SB 53-1080 BS 695, LEFT LOWER FITTING REPLACEMENT, LOWER BOLT P/N BACB30MT18T68, APP	EARED LOOSE.  BOLT WAS ACTUALLY BROKEN IN HALF AND CORRODED.  TT:  65,651.2 HOURS.  TC:  64,805.					2	L	7	2 	4F				A16WE
1999021900550	19990219	00550	CE  	1999	2	19	99ZZZX663        	1	19980311	G	3233	508202085	NUT             			BEECH 	200   	B200        	1152922	CE  										NLG ACTUATOR	STRIPPED        	D				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CE	09	75ZT	5385 				BB967				THE NOSE GEAR FAILED TO EXTEND FULLY BEFORE LANDING.  ELECTRICAL AND MANUAL EXTENSION PROCEDURE WERE NOT SUCCESSFUL CAUS	ING THE NOSE GEAR TO COLLAPSE DURING LANDING.   INSPECTION OF THE NOSE GEAR ACTUATOR, P/N 50-820208-5, REVEALED THAT NUT	 ASSY, P/N 90-820015-1, THREADS WERE STRIPPED.  ACTUATOR TT:  5,385.2 HOURS.  TC:  5,547.  CYCLES SINCE 30-MONTH END PLA	Y INSPECTION, 153.  ACTUATOR, S/N 625T81.			1	L	7	2 	4T				A24CE
1999021900551	19990219	00551	CE  	1999	2	19	99ZZZX664        	1	19980218	G	3242	CFA299	BRAKE           	GOODYEARAERO		BEECH 	35    	J35         	1151522	CE  										MLG	GLAZED          	G				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			WP	27	7202B					D5501				DURING AN ABORTED TAKEOFF, BRAKES WERE REPORTED TO BE INEFFECTIVE.  INSPECTION REVEALED BRAKE PADS AND DISCS WERE WITHIN	 LIMITS.  HOWEVER, DISCS AND PADS WERE GLAZED.					1	L	7	1 	3O				3A15
1999021900552	19990219	00552	EA  	1999	2	19	99ZZZX665        	1	19980330	G	2820		LINE            			DHAV  	DHC2  	DHC2MK3     	2800107	EA  										FUEL SYSTEM	LEAKING         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	11	53011					1646				FOUND FUEL LEAKING FROM BELLY OF AIRCRAFT.  ACCESSED AREA, FOUND LEAKING FUEL LINER FROM CORROSION.  HOLE IN LINES PREVI	OUSLY COVERED WITH SPLIT HOSE AND HOSE CLAMPS.  REPLACED LINES.  AIRCRAFT OPERATED ON FLOATS IN SALT WATER.  KETICHAN, A	LASKA.				1	H	7	1 	3T				A806
1999021900553	19990219	00553	NM  	1999	2	19	99ZZZX666        	1	19980709	G	5210	65B01836329	FRAME           			BOEING	747   	747230B     	1384889	NM  										PASSENGER DOOR	CRACKED         	B			AY54	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	35	512MC					21220				AT LOCATION, LOWER FORWARD ON DOOR, L1.  FOUND CRACK 12 INCHES VERTICAL AND 8 INCHES HORIZONTAL IN CHANNEL SECTIONS.						2	L	7	4 	4F				A20WE
1999021900554	19990219	00554	GL  	1999	2	19	99ZZZX667        	3	19980330	G	6110	10138902715	CONTROL CABLE   			BEECH 	B300  	B300        	1159232	CE  						HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	510WP	1247 				FL109				DURING RIGHT ENGINE INSPECTION, 05300 '0', FOUND RIGHT ENGINE PROPELLER CABLE, P/N 101-389027-15, LOOSE IN CLAMP, P/N RA	1039C, AND THAT CABLE HAD CHAFED IN CLAMP.  IT CANNOT BE BY ROUTINE INSPECTION.  THE CABLE MUST BE REMOVED FROM CLAMP.					2	L	7	2 	4T			RT	A24CE   		6	C	P56GL
1999021900555	19990219	00555	NM  	1999	2	19	99ZZZX668        	1	19981228	G	5320	65263078	TEE             			BOEING	727   	7272B7      	138407L	NM  										BS 1223	CORRODED        	B			KT3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	923PG					22163				DURING A C-CHECK, CORROSION WAS NOTED ON T-CHORD, STA 1223, RBL 23 (LOWER CHORD).						2	L	7	3 	4F				A3WE
1999021900556	19990219	00556	CE  	1999	2	19	99ZZZX669        	1	19980522	G	3230	998100673	BOLT            		5081033513  	BEECH 	200   	200BEECH    	1152920	CE  										RT MLG	BROKEN          	H				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			GL	13	2883	3354 				BB144				DURING LANDING, RT MAIN LANDING GEAR LEG PIVOT BOLT BROKE ALLOWING GEAR TO FOLD AFT INTO NACELLE AND RT INBOARD FLAP.  P	ROPELLER REPEATEDLY STRUCK RUNWAY DURING LANDING ROLL-OUT AND ENGINE WAS RUNNING PART OF THE TIME DURING ROLL-OUT.  BOTH	 REMOVED FOR REPAIR AS REQUIRED.				1	L	7	2 	4T				A24CE
1999010800103	19990108	00103	CE  	1999	1	8	99ZZZX67         	1	19981202	G	2140	MS208225	ELBOW           			BEECH 	58    	58TC        	1152746	CE  										HEATER	CORRODED        	B		A	R2JR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	21	23712					TK67				WHILE PERFORMING HEATER TEST PER AD NOTE 96-20-07, FOUND ELBOW FITTING FOR HEATER COMBUSTION CHAMBER DRAIN LEAKING.  FUR	THER INVESTIGATION SHOWED ALUMINUM FITTING WAS BADLY CORRODED THROUGH AND FUEL DRAIN PASSAGE WAS COMPLETELY CLOGGED WITH	 CORROSION.  WITH THIS DRAIN BLOCKED UNBURNED FUEL WILL JUST LAY IN HEATER INSTEAD OF DRAINING OVERBOARD.  SUBMITTER STA	TED COULD EXPLODE IF IGNITED.  INSTALLED MS20822-5J STAINLESS STEEL FITTING TO ELIMINATE CORROSION PROBLEM.  SUGGEST ALL	 JANITROL HEATER INSTALLATIONS BE CHECKED TO BE SURE STAINLESS FITTINGS ARE INSTALLED IN EMERGENCY FUEL DRAINS.		1	L	7	2 	3O				A23CE
1999021900563	19990219	00563	GL  	1999	2	19	99ZZZX676        	3	19980930	G	6114		HUB             			CESSNA	411   	411A        	2075904	CE  						MCAULY	3AF34C	3AF34C74    	GL  	PROPELLER	CRACKED         	B			W59R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	210Z					4110292		751006		CRACK WAS FOUND DURING PENETRANT INSPECTION ON OUTSIDE OF NR 1 SOCKET.  PROPELLER WAS BEING INSPECTED PER SL 93-11-2, AD	 95-24-11.					1	L	7	2 	3O				A7CE    		5	C	P22EA
1999021900564	19990219	00564	CE  	1999	2	19	99ZZZX677        	1	19981213	G	2140	10138001317	VALVE           			BEECH 	100   	B100        	1152919	CE  										BLEED AIR SYSTEM	MALFUNCTIONED   	B			XEFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	949SW				554	BE34				PILOT REPORTED EXCESSIVE HEAT IN COCKPIT.  FOUND RIGHT SIDE BLEED AIR SHUT-OFF VALVE STUCK OPEN.  REMOVED P/N 101-380013	-17, S/N 554.  REPLACED WITH P/N 101-380013-17, S/N 634.  RUN-UP OPERATIONAL CHECK GOOD.					1	L	7	2 	4T				A14CE
1999021900566	19990219	00566	SO  	1999	2	19	99ZZZX679        	2	19981002	G	8520		ROD             			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	SEPARATED       	D				A				UNSCHED LANDING         				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			SW	99	938V		226  			TC1835	454604CS			ENGINE DEVELOPED EXTREME VIBRATION CLIMBING THROUGH 2,500 FEET MSL.  OIL OBSERVED COMING FROM COWLING.  ENGINE SHUT DOWN	 AND SECURED.  POST-FLIGHT INSPECTION REVEALED NR 4 CYLINDER CONNECTING ROD EXITED THROUGH CRANKCASE.  PISTON BROKEN.  S	EVERAL INTERNAL PARTS INSIDE ENGINE COWL.				1	L	7	2 	3O	3	O	RT	3A16    	3E1
1999010800104	19990108	00104	SW  	1999	1	8	99ZZZX68         	1	19980911	G	7160	JE5	ACTUATOR ARM    			MOONEY	M20   	M20J        	5870219	SW  										AIR BOX	BROKEN          	B			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	2146X	6    				243413				DURING ANNUAL INSPECTION, THE ACTUATOR ARM FOR THE ALTERNATE AIR DOOR SWITCH WAS FOUND BROKEN.  SIX HOURS AFTER THE NEW 	SWITCH ACTUATOR WAS INSTALLED, THE PILOT REPORTED THE ALTERNATE AIR LIGHT WAS ON.  AFTER INVESTIGATING THE CAUSE OF THE 	LIGHT, DISCOVERED THE SWITCH ACTUATOR WAS BROKEN.				1	L	7	1 	3O				2A3
1999021900567	19990219	00567	CE  	1999	2	19	99ZZZX680        	1	19980507	G	5520	08320000180	HINGE           			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ELEVATOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	7947Q	9656 				402B0397				HINGE ATTACHMENT DOUBLER CRACKED FOR UPPER RADIUS CORNER FORWARD AND DOWN.  CRACK LENGTH, APPROXIMATELY 1.25 INCHES.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1999022600051	19990226	00051	GL  	1999	2	26	99ZZZX686        	2	19980310	G	7313	689091	FUEL NOZZLE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	DAMAGED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	369AW		1060 			470117D				COMBUSTION TURBINE LINER CHAFED, FUEL NOZZLE SHROUD DAMAGED.  FOUND DURING 100-HOUR INSPECTION.  FUEL NOZZLE WAS REPLACE	D AND SENT FOR REPAIR.  S/N AG55376.  CONTROL NR 98-3-5.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1999022600059	19990226	00059	SW  	1999	2	26	99ZZZX688        	1	19981128	G	5510	206023119109	SUPPORT         		407023800101	BELL  	407   	407         		SW  										HORIZONTAL STAB	CRACKED         	B			ALGR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	497AL					53172				DURING DAILY INSPECTION, FOUND LEFT SLAT SUPPORT, SECOND FROM INBD, CRACKED.  UPON FURTHER INSPECTION, FOUND SLAT POSITI	ONS SWAPPED ON AIRCRAFT (LEFT INSTALLED ON RIGHT SIDE AND VICE VERSA).  SWAPPED SLAT POSITIONS AND REMOVED AND REPLACED 	CRACKED SLAT SUPPORT P/N 206-023-119-109, SECOND FROM INBD ON RIGHT SIDE.				1	G	7	1 	3U			O	H2SW
1999010800105	19990108	00105		1999	1	8	99ZZZX69         	4	19981214	G	3416	5934PA58	ALTIMETER       			CESSNA	206   	TU206F      	2073353	CE  										COCKPIT	READS HIGH      	E				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			NM	08	1953U	4169 	2639 		100692	U20602306				ALTIMETER READ 6,000 FEET.  GLASS FACE WAS TAPPED ON, READING FELL TO 3,000 FEET.  ALTIMETER APPARENTLY HAS NOT BEEN OVE	RHAULED SINCE 3/90.  LOG BOOK ENTRY 2-4-75, 326.2 HOURS, SHOWS C/W AD 74-24-13.  SUBMITTER RECOMMENDED A TBO.					1	H	7	1 	3O				A4CE
1999022600078	19990226	00078		1999	2	26	99ZZZX695        	4	19980322	G	3417	AZ8107000700974	COMPUTER        			CNDAIR	CL600 	CL6002B16   	1900305	EA  										AFCS	FAILED          	D				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			SO	15	79AD		96   		90054101	5140				AIRCRAFT LEVEL AT 12,000 FEET.  325 KNOTS FOR TEN MINTUES WITH AP NAV AND ALT ANNUNCIATION.  ALT PRE-SELECT AT 12,000 FE	ET.  PILOT, LT SEAT MADE COMMENT ABOUT A FEELING.  RT SEAT PILOT THEN NOTICED THE ACFT PASSING THROUGH 12,250 FEET JUST 	WHEN ALT ALERT HAD SOUNDED.  ACFT WAS CLIMBING FOR COMMAND BARS WHICH WERE AT 7/8 DEGREES.  CREW PUNCHED OFF AUTOPILOT A	ND SLOWED CLIMB TO A STOP AT 12,650 FEET.  ATC ADVISED OF PROBLEM AND DEVIATION.  CREW MANUAL FLEW ACFT BACK TO 12,000 F	EET.  A LANDING AT DESTINATION MADE WITHOUT FURTHER INCIDENT.  NO FLAGS NOTED DURING OCCURRENCE.  GROUND FAULT TEST SHOW	ED NO FAULTS OCCURRED.  SUSPECT NR 1 ADC.  IT WAS REMOVED AND REPLACED.  BOTH ALT'S TESTED.  ACFT RETURNED TO SERVICE.	2	L	7	2 	4F			RT	A21EA
1999022600082	19990226	00082	SO  	1999	2	26	99ZZZX699        	1	19981201	G	7910	CH48108	OIL FILTER      			PIPER 	PA28  	PA28RT201T  	7102817	SO  										ENGINE	CONTAMINATED    	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	02	8075M				F01H091	28R7931302				UPON INSPECTING THE INSIDE AT THIS OIL FILTER CANISTER AS PART OF A PERIODIC FILTER CHANGE, FOUND A CUTTER STRING ABOUT 	6 INCHES LONG WITH A KNOT ABOUT HALF WAY IN THE MIDDLE, APPROXIMATELY TWO INCHES OF THIS STRING HAD MADE ITS WAY THROUGH	 THE FILTER BYPASS VALVE.				1	L	7	1 	3O				2A13
1999010800017	19990108	00017	CE  	1999	1	8	99ZZZX7          	1	19980205	G	2130	1303581	RELAY           			CESSNA	500   	560CESSNA   	2076750	CE  										PNEUMATIC SYS	MALFUNCTIONED   	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	339QS				701009	5600339				ORIGINAL PROBLEM WAS ERRATIC PRESSURIZATION.  TROUBLESHOT SYSTEM DOWN TO A BAD PNEUMATIC RELAY.  REMOVED AND REPLACED RE	LAY AND ACFT FAILED FUNCTIONAL CHECK FLIGHT.  ACFT HAD NO PRESSURIZATION.  REMOVED AND REPLACED WITH SECOND NEW RELAY. S	YSTEM OPS AND CHECKS GOOD ON GROUND AND PASSED FUNCTIONAL CHECK FLIGHT.				2	L	7	2 	4F			RT	A22CE
1999010800106	19990108	00106	EA  	1999	1	8	99ZZZX70         	2	19981201	G	7414	6351	MAGNETO         			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  					ENGINE	CRACKED         	E				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	15950	637  				32734075				MAGNETO CRACKED.  SUBMITTER STATED CRACKS MAY HAVE OCCURRED DURING DISASSEMBLY OF DEFECTIVE PART.						1	L	7	1 	3O	3	O		A3SO    	1E4
1999022600083	19990226	00083	EA  	1999	2	26	99ZZZX700        	2	19981030	G	8530	73807	SET SCREW       		60831       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					INTAKE VALVE	MALFUNCTIONED   	H				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			SO	16	89561		369  			15282786	L1916115			AIRCRAFT AT CRUISE SPEED AT APPROXIMATELY 3,000 FEET, VALVE ADJUSTING SCREW COMPLETELY BACKED OUT OF ROCKER ASSY.  LOSS 	OF INTAKE VALVE FOR THAT CYLINDER ENSUED CAUSING LOSS OF POWER, AND EMERGENCY LANDING OF AIRCRAFT.					1	H	7	1 	3O	3	O	NT	3A19    	E223
1999022600084	19990226	00084	SO  	1999	2	26	99ZZZX701        	1	19980325	G	3710		PUMP            			PIPER 	PA30  	PA30        	7103002	SO  										VACUUM SYSTEM	DAMAGED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	8607Y					301747				FOUND UPPER RIGHT HAND TUBE OF LEFT ENGINE MOUNT DENTED ON THE BOTTOM.  FOUND FITTING OF SIGMA-TEK VACUUM PUMP ALSO DAMA	GED.  DETERMINED SET-UP OF SIGMA-TEK PUMPS (PORTS PERPENDICULAR TO AXIS OF PUMP RATHER THAN PARALLEL AS ON AIRBORNE) PUT	 FITTING TOO CLOSE TO MOUNT.  VIBRATION OF ENGINE CAUSED FITTINGS TO IMPACT AND DAMAGE MOUNT.  LORD MOUNTS OK.				1	L	7	2 	3O				A1EA
1999022600085	19990226	00085	SO  	1999	2	26	99ZZZX702        	1	19980415	G	7810	40B2295	TAIL PIPE       			PIPER 	PA46  	PA46350P    		SO  										ENGINE	CRACKED         	B		A	LF1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	9140N	1119 				4622014				DURING INSPECTION, FOUND EXHAUST STAINING IN HOSE FROM HEAT MUFFLER TO ENVIRONMENTAL PACK.  REMOVED TAIL PIPE AND PRESSU	RIZED.  FOUND TO BE LEAKING UNDER FINS ON HEAT EXCHANGER.  POSSIBLE CAUSE IS NORMAL AGE/WEAR.  RECOMMEND MAKING THIS A 5	00-HOUR ITEM.  NOTE:  HEATED AIR DOES NOT MIX WITH PRESSURIZED AIR UNDER NORMAL CIRCUMSTANCES, BUT SHOULD NOT HAVE CARBO	N MONOXIDE PRESENT IN ANY PART OF SYSTEM.			1	L	7	1 	3O			RT	A25SO
1999022600086	19990226	00086	CE  	1999	2	26	99ZZZX703        	1	19980521	G	8011	SA529800M15	SPRING          			CESSNA	414   	414A        	2075907	CE  										STARTER	BROKEN          	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	2664F	348  				414A0534				PILOT REPORTED PROP STOPPED DURING START AND REQUIRED PHYSICALLY MOVING PROP TO GET ENGINE TO TURN OVER AGAIN WITH START	ER.  ENGINE STARTED AND PILOT FLEW BACK TO HOME BASE.  OIL FILTER WAS REMOVED AND BRASS SLIVERS WERE FOUND IN ALL THE FO	LDS.  STARTER ADAPTER WAS REMOVED AND SPRING SA 529800 WAS BROKEN AT THE NOTCH WHERE IT ATTACHES TO THE BRASS GEAR.  THE	 ROUGH BROKEN END WAS CUTTING SPLINTERS UP TO 3 INCHES LONG OFF THE BRASS WHEEL.  ALSO, THE SPRING CUP IN THE ADAPTER HA	D SLID OUT OF ADAPTER FAR ENOUGH TO CONTACT STARTER SHAFT.  THIS MAY HAVE CAUSED SPRING TO BREAK OR THE SPRING MAY HAVE 	BEEN DEFECTIVE.  TIME ON ADAPTER, 5,602 HOURS.  SUBMITTER RECOMMENDS RE-SECURING SPRING CUP AT O/H.	1	L	7	2 	3O				A7CE
1999022600087	19990226	00087	SO  	1999	2	26	99ZZZX704        	2	19981214	G	7420		HARNESS         			TMPSON	NAVION	NAVIONG     	6150120	SW  	CONT  	O520  	IO520B      	17032	SO  					IGNITION SYSTEM	DAMAGED         	H	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	07	2431T	113  				NAV42431				RUBBER INSULATOR STICKING IN SPARK PLUG.  LEAD PULLS LOOSE OF CRIMP ON SRPING END DURING REMOVAL.						1	L	7	1 	3O	3	O		A782    	E5CE
1999022600088	19990226	00088	SO  	1999	2	26	99ZZZX705        	2	19980319	G	8520	WDC65050	CRANKCASE       			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	7351R	3348 	1634 			TH481	270710R			ENGINE CASE HAD A CATASTROPHIC FAILURE AROUND NR 4 CYLINDER IN-FLIGHT.  POSSIBLE CAUSE - CASE FATIGUE.						1	L	7	2 	3O	3	O		3A16    	E5CE
1999022600089	19990226	00089	CE  	1999	2	26	99ZZZX706        	1	19980715	G	2571		BATTERY BOX     			CESSNA	210   	T210L       	2073449	CE  										COCKPIT	LEAKING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	08	2259S	2105 				21061203				DURING ANNUAL INSPECTION, BATTERY ACID WAS FOUND TO HAVE LEAKED INTO COCKPIT ONTO LEFT RUDDER PEDAL, ATTACHING TUBING, A	ND GENERAL AREA BELOW PEDAL.  ACID HAD FLOWED THROUGH CORRODED RIVET HOLE ONTO SEAT FOR CABIN HEAT AND DRIPPED INTO FLOO	R AREA.  SUBMITTER BELIEVED THE BATTERY WAS TOO FULL OF ACID AND GASSED DURING CHARGING ALLOWING LIQUID INTO BATTERY BOX	, AND, SUGGESTED CLOSE INSPECTION OF BATTERY BOXES DURING ALL MAINTENANCE.			1	H	7	1 	3O				3A21
1999022600091	19990226	00091	CE  	1999	2	26	99ZZZX708        	1	19980728	G	5712	57222061	RIB             			CESSNA	441   	441         	2076020	CE  										RT WING	CRACKED         	B			WTXR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	2628M	4848 				4410151				DURING A PHASE INSPECTION, FOUND A 1.25 INCH CRACK IN THE RT WING CANTED RIB TOP CAP.  CRACK STARTS AT AFT SIDE OF FORWA	RD WING SPAR AND RUNS AFT PARALLEL TO THE BEND RADIUS APPROXIMATELY 1.25 INCHES IN LENGTH.  STOP DRILLED BOTH ENDS OF CR	ACK PER CESSNA INSTRUCTIONS.				1	L	7	2 	3T			RT	A28CE
1999022600092	19990226	00092	EU  	1999	2	26	99ZZZX709        	1	19980813	G	2130	BA1723300	COUPLER         			HWKSLY	DH125 	DH125400A   	4230140	EU  										E/E BAY	FAILED          	H				D				RETURN TO BLOCK         				O			OTHER                     			NR	NOT REPORTED   	1			EA	13	498RS					NA749				HOSE COUPLER, PN BA1723-300, ON THE DUCT ASSY, SILENCER ASSY CAME OFF ONE SIDE CAUSING COMPLETE LOSS OF PRESSURZATION. R	E-INSTALLED PER MM.  REMOVED AND REPLACED BOTH CLAMPS WITH NEW.					2	L	7	2 	4J				A3EU
1999010800107	19990108	00107	SO  	1999	1	8	99ZZZX71         	1	19980724	G	3230	9582900	DOWNLOCK        			PIPER 	PA34  	PA34200     	7103405	SO  										NLG	OUT OF ADJUST   	G				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			WP	09	15068					347350008				NOSE GEAR DOWNLOCK LINK  WAS NOT ADJUSTED PROPERLY, AND, WITH WEAR IN THE NOSE LANDING GEAR SYSTEM AS A CONTRIBUTING FAC	TOR, CAUSED THE LINK ROD END TO BE BROKEN IN TWO WHEN THE LANDING GEAR WAS CYCLED.  SUBMITTER RECOMMENDED SPECIAL ATTENT	ION TO THIS AREA DURING INSPECTION AND MAINTENANCE.				1	L	7	2 	3O				A7SO
1999022600093	19990226	00093	CE  	1999	2	26	99ZZZX710        	1	19980707	G	3230	50290025	BRACKET         			CESSNA	310   	310R        	2074245	CE  										MLG	SEPARATED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05	1203W	6340 				310R2106				THE BRACKET ASSY SEPARATED AT THE BEARING BOSS DURING LANDING GEAR RETRACTION.  IT APPEARS THAT THERE MAY HAVE BEEN A CR	ACK WHICH WENT UNDETECTED IN THE BEARING BOSS AREA.  DYE PENETRANT INSPECTION RECOMMENDED.					1	L	7	2 	3O				3A10
1999022600094	19990226	00094	SO  	1999	2	26	99ZZZX711        	1	19980210	G	2720	1686900	TORQUE TUBE     			PIPER 	PA23  	PA23250     	7102308	SO  										RUDDER PEDAL	BROKEN          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	40510	5555 				277405241				PILOT COMPLAINED OF POOR TURN RADIUS TO LEFT. RUDDER CONTROL IN-FLIGHT WAS OK.  INVESTIGATION DISCLOSED PLAY BETWEEN PIL	OT'S AND CO-PILOT'S LT RUDDERS.  MATING FLANGE UNDER PILOT'S FLOOR HAD ONE OF THREE TRIANGULAR EARS BROKEN OFF, OTHER TW	O CRACKED AND FLEXING.  CRACKS RADIATING FROM BOLT HOLES.  AREA VERY DIFFICULT TO INSPECT WITHOUT REMOVING THE FORWARD F	LOOR PLATES AROUND RUDDER PEDALS.  SUBMITTER SUGGESTED DOING THIS AT EACH ANNUAL..  GUST LOADS ON RUDDER POSSIBLE CAUSE.			1	L	7	2 	3O				1A10
1999022600095	19990226	00095	SO  	1999	2	26	99ZZZX712        	1	19980728	G	5751	17100018	SPAR            			PIPER 	PA23  	PA23250     	7102308	SO  										INBD END LT AIL	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	40510	5555 				277405241				PRE-FLIGHT DISCLOSED 'CLICKING' NOISE (LIKE OIL CANNING).  NOISE ISOLATED AT HINGE ATTACH AREA AT INBOARD END OF LT AILE	RON.  REMOVED HINGE ATTACH HARDWARE TO FACILITATE INSPECTION.  RIB CRACKED IN RADIUS OF SPAR ATTACH FLANGE, OTBD OF LOWE	R ATTACH BOLT FOR HINGE.  SUSPECTED CAUSE IS GUST LOADS.  AIRCRAFT HAS NO CONTROL LOCKS.  AILERON SPAR ALSO CRACKED NEAR	BY.  USED, REPLACEMENT AILERON ALSO HAD IDENTICAL CRACK IN RIB ONLY (ALTHOUGH VENDOR WAS WARNED TO INSPECT FOR THIS).  A	LUMINUM GAUGE MAY BE TOO LIGHT.  SUBMITTER SUGGESTED INSPECTIONS IN DETAIL, FUTURE USE OF SEAT BELTS, TO SECURE CONTROLS	 WHILE TIED DOWN.	1	L	7	2 	3O				1A10
1999022600096	19990226	00096	SO  	1999	2	26	99ZZZX713        	1	19980728	G	5751	17100013	RIB             			PIPER 	PA23  	PA23250     	7102308	SO  										INBD END LT AIL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	01	40510	5555 				277405241				PRE-FLIGHT DISCLOSED 'CLICKING' NOISE (LIKE OIL CANNING).  NOISE ISOLATED AT HINGE ATTACH AREA AT INBOARD END OF LT AILE	RON.  REMOVED HINGE ATTACH HARDWARE TO FACILITATE INSPECTION.  RIB CRACKED IN RADIUS OF SPAR ATTACH FLANGE, OTBD OF LOWE	R ATTACH BOLT FOR HINGE.  SUSPECTED CAUSE IS GUST LOADS.  AIRCRAFT HAS NO CONTROL LOCKS.  AILERON SPAR ALSO CRACKED NEAR	BY.  USED, REPLACEMENT AILERON ALSO HAD IDENTICAL CRACK IN RIB ONLY (ALTHOUGH VNDOR WAS WARNED TO INSPECT FOR THIS).  AL	UMINUM GAUGE MAY BE TOO LIGHT.  SUBMITTER SUGGESTED INSPECTIONS IN DETAIL, FUTURE USE OF SEAT BELTS, TO SECURE CONTROLS 	WHILE TIED DOWN.	1	L	7	2 	3O				1A10
1999022600097	19990226	00097	CE  	1999	2	26	99ZZZX714        	1	19980320	G	5280	12114806	HINGE           			CESSNA	210   	210J        	2073439	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	3311S	3415 				21059111				ON ANNUAL INSPECTION, SEVERAL GEAR DOOR HINGES WERE FOUND CRACKED.  CESSNA P/N'S:  1211480-6, 1211480-1, AND 1211480-3. 	 TWO POSSIBLE CAUSES MIGHT BE IMPROPERLY RIGGED DOORS AND/OR THE AGE OF THE HINGES.					1	H	7	1 	3O				3A21
1999022600098	19990226	00098	CE  	1999	2	26	99ZZZX715        	1	19980320	G	5280	12114801	HINGE           			CESSNA	210   	210J        	2073439	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	3311S	3415 				21059111				ON ANNUAL INSPECTION, SEVERAL GEAR DOOR HINGES WERE FOUND CRACKED.  CESSNA P/N'S:  1211480-6, 1211480-1, AND 1211480-3. 	 TWO POSSIBLE CAUSES MIGHT BE IMPROPERLY RIGGED DOORS AND/OR THE AGE OF THE HINGES.					1	H	7	1 	3O				3A21
1999022600099	19990226	00099	CE  	1999	2	26	99ZZZX716        	1	19980320	G	5280	12114803	HINGE           			CESSNA	210   	210J        	2073439	CE  										MLG DOOR	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	13	3311S	3415 				21059111				ON ANNUAL INSPECTION, SEVERAL GEAR DOOR HINGES WERE FOUND CRACKED.  CESSNA P/N'S:  1211480-6, 1211480-1, AND 1211480-3. 	 TWO POSSIBLE CAUSES MIGHT BE IMPROPERLY RIGGED DOORS AND/OR THE AGE OF THE HINGES.					1	H	7	1 	3O				3A21
1999022600100	19990226	00100	CE  	1999	2	26	99ZZZX717        	1	19981009	G	2730	05130633	BRACKET         			CESSNA	172   	172H        	2072424	CE  										BS 22	BROKEN          	B		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	23	3910R	5538 				17255410				ELEVATOR BELLCRANK BRACKET FOUND BROKEN IN NUMEROUS SPOTS WHERE IT ATTACHES TO FUSELAGE CROSS RIBS, STA 22 UNDER FLOORBO	ARD PANEL.  DETERMINED POSSIBLE CAUSE AS NO GUSTLOCK INSTALLED DURING HIGH WINDS.					1	H	7	1 	3O			NT	3A12
1999022600101	19990226	00101	EA  	1999	2	26	99ZZZX718        	1	19981207	G	5540		POST            			SCWZER	G164  	G164B       	3952802	EA  										RUDDER	CORRODED        	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	3633Q					777B				INSPECTION OF RUDDER REVEALED SEVERE RUST CORROSION ON THE EXTERIOR OF THE LOWER RUDDER POST.  SCHWEIZER SB'S 61, 88, AN	D AD 78-08-09 CALL FOR INSPECTION OF RUDDER POST IN THIS AREA.  SUBMITTER RECOMMENDATION IS THAT AN INSPECTION BE CALLED	 FOR ON ALL G-164 SERIES AIRCRAFT AND SERIAL NUMBERS.				1	Q	7	1 	3R				1A16
1999022600102	19990226	00102	CE  	1999	2	26	99ZZZX719        	1	19981116	G	7111	6017001067	BAFFLE          		96110005701 	BEECH 	58    	58          	1152740	CE  										LT WING	MISINSTALLED    	D				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			EA	21	600RV	234  				TH1854				REFERENCE BUCK 58 PARTS CAT 57-20-24, ITEM 32.  BAFFLE PLATE MAKING CONTACT WITH HEATED FUEL VENT VALVE FLOAT NOT ALLOWI	NG VALVE TO CLOSE, DUMPING FUEL WHEN TANK IS FULL.  SHIMS REQUIRED TO ALLOW VALVE TO MOVE.  VALVE REPLACED WITH NO IMPRO	VEMENT.				1	L	7	2 	3O				3A16
1999010800108	19990108	00108	CE  	1999	1	8	99ZZZX72         	1	19981103	G	3230	22130117	BUMPER          			CESSNA	172   	172RG       	2072438	CE  										NLG WW	WORN            	D		A		O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	172RG	5105 				172RG0083				NOSE GEAR WOULD NOT EXTEND CAUSING A LANDING WITHOUT THE NOSE GEAR DEPLOYED, CAUSING DAMAGE TO THE PROPELLER AND NOSE SE	CTION.  THE NOSE GEAR BUMPER AT THE TOP OF THE WHEELWELL WHICH DETERMINES THE NOSE GEAR RETRACTION HEIGHT WAS WORN OUT. 	 THIS ALLOWS THE NOSE GEAR TO RETRACT HIGHER THAN NORMAL.  SINCE THE NOSE GEAR DOORS ARE CLOSED BY THE NOSE GEAR PULLING	 ON A MECHANICAL STRIKER BAR, THE DOORS CLOSE TIGHTER AS THE BUMPER WEARS.  THE DOORS WERE FINALLY PULLED INTO THE WHEEL	WELL CATCHING THEIR OUTER EDGE JAMMING THE GEAR IN THE UP POSITION.  CESSNA'S ROUTINE MAINTENANCE REQUIRES INSPECTION AN	D ADJUSTMENT OF THE NOSE GEAR RETRACTION HEIGHT.	1	H	7	1 	3O				3A17
1999022600103	19990226	00103	CE  	1999	2	26	99ZZZX720        	1	19980307	G	7603	12504012	BRACKET         			CESSNA	210   	210H        	2073436	CE  										THROTTLE CONTROL	CRACKED         	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	14	5981F	3991 				21058981				CRACK LOCATED ON THE THROTTLE CABLE SUPPORT BRACKET WHICH CAUSES THE THROTTLE TO RETURN TO IDLE RPM DURING FLIGHT.  SUBM	ITTER STATED THIS ITEM HAS BEEN FOUND ON 3 DIFFERENT MODELS.					1	H	7	1 	3O				3A21
1999022600104	19990226	00104	SO  	1999	2	26	99ZZZX721        	1	19980604	G	3252		SHIMMY DAMPENER 			PIPER 	PA28  	PA28151     	7102805	SO  										NLG	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	33	575DM	7854 				287715165				FOUND SHIMMY DAMPENER ROD END BROKE OFF AND MOUNT BOLT BADLY WORN (ALMOST IN TWO) AND BOLT BENT ALMOST 90 DEGREES.  THIS	 WAS DISCOVERED DURING ROUTINE MAINTENANCE DUE TO STRANGE ANGLE OF SHIMMY DAMPENER.  WHEN PART WAS CHANGED, DISCOVERED I	T HAD BEEN BROKEN FOR SOME TIME AND FINALLY BROKE COMPLETELY.  THIS LET THE SHIMMY JUST HANG THERE NOT DOING ANYTHING. S	UBMITTER SUSPECTED PART BROKE DUE TO OLD AGE AND THAT THIS AREA AND COMPONENTS HAD NOT BEEN PROPERLY INSPECTED FOR SOME 	TIME EVEN THOUGH ENG MOUNT HAD BEEN CHANGED RECENTLY FOR REASONS UNKNOWN.		1	L	7	1 	3O				2A13
1999022600105	19990226	00105		1999	2	26	99ZZZX722        	4	19981222	G	2360		STATIC WICK     			CESSNA	185   	185F        	2072820	CE  										ELEVATOR	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	05	56581					18502907				DEFLECTED WICKS INSTALLED ON AIRPLANE 15 DEGREES.  ELEMENTS BROKE OFF.  THESE WERE NEW UNITS.  AIRCRAFT WAS IN HANGAR. A	PPROXIMATE TEMPERATURE WAS 72 DEGREES FAHRENHEIT.  OTHER UNITS IN STOCK ALSO BROKE AT APPROXIMATELY 15 DEGREES TO 30 DEG	REES DEFLECTION.  SUBMITTER SUGGESTED AN ALTERNATE MATERIAL BE USED THAT IS MORE PLIABLE AND RELIABLE.				1	H	7	1 	3O				3A24
1999022600106	19990226	00106		1999	2	26	99ZZZX723        	2	19980713	G	7314	LW15473	FUEL PUMP       			AMTR  		GLASAIRIISTD			LYC   		IO360A1B6   							ENGINE	FAILED          	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			EA	17	92VH	130  				225				ENGINE DRIVEN FUEL PUMP ARM BROKE OFF FROM PUMP.  FOUND IN ENGINE SUMP.  ONE PIECE.									0
1999010800109	19990108	00109	SO  	1999	1	8	99ZZZX73         	1	19981211	G	7800		SUPPORT         			PIPER 	PA46  	PA46350P    		SO  										EXHAUST	FAILED          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	17	9194F					4622083				AIRCRAFT EXHAUST SYSTEM FAILED BY RIGHT UPPER CROSS-OVER SLIP JOINT ATTACH POINT.  THE SUPPORT BRACKET HARDWARE FAILED A	LLOWING JOINT TO SLIP APART WHICH DIRECTED EXHAUST GAS ONTO AIR CONDITIONING LINES RUPTURING LINES AND IGNITING AIR COND	ITIONING OIL WHICH CAUSED EXTENSIVE HEAT DAMAGE TO FIREWALL EXTERIOR AND INTERIOR IN BAGGAGE AREA, ENGINE WIRE HARNESS, 	AND MOTOR MOUNT.			1	L	7	1 	3O			RT	A25SO
1999010800110	19990108	00110	GL  	1999	1	8	99ZZZX74         	3	19981223	G	6114		HUB             			CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CRACKED         	B	S		ME4D	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	52553	9141 				17274554		83305		PROPELLER WAS REMOVED FROM AIRCRAFT AND INSTALLED ON ANOTHER AIRCRAFT FOR FERRY FLIGHT.  WHEN PROPELLER WAS REMOVED FROM	 AIRCRAFT AFTER FERRY FLIGHT, CRACK WAS FOUND IN HUB.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1999030500026	19990305	00026	SW  	1999	3	5	99ZZZX745        	1	19980318	G	2435	23032027	STARTER         			BELL  	206   	206B        	1181511	SW  										STARTER/GEN	FAILED          	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	90322		896  			1736				STARTER WILL NOT SPOOL ENGINE PAST 12 PERCENT.  SENT FOR REPAIR.  S/N 12506.  CONTROL NR 98-3-6.						1	G	7	1 	3U				H2SW
1999030500027	19990305	00027	GL  	1999	3	5	99ZZZX746        	2	19980318	G	7323	104500A8	GOVERNOR        			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	LEAKING         	B			LS1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	13	90322	2674 				1736				FUEL LEAKING FROM GOVERNOR DRAIN PORT BEYOND LIMITS.  SENT FOR REPAIR.  S/N 8ACK585.  CONTROL NR 98-3-7.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1999030500028	19990305	00028	NE  	1999	3	5	99ZZZX747        	1	19980215	G	6210	7615009100048	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	BROKEN          	B		A	ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	917QS					760217				AIRCRAFT WAS SECURED ON PLATFORM OFFSHORE.  ALL MAIN ROTOR BLADES WERE SECURED USING SIKORSKY TIE DOWN CLAMPS.  WINDS OF	 80+ MPH CAUSED ONE M/R BLADE TO BREAK OFF APPROXIMATELY 3 FEET FROM ROOT.  SPECIAL INSPECTION WAS C/W AND BLADE AND SPI	NDLE CHANGED.  AIRCRAFT WAS FERRIED TO MAIN BASE FOR FURTHER INSPECTION.  NO DEFECTS WERE FOUND.  CAUSE OF PROBLEM WAS C	LAMPS DO NOT HOLD IN HIGH WINDS.  RECOMMEND USING SOCK TYPE BOOT AND THROW CLAMPS AWAY.			1	G	7	2 	3U				H1NE
1999030500029	19990305	00029		1999	3	5	99ZZZX748        	4	19980503	G	3420	A0773	WIRE            			ROBSIN	R44   	R44         	7640120	WP  										COCKPIT	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	07	961SA	402  				0266				CIRCUIT BREAKER 'POPPED' AND WOULD NOT RESET.  FOUND DIRECTIONAL GYRO WIRING CHAFED ON THE UPPER CONSOLE ASSEMBLY.  REPA	IRED WIRING AND RE-TIED BUNDLE TO CLEAR THE STRUCTURE.					1	G	7	1 	3O			 	H11NM
1999030500030	19990305	00030		1999	3	5	99ZZZX749        	4	19980420	G	3455	05001756003	WIRE            		KA87        	BELL  	407   	407         	1182206	SW  										ADF	MISINSTALLED    	B			QMQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	03	407GA					53104				INNER SHIELD WOULD NOT RING ON PIN 89 OF THE ANTENNA CONNECTOR.  OPENED CONNECTOR AND FOUND DRAIN WIRE INCORRECTLY TERMI	NATED ON WIRE.  (STRIPPED END WAS PUSHED PAST SOLDER SLEEEVE).					1	G	7	1 	3U			O	H2SW
1999010800111	19990108	00111	NE  	1999	1	8	99ZZZX75         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			997  					HJ610		DEBONDED EROSION SHIELD.  DISASSEMBLED PROPELLER, CLEANED AND INSPECTED.  REMOVED BLADE, S/N 2194 AND S/N 2184.  INSTALL	ED BLADE, S/N 2998 AND S/N 3000.  ASSEMBLED PROPELLER AND STATIC BALANCED IAW MFG CMM.															5	C	P10NE
1999030500031	19990305	00031	WP  	1999	3	5	99ZZZX750        	1	19980302	G	2810	369A8116	FUEL FILLER     			HUGHES	369   	369D        	4470706	WP  										FUEL TANK	CRACKED         	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				FUEL CELL FILLER CAP LOCKING TABS CRACKED.  REPLACED FILLER ASSY.  AIRCRAFT RELEASED FOR FLIGHT.  REF:  CONTROL NR 98-3-	2.					1	G	7	1 	3U				H3WE
1999030500032	19990305	00032	GL  	1999	3	5	99ZZZX751        	2	19980501	G	7510	23053176	BLEED VALVE     			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MALFUNCTIONED   	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P		223  			611002D				ENGINE NOT MAKING POWER.  REMOVED AND REPLACED.  AWAITING INSPECTION REPORT.  REF:  CONTROL NR 98-4-15.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1999030500033	19990305	00033	GL  	1999	3	5	99ZZZX752        	2	19980309	G	7314	6899253	PUMP            			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	FAILED          	B			LS1R	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	13	1097J		2414 			900801D				FAILED BYPASS TEST, DURING INSPECTION.  PUMP WAS REPLACED.  S/N T4182.  CONTROL NR 98-3-4.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1999030500034	19990305	00034	WP  	1999	3	5	99ZZZX753        	1	19980305	G	2435	23032027	GENERATOR       			HUGHES	369   	369D        	4470706	WP  										START/GENERATOR	MALFUNCTIONED   	B			LS1R	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			EA	13	1097J		807  			900801D				GENERATOR SMOKES ON RESTART, CAUSE UNKNOWN. SENT FOR EVALUATION AND OVERHAUL.  S/N 12157.  CONTROL NR 98-3-3.						1	G	7	1 	3U				H3WE
1999030500035	19990305	00035	EU  	1999	3	5	99ZZZX754        	1	19980429	G	6230	704A33651158	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  										SWASHPLATE	BINDING         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	515BB	1206 				2726				DURING A NORMAL 100-HOUR INSPECTION, BEARING FOUND TO BE STIFF.  WITH SCALE PULL AT MORE THAN 6 POUNDS, EUROCOPTER RECOM	MENDS THIS CHECK EVERY 100 HOURS.					1	G	7	1 	3U			NC	H9EU
1999030500036	19990305	00036	WP  	1999	3	5	99ZZZX755        	1	19980302	G	6420	369D2172121	FORK            			HUGHES	369   	369D        	4470706	WP  										TAIL ROTOR	WORN            	B			LS1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	13	5027P					611002D				SUSPECT ELASTOMORIC BEARINGS WORN.  AIRCRAFT PICKED UP HIGH VIBRATION.  TAIL ROTOR FORK ASSY REPLACED.  TAIL ROTOR BALAN	CED TO BELOW .2 IPS.  AIRCRAFT RELEASED FOR FLIGHT.  REF:  CONTROL NR 98-3-1.					1	G	7	1 	3U				H3WE
1999030500040	19990305	00040	WP  	1999	3	5	99ZZZX759        	1	19980429	G	6420	NAS130438	BOLT            		A0301       	ROBSIN	R22   	R22         	7640102	WP  										TIL ROTOR	SHEARED         	H		A		A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			GL	13	228W	889  			3513	2578				TAIL ROTOR BOLT SHEARED IN-FLIGHT CAUSING SEVERE VIBRATION.  LANDING MADE WITHOUT DAMAGE.  BELIEVE BOLT FAILED DUE TO CO	RROSION/RUST SETTING UP STRESS POINTS.  SUBMITTER RECOMMENDED INSPECTION EVERY 100 HOURS.  BOLT WAS LAST INSPECTED 168.3	 HOURS PREVIOUSLY.				1	G	7	1 	3O				H10WE
1999010800112	19990108	00112	NE  	1999	1	8	99ZZZX76         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1034 					HJ651		NR 4 BLADE EROSION SHIELD DEBONDED UNDER DEICE BOOT.  REBONDED EROSION SHIELD, AND REPLACED DEICE BOOT IAW MFG CMM.																5	C	P10NE
1999030500042	19990305	00042		1999	3	5	99ZZZX761        	1	19980126	G	6220		BOLT            			AMTR  		MINI500     												ROTORHEAD	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	248F					402B				THE ROTORHEAD TOLERANCES ARE SO LOOSE THAT IT IS IMPOSSIBLE TO CORRECTLY DETERMINE THE CONING ANGLE.  THE BOLTS HOLDING 	THE GRIPS IN PLACE ALLOW THE HEADS CONE ANGLE TO VARY PLUS OR MINUS 1 DEGREE.  TWO DEGREES IS NORMAL, SO THIS IS A 50 PE	RCENT ERROR.  SUBMITTER STATED TO GROUND ALL SHIPS UNTIL THIS PROBLEM IS CORRECTED.							0
1999030500043	19990305	00043		1999	3	5	99ZZZX762        	1	19980126	G	6220	0023	SNAP RING       			AMTR  		MINI500     												BEARING MOUNT	MISMANUFACTURED 	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	10	248F					402B				THE SNAP RING THAT HOLDS THE BEARING IN PLACE WAS MACHINED .1250 INCH BELOW THE TOP OF THE BEARING.  THE SNAP RING COULD	 NOT BE PROPERLY INSTALLED, FOUND THE BEARING WAS ONLY HELD IN BY PRESS FIT.								0
1999030500044	19990305	00044		1999	3	5	99ZZZX763        	1	19980120	G	6410	BA29	BLADE           			AMTR  		MINI500     												TAIL ROTOR	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	10	249F				0105X	402B				BUILDER'S MANUAL INDICATES THAT THE PRE-CONE ANGLE SHOULD BE 2 DEGREES.  THE SUPPLIED BLADES WERE AT .25 DEGREES AND 1.1	. DEGREES.  ADDITIONAL TAIL ROTOR BLADES WERE PURCHASED, BUT THEY WERE ALSO OUT OF SPEC.  SUBMITTER SUGGESTED ALL TAIL R	OTOR BLADES SHOULD BE INSPECTED FOR CONFORMITY AND REPAIRS AND SHIMMING MUST BE ACCOMPLISHED TO CORRECT THE DEFECT IN MA	NUFACTURE.						0
1999030500045	19990305	00045		1999	3	5	99ZZZX764        	1	19980120	G	6410	BA29	BLADE           			AMTR  		MINI500     												TAIL ROTOR	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	10	249F				0813	402B				BUILDER'S MANUAL INDICATES THAT THE PRE-CONE ANGLE SHOULD BE 2 DEGREES.  THE SUPPLIED BLADES WERE AT .25 DEGREES AND 1.1	. DEGREES.  ADDITIONAL TAIL ROTOR BLADES WERE PURCHASED, BUT THEY WERE ALSO OUT OF SPEC.  SUBMITTER SUGGESTED ALL TAIL R	OTOR BLADES SHOULD BE INSPECTED FOR CONFORMITY AND REPAIRS AND SHIMMING MUST BE ACCOMPLISHED TO CORRECT THE DEFECT IN MA	NUFACTURE.						0
1999030500048	19990305	00048	EA  	1999	3	5	99ZZZX767        	2	19980123	G	8550		FILTER ADAPTER  			CESSNA	172   	172R        	2072401	CE  	LYC   	IO360 	IO360L2A    		EA  					ENGINE OIL	LOOSE           	B			VDNR	K				NONE                    				W	K		INADEQUATE Q C            	FLUID LOSS                		IN	INSP/MAINT     	1			SW	09	172SJ	11   				17280291				NEW AIRCRAFT HAD OIL LEAK; FOUND THE RETAINING BOLTS FOR THE OIL FILTER ADAPTER TO BE 'FINGER' TIGHT.  RE-TORQUED BOLTS 	PER OHM SPECS.  LEAK CHECK SATISFACTORY.					1	H	7	1 	3O	3	O	NT	3A12    	1E10
1999030500049	19990305	00049		1999	3	5	99ZZZX768        	1	19980905	G	3230	4805058102	TUBE            	AEROMARINE  	69001       	AMTR  		KITFOXIII   												LT MLG	BENT            	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	35	51870	1    				752				LEFT LANDING GEAR COLLAPSED UPON LANDING.  MINOR DAMAGE TO FLOAT KEEL AND LEFT NOSE TIRE DEFLATED.  FOUND ROTATION TUBE 	COLLAPSED AND BENT.  STOP BRACKET ROTATES PAST STOP BOLT AND GEAR UNLOCKS.  AIRCRAFT HAD 2 SIMILAR OCCURRENCES.  SUBMITT	ER STATED PART MADE OF STAINLESS MATERIAL AND SEEMS TOO SOFT.							0
1999010800113	19990108	00113	NE  	1999	1	8	99ZZZX77         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3672 					HJ835		BLADE NR 4 EROSION SHIELD DEBONDED.  DEBOND IN DEICE BOOT AREA FROM EDGE OF SHIELD AT BLADE BUTT TO ABOUT 3 INCHES OUTBO	ARD.  REPAIRED AND INSTALLED NEW DEICE BOOT IAW MFG CMM.															5	C	P10NE
1999010800114	19990108	00114	NE  	1999	1	8	99ZZZX78         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1623 					HJ181A		EROSION SHIELD DEBONDED AND CRACKED.  BLADE NR 2 (SN 221) DEBONDED 100 PERCENT UNDER DEICE BOOT AND CRACKED.  DISASSEMBL	ED PROPELLER, CLEANED, AND INSPECTED.  O/H BLADE S/N 221 REPLACING EROSION SHIELD.  ASSEMBLED AND STATIC BALANCED IAW MF	G CMM.														5	C	P10NE
1999030500446	19990305	00446	CE  	1999	3	5	99ZZZX784        	1	19981105	G	3350	AD2059	BATTERY PACK    	JET         	PS823B      	LEAR  	25    	25          	5170506	CE  										CABIN	DISCHARGED      	B			JGVR	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CE	09					4600					EMERGENCY BATTERY PACK DISCHARGED.						2	L	7	2 	4J				A10CE
1999030500447	19990305	00447	NM  	1999	3	5	99ZZZX785        	1	19981222	G	2510		SPACER          		11010       	ISRAEL	1125  	1125        		NM  										COCKPIT	BROKEN          	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	90UG	250  			054	030				SPACER BROKEN AT WELD AT SEAT BACK ATTACH BOLT TO SEAT BASE.  FOUND BY VISUAL INSPECTION OF CREW SEATS.  POSSIBLE CAUSE,	 MISALIGNMENT OF SPACER WHEN WELDED AT MANUFACTURE.  RECOMMEND LIGHTLY LUBRICATE SEAT TRACKS AND CHECK SEAT BACK ALIGNME	NT WHEN INSTALLING SEAT ON TRACK.				2	L	7	2 	4F			RT	A16NM
1999030500450	19990305	00450	EU  	1999	3	5	99ZZZX788        	1	19981207	G	3411		LINE            			BRAERO	DH125 	BAE125800A  	1500285	EU  										CABIN	CHAFED          	B	P		JGVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	09	805X	2465 				NA0465				DURING 24-MONTH PITOT/STATIC CERTIFICATION INSPECTION, FOUND NR 2 ADC P2 PITOT LINE CHAFED THROUGH BY AUTOPILOT SERVO CA	BLE.  THIS AREA IS DIFFICULT TO SEE WITH INSTALLED COMPONENTS IN PLACE.  NOTE:  THIS IS SECOND AIRCRAFT AT THIS FACILITY	 FOUND WITH THIS PROBLEM.				2	L	7	2 	4F			RT	A3EU
1999010800115	19990108	00115	NE  	1999	1	8	99ZZZX79         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3497 					HJ194A		EROSION SHIELD DEBONDED.  EROSION SHIELD DEBONDED UNDER DEICE BOOT BEYOND LIMITS.  DISASSEMBLED PROPELLER, O/H BLADE, S/	N 847MA.  REASSEMBLED PROPELLER AND STATIC BALANCED IAW MFG CMM.															5	C	P10NE
1999030500460	19990305	00460	EA  	1999	3	5	99ZZZX797        	2	19981116	G	7321	A74195	FUEL CONTROL    			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					RT ENGINE	FAILED          	H				A				UNSCHED LANDING         				X			ENGINE FLAMEOUT           			CR	CRUISE         	1			SO	14	57RF		2596 			688	PCE41943			RIGHT ENGINE FLAMED OUT IN CRUISE.  AIRCRAFT LANDED.  TROUBLESHOOTING DISCOVERED THAT FUEL CONTROL WAS BYPASSING 100 PER	CENT OF FUEL BACK TO FUEL CONTROL.  REPLACED FUEL CONTROL, ENGINE OPERATION RETURNED TO NORMAL.  FCU SENT TO OVERHAUL SH	OP FOR INSPECTION AND REPAIR.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
1999010800018	19990108	00018	CE  	1999	1	8	99ZZZX8          	1	19980625	G	7897		WIRE            			CESSNA	500   	560CESSNA   	2076750	CE  										LT THRUST REVERS	CHAFED          	B			CWQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	05	344QS	2910 				5600344				LEFT ENGINE THRUST REVERSER CIRCUIT BREAKER TRIPPED IN-FLIGHT.  TROUBLESHOT AND DETERMINED THAT WIRE RELATED TO THAT SYS	TEM WAS CHAFING ON THE OIL RPESSURE INDICATOR.  SECURED AND INSULATED WIRE FROM INSTRUMENT.					2	L	7	2 	4F			RT	A22CE
1999010800116	19990108	00116	NE  	1999	1	8	99ZZZX80         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2828 					HJ337		EROSION SHIELD DEBONDED.  EROSION SHIELD ON BLADE NR 4 DEBONDED BEYOND LIMITS.  REMOVED AND REPLACED EROSION SHIELD AND 	STATIC BALANCED PROPELLER IAW MFG CMM.															5	C	P10NE
1999030500463	19990305	00463	CE  	1999	3	5	99ZZZX800        	1	19980223	G	3411	CM29337	HEAT            			CESSNA	500   	560CESSNA   	2076750	CE  										RT STATIC PORT	INOPERATIVE     	D				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	13	591M	4266 				5600085				PILOT'S LEFT HAND STATIC HEATER FAILED, NO ANNUNCIATION WAS OBSERVED.  REPLACED DEFECTIVE STATIC PART.  AFTER SEVERAL HO	URS OF TROUBLESHOOTING AND SEVERAL PHONE CALLS TO CESSNA TO FIND OUT WHY THERE WAS NO FAIL ANNUNCIATION, IT WAS DETERMIN	ED THE SYSTEM WAS OPERATING AS DESIGNED.  CONTRARY TO APPROVED MANUALS, THE PITOT/STATIC HEATER FAIL LIGHT WILL ONLY ILL	UMINATE WITH A PITOT TUBE HEATER FAIL.  STATIC HEATER FAIL, EITHER ONE OR BOTH, WILL NOT SHOW ON THE ANNUNCIATOR PANEL. 	 THE SYSTEM SHOULD WORK AS AN INDICATOR OF A FAILURE OF ANY ONE OF THE THREE HEATING ELEMENTS.		2	L	7	2 	4F			RT	A22CE
1999010800117	19990108	00117	NE  	1999	1	8	99ZZZX81         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			2266 					HJ869		NR 2 BLADE, EROSION SHIELD 90 PERCENT DEBONDED.  REMOVED AND REPLACED EROSION SHIELD, O/H BLADE S/N 2945.  ASSEMBLED PRO	PELLER AND STATIC BALANCED IAW MFG CMM.															5	C	P10NE
1999030500477	19990305	00477	NE  	1999	3	5	99ZZZX814        	2	19981207	G	7200		ENGINE          			CESSNA	500   	S550        	2076607	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NR 2	MALFUNCTIONED   	H				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			SO	25	1982U	3450 				S5500038				STARTED DESCENT FROM 31,000 FEET.  AT 25,000 FEET, REDUCED POWER AND FELT VIBRATION ON RIGHT SIDE.  SHUT NR 2 DOWN IMMED	IATELY.  SINCE TOTAL TIME WAS 3,450 HOURS, OVERHAULED BOTH MAIN BEARINGS, STARTED TO FAIL.					1	L	7	2 	4F	4	F	RT	A22CE   	E1NE
1999010800118	19990108	00118	NE  	1999	1	8	99ZZZX82         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			3435 					HJ455		EROSION SHIELD ON BLADE NR 3 DEBONDED.  REPAIRED EROSION SHIELD UNDER DEICE BOOT IAW MFG CMM.																5	C	P10NE
1999010800119	19990108	00119	NE  	1999	1	8	99ZZZX83         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1677 					HJ514		EROSION SHIELD DEBONDED.  NR 4 BLADE DEBONDED BEYOND LIMITS, NR 1 BLADE DEBONDED, REPAIRED EROSION SHIELD.  REMOVED BLAD	E NR 4 AND REPLACED WITH BLADE, S/N 818MA.  BLADE WAS STATIC BALANCED BEFORE BEING INSTALLED.  ASSEMBLED PROPELLER IAW M	FG CMM.														5	C	P10NE
1999010800120	19990108	00120	NE  	1999	1	8	99ZZZX84         	3	19981215	G	6111	D5133	SHIELD          													HARTZL	HCE4A	HCE4A3A     	NE  	PROPELLER BLADE	DEBONDED        	B			GLBR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	01			1092 					HJ901		EROSION SHIELD ON BLADE, S/N 517 (NR 3) DEBONDED UNDER DEICE BOOT BEYOND LIMITS.  DISASSEMBLED, CLEANED, AND INSPECTED P	ROPELLER.  O/H BLADE, S/N 517DA.  ASSEMBLED PROPELLER, LUBRICATED WITH AEROSHELL NR 6, AND STATIC BALANCED IAW MFG CMM. 	 BLADE NR 3 HAD OVER 60 PERCENT DEBONDING UNDER DEICE BOOT.														5	C	P10NE
1999010800121	19990108	00121		1999	1	8	99ZZZX85         	4	19981204	G	6122	D20887	SHAFT           	MCAULY      	C29003K523  															PROP GOVERNOR	CRACKED         	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	04		1700 			970069					DURING DISASSEMBLY FOR OVERHAUL, DRIVESHAFT P/N D-20887 (NEW STYLE) WASNOTED TO BE CRACKED AT THE UPPER FLUTES (NEAR FLY	WEIGHTS).  THIS GOVERNOR WAS NOT SUBJECT TO A PROPELLER STRIKE OR SUDDEN STOPPAGE.
1999031200406	19990312	00406	EA  	1999	3	12	99ZZZX859        	2	19980601	G	8510	LW127996S180	HOSE            			MOONEY	M20   	M20M        	5870222	SW  	LYC   	0540  	TIO540AF1B  	41532	EA  					ENGINE	KINKED          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	01	628JF	211  				270214	L969961A			AIRCRAFT RPM WOULD SURGE; MANIFOLD PRESSURE IS UNCONTROLLED, CAUSE WAS HOSE BEING KINKED.  SUBMITTER STATED THIS HAS BEE	N NOTED ON SEVERAL OTHER AIRCRAFT OF THE SAME MODEL.					1	L	7	1 	3O	3	O	RT	2A3     	E14EA
1999010800122	19990108	00122	SO  	1999	1	8	99ZZZX86         	1	19981209	G	3700	842CW	SHAFT           			PIPER 	PA31  	PA31P       	7103120	SO  										VACUUM PUMP	SHEARED         	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	252MA	345  			7AN8	31P33				PUMP SHAFT SHEARED, FOUND PROPELLER SEIZED.						1	L	7	2 	3O				A8EA
1999031200413	19990312	00413	EA  	1999	3	12	99ZZZX866        	1	19981214	G	5220	601R330501	HANDLE          			CNDAIR	CL600 	CL6002B19   		EA  										EMERGENCY EXIT	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4725 			0024	7008				DURING AIRCRAFT INSPECTION, FOUND THE CREW ESCAPE HATCH EXTERNAL HANDLE INNER ATTACH SURFACE AND HOUSING CORRODED.  NO D	AMAGE LIMITS LISTED.  REPLACED HANDLE/HOUSING ASSY WITH A SERVICEABLE ASSY, P/N 601R33050-1, S/N 0419.					2	L	7	2 	4F			RT	A21EA
1999031200414	19990312	00414	EA  	1999	3	12	99ZZZX867        	1	19981214	G	3222	161761	BEARING         			CNDAIR	CL600 	CL6002B19   		EA  										NLG	CHAFED          	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4725 				7008				DURING CUSTOMER ELECTED NOSE LANDING GEAR INTERNAL INSPECTION, FOUND NOSE LANDING GEAR LOWER STRUT BEARING CHAFING INTO 	THE INNER BORE SURFACE OF THE LANDING GEAR UPPER HOUSING P/N MESSIER DOWTY 16040 (NLG).  REPAIRED DAMAGED UPPER HOUSING 	INNER BORE SURFACE IAW DOWTY CONCESSION LETTER RO 98/369 NO CO95-995 CONCESSION LETTER LIMITS OPERATOR TO 1 YEAR OR 1,20	0 CYCLES AFTER REWORK.  ALSO, REPLACED LOWER STRUT BEARING WITH P/N 61676-5.  CONDITION WAS NOTED ON THIS AIRCRAFT DURIN	G A DETAILED INSPECTION.  AIRCRAFT S/N 7008 IS THE FIRST NLG INTERNAL INSPECTION PERFORMED AT BOMBARDIER (BDX).  PART TC	:  6,453.	2	L	7	2 	4F			RT	A21EA
1999031200415	19990312	00415	EA  	1999	3	12	99ZZZX868        	1	19981214	G	3222	161241	AXLE ASSY       			CNDAIR	CL600 	CL6002B19   		EA  										NLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4726 			DCL032	7008				DURING CUSTOMER ELECTED NOSE LANDING GEAR INSPECTION, UPON REMOVAL OF THE AXLE ASSY, FOUND EXCESSIVE CORROSION ON THE IN	NER PIN (ATTACH) BORE AND THE INNER SURFACE OF THE AXLE ASSY/PISTON MATING SURFACE.  AXLE ASSY WAS REPLACED WITH P/N MES	SIER DOWTY 16124-101, S/N DCL358 IAW DOWTY ENGINEERING.  PART TOTAL CYCLES:  6,453.				2	L	7	2 	4F			RT	A21EA
1999031200416	19990312	00416	EA  	1999	3	12	99ZZZX869        	1	19981214	G	3222	161201	PISTON          			CNDAIR	CL600 	CL6002B19   		EA  										NLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4726 			DCL032	7008				DURING CUSTOMER ELECTED NOSE LANDING GEAR INSPECTION UPON REMOVAL OF THE AXLE ASSY, FOUND EXCESSIVE CORROSION ON THE INN	ER PIN BORE SURFACES WHERE THE AXLE ATTACH PIN ATTTACHES TO PISTON.  ASSY WAS REPLACED WITH P/N 16120-1, S/N B15-3 PER M	ESSIER DOWTY ENGINEERING.  TOTAL PART CYCLES:  6,453.				2	L	7	2 	4F			RT	A21EA
1999010800123	19990108	00123	EA  	1999	1	8	99ZZZX87         	2	19981209	G	8520		CRANKSHAFT      			UNIVAR	108   	1081        	9230404	NM  	FRNKLN	6A4165	6A4165B3    	27025	EA  					ENGINE	BROKEN          	G				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	15	8018K	1798 	210  			1083018	31736			ENGINE LOST POWER RESULTING IN FORCED LANDING.  INVESTIGATION REVEALED THE CRANKSHAFT BROKE AT THE NR 2 CONNECTING ROD J	OURNAL.					1	H	7	1 	3O	3	O		A767    	E238
1999031200417	19990312	00417	EA  	1999	3	12	99ZZZX870        	1	19981214	G	3222	161703	DIAPHRAGM       			CNDAIR	CL600 	CL6002B19   		EA  										NLG	CORRODED        	B			SH5R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	5100X	4726 				7008				DURING CUSTOMER ELECTED NOSE LANDING GEAR INSPECTION UPON REMOVAL OF THE AXLE ASSY, FOUND EXCESSIVE CORROSION ON THE OUT	ER MATING SURFACES OF THE DIAPHRAGM ASSY.  REPLACED DIAPHRAGM ASSY WITH A SERVICEABLE ASSY PER MESSIER DOWTY ENGINEERING	.  TOTAL PART CYCLES:  6,453.				2	L	7	2 	4F			RT	A21EA
1999031200422	19990312	00422		1999	3	12	99ZZZX875        	4	19981102	G	3160	991406114	ANNUNCIATOR PNL 		466114      	CESSNA	650   	650         	2076802	CE  										COCKPIT	FAILED          	B				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			EA	09	2UP		38   		147	6500227				ON DESCENT INTO HOME BASE AIRPORT, FLIGHT CREW SMELLED ELECTRICAL ODOR IN COCKPIT FOLLOWED BY ALL ANNUNCIATOR LIGHTS ILL	UMINATED.  CREW DECLARED AN EMERGENCY AND LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED FAULT IN ANNUNCIATOR PANEL. C	ESSNA REQUESTED PANEL BE SENT TO THEIR LAB FOR INVESTIGATION.  38 HOURS ON UNIT SINCE REPAIR.  REPAIRED UNIT, DID NOT WO	RK PROPERLY ON INSTALLATION.  UNIT DID NOT WORK IN BRIGHT MODE.			2	L	7	2 	4F				A9NM
1999031200428	19990312	00428	CE  	1999	3	12	99ZZZX879        	1	19981130	G	3020		DEICER BOOTS    			MTSBSI	MU2   	MU2B60      	5780460	CE  										COOLER	WORN            	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	1164F					1562SA				DE-ICER BOOTS ON OIL COOLER INLET WORN.  CHANGED THERMOSTAT AND BOTH DE-ICER BOOTS ON LEFT SIDE, AND CHANGED INBOARD DE-	ICER BOOT ON RIGHT SIDE.					1	H	7	2 	3T			RT	A10SW
1999010800124	19990108	00124	CE  	1999	1	8	99ZZZX88         	1	19981214	G	5312	07536007	DOUBLER         			CESSNA	182   	182S        	2072701	CE  										BULKHEAD	CRACKED         	B			MZER	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	9510A	142  				18280069				AIRCRAFT IN FOR FIRST ANNUAL SINCE NEW.  FOUND LOWER FIREWALL REINFORCEMENT DOUBLER CRACKED ON EACH SIDE WHERE LOWER COW	L ATTACHES TO IT.					1	H	7	1 	3O			NT	3A13
1999031200429	19990312	00429	WP  	1999	3	12	99ZZZX880        	2	19980725	G	7261		PUMP            			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					OIL SYSTEM	FAILED          	B			ESMR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11	46AK					754SA				DROP IN OIL PRESSURE.  OIL LUBRICATION SYSTEM/REAR SCAVENGE PMP BEGINNING TO FAIL.  SCAVENGE PUMP FAILURE.						1	H	7	2 	3T	4	T	RT	A10SW   	E4WE
1999031200430	19990312	00430	SO  	1999	3	12	99ZZZX881        	1	19981001	G	7830	292502	CONTROL CABLE   			LKHEED	1329  	132923E     	5263116	SO  										THRUST REVERSER	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	11						5106				NR 3 ENGINE THRUST REVERSER SUPPORT CASTING BROKEN AT IDLER ARM STOP.  SUPPORT CASTING WAS REMOVED AND REPLACED WITH NEW	 CASTING.  WHEN RE-RIGGING THRUST REVERSER, FOUND FEEDBACK CABLE BROKEN.  THE FEEDBACK CABLE CONTROLS THE OPERATION OF T	HE THRUST REVERSER AIR MOTOR.  SUSPECT THE FEEDBACK CABLE BROKE AND THE THRUST REVERSER DOORS TRIED TO OVERSTOW AND BROK	E THE SUPPORT CASTING.  AIRCRAFT N NR YV-03CP.			2	L	7	4 	4J			 	2A15
1999031200435	19990312	00435	CE  	1999	3	12	99ZZZX886        	1	19981026	G	3097		WIRE            			BEECH 	200   	200BEECH    	1152920	CE  										WINDSHIELD HEAT	FAILED          	B			ESMR	B	A			EMER. DESCENT           	UNSCHED LANDING         			A			FLAME/FIRE                			CR	CRUISE         	1			SO	11	601CF					BB25				PILOT IN CRUISE AT 25,000 FEET.  PRIOR TO DESCENDING, WINDSCREEN WAS FOGGED UP.  AS DEFROSTER ON, PILOT DECIDED TO TRY T	HE WINDSHIELD HEAT.  APPROXIMATELY FIVE MINUTES LATER, FIRE BURST FROM THE LEAD WIRES OF THE WINDSHIELD HEAT.  IMMEDIATE	LY DECLARED AN EMERGENCY AND STARTED EMERGENCY DESCENT.  SUSPECTED FIRE WAS FROM WINDSHIELD HEAT, FIRE STOPPED AS SOON A	S HEAT TURNED OFF.  BECAUSE FIRE STARTED AFTER THE WINDSHIELD HEAT WAS TURNED ON AND THE WIRES THAT BURNED WERE LEADING 	TO THE WINDOW, SUSPECT WINDSHIELD HEAT WAS THE PROBLEM.  MAINTENANCE CHECKED ALL WIRING AND FOUND WINDSHILD TO BE INTERN	ALLY SHORTED IN THE HEATED AREA OF WIRE FILAMENTS.  NEW WINDSHIELD ON ORDER.	1	L	7	2 	4T			 	A24CE
1999031200436	19990312	00436	NE  	1999	3	12	99ZZZX887        	2	19981123	G	7510	F10A5P202429	LINE            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	01518	NE  					RT ENGINE	CRACKED         	B			CW7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	331CW					231	P77214			RIGHT ENGINE ANTI-ICE WAS INOPERATIVE.  TROUBLESHOT SYSTEM, FOUND BLOWN BLEED AIR LINE.  REMOVED AFTERBODY TO GAIN ACCES	S TO MANIFOLD LOCATED ON VERY TOP OF ENGINE.  INSTALLED NEW MANIFOLD.  ENGINE TT:  65,887.					2	M	7	2 	4F	4	F		A2SW    	E6WE
1999031200437	19990312	00437	NE  	1999	3	12	99ZZZX888        	2	19981123	G	7510	F10A5P202413	LINE            			ISRAEL	1124  	1124        	4500102	EU  	GARRTT	TFE731	TFE73131G   	01518	NE  					RT ENGINE	CRACKED         	B			CW7R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	25	331CW					231	P77214			RIGHT ENGINE ANTI-ICE WAS INOPERATIVE.  TROUBLESHOT SYSTEM, FOUND BLOWN BLEED AIR LINE.  REMOVED AFTERBODY TO GAIN ACCES	S TO MANIFOLD LOCATED ON VERY TOP OF ENGINE.  INSTALLED NEW MANIFOLD.  ENGINE TT:  65,887.					2	M	7	2 	4F	4	F		A2SW    	E6WE
1999031200438	19990312	00438	NE  	1999	3	12	99ZZZX889        	2	19980417	G	7320	1203KDC008A	EEC             			BRAERO	1000  	BAE1251000A 	1500104	EU  	PWA   	305   	PW305B      	52120	NE  					ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	410US				YM373	NA1000	PCE305023			ENGINE UNRESPONSIVE TO THROTTLE MOVEMENT.  TROUBLESHOT FADEC FAULT 'TE' (ENGINE SPEED LIMITED AT IDLE WHEN INTRANSIT DIS	CRETE).  FADEC 'SEES' THRUST REVERSER INTRANSIT, HOLDS ENGINE AT IDLE.  FOUND ELECTRONIC ENGINE CONTROL AT FAULT.  REPLA	CED EEC.  OPS CHECK GOOD.				2	L	7	2 	4F	4	F	RT	A3EU    	E35NE
1999010800125	19990108	00125		1999	1	8	99ZZZX89         	4	19981210	G	3418	S24881	WARNING HORN    																	COCKPIT	MALFUNCTIONED   	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07										INSTALLED NEW STALL WARNING REEDS IN 3 AIRCRAFT.  ALL HAD HORN ON ALL THE TIME.  CHECKED REED, FOUND REED SOUNDED WITH B	OTH PRESSURE AND SUCTION.  SUBMITTER RECOMMENDS TESTING ALL REED ASSEMBLIES PRIOR TO INSTALLATION BY LIGHTLY BLOWING INT	O REED.  THERE SHOULD BE NO TONE HEARD, TONE SHOULD ONLY BE HEARD WITH SUCTION APPLIED.
1999010800019	19990108	00019	CE  	1999	1	8	99ZZZX9          	1	19980219	G	2742	636121521	ACTUATOR        			CESSNA	500   	560CESSNA   	2076750	CE  										HORIZONTAL STAB	MISINSTALLED    	B			CWQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			GL	05	343QS	219  				5600444				DURING INSPECTION ATTEMPT TO LUBRICATE THE LEFT ELEVATOR TRIM ACTUATOR, DETERMINED THE PART NUMBER AND GREASE ZERT LOCAT	ION WAS THAT OF THE RIGHT SIDE PART.					2	L	7	2 	4F			RT	A22CE
1999010800126	19990108	00126	SO  	1999	1	8	99ZZZX90         	2	19981130	G	7314	476411	PUMP            	FACET       		CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					FUEL SYSTEM	INOPERATIVE     	B			EKIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	421KP	349  				421B0142	267154R			FUEL RE-CIRCULATING PUMPS IN LEFT AND RIGHT TIP TANKS INOPERATIVE.  BOTH PUMPS REPLACED WITHIN THE LAST 15 MONTHS.						1	L	7	2 	3O	3	O		A7CE    	E7CE
1999031200674	19990312	00674	SW  	1999	3	12	99ZZZX900        	1	19980228	G	6320	204040129001	RETAINER        		206040004111	BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	CRACKED         	B			ZV1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5000G	11944	1520 		BMC45221	45163				UPON TEAR-DOWN OF TRANSMISSION FOR INSPECTION, SCREEN ASSY WAS FULL OF NYLON PIECES.  INVESTIGATION REVEALED RETAINERS O	N PLANETARY GEAR, 1 EACH, COMPLETELY MISSING AND, 2 EACH, CRACKED.					1	G	7	1 	3U				H2SW
1999031200677	19990312	00677	NE  	1999	3	12	99ZZZX902        	2	19980922	G	7240	414302017	HOUSING         			BELL  	222   	222         	1182122	SW  	LYC   	LTS101	LTS101750C1 	41560	NE  					COMBUSTOR	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	911LW	118  			4044PX	47520	LE47020			HOUSING CRACKED AT 6 O'CLOCK STRUT.  REMOVED AND REPLACED.						1	G	7	2 	3U	3	U		H9SW    	E5NE
1999031200678	19990312	00678	EU  	1999	3	12	99ZZZX903        	1	19980917	G	7712	117902121	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	STICKS          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	839  			107	7505				NR 1 TORQUE NEEDLE STICKS.   REMOVED AND REPLACED.  REF:  RMA NR R016965.						1	G	7	2 	3U			NC	H13EU
1999031200679	19990312	00679	SW  	1999	3	12	99ZZZX904        	1	19980909	G	6230	222010400127	SWASHPLATE      			BELL  	230   	230         	1182149	SW  										MAIN ROTOR	WORN            	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	4UV	1848 			EA139	23019				BOTH SLIDERS WORN.  ALL BOLTS NOT TORQUED.   REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999031200680	19990312	00680	EU  	1999	3	12	99ZZZX905        	1	19980828	G	2435	23032022	STARTER         			BOLKMS	117   	BK117A3     	5626015	EU  										START/GENERATOR	DAMAGED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	35   			23766	7103				DRIVE DAMPER BROKEN.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999031200681	19990312	00681	EU  	1999	3	12	99ZZZX906        	1	19980826	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										TRIPLE TACH	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	170MC				282	7217				TACHOMETER'S NR 1 AND NR 2 NEEDLE SPLIT 2 PERCENT.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999031200682	19990312	00682	EU  	1999	3	12	99ZZZX907        	1	19980821	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117MH	4    			791	7112				NG INDICATOR INTERMITTENT.  WORKS FOR SOME TIME, THEN SPINS OUT OF CONTROL.  REMOVED AND REPLACED.						1	G	7	2 	3U				H13EU
1999031200684	19990312	00684	EU  	1999	3	12	99ZZZX909        	1	19981005	G	5240	1173084103	HINGE           			BOLKMS	BK117 	BK117C1     	5626025	EU  										SERVICE DOOR	CRACKED         	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	117NC	483  				7509				DOOR HINGE CRACKED.  PART SCRAPPED ON SITE.  REF:  RMA NR R014017.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H13EU
1999010800127	19990108	00127	SO  	1999	1	8	99ZZZX91         	1	19980817	G	7932	LW14732	DIPSTICK        		LW11033     	PIPER 	PA24  	PA24250     	7102404	SO  										ENGINE	SHEARED         	D	P			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	05	6523P	4980 	232  			241645				PILOT INSERTED THE OIL DIPSTICK INTO THE OIL FILLER ACCESS AREA INCORRECTLY.  IN SO DOING, BY RUNNING THE ENGINE, THE DI	PSTICK SHEARED OFF IN THE CRANKSHAFT AND ROD AREA CAUSING SUBSTANTIAL DAMAGE TO THE ENGINE.  DESIGN CHANGE ON ENGINE AND	/OR RE-ENFORCEMENT ON THE CORRECT INSERTION OF THE OIL DIPSTICK (SHOULD NOT REQUIRE FORCE) IS RECOMMENDED.				1	L	7	1 	3O				1A15
1999031200685	19990312	00685	SW  	1999	3	12	99ZZZX910        	1	19980929	G	2820	222366649101	VALVE           			BELL  	230   	230         	1182149	SW  										SUMP DRAIN	LEAKING         	B			TI1R	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	05	4UV	1825 			9206242	23019				SUMP DRAIN LEAKING.  REMOVED AND REPLACED.						1	G	7	2 	3U			NC	H9SW
1999031200686	19990312	00686	EU  	1999	3	12	99ZZZX911        	1	19980928	G	7714	1179405303	INDICATOR       			BOLKMS	117   	BK117A3     	5626015	EU  										TRIPLE TACH	FAILED          	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	527MB	1    			425	7103				NR 2 NEEDLE ON TACHOMETER INDICATOR STAYS AT ZERO, NR 1 NEEDLE RUNS 15 PERCENT LOW, AND ROTOR NEEDLE RUNS 4-5 PERCENT HI	GH.  REMOVED AND REPLACED.					1	G	7	2 	3U				H13EU
1999031200687	19990312	00687	EU  	1999	3	12	99ZZZX912        	1	19980917	G	7714	117902101	INDICATOR       			BOLKMS	BK117 	BK117C1     	5626025	EU  										COCKPIT	MALFUNCTIONED   	B			TI1R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	317MC	3170 			140	7505				BACK LIGHT ON LED DISPLAY INOPERATIVE.  REMOVED AND REPLACED.  REF:  RMA NR R016740.						1	G	7	2 	3U			NC	H13EU
1999031901097	19990319	01097	SO  	1999	3	19	99ZZZX914        	2	19980515	G	8520	632041	ROD             								CONT  	O520  	IO520F      	17032	SO  					ENGINE	DAMAGED         	B	L			K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	99							280002R			FOUND CONNECTING ROD BOLT-TO-HOLE CLEARANCE ON ROD CAP EXCESSIVELY TIGHT (OUT OF FACTORY LIMITS) TO THE POINT OF HAVING 	TO HAMMER THE BOLT INTO THE ROD CAP BOLT HOLE.  AFTER INVESTIGATION WITH INSIDE AND OUTSIDE MICROMETERS AND CLOSE OBSERV	ATION OF THE INSIDE OF THE BOLT HOLE WITH A MICROSCOPE, FOUND THE BOLT HOLE IN THE ROD CAP AND ROD WAS DISTORTED IN THE 	SAME AREA ON THE INSIDE OF THE HOLE AS THE NUMBER POSITION STAMPED ON THE OUTSIDE OF THE HOLE.								3	O			E5CE
1999031901098	19990319	01098	CE  	1999	3	19	99ZZZX915        	1	19981221	G	8120	40679558	TURBOCHARGER    		TH08A67     	CESSNA	340   	340A        	2076405	CE  										ENGINE	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05					AG020191					AIRCRAFT IS LOCATED IN AUSTRALIA.  IT WAS REPORTED THAT THE ENGINE WAS SURGING IN-FLIGHT.  INVESTIGATION THERE FOUND A T	URBOCHARGER WITH 'EXCESSIVE END FLOAT'.  THE TURBOCHARGER WAS RETURNED TO ALLIED SIGNAL AND INSPECTION FOUND A WORN THRU	ST BEARING.				1	L	7	2 	3O				3A25
1999031901099	19990319	01099	SO  	1999	3	19	99ZZZX916        	1	19980709	G	2720		CLEVIS          			GULSTM	AA5   	AA5         	0631410	SO  										RUDDER	WORN            	H	P	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	17										SUBMITTER HAS FOUND MANY CLEVIS BOLTS WORN AT LEAST 1/3 THROUGH WHERE CLEVIS BOLT ATTACHES CABLE FROM RUDDER TO RUDDER B	AR. THE RUDDER BAR HOLE ALSO IS ELONGATED EXCESSIVELY.  IF UNDETECTED THIS WILL CAUSE SEPARATION OF RUDDER CABLE FROM RU	DDER BAR/RUDDER PEDALS.  HARD TO FIND AS THIS IS UNDER CONSTANT TENSION BY RUDDER SPRINGS.  NEED TO RELAX SPRING TENSION	 IN ORDER TO THOROUGHLY INSPECT THESE BOLTS.  RECOMMEND AD BE ISSUED MANDATING A THOROUGH INITIAL INSPECTION AND THEN RE	PETITIVE INSPECTION SAY EVERY 500 HRS TO ENSURE INTEGRITY OF PART.  BOLT, PN AN2311.  BAR,  PN 601031501.		1	L	7	1 	3O				A16EA
1999010800128	19990108	00128	SO  	1999	1	8	99ZZZX92         	2	19980625	G	8550	653236	GEAR            			CESSNA	172   	R172E       	2072413	CE  	CONT  	O360  	IO360D      	17025	SO  					ENGINE	FAILED          	C				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	09	24FC	717  				R1720199	062942R			WHILE IN-FLIGHT, OIL PRESSURE AND TACHOMETER DROPPED TO ZERO.  WAS ABLE TO LAND ON PRIVATE GRASS STRIP WITHOUT INCIDENT.	  DETERMINED THE OIL PUMP DRIVE GEAR FAILED CAUSING FAILURE OF OIL PUMP, TACH DRIVE, AND ALTERNATOR GEAR.  ON AN EARLIER	 DATE, FORCED TO MAKE AN EMERGENCY LANDING WITHOUT INCIDENT IN SAME TYPE AIRCRAFT.  IT WAS ALSO DETERMINED THE OIL PUMP 	DRIVE GEAR HAD FAILED.			1	H	7	1 	3O	3	O		3A17    	E1CE
1999010800129	19990108	00129	EA  	1999	1	8	99ZZZX93         	2	19980826	G	8530	LW12993	CYLINDER        			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	SEPARATED       	B	P		A5OR	A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			SO	09	2756V	2660 	894  			177RG0682	L1342151A			PILOT REPORTED FAILURE OCCURRED AFTER TAKEOFF WHILE TURNING DOWN WIND AT 1,100 FEET AGL.  A LOUD BANG WAS HEARD FROM THE	 ENGINE WITH SMOKE AND OIL COVERING WINDSHIELD FOLLOWED BY A LOSS IN OIL PRESSURE.  ENG SHUT DOWN AND UNEVENTFUL DEAD ST	ICK LANDING MADE.  INVEST REVEALED A HOLE IN THE COWLING AND ACFT COVERED WITH OIL FROM ENG.  REMOVED TOP COWLING TO FIN	D NR 1 CYL HEAD SEPARATED FROM CYL BARREL.  ENG HAS 894.0 HRS SINCE MAJOR O/H WITH CERMICROME CYLINDERS.  A COMPRESSION 	TEST 20 HRS BEFORE FAILURE OCCURRED WAS 72/80.  THERE WAS NO INDICATION OF LEAKAGE FROM CYL.  HOWEVER, CYL HEAD APPEARED	 CRACKED ABOUT HALF WAY AROUND CYL BARREL FOR SOME TIME.  FAILURE OCCURRED WHERE CYL HEAD TREADS ONTO THE BARREL.	1	H	7	1 	3O	3	O		A20CE   	1E10
1999031901120	19990319	01120		1999	3	19	99ZZZX937        	4	19981201	G	6113	22520733	BULKHEAD        			CESSNA	182   	R182        	2072734	CE  										PROPELLER	BROKEN          	B				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	182SX					R18202025				A SPINNER WOBBLE WAS NOTICED.  THE SPINNER, P/N 2250274-3, WAS REMOVED AND THE FRONT BULKHEAD WAS FOUND BROKEN.  ALSO, F	OUND A CRACKED AFT BULKHEAD HALF (P/N 2252073-3) AND ONE ATTACH PLATE (P/N C5046).  THE SPINNER WAS INSTALLED NEW ON 5-1	4-96 AT 1,330.0 TT.  THE PARTS WERE PAINTED AND INSTALLED.  THE PROPELLER WAS BALANCED REQUIRING MINIMAL WEIGHT.  THE AI	RCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3O			RT	3A13
1999010800130	19990108	00130	CE  	1999	1	8	99ZZZX94         	1	19980902	G	5311	1694000117	FRAME           			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	831KS	4789 				M1548				FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FUSELAGE SKIN	.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MOUNTING INSTR	UMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1999031900731	19990319	00731		1999	3	19	99ZZZX941        	4	19981201	G	6113	22520743	SPINNER         			CESSNA	182   	R182        	2072734	CE  										NOSE	CRACKED         	B				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SO	05	182SX	269  				R18202025				AT 1,602.4 HOURS TT, A SPINNER WOBBLE WAS NOTICED.  THE SPINNER (PN 2252074-3) WAS REMOVED AND THE FRONT BULKHEAD WAS FO	UND BROKEN.  ALSO, FOUND A CRACKED AFT BULKHEAD HALF (PN 2252073-3) AND ONE ATTACH PLATE (PN C5046).  THE SPINNER WAS IN	STALLED NEW ON 5-14-96 AT 1,330.0 HOURS TT.  THE PARTS WERE PAINTED AND INSTALLED.  THE PROPELLER WAS BALANCED REQUIRING	 MINIMAL WEIGHT.  THE AIRCRAFT WAS RETURNED TO SERVICE.			1	H	7	1 	3O			RT	3A13
1999031900732	19990319	00732	CE  	1999	3	19	99ZZZX942        	1	19981204	G	2430		FILTER          	FORD        		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ALTERNATOR	SHORTED         	H				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	1854V					17263771				DURING FLIGHT, THE CONDENSER BROKE OFF THE BACK OF THE ALTERNATOR AND SHORTED OUT BETWEEN POWER (A+) AND THE FIELD WIRE 	(F).  THIS CAUSED THE ALTERNATOR TO GO TO FULL OUTPUT.  THE PILOT THEN SHUT OFF THE MASTER WHICH SUBMITTER BELIEVED ALLO	WED THE ALTERNATOR TO PRODUCE UNREGULATED HIGH VOLTAGE WHICH DAMAGED ELECTRICAL AND AVIONICS COMPONENTS.  TERMINAL BOOTS	, MS 29171-15, MAY HAVE HELPED PREVENT THIS FROM HAPPENING.			1	H	7	1 	3O	3	O	NT	3A12    	E274
1999031900734	19990319	00734	CE  	1999	3	19	99ZZZX944        	1	19981229	G	7997		WIRE            			BEECH 	90    	C90         	1152913	CE  										INDICATOR	CHAFED          	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	99	24GJ					LJ769				NR 1 ENGINE LOST OIL PRESSURE INDICATION.  WIRE ON TRANSMITTER AT CANON PLUG FOUND CHAFED UNDER ADEL CLAMP.						1	L	7	2 	3T			 	3A20
1999031900735	19990319	00735	EA  	1999	3	19	99ZZZX945        	2	19981116	G	7414	D4LN3000	MAGNETO         	BENDIX      		MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A1B6   	41514	EA  					ENGINE	FAILED          	G				A				UNSCHED LANDING         				R	N		PARTIAL RPM/PWR LOSS      	FALSE WARNING             		CR	CRUISE         	1			SW	17	201QK		776  		3050584	240290	L2227951A			DURING CRUISE FLIGHT, THE ENGINE FAILED TO PRODUCE POWER DUE TO A TOTAL FAILURE OF THE DUAL MAGNETO.  POST-ACCIDENT INVE	STIGATION REVEALED BOTH THE LEFT AND RIGHT IGNITION POINTS OF THE BENDIX D4LN-300 DUAL MAGNETO WERE NOT OPENING.  THE PL	ASTIC CAM FOLLOWERS OF BOTH CONTACT POINT ASSEMBLIES WERE MELTED WHERE THEY REST AGAINST THE CAM.  UPON ADJUSTMENT OF TH	E POINT, THE ENGINE WAS RUN SUCCESSFULLY.  ADDITIONALLY, SEVERAL OUNCES OF ENGINE OIL DRAINED FROM THE MAGNETO WHEN THE 	CAP WAS REMOVED.  IT APPEARS THAT THE OIL ENTERED THE MAGNETO DUE TO A BROKEN BEARING RETAINER SCREW.		1	L	7	1 	3O	3	O		2A3     	1E10
1999031900736	19990319	00736	SW  	1999	3	19	99ZZZX946        	1	19981101	G	3246	850X100253500	TIRE            			GULSTM	690TP 	690B        	7630516	SW  										MLG	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	07	205BN	25   			7288P00801	11404				TIRES WERE REPLACED BECAUSE THEY WOULD NOT HOLD AIR.  INSPECTION REVEALED DILATING HOLES ALLOWING AIR LOSS TO CONTINUE A	FTER SEVERAL DAYS.  LEAKAGE BECAME WORSE TO THE POINT RE-INFLATION WAS NEEDED AFTER EACH FLIGHT.  HIGH RISK OF LANDING W	ITH FLAT TIRE ON TRIP OVER 2 HOURS.  MICHELIN NOTIFIED.  DILATING HOLES ARE MARKED WITH GREEN, BUT NOT ALL HOLES LEAKED.				1	H	7	2 	3T				2A4
1999031900737	19990319	00737	SW  	1999	3	19	99ZZZX947        	1	19981101	G	3246	850X100253500	TIRE            			GULSTM	690TP 	690B        	7630516	SW  										MLG	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	07	205BN	25   			7291P00140	11404				TIRES WERE REPLACED BECAUSE THEY WOULD NOT HOLD AIR.  INSPECTION REVEALED DILATING HOLES ALLOWING AIR LOSS TO CONTINUE A	FTER SEVERAL DAYS.  LEAKAGE BECAME WORSE TO THE POINT RE-INFLATION WAS NEEDED AFTER EACH FLIGHT.  HIGH RISK OF LANDING W	ITH FLAT TIRE ON TRIP OVER 2 HOURS.  MICHELIN NOTIFIED.  DILATING HOLES ARE MARKED WITH GREEN, BUT NOT ALL HOLES LEAKED.				1	H	7	2 	3T				2A4
1999031900738	19990319	00738	SW  	1999	3	19	99ZZZX948        	1	19981101	G	3246	850X100253500	TIRE            			GULSTM	690TP 	690B        	7630516	SW  										MLG	LEAKING         	C				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	07	205BN	25   			8276P00183	11404				TIRES WERE REPLACED BECAUSE THEY WOULD NOT HOLD AIR.  INSPECTION REVEALED DILATING HOLES ALLOWING AIR LOSS TO CONTINUE A	FTER SEVERAL DAYS.  LEAKAGE BECAME WORSE TO THE POINT RE-INFLATION WAS NEEDED AFTER EACH FLIGHT.  HIGH RISK OF LANDING W	ITH FLAT TIRE ON TRIP OVER 2 HOURS.  MICHELIN NOTIFIED.  DILATING HOLES ARE MARKED WITH GREEN, BUT NOT ALL HOLES LEAKED.				1	H	7	2 	3T				2A4
1999010800131	19990108	00131	CE  	1999	1	8	99ZZZX95         	1	19980902	G	5311	1694000118	FRAME           			BEECH 	23    	C23         	1151242	CE  										INSTRUMENT PANEL	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	11	831KS	4789 				M1548				FOUND CRACKING IN FRAME ANGLE WHICH MOUNTS INSTRUMENT PANEL TO FUSELAGE AND CRACKS IN ADJACENT CHANNEL AND FUSELAGE SKIN	.  SUSPECT CRACKING BECAUSE OF LANDINGS MADE IN TRAINING AIRCRAFT.  SUGGEST CLOSE INSPECTION OF STRUCTURE MOUNTING INSTR	UMENT PANEL EVERY 100 HOURS OR ANNUALLY.				1	L	7	1 	3O				A1CE
1999031900744	19990319	00744	GL  	1999	3	19	99ZZZX954        	3	19980112	G	6110	MS21260	FERRULE         			PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2Y*      	GL  	PROPELLER ASSY	FAILED          	D	S			K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	23PE	4732 				447995058				PART FAILED DURING TRAINING FLIGHT.  FERRULE SHAFT BROKE JUST AFT OF THREADED PORTION.						1	L	7	2 	3O				A19S0   		5	C	P920
1999031900749	19990319	00749	CE  	1999	3	19	99ZZZX959        	1	19980610	G	2822	476411	PUMP            			CESSNA	310   	310R        	2074245	CE  										LEFT WING	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	15	310TM	52   				310R1208				WING TIP TRANSFER PUMP TRIPPED CIRCUIT BREAKER.  THIS IS THE THIRD PUMP INSTALLED IN THIS LOCATION IN 18 MONTHS; CESSNA 	WAS ADVISED OF THE PROBLEM.					1	L	7	2 	3O				3A10
1999010800132	19990108	00132	CE  	1999	1	8	99ZZZX96         	1	19980921	G	2434	125021315	SUPPORT         			CESSNA	206   	P206B       	2073309	CE  										ALTERNATOR	CRACKED         	D	S	A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	13	4790F	5186 				P2060390				DURING AN ENGINE CHANGE, THE ALTERNATOR SUPPORT BRACKET WAS FOUND CRACKED.  THE CRACK WAS ABOUT 1.25 INCHES LONG AND SEE	MS TO HAVE STARTED AT THE MANUFACTURER'S WELD.  CESSNA SIL SE 79-5 CALLS FOR REPLACEMENT OF THIS PART WITH AN INTEGRAL E	NGINE MOUNT LEG/ALTERNATOR SUPPORT BRACKET (ONE PIECE).				1	H	7	1 	3O				A4CE
1999031900752	19990319	00752	EA  	1999	3	19	99ZZZX962        	2	19980805	G	7322	46E21297	ARM             			PIPER 	PA46  	PA46350P    		SO  	LYC   	O540  	TIO540AE2A  	41532	EA  					CARBURETOR	BROKEN          	B	S		FCPR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	318CW	51   				4636153	L996461A			ARM BROKE.  REPLACED ARM.  SYSTEM OPERATED NORMALLY.  ARM COMES AS PART OF CONTROLLER.						1	L	7	1 	3O	3	O	RT	A25SO   	E14EA
1999031900754	19990319	00754	NE  	1999	3	19	99ZZZX964        	1	19981109	G	2821	1742570	FUEL FILTER     	FACET       		CONAER	LA4   	LA4200      	5110310	NE  										FUEL SYSTEM	DIRTY           	D		A		A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		NR	NOT REPORTED   	1			NE	05	36LK	338  				1041				IN-FLIGHT, ENGINE STOPPAGE.  PILOT EXPERIENCED ENGINE STOPPAGE IN-FLIGHT, SAW FUEL PRESSURE GAUGE REGISTERING ZERO.  WHE	N HE TURNED ON FUEL PUMP BOOST SWITCH, ENG RE-STARTED AND MADE A SAFE LANDING.  UPON INVESTIGATION OF FUEL SYSTEM, FOUND	 THE FUEL FILTER DIRTY AND PARTIALLY PLUGGED, WATER AND CONTAMINENTS IN FUEL SERVO.  OVERHAULED FUEL SERVO AND INSTALLED	 ANOTHER FUEL FILTER ELEMENT (PN 1743117-03).  OPS CHECK OK.  NOTE: THESE FILTERS ARE INSTALLED IN A HORIZONTAL POSITION	 AND NO DRAIN MAKING IT IMPOSSIBLE TO DRAIN WATER AND CONTAMINENTS.		1	H	7	1 	3O				1A13
1999010800133	19990108	00133	SO  	1999	1	8	99ZZZX97         	2	19980713	G	8520	646320	ROD             			CESSNA	337   	M337B       		CE  	CONT  	O360  	IO360D      	17025	SO  					ENGINE	FAILED          	C				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	25	475DF	376  				337M0343	239778R			INVESTIGATION FOUND NR 5 CONNECTING ROD CAME APART.  CAUSE UNDER INVESTIGATION.						1	H	7	2 	3O	3	O		A6CE    	E1CE
1999031900972	19990319	00972	CE  	1999	3	19	99ZZZX971        	1	19981102	G	5620	1014400424	WINDOW          			BEECH 	200   	200BEECH    	1152920	CE  										CABIN	CRACKED         	B			ABOR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	15	49KC	6854 				BB318				DURING POST-FLIGHT INSPECTION, FLIGHT CREW DISCOVERED A 6 INCH CRACK IN RIGHT 'VESTIBULE' WINDOW.  THEY REPORTED NO PRES	SURE LOSS OR NO ABNORMAL INDICATION DURING THEIR FLIGHT.  MAINTENANCE REMOVED AND REPLACED WINDOW AND FOUND NO OBVIOUS R	EASON FOR THE CRACK.				1	L	7	2 	4T				A24CE
1999031900975	19990319	00975	EA  	1999	3	19	99ZZZX974        	2	19981124	G	8530	LW13521	BEARING INSERT  			PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					NR 4 CYLINDER	WORN OUT        	B			MI2R	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CE	07	4954L	998  				284325	L1160836A			ENGINE LOST OIL PRESSURE IN-FLIGHT.  ENGINE TEAR DOWN FOUND NR 4 ROD INSERT WAS COMPLETELY BURNED OUT.  INSERT COULD HAV	E SPUN IN ROD CLOSING OFF OIL SUPPLY.  THIS CAUSED THE ROD BOLT TO BREAK.  THE ROD CAP WAS DRIVEN THROUGH THE BOTTOM OF 	THE CASE INTO OIL SUMP.  NR 3 ROD WAS EXCESSIVELY HOT AND THE ROD NUTS WERE LOOSE.  ANOTHER PROBLEM WAS NR 2 PISTON PIN 	PLUG HAD BROKEN OFF IN THE PIN AND THE LARGE END HAD BEEN WORKING IN THE PISTON PIN HOLE MAKING IT VERY LARGE.  THE OIL 	RING WAS BROKEN AND THE CYLINDER WAS SCORED.   THE ENG HAS AN OIL FILTER.  OIL WAS CHANGED 32 HRS AGO.		1	L	7	1 	3O	3	O		2A13    	E286
1999031900976	19990319	00976	SW  	1999	3	19	99ZZZX975        	1	19981216	G	5541	442283	SPAR            			GULSTM	112   	114         	7630314	SW  										RUDDER	CRACKED         	D				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	05	4945W	2402 				14267				RUDDER SPAR CRACK AT UPPER HINGE FITTING (PN 44254-501) WAS DISCOVERED DURING AN ANNUAL INSPECTION.						1	L	7	1 	3O				A12SO
1999031900978	19990319	00978	SO  	1999	3	19	99ZZZX977        	2	19981221	G	7397	991008219	WIRE            	GULL        		CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  					LT/RT FUEL CELL	CHAFED          	B	P	A	YR4R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	05	4919A	4248 				310R1403				DURING ANNUAL INSP, TOP INSP PANEL ON RT WING AUX TANK WAS LEAKING FUEL.  AFTER REMOVING, NOTICED FUEL QTY SENDING UNIT 	WIRES INSIDE THE FUEL TANK WERE EXCEPTIONALLY LONG.  FOUND INSULATION CHAFED OFF WIRES AND BARE WIRE SHOWING.  NOTICED W	IRES WERE CHAFED ON LT AUX TANK AND BARE WIRE SHOWING.  SENDING UNITS REMOVED FROM LT AND RT FUEL AUX TANKS AND WIRES FO	UND FLOATING IN FUEL INSIDE TANKS.   DUE TO EXCESSIVE LENGTH IN THE WIRES, THEY WERE MOVING BACK AND FORTH WITH THE SLOS	HING OF FUEL AND CHAFING AGAINST THE BOTTOM OF FUEL CELL.  FUEL CELL AND FUEL QTY SENDING UNITS INSTALLED WHEN ACFT NEW 	1978.  ACFT RECORDS SHOW NO FUEL CELL CHANGES SINCE NEW.  AS OF NOW, NO INSP REQUIREMENTS TO GO INSIDE FUEL CELLS.	1	L	7	2 	3O	3	O	 	3A10    	E5CE
1999031900979	19990319	00979	CE  	1999	3	19	99ZZZX978        	1	19980223	G	2400	S23262	CIRCUIT BREAKER 			CESSNA	310   	310Q        	2074242	CE  										COCKPIT	FAILED          	E				A				UNSCHED LANDING         				N			FALSE WARNING             			NR	NOT REPORTED   	1			CE	07	4063Q	4101 				310Q0724				DURING IFR NIGHT-TIME FLIGHT, PILOT NOTICED RT ALTERNATOR FAILURE LIGHT HAD ILLUMINATED.  PILOT NOTICED LIGHTS AND OTHER	 ELECTRICAL EQUIPMENT DIMMED AND PROCEEDED TO TERMINATE FLIGHT AT NEAREST AIRPORT.  UPON EXAMINATION, FOUND RT ALTERNATO	R BELT MISSING TEETH AND THROWN FROM ENGINE PULLEY AND ALTERNATOR CIRCUIT BREAKER TRIPPED.  ALSO, FOUND THAT LT ALTERNAT	OR WS OPERATING, BUT THAT WHEN ELECTRICAL LOAD WAS PLACED ON CIRCUIT BREAKER FOR LT, THAT IT OPENED INTERNALLY EVEN THOU	GH IT WAS VISUALLY CLOSED.  FURTHER CHECKS FOUND BREAKER TESTED GOOD WITH OHMMETER, BUT WHEN ANY POWER WAS APPLIED, BREA	KER WOULD OPEN.  REPLACED CIRCUIT BREAKER AND BOTH BELTS, RUN-UP AND CHECKED GOOD.	1	L	7	2 	3O				3A10
1999031900980	19990319	00980		1999	3	19	99ZZZX979        	4	19981026	G	2562		WIRE            			CESSNA	172   	172R        	2072401	CE  										BEACON	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	16	406ER	320  				17280297				PILOT'S CONTROL WHEEL SHAFT PICKED UP WIRE BUNDLE WHERE IT RUNS UNDER THE SHAFT.  THIS PINCHED THE BEACON WIRE BREAKING 	THROUGH THE INSULATION AND BURNING THE WIRE IN HALF.					1	H	7	1 	3O			NT	3A12
1999010800134	19990108	00134	CE  	1999	1	8	99ZZZX98         	1	19980910	G	3222	50450182	WASHER          		51411011    	CESSNA	421   	421C        	2076016	CE  										LT MLG	SHEARED         	B			VA1R	O				OTHER                   				O			OTHER                     			LD	LANDING        	1			SW	19	2JA	4295 	186  			421C0154				AIRCRAFT LANDED ON RUNWAY 1 WITH WIND FROM THE NW AT 18 TO 23 KNOTS.  AT TOUCH-DOWN, LT MAIN GEAR ROTATED 90 DEGREES AND	 SKIDDED UNTIL ACFT STOPPED NEAR LT SIDE OF RUNWAY.  BOLT AN175-20, BUSHING 5041013-1, NUT AN310-5, AND WASHERS WERE STI	LL ATTACHED TO UPPER LINK ASSY, P/N 5141005-7.  WASHER, P/N 5045018-2, HAD SHEARED THE OUTER PORTION AND ALLOWED NUT, P/	N AN310-5, TO PULL THROUGH LOWER LINK ASSY, P/N 5141005-7, LETTING LOWER STRUT/WHEEL TO TURN 90 DEGREES.  WASHER, P/N 50	45018-2, DID APPEAR TO HAVE PRIOR WEAR.  SUBMITTER SUSPECTS POOR PRE-FLIGHT INSP, LANDING TECHNIQUE, AND/OR LACK OF PROP	ER MAIN.	1	L	7	2 	3O				A7CE
1999031900986	19990319	00986	CE  	1999	3	19	99ZZZX985        	1	19980928	G	8120	4067958	TURBOCHARGER    		TH08A67     	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  					ENGINE	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	05	8120				AJ037587	414A0331				SUBJECT AIRCRAFT WOULD NOT DEVELOP SPECIFIED BOOST.  INVESTIGATION FOUND EXCESSIVE AXIAL PLAY IN THE TURBOCHARGER AND OT	HER UNRELATED EXHAUST SYSTEM PROBLEMS.  THE TURBOCHARGER WAS RETURNED TO ALLIED SIGNAL AND INSPECTION FOUND A WORN THRUS	T BEARING.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1999010800135	19990108	00135	CE  	1999	1	8	99ZZZX99         	1	19980514	G	5220	52111302	EMERGENCY EXIT  			CESSNA	402   	402B        	207590P	CE  										RIGHT	SEPARATED       	D				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			SW	11	3748C	5295 				402B0606				EMERGENCY EXIT WINDOW DEPARTED THE AIRCRAFT IN-FLIGHT FROM HOPE, ARK TO LITTLE ROCK, ARK.  THIS WAS A CHARTER FLIGHT WIT	H ONE PILOT AND THREE PASSENGERS ON BOARD.  THE AIRCRAFT LANDED AT LITTLE ROCK AIRPORT UNEVENTFULLY.   THIS STYLE EMERGE	NCY EXIT WINDOW HAS A CHANNEL-TYPE HINGE AT THE TOP AND A STEEL RELEASE PIN CONNECTED TO THE RELEASE CABLE ASSEMBLY AT T	HE LOWER FORWARD SIDE, AND IS SECURED WITH BRASS SAFETY WIRE.  THE LOWER AFT SIDE HAS AN ALUMINUM SHEAR PIN.  THE BRASS 	SAFETY WIRE WAS TWISTED TOO TIGHT AND LATER BROKE CAUSING THE PIN TO WORK OUT.		1	L	7	2 	3O				A7CE
1998080700238	19980807	00238		1998	8	7	A3L298011        	1	19980701	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  														WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B0765					INSPECTION FOUND BROKEN WHEEL BOLT.  SUSPECT FATIGUE RELATED FAILURE OR INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTE	D USING SNUG ANGLE TORQUE METHOD.  (X)
1998050800003	19980508	00003	NM  	1998	5	8	A3L2980310       	1	19980417	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B4237					WHEEL INSPECTION FOUND BROKEN BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998041700085	19980417	00085	NM  	1998	4	17	A3L298038        	1	19980327	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B9724					INSPECTION FOUND GEAR WHEEL WITH BROKEN BOLT.						2	L	7	2 	4F			RT	A16WE
1998050800002	19980508	00002	WP  	1998	5	8	A3L298039        	1	19980417	G	3246	2601483	BOLT            	BENDIX      	26088911A   	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B1871					INSPECTION FOUND WHEEL BOLT WITH A FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED U	SING SNUG ANGLE TORQUE METHOD.					2	L	7	2 	4F			RT	A6WE
1998050800001	19980508	00001	WP  	1998	5	8	A3L298041        	1	19980417	G	3246	2601483	BOLT            	BENDIX      	26088911A   	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					H0105					INSPECTION FOUND WHEEL BOLT WITH FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USI	NG SNUG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE
1998050800012	19980508	00012	NM  	1998	5	8	A3L298042        	1	19980420	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B9220					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998050800011	19980508	00011	NM  	1998	5	8	A3L298043        	1	19980420	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B8868					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998050800007	19980508	00007	WP  	1998	5	8	A3L298044        	1	19980422	G	3246	2601483	BOLT            	BENDIX      	26088911A   	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B1251					INSPECTION FOUND FATIGUE RELATED BOLT FAILURE.  SUSPECT INSUFFICIENT REPLOAD TORQUE.  SUBMITTER SUGESSTED USING A SNUG A	NGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE
1998050800009	19980508	00009	WP  	1998	5	8	A3L298045        	1	19980422	G	3246	2601483	BOLT            	BENDIX      	26088911A   	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B2017					INSPECTION FOUND FATIGUE RELATED BOLT FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING A SNUG A	NGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE
1998052900386	19980529	00386	NM  	1998	5	29	A3L298046        	1	19980511	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B7839					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998052900384	19980529	00384	WP  	1998	5	29	A3L298047        	1	19980511	G	3246	2601483	BOLT            	BENDIX      	26088914    	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B4880					INSPECTION FOUND FATIGUE RELATED WHEEL BOLT FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING SN	UG ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE
1998052900385	19980529	00385	NM  	1998	5	29	A3L298048        	1	19980511	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B3196					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998062600119	19980626	00119		1998	6	26	A3L298051        	1	19980529	G	3246	2601483	BOLT            	BENDIX      	26088911A   															WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B0187					INSPECTION FOUND WHEEL BOLT FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING SN	UG ANGLE TORQUE METHOD.  (X)
1998062600120	19980626	00120		1998	6	26	A3L298052        	1	19980529	G	3246	2601483	BOLT            	BENDIX      	26088911A   															WHEEL	FAILED          	B			A3L2	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	09					B3308					INSPECTION FOUND WHEEL BOLT FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING SN	UG ANGLE TORQUE METHOD.  (X)
1998041000027	19980410	00027	NM  	1998	4	10	A3L3980302       	1	19980319	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B9525					WHEEL INSPECTION FOUND BROKEN BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998080700237	19980807	00237	NM  	1998	8	7	A3L398031        	1	19980318	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	737300      	1384610	NM  										WHEEL	BROKEN          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B2792					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998050800010	19980508	00010	NM  	1998	5	8	A3L398042        	1	19980421	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B4379					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998050800008	19980508	00008	WP  	1998	5	8	A3L398043        	1	19980422	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B0612					INSPECTION FOUND FATIGUE RELATED BOLT FAILURES.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING A SNUG 	ANGLE TORQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE
1998050800910	19980508	00910	WP  	1998	5	8	A3L398044        	1	19980423	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B0290					INSPECTION FOUND FATIGUE RELATED BOLT FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING A SNUG A	NGLE TORQUE METHOD.					2	L	7	2 	4F			RT	A6WE
1998051500278	19980515	00278	WP  	1998	5	15	A3L398045        	1	19980430	G	3246	2601483	BOLT            	BENDIX      	2608891     	DOUG  	DC9   	DC983       	3022083	WP  										WHEEL	FAILED          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19										INSPECTION FOUND FATIGUE RELATED FAILURE.  SUSPECT INSUFFICIENT PRELOAD TORQUE.  SUBMITTER SUGGESTED USING SNUG ANGLE TO	RQUE METHOD.  (X)					2	L	7	2 	4F			RT	A6WE
1998051500277	19980515	00277	NM  	1998	5	15	A3L398046        	1	19980430	G	3246	2602540	BOLT            			BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19										INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998052200598	19980522	00598	NM  	1998	5	22	A3L398051        	1	19980508	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B8542					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998062600090	19980626	00090	NM  	1998	6	26	A3L398052        	1	19980526	G	3246	2602540	BOLT            	BENDIX      	26066712    	BOEING	737   	7373A4      	1384585	NM  										WHEEL	BROKEN          	B			A3L3	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	19					B8657					INSPECTION FOUND BROKEN WHEEL BOLT.  (X)						2	L	7	2 	4F			RT	A16WE
1998052200053	19980522	00053	WP  	1998	5	22	A3LD98031        	1	19980401	G	3246	MS21250	TIE BOLT        		9560892     	DOUG  	DC9   	DC931       	3022065	WP  										WHEEL	BROKEN          	B			A3LD	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	05					OCT783380					INSPECTION FOUND BROKEN TIE BOLT.  (X)						2	L	7	2 	4F				A6WE
1998082800326	19980828	00326	NM  	1998	8	28	AALA981354       	1	19980709	G	3297		WIRE            			BOEING	727   	727223      	1384074	NM  										NLG	BROKEN          	A			AALA	O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			SW	07	873AA					21385				DFW - FLT 0513 - DURING APPROACH DFW, NOSE GEAR UNSAFE INDICATION LIGHT ILLUMINATED.  VERIFIED GEAR DOWN AND LOCKED AND 	LANDED DFW WITHOUT INCIDENT.  REPAIRED WIRE IN NLG WIRE HARNESS.  ACCOMPLISHED GEAR SWING.  SYSTEM GROUND CHECKED, NORMA	L OPERATION.  (X)				2	L	7	3 	4F			 	A3WE
1998021100849	19980211	00849	WP  	1998	2	11	AU980002         	1	19980108	G	6210	369021100516A	BLADE           			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					M/R BLADE	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					E342		830754			(AUS) MAIN ROTOR BLADE DOUBLER DEBONDED IN AREA OF BLADE ROOT LOWER SURFACE. DEPTH OF DEBOND 55MM (2.165IN).						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998021100850	19980211	00850	EU  	1998	2	11	AU980003         	1	19980108	G	5741	TB1011034900	BRACKET         	SOCATA      	TB10        	SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	LT WING AFT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING REAR ATTACHMENT BRACKET BROKEN THROUGH LOWER BOLT HOLE. SUSPECT CAUSED BY UNREPORTED HEAVY LANDING.						1	L	7	1 	30	3	O	NT	A51EU   	E286	5	C	P920
1998021100851	19980211	00851		1998	2	11	AU980004         	1	19980105	G	7722	10151N01T00	INDICATOR       								PWA   	PWA120	PW125B      		NE  					ENG. EGT/TIT	FAILED          	W				K				NONE                    				O		I	OTHER                     		FLT. ATTITUDE INST.       	CR	CRUISE         	1			AU	S 					110AB					(AUS) RH ENGINE ITT GAUGE FAILED. A REPLACEMENT INDICATOR FAILED ON THE NEXT FLIGHT.											4	T			E20NE
1998021100852	19980211	00852	SO  	1998	2	11	AU980005         	1	19980104	G	3233	2112600000	ROD END         			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					MLG  ACTUATOR	WORN            	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) RH MAIN LANDING GEAR RETRACTION ACTUATOR RODEND WORN						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998021100853	19980211	00853	EA  	1998	2	11	AU980006         	2	19980107	G	7532	310082903	BLEED VALVE     	PWA         	PT6A346     	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT ENG BLEED	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 			2643 		PCE57034		PCE57034			(AUS) LH ENGINE BLEED VALVE DIRTY CAUSING THE BLEED VALVE TO STICK WHEN CLOSING RESULTING IN COMPRESSOR STALLS. AIRCRAFT	 OPERATES FROM UNSEALED AIRSTRIPS.					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
1998021100854	19980211	00854	EU  	1998	2	11	AU980007         	1	19980107	G	2435	23078010	GENERATOR       			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	RT ENG START/GEN	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 			754  		1826					(AUS) RH ENGINE STARTER/GENERATOR FAILED						2	H	7	2 	4T	4	T		A41EU   	E26NE	6	C	P14NE
1998021100855	19980211	00855	SO  	1998	2	11	AU980008         	1	19980112	G	5520	4975802	HINGE           		4223104     	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	ELEV RT INB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR HINGE INBOARD RH BRACKET CRACKED IN RADIUS.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998021100856	19980211	00856	CE  	1998	2	11	AU980009         	1	19980113	G	3213		TORQUE LINK     			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	BEECH	215	215107      	CE  	MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR TORQUE LINKS WORN EXCESSIVELY.						1	L	7	1 	3O	3	O		A777    	E267	5	C	P873
1998021100857	19980211	00857	NM  	1998	2	11	AU980010         	1	19980101	G	2520		SEAT            			BOEING	737   	737377      		NM  										CABIN NR 8G	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SEAT 8G WORN. THE SEAT WAS OBSTRUCTING THE OVERWING EXIT WHEN INTHE UPRIGHT POSITION.						2	L	7	2 	4F			RT	A16WE
1998021100858	19980211	00858	NE  	1998	2	11	AU980011         	2	19980102	G	7250		BLADE           								CFMINT	CFM56 	CFM565A1    		NE  					HP TURBINE	FAILED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 							731153			(AUS) NO ENGINE HIGH PRESSURE TURBINE BLADE FAILED. APPROXIMATELY 33% OF THE BLADE TRAILING EDGE WAS MISSING.											4	F			E29NE
1998021100859	19980211	00859	CE  	1998	2	11	AU980012         	1	19980113	G	3222		BUSHING         			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	BEECH	215	215107      	CE  	NLG STRUT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR STRUT ASSEMBLY BUSHES WORN EXCESSIVELY.						1	L	7	1 	3O	3	O		A777    	E267	5	C	P873
1998021100860	19980211	00860	CE  	1998	2	11	AU980013         	1	19980113	G	2810		CAP             			BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	BEECH	215	215107      	CE  	MAIN FUEL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN FUEL CAPS (2OFF) FAULTY.						1	L	7	1 	3O	3	O		A777    	E267	5	C	P873
1998021100861	19980211	00861		1998	2	11	AU980014         	4	19980113	G	3455		ANTENNA         	BEECH       	G35         	BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	BEECH	215	215107      	CE  	ADF SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ADF SENSOR ANTENNA BROKEN.						1	L	7	1 	3O	3	O		A777    	E267	5	C	P873
1998021100862	19980211	00862	CE  	1998	2	11	AU980015         	1	19980113	G	2432		BATTERY         	BEECH       	G35         	BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	BEECH	215	215107      	CE  	DC SYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BATTERY CORRODED.						1	L	7	1 	3O	3	O		A777    	E267	5	C	P873
1998021100863	19980211	00863	CE  	1998	2	11	AU980016         	1	19980113	G	3230		BUSHING         	BEECH       	G35         	BEECH 	35    	G35         	1151516	CE  	CONT  	E225  	E2258       	17015	SO  	BEECH	215	215107      	CE  	NLG RETRACT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE BUSHES WORN AND ONE ATTACHMENT BOLT LOOSE.						1	L	7	1 	3O	3	O		A777    	E267	5	C	P873
1998021100864	19980211	00864	EU  	1998	2	11	AU980017         	1	19980103	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					APU	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8601 		CL7707ANSETT					(AUS) APU FIRE EXTINGUISHER BOTTLE EMPTY. FOUND DURING INSPECTION IAW ER BA6-26-20-15.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998021100865	19980211	00865	EU  	1998	2	11	AU980018         	1	19980104	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENGINE	EMPTY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4251 		CM9542ANSETT					(AUS) NO4 ENGINE OUTBOARD FIRE BOTTLE UNDERWEIGHT. FOUND DURING INSPECTION IAW ER BA6-26-20-15.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998021100866	19980211	00866	CE  	1998	2	11	AU980019         	1	19980109	G	2612	24412886	FIRE WIRE       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	LOW RESISTANCE  	W				K				NONE                    				E	B	N	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             	DE	DESCENT        	1			AU	S 							114419			(AUS) RH ENGINE FORWARD FIRE WIRE LOW RESISTANCE.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998021100867	19980211	00867		1998	2	11	AU980020         	1	19980113	G	7120	AN35A	BOLT            								GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ENG MOUNT LT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH LOWER ENGINE MOUNT BRACKET BOLTS LOOSE. SUSPECT BOLTS INCORRECTLY TORQUED AT MANUFACTURE.											4	T			E4WE	6	C	3PNE
1998021100868	19980211	00868	CE  	1998	2	11	AU980021         	1	19980105	G	5312		BULKHEAD        			CESSNA	182   	182P        	2075816	CE  										FWD DOOR POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR POST BULKHEAD CRACKED. FOUND DURING INSPECTION IAW AD/CESSNA180/75 AMDT1.						1	H	7	1 	3O			NT	TA13
1998021100869	19980211	00869	NE  	1998	2	11	AU980022         	2	19980110	G	7261	0301047170	PIPE            								TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					NR 1 ENG OIL	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 							385			(AUS) NO1 ENGINE OIL PRESSURE PIPE TO THE REAR BEARING CRACKED AROUND FLARE. LOSS OF 3.5 LITRES OF ENGINE OIL. SUSPECT P	IPE WAS OVERTORQUED.										3	U			E19EU
1998021100870	19980211	00870	CE  	1998	2	11	AU980023         	1	19980113	G	2910	57270021	PIPE            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	HYD MAIN	HOLED           	W				K				NONE                    				K	O	J	FLUID LOSS                	OTHER                     	WARNING INDICATION        	TO	TAKEOFF        	1			AU	S 										(AUS) HYDRAULIC PIPE TO FLAP SELECTOR CONTAINED PINHOLE LEAKS. LOSS OF HYDRAULIC FLUID						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998021100871	19980211	00871	SW  	1998	2	11	AU980024         	1	19980109	G	7722	3038266	HARNESS         	PWA         	PT6T3B      	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENG. EGT/TIT	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					60221		60221			(AUS) NO2 ENGINE ITT (T5) HARNESS INTERMITTENT FAULT.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998021900095	19980219	00095	SO  	1998	2	19	AU980025         	1	19980108	G	2752	3203001005	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP ACTUATOR	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					1083					(AUS) LH INBOARD FLAP ACTUATOR FAULTY						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998021900096	19980219	00096	SO  	1998	2	19	AU980026         	1	19980101	G	2710	12027655007	CONTROL CABLE   			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      	 	NE  					AILERON CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH UPPER AILERON CABLE FRAYED IN AREA WHERE THE CABLE PASSES THROUGH THE INBOARD ENGINE NACELLE						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998021900097	19980219	00097	EU  	1998	2	19	AU980027         	2	19980113	G	7322	52B	SPRING          		643         						ROTAX 	912   	ROTAX912    	55555	EU  					LT CARB	RUSTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH CARBURETTOR CHOKE RETURN SPRING RUSTED AND BROKEN.											3	I			EXPE3I
1998022500002	19980225	00002	NE  	1998	2	25	AU980028         	2	19980115	G	7321		CONNECTOR       								PWA   	PW120 	PW123       		NE  					NR 2 ENG EEC	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 							PCE123271			(AUS) NO2 ENGINE ELECTRONIC ENGINE CONTROL (EEC) CONNECTOR FAULTY. HIGH RESISTANCE BETWEEN PINS R AND Q ON P1.											4	T			E20NE
1998021900098	19980219	00098	WP  	1998	2	19	AU980029         	1	19980107	G	6710	269A9937	TORQUE TUBE     			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					M/R CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COLLECTIVE TORQUE TUBE WORN BY BOOT PNO 269A-4031-19 LOCATED AT REAR OF CABIN.						1	G	7	1 	3O	3	O		4H12    	1E10
1998022500003	19980225	00003	SO  	1998	2	25	AU980030         	1	19980111	G	3232	757225	ROD END         	OZONE       	458826      	EMB   	120   	EMB120      	3260201	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT MLG  DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					3498					(AUS) LH MAIN LANDING GEAR DOOR RETRACTION RAM RODEND BROKEN ALLOWING THE DOOR TO REMAIN CLOSED. RETRACTING LANDING GEAR	 HAD PUSHED THE DOOR INTO THE WHEEL WELL BREAKING THE FORWARD HINGE AND BENDING THE REAR HINGE. THE DOOR ACTUATOR HAD AL	SO BROKEN OFF AT THE UPPER ATTACHMENT POINT DUE TO CONTACT WITH THE DOOR.				2	L	7	2 	4T			RT	A31SO   		5	C	P33EA
1998021900099	19980219	00099	NM  	1998	2	19	AU980032         	1	19980115	G	3233	D25W2520055	ACTUATOR        			ISRAEL	1125  	1125        		NM  										RT MLG	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 					IL020					(AUS) RH MAIN LANDING GEAR ACTUATOR LEAKING FROM VENT HOLES. SUSPECT INTERNAL SEAL FAILURE.						2	L	7	2 	4F			RT	A16NM
1998021900100	19980219	00100	NM  	1998	2	19	AU980033         	1	19980120	G	3233	25W316975003	PIN             			ISRAEL	1125  	1125        		NM  										RT MLG ACTUATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR ACTUATOR UPPER ATTACHMENT PIN FAILED AT SPLIT PIN HOLE ON THE DOOR ROD PIVOT SPIGOT. AREA OF 	FAILURE APPEARS TO HAVE BEEN CRACKED FOR SOME TIME WITH EVIDENCE OF CORROSION.					2	L	7	2 	4F			RT	A16NM
1998021900101	19980219	00101	CE  	1998	2	19	AU980034         	1	19980116	G	2750	16612	SWITCH          			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	TE FLAP CONTROL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SWITCH FAULTY. FLAP SWITCH INTERNAL SPRING FAILS TO RETURN SWITCH TO NEUTRAL POSITION.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998021900102	19980219	00102	SO  	1998	2	19	AU980035         	2	19980119	G	8530	646680CP	CYLINDER        	CONT        		CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	NR 2 ROCKER	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 			330  				459007			(AUS) NO2 CYLINDER ROCKER SHAFT BOSS FAILED. CRACK HAD EXISTED FOR SOME TIME BEFORE FAILURE.						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA
1998021900103	19980219	00103	EA  	1998	2	19	AU980036         	2	19980115	G	8520	L2185748A	CRANKCASE       	LYC         							LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	HOLED           	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					L2185748A		L2185748A			(AUS) ENGINE FAULTY. THE FOLLOWING DEFECTS WERE FOUND DURING BULK STRIP:- 1. CRANKSHAFT CRACKED 2. CAMSHAFT LOBES DAMAGE	D 3. CRANKCASE HOLED. 4. CONNECTING RODS (6OFF) BADLY SCORED. 5. OIL PUMP BODY BADLY SCORED										3	O			1E4
1998021900104	19980219	00104	SO  	1998	2	19	AU980037         	2	19980119	G	8520		CRANKCASE       	CONT        		CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3AF34C	3AF34C74    	GL  	NR 5 CYL STUD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							1803			(AUS) CRANKCASE CRACKED IN AREA OF NO5 CYLINDER STUD. CRACK LENGTH APPROXIMATELY 30MM (1.18IN). INCORRECT NUT ALSO FOUND	 ON STUD.					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P22EA
1998021900105	19980219	00105	EU  	1998	2	19	AU980038         	1	19980114	G	2800		FUEL SYSTEM     			MUDRY 	10    	CAP10B      		EU  	LYC   	O360  	AEIO360B2F  	41514	EA  	HOFMAN	HO29	HO29HM180   	EU  	ENG  FUEL SY	MALFUNCTION     	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 							L2597551A	77166D		(AUS) DURING TRAINING CIRCUITS ON DOWNWIND TURN, POWER WAS REDUCED FROM FULL SETTING TO 2000RPM AND THE ENGINE SUFFERED 	A POWER LOSS AND WOUND DOWN TO 800RPM. SUSPECT FUEL MANAGEMENT.					1	L	7	1 	3O	3	O		A36EU   	1E10	5	N	P3EU
1998021900106	19980219	00106	EU  	1998	2	19	AU980039         	1	19980107	G	3213	NB40C075	FITTING         			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) OLEO ASSEMBLY TO LANDING GEAR LEG ATTACHMENT FITTING HAD BOTH FLANGES BROKEN OFF ALLOWING THE WHEELS TO PIVOT THRO	UGH 360 DEGREES.					1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920
1998022500004	19980225	00004		1998	2	25	AU980040         	4	19980121	G	3425	4066300901	SYMBOL GENERATOR			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					INTEGRATED FLT.	CONTAMINATED    	W				K				NONE                    				I			FLT. ATTITUDE INST.       			CL	CLIMB          	1			AU	S 										(AUS) LH SYMBOL GENERATOR FAULTY DUE TO WATER CONTAMINATION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998021900107	19980219	00107	NM  	1998	2	19	AU980041         	1	19980114	G	5312	651630084	BULKHEAD        			BOEING	737   	737376      		NM  										FWD PRESSURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED						2	L	7	2 	4F			RT	A16WE
1998022500005	19980225	00005	EU  	1998	2	25	AU980042         	1	19980107	G	3233	002001519	BEARING         			AIRBUS	320   	A320212     		EU  										RT MLG ACT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR RETRACTION ACTUATOR ROD END BEARING BALL CRACKED IN SEVERAL PLACES. FOUND DURING INSPECTION I	AW ER A32-32-10-52.					2	L	7	2 	4F			RT	A28NM
1998021900108	19980219	00108	CE  	1998	2	19	AU980043         	1	19980101	G	3297		WIRE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT MLG DWNLOCK	BROKEN          	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		DE	DESCENT        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK SWITCH WIRE BROKEN.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA
1998021900109	19980219	00109	CE  	1998	2	19	AU980044         	1	19980114	G	3230	1048200503	ARM             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	NLG RETRACT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR RETRACT/EXTEND ARM CRACKED IN AREA WHERE THE ARM JOINS THE INPUT DRIVE BOSS.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998021900110	19980219	00110	NM  	1998	2	19	AU980045         	1	19980112	G	2761	654494710	HOUSING         	BOEING      	65448517    	BOEING	737   	73733A      	1384673	NM  										LT INB SPOILER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					5007ANSETTSN					(AUS) LH INBOARD GROUND SPOILER INBOARD ACTUATOR PIVOT BEARING LUG BROKEN. CRACK ORIGINATES FROM CORROSION PITTING IN TH	E PIVOT BEARING BORE.					2	L	7	2 	4F			RT	A16WE
1998021900111	19980219	00111	EU  	1998	2	19	AU980046         	2	19980109	G	8520	KR012013	CONNECTING ROD  	IVCHENKO    		YAKLEV	YAK   	YAK52       	9830220	GL  	VEDENY		M14P        		EU  					ENG MASTER	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 					KR012013		KR012013			(AUS) ENGINE MASTER CONNECTING ROD FAILED.						1	L	7	1 	3R			RT	EXPA1L71	USSR
1998021900112	19980219	00112	SO  	1998	2	19	AU980047         	2	19980120	G	8520	270675R	CRANKCASE       	CONT        							CONT  	O520  	IO520M      	17032	SO  					OIL FILL TUBE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					270675R		270675R			(AUS) CRANKCASE CRACKED AROUND OIL FILLER TUBE LOCATING HOLE. CAMSHAF TLOBE WORN.											3	O			E5CE
1998021900113	19980219	00113	SW  	1998	2	19	AU980048         	1	19980127	G	2731	2719008001	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ELEVATOR TAB CON	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 			845  		77					(AUS) PITCH TRIM ACTUATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998021900114	19980219	00114	NM  	1998	2	19	AU980049         	1	19980122	G	3260	864202	PROXIMITY SENSOR			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LT MLG POSITION	FAILED          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) LH LANDING GEAR OUTBOARD PROXIMITY SENSOR FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998021900115	19980219	00115	EU  	1998	2	19	AU980050         	1	19980101	G	7714	3022374	SEAL            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  	HARTZL	HCB5M	HCB5MP3     	GL  	LT ENG TACH	FAILED          	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CR	CRUISE         	1			AU	S 							PCE97080			(AUS) LH ENGINE GAS GENERATOR TACHO GENERATOR SHAFT SEAL FAILED.						2	H	7	2 	4T	4	T		A41EU   	E4EA	6	C	P44GL
1998021900116	19980219	00116	SW  	1998	2	19	AU980051         	1	19980114	G	5347		SEAT TRACK      			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	PILOT SEAT	FOD             	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) PILOTS SEAT STOPS DISENGAGED AND SEAT SLID BACK.  PILOT CHECKED SEAT WAS PROPERLY ENGAGED AND COMMENCED TAKEOFF. A	T APPROXIMATELY 60FT THE STOPS DISENGAGED AND THE SEAT SLID BACK AGAIN CAUSING THE PILOT TO LOSE CONTROL.  THE AIRCRAFT 	WAS DAMAGED ON LANDING.  INVESTIGATION FOUND THE SEAT TRACKS TO BE SERVICEABLE.  A SMALLROCK WAS FOUND IN THE SEAT TRACK	 HOLE PREVENTING THE LOCKING PIN FROM FULLY ENGAGING AND IS CONSIDERED TO BE THE CAUSE OF THE PROBLEM.			1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA
1998021900117	19980219	00117	NM  	1998	2	19	AU980052         	1	19980122	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										RT WS 230	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT SPOILER CABLES (3OFF) LOCATED IN RH WING ADJACENT TO STN 230 CONTAINED BROKEN STRANDS. FOUND DURING INSPECT	ION IAW SPECIAL INSPECTION B737/3/97A.					2	L	7	2 	4F			RT	A16WE
1998021900118	19980219	00118	SW  	1998	2	19	AU980053         	1	19980127	G	3213	2751544001	TORQUE LINK     			FRCHLD	SA227 	SA227CC     		SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	RT LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR UPPER TORQUE LINKS CRACKED IN AREA OF THE CENTRE PIVOT LUGS.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998022500006	19980225	00006	CE  	1998	2	25	AU980054         	1	19980114	G	6120		CONTROL CABLE   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LT PROPELLER	LOOSE           	W				O				OTHER                   				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) LT PROPELLER REVERSING LEVER CABLE LOOSE ON INNER WIRE AND BALL END.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
1998021900119	19980219	00119	NM  	1998	2	19	AU980055         	1	19980115	G	2510	3A0900022012	SEAT            			BOEING	737   	737376      		NM  										1ST OFFICER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					7703					(AUS) FIRST OFFICERS SEAT LOCKING SYSTEM FAULTY.						2	L	7	2 	4F			RT	A16WE
1998021900120	19980219	00120	CE  	1998	2	19	AU980056         	1	19980129	G	2810	41423	FUEL CELL       			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	FUEL STORAGE	WRONG SIZE      	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			AU	S 										(AUS) NEW FUEL CELL IS INCORRECT SIZE. WHEN FITTED THE FUEL CELL HAS LARGE CREASES IN UPPER OUTBOARD FORWARD CORNER. FUE	L CELL PNO 4142-3 REPLACES CELL PNO 4026102-3. CELL MANUFACTURED BY FFC MANUFACTURING MEMPHIS TENNESSEE USA. SERIAL NUMB	ER CR 1135. DATE OF MANUFACTURE 10/97.				1	L	7	2 	3O				A7CE    		5	C	P22EA
1998021900121	19980219	00121	NM  	1998	2	19	AU980057         	1	19980120	G	3240	65C268093103	PIPE            			BOEING	737   	737376      		NM  										LT INB BRAKE	WORN            	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) LH INBOARD BRAKE PRESSURE LINE WORN THROUGH DUE TO CONTACT WITH THE DOWNLOCK BUNGEE SPRINGS WHEN THE LANDING GEAR 	WAS RETRACTED. LOSS OF SKYDROL HYDRAULIC FLUID.					2	L	7	2 	4F			RT	A16WE
1998021900122	19980219	00122	SO  	1998	2	19	AU980058         	1	19980128	G	7722	3027629	BUS BAR         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT ENG T5	FAILED          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 							PCE56751			(AUS) RH ENGINE T5 BUS BAR LUG BROKEN OFF.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
1998021900123	19980219	00123	NE  	1998	2	19	AU980059         	2	19980116	G	7321	722R17107R	SENSOR          								PWA   	PWA120	PW125B      		NE  					RT ENG T1-8	FAULTY          	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							124033			(AUS) RH ENGINE T1-8 SENSOR PROBE FAULTY.											4	T			E20NE
1998021900124	19980219	00124	WP  	1998	2	19	AU980060         	2	19980112	G	7250	310160310	BLADE           	GARRTT      		SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	1ST STAGE TURB	FAILED          	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 			7313 		P44406C		P44406C	DR1DRG231281		(AUS) FIRST STAGE TURBINE BLADES (3OFF) FAILED AT APPROXIMATELY MID SPAN. SEVERE DOWNSTREAM FOD TO SECOND AND THIRD STAG	E TURBINE ASSEMBLIES.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
1998032600682	19980326	00682	CE  	1998	3	26	AU980061         	1	19980119	G	5730	58530158	COVER           	BEECH       	585301565   	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	WING SPAR	SEPARATED       	W				K				NONE                    				O	E		OTHER                     	VIBRATION/BUFFET          		TO	TAKEOFF        	1			AU	S 										(AUS) LH SPAR COVER SEPARATED AND JAMMED BETWEEN LANDING GEAR MICROSWITCHES.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998032600683	19980326	00683	NM  	1998	3	26	AU980062         	1	19980113	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										LT- RT SPOILER	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH WING SPOILER CABLES FRAYED. CABLES AFFECTED, PNO WSB1-4 AND PNO WSB2-4 IN RH WING AND PNO WSB2-3 AND PNO	 WSB1-3 IN LH WING.					2	L	7	2 	4F			RT	A16WE
1998032600684	19980326	00684	NM  	1998	3	26	AU980063         	1	19980112	G	5330		SKIN            			BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					BS 485	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN AND STRINGER 31R LOCATED AT STN 485 DAMAGED BY FORK LIFT DURING LOADING OF FORWARD CARGO HOLD.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998032600685	19980326	00685		1998	3	26	AU980064         	4	19980122	G	2562		BATTERY         		E01         	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	EMERGENCY LOCATO	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								100124		(AUS) ELT BATTERIES LEAKING. FOUND DURING BATTERY CHANGE.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998032600686	19980326	00686	SW  	1998	3	26	AU980065         	1	19980107	G	2742	2743062913	FITTING         	SWRNGN      	ACTUATOR    	FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HORIZ STAB ACT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					215					(AUS) HORIZONTAL STABILISER PITCH TRIM ACTUATOR FITTING CRACKED.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998041700271	19980417	00271	EU  	1998	4	17	AU980066         	1	19980130	G	3244		TIRE            			REIMS 	406   	F406        		EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TIRE CONTAINED FLAT SPOT. FOUND DURING INSPECTION FOLLOWING ABORTED TAKEOFF DUE TO BIRD STRIKE AVOIDANCE.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
1998032600687	19980326	00687	EU  	1998	3	26	AU980067         	1	19980120	G	2910		O-RING          			BAC   	146   	AVRO146RJ70A	1500095	EU  										HYD GREEN SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) LH SPOILER RESTRICTOR FITTING `O' RING SEAL FAILED. LOSS OF GREEN SYSTEM HYDRAULIC FLUID.						2	H	7	4 	4F			RT	A49EU
1998032600688	19980326	00688	EU  	1998	3	26	AU980068         	1	19980130	G	3297	F8912001401	WIRE            			FOKKER	F27   	F27MK50     	       	EU  										PARKING BRAKE	INCORRECT       	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) PARK BRAKE ELECTRICAL WIRING INCORRECTLY CONNECTED DURING INCORPORATION OF SB F50-32-018. PERSONNEL/MAINTENANCE ER	ROR.					2	H	7	2 	4T			RT	A817
1998032600689	19980326	00689	CE  	1998	3	26	AU980069         	1	19980122	G	2910	AE1003757G0310	HOSE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HYDRAULIC MAIN	DETERIORATED    	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC PRESSURE HOSE LOCATED BETWEEN RH HYDRAULIC PUMP AND FIREWALL DAMAGED AND LEAKING. LANDING GEAR WOULD NOT	 EXTEND AND AIRCRAFT LANDED WITH GEAR UP. INVESTIGATION FOUND THAT THE HOSE FAILED DUE TO EXPOSURE TO HEAT WITH THE FIRE	 SLEEVING AND THE OUTER HOSE CASE BURNED THROUGH DUE TO POSITIONING ON THE RH ENGINE EXHAUST PIPE STAINLESS STEEL SHROUD	 WHICH WAS TOUCHING THE EXHAUST PIPE.			1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998032600690	19980326	00690		1998	3	26	AU980070         	4	19980105	G	2565	5A26441	RESERVOIR       		7A1323107   	BOEING	747   	747438      	       	NM  										ESCAPE SLIDE	MISMANUFACTURED 	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					G564					(AUS) UPPER DECK ESCAPE SLIDE UPPER TUBE INFLATION BOTTLE INCORRECTLY INSTALLED RESULTING IN FLATTENED DISCHARGE LINES. 	FOUND DURING WORKSHOP INSPECTION FOLLOWING REMOVAL FROM AIRCRAFT.					2	L	7	4 	4F			RT	A20WE
1998032600691	19980326	00691	EU  	1998	3	26	AU980071         	1	19980128	G	5711		WEB             			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING SPAR WEB CRACKED BEYOND LIMITS.						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920
1998032600692	19980326	00692	EU  	1998	3	26	AU980072         	1	19980129	G	5711		WEB             			BNORM 	BN2   	BN2A26      	1520226	EU  	LYC   	O540  	O540E4C5    	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	RT WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH SPAR WEBS CRACKED BEYOND LIMITS.						1	H	7	2 	3O	3	O		A17EU   	E295	5	C	P920
1998032600693	19980326	00693	NM  	1998	3	26	AU980073         	1	19980103	G	2421	AM739515B	GENERATOR       			BOEING	767   	767338      		NM  										LT IDG	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			AU	S 					F1316					(AUS) LH INTEGRATED DRIVE GENERATOR (IDG) FAILED.						2	L	7	2 	4F			RT	A1NM
1998032600694	19980326	00694	EU  	1998	3	26	AU980074         	1	19980107	G	3297		WIRE            			BAG   	JETSTM	JETSTM3101  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LANDING GEAR RET	BROKEN          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR WIRING CONNECTED TO THE STEERING ISOLATION VALVE PLUG PULLED OUT AND SHORTED OUT.						2	L	7	2 	4T			RT	A21EU   		6	C	P61GL
1998032600695	19980326	00695	EA  	1998	3	26	AU980075         	2	19980203	G	7322	78356	WASHER          	FACET       	MA45        	PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8       	EA  	FUEL CARB	WORN            	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 					CP0229		L2242936A			(AUS) CARBURETTOR MIXTURE SHAFT RETAINING RING WORN AND LOOSE ALLOWING THE MIXTURE SHAFT TO MOVE FROM ITS NORMAL POSITIO	N. THIS CAUSED A RICH CUT WHEN THE ENGINE WAS BROUGHT BACK TO IDLE FOR LANDING.					1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA
1998032600696	19980326	00696	NM  	1998	3	26	AU980076         	1	19980118	G	2611		TUBE            			BOEING	757   	757200      	1384950	NM  										SMOKE DETECTION	CONTAMINATED    	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) CARGO BAY SMOKE DETECTOR SAMPLING TUBES CONTAMINATED WITH DUST CAUSING FALSE WARNINGS.						2	L	7	2 	4F			RT	A2NM
1998032600697	19980326	00697	EA  	1998	3	26	AU980077         	2	19980122	G	7532	310334701	DIAPHRAGM       	PWA         	BLEEDVALVE  						PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COMPRESSOR BLEED	FAILED          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			295  		4P791		PCE41727			(AUS) ENGINE WOULD ONLY PRODUCE 40PSI TORQUE DURING TAKEOFF. GROUND INVESTIGATION FOUND THAT THE COMPRESSOR BLEED VALVE 	DIAPHRAGM WAS HOLED.										4	T			E4EA	6	C	P15EA
1998032600698	19980326	00698	SO  	1998	3	26	AU980078         	1	19980120	G	2752	3203001007	ACTUATOR        			EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118A      		NE  					TE FLAP ACTUATOR	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					0046					(AUS) RH OUTBOARD FLAP ACTUATOR FAULTY. INVESTIGATION FOUND THAT THE ACTUATOR WAS NOT KEEPING THE FLAP WITHIN THE TOLERA	NCE OF DISAGREEMENT WITH THE OTHER FLAPS.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998032600699	19980326	00699	EU  	1998	3	26	AU980079         	1	19980103	G	2421	728471B	IDG             			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AC GENERATOR-ALT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					0594		LFO5961			(AUS) NO1 ENGINE INTEGRATED DRIVE GENERATOR (IDG) LEAKING OIL FROM SIGHT GLASS.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998032600700	19980326	00700	NM  	1998	3	26	AU980080         	1	19980131	G	3150		WARNING LIGHT   			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					CENTRAL WARNING	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) MASTER CAUTION LIGHT ILLUMINATED DURING TAKEOFF. INDIVIDUAL CAUTION LIGHT COULD NOT BE IDENTIFIED AND ALL SYSTEMS 	CHECKED OUT SERVICEABLE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998032600701	19980326	00701	SW  	1998	3	26	AU980081         	1	19980103	G	5711		STRAP           			GULSTM	500   	500B        	0141106	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK4     	GL  	WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH WING UPPER SPAR STRAP CRACKED. RH WING LOWER SPAR STRAP ALSO CRACKED. FOUND DURING INSPECTION IAW SB 223.						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA
1998032600702	19980326	00702	SO  	1998	3	26	AU980082         	1	19980115	G	2842	4064802030405	TRANSMITTER     			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL QUANTITY	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) FIVE OUT OF EIGHT FUEL QUANTITY TRANSMITTERS WERE FAULTY WITH RESISTANCE VALUES OUT OF LIMITS.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998032600703	19980326	00703	SW  	1998	3	26	AU980083         	1	19980129	G	2752	2736053003	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	TE FLAP ACTUATOR	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			AU	S 			2417 		170					(AUS) RH WING FLAP ACTUATOR HOUSING CRACKED CIRCUMFERENTIALLY AND LEAKING HYDRAULIC FLUID. CRACK IS LOCATED APPROXIMATEL	Y 5.5MM (0.218IN) FROM THE BASE OF THE ACTUATOR CYLINDER. CRACK LENGTH APPROXIMATELY 32MM (1.25IN).					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998032600704	19980326	00704	SO  	1998	3	26	AU980084         	1	19980105	G	5510	42235	HINGE           	PIPER       	40155       	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER OUTBOARD HINGE BRACKETS CRACKED.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600705	19980326	00705	SO  	1998	3	26	AU980085         	1	19980123	G	5523	4042010	BRACKET         	PIPER       	4042009     	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	ELEV TAB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB HINGE BRACKETS PNO 4042-010, PNO 4042-009 AND PNO 4042-008 CRACKED.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600706	19980326	00706	EU  	1998	3	26	AU980086         	1	19980124	G	3246	50092371	WHEEL           			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R320	R3204123F1  	NE  	BEARING HOUSING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1285 		941820					(AUS) WHEEL INBOARD BEARING HOUSING BROKEN UP. SECONDARY DAMAGE TO THE BRAKE UNIT. WHEEL HAD BEEN REPAIRED 2586 LANDINGS	 PREVIOUSLY BY THE INSTALLATION OF A BUSHING BETWEEN THE WHEEL BEARING OUTER CUP AND THE BEARING HOUSING (REPAIR SCHEME 	R2 CMM32-41-16).				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P5NE
1998032600707	19980326	00707	EU  	1998	3	26	AU980087         	1	19980115	G	2720		TENSIONER       			FOKKER	F27   	F27MK50     		EU  										RUDDER CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER/ELEVATOR CABLE TENSION REGULATOR LH SUPPORT BOX BEAM CRACKED IN TWO PLACES. CRACK LENGTHS 25MM (0.984IN)						2	H	7	2 	4T			RT	A817
1998032600708	19980326	00708	EU  	1998	3	26	AU980088         	1	19980203	G	2912	QAO6881	FILTER          			FOKKER	F27   	F27MK50     		EU  										HYD SYS	FAULTY          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) HYDRAULIC SYSTEM RETURN FILTER FAULTY.						2	H	7	2 	4T			RT	A817
1998032600709	19980326	00709	SO  	1998	3	26	AU980089         	1	19980123	G	3260	MS272402	SWITCH          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LANDING GEAR POS	FAILED          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWN MICROSWITCH FAULTY.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
1998032600710	19980326	00710	EU  	1998	3	26	AU980090         	1	19980104	G	6123	4049AA	PUMP            			JETAIR	JETSTM	JETSTM4101  	1500501	EU  	GARRTT	TPE331	TPE33114GR  	01514	NE  	MCAULY	5JFR	B5JFR36C1101	GL  	PROP FEATHER	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					64708					(AUS) PROPELLER UNFEATHERING PUMP FAILED.						2	L	7	2 	4T	4	T	RT	A41NM   	E18NE	5	C	P15WE
1998032600711	19980326	00711	CE  	1998	3	26	AU980091         	1	19980130	G	2910	520010789	PIPE            	CESSNA      	402C        	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HYD MAIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4020508					(AUS) RH MAIN LANDING GEAR RETRACTION SYSTEM HYDRAULIC PIPE LOCATED IN AREA BELOW THE RH FLOOR CONTAINED PITTING CORROSI	ON. SUSPECT DUETO CONTACT WITH DUCTING INSULATION.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998032600712	19980326	00712	EU  	1998	3	26	AU980092         	1	19980125	G	2750	A2753301620000	LINK            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					TE FLAP CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH INBOARD FLAP BEVEL GEARBOX TO ATTACHMENT BRACKET LINK BROKEN AT ATTACHMENT HOLE. CAUSED BY EXFOLIATION CORROSIO	N.					2	L	7	2 	4F	4	F		A35EU   	E23EA
1998032600713	19980326	00713	NM  	1998	3	26	AU980093         	1	19980131	G	2910	312A101028	PIPE            			BOEING	737   	737476      		NM  										HYD MAIN	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED IN NO1 PYLON CHAFED AND LEAKING. PIPE HAD BEEN CHAFING ON A PIPE PIN WHICH WAS PART OF THE 	ENGINE CHANGE EQUIPMENT AND WHICH WAS WEDGED BELOW THE PIPE. FOD. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4F			RT	A16WE
1998032600714	19980326	00714	NM  	1998	3	26	AU980094         	1	19980130	G	5312	651630084	BULKHEAD        			BOEING	737   	737476      		NM  										FWD PRESS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CONTAINED THREE CRACKS IN THE WEBS ANDTWO CRACKS IN THE CHORDS. ALSO FOUND A CRACKED BRA	CKET SUPPORTING THE HORIZONTAL INTERCOSTAL AT WL207 AND LBL17.					2	L	7	2 	4F			RT	A16WE
1998032600716	19980326	00716	SW  	1998	3	26	AU980096         	1	19980205	G	2730	REP4MR	ROD END         		REP4ML6     	FRCHLD	SA227 	SA227DC     	3377521	SW  										ELEVATOR CONTROL	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL ROD RODEND RETAINER/DUST COVERS DAMAGED. FOUND DURING INSPECTION IAW SB CC7-27-010.						2	L	7	2 	4T			RT	A18SW
1998032600717	19980326	00717	WP  	1998	3	26	AU980097         	1	19980117	G	6220	369D2100411	FAIRING         			HUGHES	369   	369E        	4470707	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR HEAD	SEPARATED       	W				K				NONE                    				F	D		FLT CONT AFFECTED         	INFLIGHT SEPARATION       		CR	CRUISE         	1			AU	S 										(AUS) MAIN ROTOR HEAD FAIRING (CHINAMANS HAT) SEPARATED FROM AIRCRAFT.SUSPECT FAIRING DEVELOPED A CRACK ALLOWING THE FAI	RING TO FLEX AND LOOSEN THE ATTACHMENT SCREWS.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998032600718	19980326	00718	GL  	1998	3	26	AU980098         	1	19980120	G	3210		LANDING GEAR    			AMTR  	MAXAIR	XP503       	9570746	GL  	AMTR  	582   	582         		GL  					MAIN LANDING GEA	DAMAGED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT HIT FENCE WHEN CONTROL LOST DURING LANDING. DAMAGE CAUSED TO LANDING GEAR, NOSE POD AND LOWER FUEL TANK. 	THIS DEFECT WAS RECEIVED FROM THE AUF AND IS FOR INFORMATION ONLY.					1	H	7	1 	3I	3	I	NT	EXPA1H71	EXP31
1998032600719	19980326	00719	SO  	1998	3	26	AU980099         	1	19980205	G	3222	40273000	TRUNNION        			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NOSE GEAR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION DEFORMED IN AREA OF NOSE WHEEL STEERING LOCK/STOP. CRACKING STARTING TO DEVELOP ON THE 	INSIDE EDGE OF THE STOP.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600720	19980326	00720	SO  	1998	3	26	AU980100         	1	19980205	G	3222	4533303	PISTON          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NLG OLEO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR OLEO PISTON CHROME PLATING WORN. SIZE OF WORN AREA APPROXIMATELY 50.8MM (2IN) IN DIAMETER.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600721	19980326	00721	SO  	1998	3	26	AU980101         	1	19980205	G	3252	2170105	DAMPER          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	SHIMMY DAMPER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR SHIMMY DAMPER PISTON CORRODED AND CHROME PLATING RUSTED OFF. SHIMMY DAMPER ALSO LOW ON OIL.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600722	19980326	00722	SO  	1998	3	26	AU980102         	1	19980205	G	3233	757499	ACTUATOR        	WIEBEL      	21151       	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR ACTUATOR SHAFT BROKEN. RAM ADJUSTMENT STOP HAS BEEN ILLEGALLY MODIFIED WITH THE PLAIN NUT REPLAC	ED WITH A METALLOCKNUT AND THE REMAINING LOCKING NUT NOT LOCKWIRED. UNAPPROVED PART. PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O			 	A20SO   		5	C	P33EA
1998032600723	19980326	00723	SO  	1998	3	26	AU980103         	1	19980205	G	2731	17088000	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR TAB CON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM ACTUATOR WORN. ILLEGAL METAL SHIM INSTALLED BETWEEN THE ACTUATOR DRUM AND THE DRUM HOUSING. PERSONNE	L/MAINTENANCE ERROR. UNAPPROVED PART.					1	L	7	2 	3O			 	A20SO   		5	C	P33EA
1998032600724	19980326	00724	SO  	1998	3	26	AU980104         	1	19980205	G	5753	4018543	FLAP            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	TE FLAP STRUCTUR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH FLAP LEADING EDGE SKIN SEPARATED OVER A LENGTH OF 203.2MM(8IN) IN AREA BEHIND ENGINE DUE TO CORROSION AND RIVET	 FAILURE.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600725	19980326	00725	SO  	1998	3	26	AU980105         	1	19980205	G	5320	43179001	FRAME           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RUD TORQ TUBE MT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER PEDAL TORQUE TUBE CENTRE MOUNT SEPARATED FROM THE CENTRE CONSOLE ASSEMBLY.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600726	19980326	00726	SO  	1998	3	26	AU980106         	1	19980205	G	3210		LANDING GEAR    			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH, RH AND NOSE LANDING GEAR TRUNNIONS, LINKS, ROD AND ACTUATOR BEARINGS AND BUSHINGS WORN BEYOND LIMITS. ALL LAND	ING GEARS HAVE EXCESSIVE WEAR AND PLAY.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600727	19980326	00727	SO  	1998	3	26	AU980107         	1	19980205	G	5710	454490809	FRAME           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT & RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING ARCH FRAMES CONTAIN NUMEROUS CRACKS. LONGEST CRACK IS MORE THAN 127MM (5IN) IN LENGTH. CAUSED BY CO	NTACT WITH BRAKE CYLINDERS.					1	L	7	2 	3O			 	A20SO   		5	C	P33EA
1998032600728	19980326	00728	SO  	1998	3	26	AU980108         	1	19980205	G	5311	4105008	FRAME           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	DOOR SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR HINGE SUPPORT FRAME FAILED CAUSING THE DOOR SILL AND FLOOR SKIN TO CRACK. SUSPECT CAUSED BY ILLEGAL USE	 OF CHAINS FORTHE DOOR SUPPORT INSTEAD OF CABLE AND TURNBARREL ASSEMBLY.UNAPPROVED PART.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600729	19980326	00729	SO  	1998	3	26	AU980109         	1	19980205	G	5280	475293031	DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH MAIN LANDING GEAR FLIPPER DOORS EXTENSIVELY CRACKED.DOORS HAD BEEN PREVIOUSLY REPAIRED.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998032600730	19980326	00730	SO  	1998	3	26	AU980110         	1	19980205	G	8120	452939	BLANKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT RT EXH TURBO	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L720561A			(AUS) LH AND RH ENGINE TURBOCHARGER INSULATION BLANKETS DETERIORATED AND BURNT.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998032600731	19980326	00731	SO  	1998	3	26	AU980111         	1	19980205	G	5751	452386	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT RT AIL HINGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH AILERON HINGE BEARINGS WORN.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200574	19980402	00574	SO  	1998	4	2	AU980112         	1	19980205	G	2520	4669523	SPACER          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PASSENGER  SEAT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SEATS INSTALLED WITHOUT SPACERS CAUSING DAMAGE TO THE MOUNTING PLATES AND SEAT LOCK MECHANISM.						1	L	7	2 	3O			 	A20SO   		5	C	P33EA
1998040200575	19980402	00575	SO  	1998	4	2	AU980113         	1	19980205	G	7160	78164	CLIP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE AIR INTAK	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L720561A			(AUS) TURBOCHARGER BYPASS DOOR MAGNETIC CATCH SEPARATED FROM MOUNTING RUBBER. THE CATCH WAS REATTACHED USING `SILASTIC'.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200576	19980402	00576	SO  	1998	4	2	AU980114         	1	19980205	G	2913	2680210	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT ENGINE HYD	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH ENGINE DRIVEN HYDRAULIC PUMP FAULTY.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200577	19980402	00577	EA  	1998	4	2	AU980115         	2	19980205	G	7314	LW13918	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE FUEL	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) RH ENGINE DRIVEN FUEL PUMP LOW PRESSURE OUTPUT.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200578	19980402	00578	EA  	1998	4	2	AU980116         	2	19980205	G	8530	LW13918	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT ENG NR 2-3	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) LH ENGINE NO2 AND NO3 CYLINDER HAD LOW COMPRESSION. NO2 CYLINDER PISTON DAMAGED. AFT THROUGH BOLTS EXCESSIVELY LOO	SE. ENGINE HAD COMPLETED 14 HOURS OPERATION SINCE A BULK STRIP.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200579	19980402	00579	SO  	1998	4	2	AU980117         	1	19980205	G	7160	5491602	DOOR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENG AIR INTAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) ENGINE AIR INTAKE ALTERNATE AIR DOOR RETURN SPRING BROKEN. DOOR HINGE SHAFT AND BUSHES EXCESSIVELY WORN.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200580	19980402	00580	SO  	1998	4	2	AU980118         	1	19980205	G	7120	4000707	MOUNT           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) RH ENGINE MOUNTS BADLY CORRODED.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200581	19980402	00581	SO  	1998	4	2	AU980119         	1	19980205	G	3250	44386000	ARM             			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL STEERING ARM CRACKED.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200582	19980402	00582	SO  	1998	4	2	AU980120         	1	19980205	G	6120	2489417	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	PROP CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT PROPELLER PITCH CONTROL CABLE FAILED.						1	L	7	2 	3O			 	A20SO   		5	C	P33EA
1998040200583	19980402	00583	SO  	1998	4	2	AU980121         	1	19980205	G	7160	5491602	DUCT            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENG AIR INTAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) RH ENGINE ALTERNATE AIR DOOR RETURN SPRING BROKEN. DOOR AXLESHAFT AND BUSHINGS BADLY WORN.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200584	19980402	00584	EA  	1998	4	2	AU980122         	2	19980205	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENG	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) RH ENGINE CONDITION POOR. ALL ELECTRICAL WIRES, IGNITION HARNESSES, HYDRAULIC AND OIL HOSES NOT SECURED. NO GROMME	TS TO PROTECT HOSES AND WIRING WHERE THEY PASS THROUGH BAFFLES. DRAIN LINES AND FITTINGS FOR FUEL PUMP, HYDRAULIC PUMP A	ND WASTE GATE MISSING. CHT PROBE FITTED TO THE INCORRECT CYLINDER.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200585	19980402	00585	EA  	1998	4	2	AU980123         	2	19980205	G	8500		ENGINE          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	LT ENG	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L160568A			(AUS) LH ENGINE CONDITION POOR. ALL ELECTRICAL WIRES, IGNITIONHARNESSES, HYDRAULIC AND OIL HOSES NOT SECURED. NO GROMMET	S FOR PROTECTION OF WIRES AND HOSES WHERE THEY PASS THROUGH BAFFLES.DRAIN LINES FOR FUEL PUMP, HYDRAULIC PUMP AND WASTE 	GATE MISSING. CHT PROBE FITTED TO THE INCORRECT CYLINDER.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200586	19980402	00586	SO  	1998	4	2	AU980124         	1	19980205	G	5520	452386	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT & RT ELEV	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH AND RH ELEVATOR HINGE BEARINGS WORN.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200587	19980402	00587	SO  	1998	4	2	AU980125         	1	19980205	G	5540	452386	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RUDDER HINGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER HINGE BEARINGS WORN.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998041500003	19980415	00003	WP  	1998	4	15	AU980126         	2	19980204	G	7210	M274263144C	CIRCLIP         	GARRTT      	COUPLING    	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENG RED BOX	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 					LOT3308		P70182			(AUS) LH ENGINE REDUCTION GEARBOX MAINSHAFT COUPLING ASSEMBLY PNO 3103726-2 CIRCLIP FAILED ALLOWING THE COUPLING TO MOVE	 FORWARD ONTO THE HIGH SPEED PINION GIVING MINIMAL SPLINE CONTACT AND EVENTUAL DECOUPLING OF THE DRIVE.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998040200588	19980402	00588	NE  	1998	4	2	AU980127         	2	19980125	G	7230		ENGINE          	LYC         	LTS101750   	BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENG COMPRESSOR	STALLED         	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AU	S 										(AUS) NO1 ENGINE SUFFERED A COMPRESSOR STALL.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998040200589	19980402	00589	NM  	1998	4	2	AU980128         	1	19980121	G	2810		BONDING         			BOEING	737   	737476      		NM  										AUX FUEL TANK	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AUXILIARY FUEL TANK VAPOUR SHROUD FITTING BONDS OUT OF TOLERANCE. FOUND DURING INSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200590	19980402	00590	NM  	1998	4	2	AU980129         	1	19980121	G	2810		BONDING         			BOEING	737   	737476      		NM  										CENTER FUEL TANK	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE FUEL TANK ATTACHMENT POINTS POORLY BONDED. FOUND DURING INSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200591	19980402	00591	NM  	1998	4	2	AU980130         	1	19980124	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL TANK	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK VAPOUR SHROUD FITTING BONDS OUT OF TOLERANCE. FOUND DURING INSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200592	19980402	00592	NM  	1998	4	2	AU980131         	1	19980124	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE FUEL TANK ATTACHMENT POINTS POORLY BONDED. FOUND DURINGINSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200593	19980402	00593	NM  	1998	4	2	AU980132         	1	19980124	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK VAPOUR SHROUD FITTING BONDS OUT OF TOLERANCE. FOUND DURING INSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200594	19980402	00594	NM  	1998	4	2	AU980133         	1	19980124	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE FUEL TANK ATTACHMENT POINTS POORLY BONDED. FOUND DURINGINSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200595	19980402	00595	NM  	1998	4	2	AU980134         	1	19980129	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK VAPOUR SHROUD FITTING BONDS OUT OF TOLERANCE. FOUND DURING INSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200596	19980402	00596	NM  	1998	4	2	AU980135         	1	19980129	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE FUEL TANK ATTACHMENT POINTS POORLY BONDED. FOUND DURINGINSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200597	19980402	00597	NM  	1998	4	2	AU980136         	1	19980130	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK VAPOUR SHROUD FITTING BONDS OUT OF TOLERANCE. FOUND DURING INSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200598	19980402	00598	NM  	1998	4	2	AU980137         	1	19980130	G	2810		BONDING         			BOEING	737   	737476      		NM  										FUEL STORAGE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTRE FUEL TANK ATTACHMENT POINTS POORLY BONDED. FOUND DURINGINSPECTION IAW EI 734-28-25.						2	L	7	2 	4F			RT	A16WE
1998040200599	19980402	00599	SO  	1998	4	2	AU980138         	2	19980131	G	7322	194593	PLUNGER         	FACET       	CARBURETTOR 	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	CARB ACCEL PUMP	DAMAGED         	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 					B52420067		253110			(AUS) CARBURETTOR ACCELERATOR PUMP PLUNGER LEATHER CAP TORN IN TWO PLACES.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998040200600	19980402	00600	SO  	1998	4	2	AU980139         	2	19980209	G	8500		ENGINE          			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	POWER SECT	VIBRATION       	W				K				NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 							294836R			(AUS) ENGINE VIBRATION FELT THROUGH FLOOR AND RUDDER PEDALS.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA
1998040200601	19980402	00601	SO  	1998	4	2	AU980140         	2	19980130	G	8530	131324	ENGINE          	CONT        	O470        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	EXH VLV GUIDES	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					131324		131324			(AUS) ENGINE EXHAUST VALVE GUIDES BADLY WORN. PISTON AND PISTON RINGS BADLY WORN. PISTON PINS AND CONNECTING ROD BUSHES 	WORN. OIL FILTER ALMOST COMPLETELY BLOCKED WITH CARBON. FUEL STRAINER LEAKING.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200602	19980402	00602	CE  	1998	4	2	AU980141         	1	19980130	G	5510	18256315	STABILIZER      	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	HORIZONTAL STABI	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) HORIZONTAL STABILISER SEVERELY CORRODED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200603	19980402	00603	CE  	1998	4	2	AU980142         	1	19980130	G	5531	18256315	STABILIZER      	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	VERT STAB SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) VERTICAL STABILIZER SEVERELY CORRODED. FORWARD SPAR CORRODEDTHROUGH.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200604	19980402	00604	CE  	1998	4	2	AU980143         	1	19980130	G	5520	18256315	RIVET           	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEVATOR STRUCTU	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) ELEVATOR BALANCE TAB RIVETS LOOSE.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200605	19980402	00605	CE  	1998	4	2	AU980144         	1	19980130	G	5521	18256315	SPAR            	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) ELEVATOR SPAR AND RIB CRACKED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200606	19980402	00606	CE  	1998	4	2	AU980145         	1	19980130	G	2730	18256315	RIVET           	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEV TORQ TUBE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) ELEVATOR TORQUE TUBE RIVETS LOOSE AND WORKING.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200607	19980402	00607	CE  	1998	4	2	AU980146         	1	19980130	G	5342	18256315	FITTING         	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	STAB ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) STABILISER ATTACHMENT FITTING LOCATED IN REAR FUSELAGE CORRODED AND RIVETS MISSING.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200608	19980402	00608	CE  	1998	4	2	AU980147         	1	19980130	G	5330	18256315	RIVET           	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	AFT FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) RIVETS LOCATED IN REAR FUSELAGE HAD THE RIVET HEADS DAMAGED BY BEING SANDEDFLAT.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200609	19980402	00609	CE  	1998	4	2	AU980148         	1	19980130	G	5730	18256315	DOUBLER         	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	WING FLAP BAYS	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) INSPECTION PANEL DOUBLERS LOCATED IN FLAP BAYS CORRODED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200610	19980402	00610	CE  	1998	4	2	AU980149         	1	19980130	G	5711	18256315	SPAR            	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	LT WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) LH WING FORWARD SPAR RIVETS (20OFF) CORRODED AND RIVET HEADS POPPED OFF. LH WING SPAR SEVERELY CORRODED. RH WING F	ORWARD SPAR RIVETS HAD RIVET HEADS POPPED					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200611	19980402	00611	CE  	1998	4	2	AU980150         	1	19980130	G	2810	18256315	FUEL CELL       	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	LT FUEL	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) LH FUEL TANK BLADDER CRACKED AND LEAKING.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200612	19980402	00612	CE  	1998	4	2	AU980151         	1	19980130	G	5320	18256315	ANGLE           	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) FUSELAGE ANGLE BADLY CORRODED IN AREA OF WING STRUT ATTACHMENT.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200613	19980402	00613	CE  	1998	4	2	AU980152         	1	19980130	G	5610	18256315	WINDSHIELD      	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	COCKPIT	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) WINDSCREEN BADLY CRAZED AND OPAQUE.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200614	19980402	00614	CE  	1998	4	2	AU980153         	1	19980130	G	2730	18256315	CONTROL CABLE   	CESSNA      	182H        	CESSNA	182   	182H        	2072718	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEVATOR CONTROL	MISROUTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					18256315					(AUS) ELEVATOR CONTROL CABLE INCORRECTLY ROUTED.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998040200615	19980402	00615	EA  	1998	4	2	AU980154         	2	19980201	G	7414	8442094	MAGNETO         	BENDIX      	D6RN3200    	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENG LT MAG	SHORTED         	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		TO	TAKEOFF        	1			AU	S 					8442094		RL238068A			(AUS) RH ENGINE LH MAGNETO PRIMARY LEAD SHORT CIRCUITED TO MAGNETO CASE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200616	19980402	00616	SO  	1998	4	2	AU980155         	2	19980212	G	8520	22087672D	CRANKSHAFT      	CONT        	IO520D      						CONT  	O520  	IO520D      	17032	SO  					NR 2 MAIN JOURNL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					22087672D		22087672D			(AUS) ENGINE CRANKSHAFT NO2 MAIN BEARING JOURNAL CRACKED. CRANKCASE NO2 MAIN BEARING SADDLES DAMAGED. CAMSHAFT GEAR TEET	H CRACKED. OIL TRANSFER COLLAR BADLY DAMAGED										3	O			E5CE
1998040200617	19980402	00617	NM  	1998	4	2	AU980156         	1	19980205	G	5312	651630084	BULKHEAD        			BOEING	737   	737376      		NM  										FWD PRESSURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FORWARD PRESSURE BULKHEAD CONTAINED FIVE WEB CRACKS ANDTWO CRACKS IN THE LH VERTICAL STIFFENER.						2	L	7	2 	4F			RT	A16WE
1998040200618	19980402	00618	CE  	1998	4	2	AU980157         	1	19980202	G	3242	101800213	BRAKE DISC      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					RT OUTB BRAKE	WORN            	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 			167  							(AUS) RH OUTBOARD BRAKE ROTOR CRACKED. RH OUTBOARD WHEEL CRACKED AT BRAKE DRIVE  LUG.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998040200619	19980402	00619	SO  	1998	4	2	AU980158         	2	19980216	G	8530	G46754	VALVE           	CONT        	O470K       	BEECH 	33    	35C33       	1151408	CE  	CONT  	O470  	IO470K      	17026	SO  	MCAULY	2A36C	2A36C23     	GL  	NR 3 CYL EXH	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					MA		86756K			(AUS) NO1 CYLINDER EXHAUST VALVE LEAKING AND VALVE GUIDE WORN (STILLWITHIN LIMITS). NO3 CYLINDER INLET VALVE LEAKING.						1	L	7	1 	3O	3	O		3A15    	3E1	5	C	P880
1998040200620	19980402	00620	CE  	1998	4	2	AU980159         	1	19980213	G	2824	74D81	VALVE           			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520N   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	FUEL XSFER VALVE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INLET FUEL VALVE ASSEMBLY WORN. VALVE FAILED TEST IAW AD/CESSNA400/100A4 DUE TO WORN VALVE STEM.						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL
1998040200621	19980402	00621		1998	4	2	AU980160         	1	19980213	G	3246	AHA1407	WHEEL           	DUNLOP      	BAE146      															BEAD SEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					KE205					(AUS) WHEEL BEAD SEAT CRACKED. CRACK LENGTH 100MM (4IN). FOUND DURING EDDY CURRENT INSPECTION. WHEEL IS FROM AN INDONESI	AN REGISTERED AIRCRAFT PK-MTA.
1998040200622	19980402	00622	CE  	1998	4	2	AU980161         	1	19980211	G	3230	MS203921C17	PIN             			CESSNA	210   	210L        	2073448	CE  										NLG UPLOCK	SEPARATED       	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR UPLOCK TO UPLOCK ACTUATOR CLEVIS PIN DISENGAGED. AIRCRAFT LANDED WITH NLG RETRACTED CAUSING MINO	R DAMAGE TO THE PROPELLER AND AIRFRAME.					1	H	7	1 	3O				3A21
1998040200623	19980402	00623		1998	4	2	AU980162         	1	19980210	G	7712	310823801	SENSOR          								PWA   	PWA120	PW125B      		NE  					LT ENGINE TORQ	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 							124031			(AUS) LH ENGINE TORQUE SENSOR INTERNAL FAULT.											4	T			E20NE
1998040200624	19980402	00624	CE  	1998	4	2	AU980163         	1	19980211	G	3230	12416345	DOWNLOCK HOOK   			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	LT MLG	STUCK           	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LH MAIN LANDING GEAR DOWNLOCK HOOK STUCK DUE TO LACK OF LUBRICATION.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA
1998040200625	19980402	00625	SO  	1998	4	2	AU980164         	1	19980211	G	2910		HYDRAULIC SYSTEM			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	HYDRAULIC MAIN	LOW QUANTITY    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC FLUID QUANTITY LOW. LANDING GEAR WOULD NOT FULLY EXTEND.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200626	19980402	00626	EU  	1998	4	2	AU980165         	1	19980212	G	5720	4FS7023	BRACKET         			HWKSLY	DH114 	DH1142DA    	2800504	EU  	LYC   	O540  	IO540K1C5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	WING MAIN SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NSN					(AUS) WING MAIN SPAR SUPPORT BRACKET CRACKED.						2	L	7	4 	3I	3	O		A816    	1E4	5	C	P6EA
1998040200627	19980402	00627	SO  	1998	4	2	AU980166         	1	19980203	G	3230	574442	SIDE BRACE      			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT LANDING GEAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH MAIN LANDING GEAR FORWARD SIDE BRACE CRACKED. FOUND DURING INSPECTION IAW AD/PA31/114 AMDT3.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200628	19980402	00628	WP  	1998	4	2	AU980167         	1	19980206	G	6220	269A12903	DAMPER          			HUGHES	269   	269C        	4470504	WP  										MAIN ROTOR HEAD	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR ELASTOMERIC DAMPERS FAULTY. AIRCRAFT HAD SUFFERED A HARD LANDING/SUDDEN STOPPAGE APPROXIMATELY 150 HOUR	S PREVIOUSLY.INSPECTION THEN FOUND NIL DEFECTS BUT SINCE THAT TIME THE AIRCRAFT HAD DEVELOPED A VIBRATION AND AN INSPECT	ION HAD FOUND ONE DAMPER DELAMINATED AND ONE DAMPER OUT OF LIMITS. THE THIRD DAMPER FAILED THE LOAD/STRETCH TEST.				1	G	7	1 	3O				4H12
1998040200629	19980402	00629		1998	4	2	AU980168         	4	19980118	G	3416	AK350	ENCODER         			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	ALTIMETER	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			CR	CRUISE         	1			AU	S 					3521189					(AUS) ALTITUDE ENCODER FAULTY. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA
1998040200630	19980402	00630	CE  	1998	4	2	AU980169         	1	19980218	G	3230		TUBE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LT LANDING GEAR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LH LANDING GEAR DRIVE TUBE CREASED AT INBOARD FITTING.						1	L	7	2 	3O	3	O		3A16    	E5CE
1998040200631	19980402	00631	NM  	1998	4	2	AU980170         	1	19980121	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										DRAG CONTROL SYS	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLIGHT SPOILER CABLES FRAYED. CABLES LOCATED IN THE FOLLOWING POSITIONS:- 1. CABLE PNO BACC2A3A02794EG AT LH 	WSB1-3 2. CABLE PNO BACC2A3A03216FG AT LH WSB2-3 3. CABLE PNO BACC2A3A03051FG AT RH WSB2-4 4. CABLE PNO BACC2A3A02652FG 	AT RH WSB1-3 FOUND DURING SPECIAL INSPECTION  B737-3-97A.				2	L	7	2 	4F			RT	A16WE
1998040200632	19980402	00632	NM  	1998	4	2	AU980171         	1	19980123	G	2760	BACC2C3D03051EG	CONTROL CABLE   			BOEING	737   	737377      	       	NM  										DRAG CONTROL SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLIGHT SPOILER CABLE LOCATED RH SIDE AT WSB2-4 AT WS136 PULLEY WORN BEYOND LIMITS. FOUND DURING SPECIAL INSPE	CTIONB737-3-97A.					2	L	7	2 	4F			RT	A16WE
1998040200633	19980402	00633	NM  	1998	4	2	AU980172         	1	19980115	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										DRAG CONTROL SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT SPOILER CABLES WORN BEYOND LIMITS. CABLES LOCATED IN THE FOLLOWING POSITIONS AT LH WING REAR SPAR STN 210:-	1. CABLE PNO BACC2C3D02428EG AT WSA1-32. CABLE PNO BACC2C3D01853FG AT WSA2-3FOUND DURING SPECIAL INSPECTION MSI-B737-3-9	7A.				2	L	7	2 	4F			RT	A16WE
1998040200634	19980402	00634	NM  	1998	4	2	AU980173         	1	19980211	G	2760		CONTROL CABLE   			BOEING	737   	73733A      	1384673	NM  										DRAG CONTROL SYS	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLIGHT SPOILER CABLES WORN BEYOND LIMITS. CABLES LOCATED ATTHE FOLLOWING POSITIONS IN THE LH WING AT STN230LH	:-1. CABLE PNO BACC2C3D02794EG AT WSB1-32. CABLE PNO BACC2C3D03216FG AT WSB2-33. CABLE PNO BACC2C3D02428EG AT WSA1-34. C	ABLE PNO BACC2C3D01853FG AT WSA2-3 FOUND DURING SPECIAL INSPECTION B737-3-97A.				2	L	7	2 	4F			RT	A16WE
1998040200635	19980402	00635	CE  	1998	4	2	AU980174         	1	19980218	G	2710		AILERON         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					AILERON CONTROL	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL SYSTEM INCORRECTLY RIGGED.						1	L	7	2 	3O	3	O	 	3A16    	E5CE
1998040200636	19980402	00636	CE  	1998	4	2	AU980175         	1	19980218	G	7810		EXHAUST SYSTEM  			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE COLLECTOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EXHAUST ASSEMBLIES (3OFF4) DAMAGED DUE TO SEVERE BULGING.						1	L	7	2 	3O	3	O		3A16    	E5CE
1998040200637	19980402	00637	CE  	1998	4	2	AU980176         	1	19980218	G	7920		HOSE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE OIL SYS	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL ENGINE HOSES TIME EXPIRED. HOSES WERE NOT CHANGED DURING RECENT ENGINE CHANGE.						1	L	7	2 	3O	3	O		3A16    	E5CE
1998040200638	19980402	00638	NM  	1998	4	2	AU980179         	1	19980124	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										DRAG CONTROL SYS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLIGHT SPOILER CABLES FRAYED AT WING STN 230:- 1. CABLE PNO BACC2A3A03216FG LOCATED AT LH WSB2-3 2. CABLE PNO	 BACC2A3A02794EG LOCATED AT LH WSB1-3 3. CABLE PNO BACC2A3A03051FG LOCATED AT RH WSB2-4 FOUND DURING SPECIAL INSPECTION 	IAW B737-3-97A.				2	L	7	2 	4F			RT	A16WE
1998040200639	19980402	00639	NM  	1998	4	2	AU980180         	1	19980116	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										DRAG CONTROL SYS	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLIGHT SPOILER CABLES FRAYED AT WING STN 230 IN THE FOLLOWING LOCATIONS:- 1. CABLE PNO BACC2A3A02794EG LOCATE	D AT LH WSB1-32. CABLE PNO BACC2A3A02625FG LOCATED AT RH WSB1-43. CABLE PNO BACC2A3A03051FG LOCATED AT RH WSB2-4FOUND DU	RING SPECIAL INSPECTION IAW MSI-B737-3-97A.				2	L	7	2 	4F			RT	A16WE
1998040200640	19980402	00640	SW  	1998	4	2	AU980181         	1	19980121	G	3230		LANDING GEAR    			MTSBSI	MU2   	MU2B30      	5780410	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	LANDING GEAR RET	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR FAILED TO RETRACT. SYSTEM WORKED NORMALLY DURING GROUND CHECKS WHEN FOLLOWING RESETTING OF THE EMERGE	NCY EXTENSION SYSTEM. SUSPECT CAUSED BY MOVEMENT OF THE EMERGENCY EXTENSION HANDLE DURING MAINTENANCE.					1	H	7	2 	3T				A2PC    		6	C	P15EA
1998040200641	19980402	00641	EA  	1998	4	2	AU980182         	2	19980212	G	7314	LW15473	PUMP            			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE FUEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1164451A			(AUS) ENGINE FUEL PUMP DRIVE LEVER FAILED ACROSS PIVOT PIN HOLES. LEVER SECTION WITHIN THE PUMP HAS SECONDARY CRACKING A	ND IS SLIGHTLY BOWED OUTWARDS. BROKEN PORTION OF LEVER FOUND IN THE ENGINE SUMP.					1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920
1998040200642	19980402	00642	NM  	1998	4	2	AU980183         	1	19980218	G	3260	864202	SWITCH          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					NLG PROX	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR DRAG BRACE PROXIMITY SWITCH FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998040200643	19980402	00643	SO  	1998	4	2	AU980184         	1	19980211	G	3230	4098301	DOWNLOCK HOOK   			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RT MLG	BINDING         	W				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) RH MAIN LANDING GEAR DOWNLOCK HOOK BINDING.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200644	19980402	00644	CE  	1998	4	2	AU980185         	1	19980217	G	2450	CM358950	SWITCH          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	AC POWER DISTRIB	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			AU	S 										(AUS) NO1 AVIONICS SWITCH/CIRCUIT BREAKER INTERMITTENT FAULT.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998040200645	19980402	00645	EU  	1998	4	2	AU980186         	1	19980218	G	2424	737854D	GCU             			FOKKER	F27   	F27MK50     		EU  										AC REGULATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					0168					(AUS) LH GENERATOR CONTROL UNIT (GCU) FAILED.						2	H	7	2 	4T			RT	A817
1998040200646	19980402	00646	CE  	1998	4	2	AU980187         	1	19980206	G	2750	511523716	GEARBOX         	CESSNA      	402C        	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	TE FLAP CONTROL	FAILED          	W				K				NONE                    				O	F		OTHER                     	FLT CONT AFFECTED         		DE	DESCENT        	1			AU	S 			12546		NSN					(AUS) FLAP GEARBOX IDLER GEAR TEETH SHEARED OFF.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998040200647	19980402	00647	EA  	1998	4	2	AU980188         	2	19980220	G	8530	SL75089STD	PISTON          			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	LO360A1G6   	41514	EA  					RECIP ENG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L24571A			(AUS) PISTON CRACKED.						1	L	7	2 	3O	3	O		A29CE   	1E10
1998040200648	19980402	00648	NE  	1998	4	2	AU980189         	2	19980109	G	7314	216041101	SEAL            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE FUEL PUMP	SCORED          	W				K	E			NONE                    	ENGINE SHUTDOWN         			O	K		OTHER                     	FLUID LOSS                		NR	NOT REPORTED   	1			AU	S 					1069ANSETTSN		LF05877A			(AUS) NO2 ENGINE LOW PRESSURE FUEL PUMP SHAFT CARBON SEAL CONTACT FACE WORN AND SCORED. INTERNAL `O' RING SEAL DAMAGED. 	FUEL PUMP DRIVESHAFT SPLINES EXCESSIVELY WORN. SUSPECT CAUSED BY LUBRICATING GREASE BEING WASHED OUT OF SPLINES BY FUEL 	LEAKING PAST THE SHAFT SEAL.				2	H	7	4 	4F	4	F		A49EU   	E6NE
1998040200649	19980402	00649	CE  	1998	4	2	AU980190         	1	19980212	G	2140	748	PIPE            		8259JR2     	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	HEATING SYSTEM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					748					(AUS) CABIN HEATER FUEL LINE CORRODED AND HOLED ON 90 DEGREE BEND.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998040200650	19980402	00650	EU  	1998	4	2	AU980191         	1	19980213	G	3320	31851A	CONNECTOR       			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	PASSENGER COMPAR	BURNT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN LIGHT CONNECTOR ON LEFT REAR LAMP OVERHEATED. CONNECTING WIRE MELTED AND BURN MARKS ON TRIM.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
1998040200651	19980402	00651		1998	4	2	AU980192         	1	19980222	G	7160	2	HOSE            								ROTAX 	912   	ROTAX912    	55555	EU  					LT & RT ENG INT	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) LH AND RH ENGINE INDUCTION SCAT HOSES FAILED AT CARBURETTOR CONNECTION.											3	I			EXPE3I
1998040200652	19980402	00652	SO  	1998	4	2	AU980193         	1	19980204	G	5312	5269401	BULKHEAD        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE RH FRONT SPAR ATTACHMENT BULKHEAD CRACKED. BULKHEAD, CHANNEL PNO 40603-02 AND REINFORCEMENT PLATE PNO 530	16 WERE REPLACED. FOUND DURING REPAIR OF CRACKED FUSELAGE SKIN.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998040200653	19980402	00653	SO  	1998	4	2	AU980194         	1	19980203	G	3230	402773	SIDE BRACE      			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LANDING GEAR RET	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RH MAIN LANDING GEAR FORWARD SIDE BRACE CRACKED. FOUND DURING INSPECTION IAW AD/PA31/114 AMDT3.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998040200654	19980402	00654	EA  	1998	4	2	AU980195         	2	19980118	G	7250	3012264	COVER           			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TURBINE SECTION	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NO2 BEARING COVER INCORRECTLY SEATED. PERSONNEL/MAINTENANCE ERROR.						1	L	7	2 	4T	4	T	 	A21SO   	E4EA	6	C	P15EA
1998040200655	19980402	00655	SW  	1998	4	2	AU980197         	1	19980217	G	2721	848	BEARING         	AIRIGHT     	1093001     	FRCHLD	SA227 	SA227DC     	3377521	SW  										RUDDER TAB CONTR	SEIZED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					848					(AUS) RUDDER TRIM ACTUATOR SEALED BEARING SEIZED PREVENTING ACTUATOR FROM ROTATING.						2	L	7	2 	4T			RT	A18SW
1998040200656	19980402	00656	SW  	1998	4	2	AU980198         	1	19980225	G	2770	2770066001	PLUNGER         			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	GUST LOCK/DAMPER	FAILED          	W		A		K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) RUDDER GUST LOCK SYSTEM PLUNGER ASSEMBLY INTERNAL SLEEVE SEPARATED AND MIGRATED ALONG THE PLUNGER SPIGOT FOULING T	HE RUDDER BELLCRANK.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998040200657	19980402	00657	EU  	1998	4	2	AU980199         	1	19980205	G	5311	F5101480001	FRAME           			FOKKER	F27   	F27MK50     		EU  										FUSELAGE MAIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME CRACKED IN UPPER CHAMFERED FLANGE RADIUS. CRACK WAS CONFIRMED USING DYE PENETRANT INSPECTION. FOUND	 DURING INSPECTION IAW ER F5-53-10-15/SB F50-53-035.					2	H	7	2 	4T			RT	A817
1998040200658	19980402	00658	EU  	1998	4	2	AU980200         	1	19980219	G	3320	TR9925	POWER UNIT      			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	PASSENGER COMPAR	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LIGHTING POWER UNIT FAULTY.						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL
1998040200659	19980402	00659	EU  	1998	4	2	AU980201         	1	19980219	G	3242	AT53421	BRAKE           			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	LT BRAKE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					141					(AUS) LH BRAKE UNIT JAMMED. INVESTIGATION FOUND THAT THREE BRAKE PADS HAD BROKEN AWAY FROM THE STATOR DUE TO RIVETTING O	F THE PADS TO THE STATOR USING THE INCORRECT TOOLING. PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL
1998040200660	19980402	00660	SW  	1998	4	2	AU980202         	1	19980107	G	6310	206040205005	BEARING         	BELL        	206B3       	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE/TRANSMISS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1979 		BMB10996					(AUS) TRANSMISSION FREE WHEEL ASSEMBLY FORWARD BEARING PNO206-040-205-005 AND SHAFT BEARING SURFACE PNO 206-040-222-005 	FAILED.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998040200661	19980402	00661		1998	4	2	AU980203         	4	19980220	G	2330	508211	AMPLIFIER       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					INTERPHONE & PA	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 					150					(AUS) PUBLIC ADDRESS SYSTEM AMPLIFIER FAILED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998040200662	19980402	00662	SO  	1998	4	2	AU980204         	1	19980216	G	3610	97962641	VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					ENGINE BLEED AIR	FAILED          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					UK					(AUS) RH ENGINE BLEED AIR SHUTOFF VALVE FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998040200663	19980402	00663	CE  	1998	4	2	AU980205         	1	19980216	G	2460	7277220	CIRCUIT BREAKER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	FLAP MOTOR	OPEN            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAP MOTOR CIRCUIT BREAKER INTERMITTENT OPEN CIRCUIT.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998040200664	19980402	00664	NE  	1998	4	2	AU980206         	2	19980217	G	7324	25890	FLOW DIVIDER    			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					RT ENG FUEL	FAULTY          	W				K				NONE                    				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		DE	DESCENT        	1			AU	S 					1106		115476			(AUS) RH ENGINE FUEL FLOW DIVIDER FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998041700272	19980417	00272	EU  	1998	4	17	AU980207         	1	19980211	G	3260		SWITCH          			BAG   	JETSTM	JETSTM3107  	1500215	EU  										NLG	OUT OF ADJUST   	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR MICROSWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4T			RT	BA15CAA
1998041700273	19980417	00273	NM  	1998	4	17	AU980208         	1	19980212	G	2150		AIR CONDITIONING			BOEING	767   	767338      		NM  										LT & RT PACK	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DOUBLE AIR CONDITIONING PACK FAILURE.  LT PACK RETURNED TO NORMAL FOLLOWED BY RT PACK.						2	L	7	2 	4F			RT	A1NM
1998041700274	19980417	00274	SO  	1998	4	17	AU980209         	2	19980218	G	8530		CYLINDER        			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					ROCKER PAD	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			468  				355891			(AUS) RT FRONT CYLINDER HEAD SEPARATED AT ROCKER BOLT DOWN PAD.						1	H	7	1 	3O	3	O		3A17    	E1CE
1998041700275	19980417	00275	SO  	1998	4	17	AU980210         	2	19980222	G	8530		CYLINDER        			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  					RT AFT HEAD	SEPARATED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			478  				355891			(AUS) RT REAR CYLINDER HEAD SEPARATED.						1	H	7	1 	3O	3	O		3A17    	E1CE
1998041700276	19980417	00276	EU  	1998	4	17	AU980211         	1	19980224	G	2432	40765	BATTERY         			STBROS	SD3   	SD360       	8100606	EU  										LT DC SYS	OVERHEATED      	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			771  		9101037					(AUS) LT BATTERY OVERHEATED.  BATTERY WAS STILL TOO HOT TO HANDLE THREE HOURS LATER.						2	H	7	2 	4T				A41EU
1998041700277	19980417	00277	EU  	1998	4	17	AU980213         	1	19980226	G	2916	355A7513300401	RESERVOIR       			AEROSP	AS355 	AS355F1     	8680810	EU  										HYDRAULIC	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			LD	LANDING        	1			AU	S 			6246 							(AUS) HYDRAULIC RESERVOIR CRACKED IN AREA AROUND OUTLET PIPE .						1	G	7	2 	3U				H11EU
1998041700278	19980417	00278	NE  	1998	4	17	AU980214         	2	19980225	G	8530	8408	VALVE GUIDE     			DHAV  	DHC2  	DHC2EVANS   	2801832	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NR 1 CYL EXH	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			269  		8408		8408			(AUS) NR 1 CYLINDER EXHAUST VALVE GUIDE LOOSE.						1	H	7	1 	3O	3	R		A806    	5E1
1998041700279	19980417	00279	EU  	1998	4	17	AU980215         	1	19980108	G	2823		FITTING         			PARTEN	P68   	P68B        		EU  										FUEL SELECTOR	LOOSE           	W				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		CR	CRUISE         	1			AU	S 										(AUS) RT ENGINE SURGED AND FAILED.  LT ENGINE SURGED AND THEN FAILED DURING TAXI FOLLOWING LANDING.  INVESTIGATION FOUND	 THAT THE RT FUEL SELECTOR FITTING WAS LOOSE ALLOWING AIR TO ENTER THE FUEL SYSTEM CAUSING THE RT ENGINE TO STOP.  NO PO	SITIVE CAUSE WAS IDENTIFIED FOR THE STOPPAGE OF THE LT ENGINE.				1	H	7	2 	3O				A31EU
1998041700280	19980417	00280	EU  	1998	4	17	AU980216         	1	19980302	G	2550		CABLE CUTTER    	LUCAS       		AEROSP	SA365 	SA365C      	8680667	EU  										HOIST	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			312  		265					(AUS) HOIST CABLE CUTTER FIRED AND CUT CABLE.  HOIST CONTROL WAS IN THE`OFF' POSITION.						1	G	7	2 	3U				H10EU
1998041700281	19980417	00281	EA  	1998	4	17	AU980217         	2	19980228	G	8520		TAPPET          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 4 CYL CAM	FAILED          	W				K				NONE                    				E	R	K	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	FLUID LOSS                	NR	NOT REPORTED   	1			AU	S 							L655261A			(AUS) LT ENGINE CRANKCASE HOLED IN AREA ADJACENT TO NR 4 CYLINDER INLET CAM FOLLOWER.  CAM FOLLOWER HEAD MISSING.  NR 3 	CYLINDER CAM FOLLOWER ALSO DAMAGED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998041700282	19980417	00282	NM  	1998	4	17	AU980218         	1	19980223	G	3810	288231	COMPRESSOR      			BOEING	737   	737376      		NM  										POTABLE WATER	OVERHEATED      	W				K				NONE                    				O	M		OTHER                     	OVER TEMP                 		IN	INSP/MAINT     	1			AU	S 										(AUS) POTABLE WATER COMPRESSOR OVERHEATED.  SUSPECT COMPRESSOR WAS OPERATING CONTINUOUSLY AND DID NOT CUT OFF.						2	L	7	2 	4F			RT	A16WE
1998041700283	19980417	00283	NM  	1998	4	17	AU980219         	1	19980220	G	5610	66193551	RELEASE PIN     			BOEING	737   	737376      		NM  										NR 2 RT COCKPIT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 RT COCKPIT WINDOW FAILED TO OPEN USING THE EXTERNAL EMERGENCY RELEASE HANDLE.  SUSPECT INCORRECTLY ADJUSTED R	ELEASE MECHANISM.					2	L	7	2 	4F			RT	A16WE
1998041700284	19980417	00284	EA  	1998	4	17	AU980220         	2	19980211	G	7210		GEAR            			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					RT ENG RED GRBOX	FAILED          	W				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 							PCE85444			(AUS) RT ENGINE REDUCTION GEARBOX PLANETARY GEAR FAILURE.  METAL CONTAMINATION OF GEARBOX.  GEARBOX DECOUPLED FROM POWER	 TURBINE.  SECOND STAGE TURBINE SHED ALL BLADES CAUSING INTERNAL DAMAGE.					1	L	7	2 	4T	4	T		A23SO   	E4EA
1998041700285	19980417	00285	CE  	1998	4	17	AU980221         	1	19980223	G	5320	52130409	WEB             		C404        	CESSNA	404   	404CESSNA   	2075901	CE  										NLG SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4040803					(AUS) NOSE LANDING GEAR SUPPORT WEBS P/N 5213040-9 (LT) AND P/N 5213040-10 (RT) CRACKED.						1	L	7	2 	3O				A25CE
1998041700286	19980417	00286	EU  	1998	4	17	AU980222         	1	19980212	G	7931	IPTE55100	TRANSDUCER      			SAAB  	SF340 	SF340A      	7850100	EU  										ENGINE OIL PRESS	FAILED          	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		DE	DESCENT        	1			AU	S 					298884521200					(AUS) RT ENGINE OIL PRESSURE TRANSDUCER FAULTY.						2	L	7	2 	4T			RT	A52EU
1998041700287	19980417	00287	EU  	1998	4	17	AU980223         	2	19980226	G	8500		ENGINE          								RROYCE	GIPSY 	GIPSY30*    	20005	EU  					LT ENG	MALFUNCTION     	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 							66793			(AUS) LT ENGINE FLUCTUATING.  ENGINE BOOST AND OIL PRESSURE DROPPED OFF AND ENGINE RAN ROUGH.											3	I			E294
1998041700288	19980417	00288	NM  	1998	4	17	AU980224         	1	19980218	G	5312	651630084	BULKHEAD        			BOEING	737   	737376      		NM  										FWD PRESSURE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB CRACKED IN SIX PLACES.						2	L	7	2 	4F			RT	A16WE
1998041700289	19980417	00289		1998	4	17	AU980225         	4	19980226	G	2562	4520130	BATTERY         		ELT1104     	PARTEN	P68   	P68B        		EU  										EMERG LOCATOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					52457					(AUS) ELT BATTERY ACID SPILLAGE.  ACID ATE THROUGH THE BATTERY CASE AND BATTERY MOUNTING PLATE.						1	H	7	2 	3O				A31EU
1998041700290	19980417	00290	CE  	1998	4	17	AU980226         	1	19980130	G	2752	101521016	ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  										TE FLAP	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					S0501					(AUS) RT INBOARD FLAP ACTUATOR INCORRECTLY ASSEMBLED WITH THE INTERNAL WORKINGS FROM AN OUTBOARD ACTUATOR WHICH ARE APPR	OXIMATELY 50.8MM (2 INCHES) SHORTER.  THE ACTUATOR WAS BEING INSTALLED FOR THE FIRST TIME FOLLOWING RECEIPT FROM OVERHAU	L IN THE USA.  PERSONNEL/MAINTENANCE ERROR.				1	L	7	2 	4T			 	A24CE
1998041700291	19980417	00291		1998	4	17	AU980227         	1	19980217	G	7920	115D6248	HOSE            																	ENGINE OIL	RUPTURED        	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		CL	CLIMB          	1			AU	S 										(AUS) ENGINE OIL HOSE FAILED.  HOSE HAD DETERIORATED DUE TO HEAT.
1998041700292	19980417	00292	EU  	1998	4	17	AU980228         	1	19980305	G	5270		SWITCH          			BAC   	146   	146200A     	1500266	EU  										DOOR WARNING SYS	OUT OF ADJUST   	W				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) HYDRAULIC BAY DOOR WARNING MICROSWITCH OUT OF ADJUSTMENT.						2	H	7	4 	4F				A49EU
1998041700293	19980417	00293	EU  	1998	4	17	AU980229         	1	19980306	G	3234		SEAL            	HTE         		BAC   	146   	146100A     	1500260	EU  										GEAR SELECTOR	WORN            	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE SEALS WORN.						2	H	7	4 	4F			RT	A49EU
1998041700294	19980417	00294	NE  	1998	4	17	AU980230         	2	19980301	G	7210	3035480	GEARBOX         								PWA   	PWA120	PW125B      		NE  					ENGINE RED GRBOX	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					EC542124028		TM124019			(AUS) ENGINE REDUCTION GEARBOX CHIP DETECTOR CONTAINED SEVEN CHIPS IDENTIFIED AS M50 BEARING MATERIAL.											4	T			E20NE
1998041700295	19980417	00295	NE  	1998	4	17	AU980231         	2	19980221	G	7230		COMPRESSOR      			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					LT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							63417			(AUS) LT ENGINE COMPRESSOR DAMAGED.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998041700296	19980417	00296	SO  	1998	4	17	AU980232         	2	19980306	G	8520	643202	CRANKCASE STUD  			CESSNA	402   	402A        	207590M	CE  	CONT  	O520  	TSIO520E    	17040	SO  					NR 5 CYL PAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							502423			(AUS) CRANKCASE CRACKED AT NR 5 CYLINDER MOUNTING PAD.  BOTTOM TWO MOUNT STUDS BROKEN.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998041700297	19980417	00297	SO  	1998	4	17	AU980233         	1	19980220	G	3213	6531904	CYLINDER        			PIPER 	PA28  	PA28151     	7102805	SO  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR CYLINDER CRACKED IN AREA OF TORQUE LINK ATTACHMENT LUG RADIUS.						1	L	7	1 	3O				2A13
1998041700298	19980417	00298	SW  	1998	4	17	AU980234         	1	19980303	G	6220	471402511	SUPPORT         			BELL  	47    	47G3B       	1181026	SW  										MAIN ROTOR HEAD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILIZER BAR DAMPER SUPPORT PLATE CRACKED AT ONE OF THE FOUR MOUNTING BOLT HOLES.						1	G	7	1 	3O				2H3
1998041700299	19980417	00299	NM  	1998	4	17	AU980235         	1	19980221	G	2420		WIRE            			BOEING	767   	767338      	1385151	NM  										AC GENERATION SY	CHAFED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			TO	TAKEOFF        	1			AU	S 										(AUS) LT ENGINE MAIN GENERATOR FAILED DUE TO CHAFED CABLES.  APU WAS STARTED BUT FAILED DUE TO FAULTY OIL QUANTITY PROBE	.					2	L	7	2 	4F			RT	A1NM
1998041700300	19980417	00300	CE  	1998	4	17	AU980236         	1	19980309	G	2435	23048016	STARTER/GEN     			BEECH 	200   	200BEECH    	1152920	CE  										RT ENG	FAILED          	W				K				NONE                    				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					11616					(AUS) RT STARTER/GENERATOR FAILED.						1	L	7	2 	4T				A24CE
1998041700301	19980417	00301	EU  	1998	4	17	AU980237         	1	19980302	G	3411		PROBE           			BAC   	146   	146300A     	1500267	EU  										PITOT/STATIC SYS	FOD             	W				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) PITOT PROBE BLOCKED BY WASP NEST.						2	H	7	4 	4F			RT	A49EU
1998041700302	19980417	00302	CE  	1998	4	17	AU980238         	1	19980223	G	2810	21219	FUEL CELL       			BEECH 	55    	D55         	1152730	CE  										FUEL STORAGE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT FUEL CELL DETERIORATED.  DRAIN FITTING TORN.  INTERNAL BAFFLE LOOSE.						1	L	7	2 	3O				3A16
1998041700303	19980417	00303	CE  	1998	4	17	AU980239         	1	19980305	G	3211	24411009	PIVOT           			CESSNA	172   	172RG       	2072438	CE  										RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR PIVOT CRACKED.						1	H	7	1 	3O				3A17
1998041700304	19980417	00304	CE  	1998	4	17	AU980240         	1	19980305	G	3233	9882015	HOUSING         			CESSNA	172   	172RG       	2072438	CE  										MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR ACTUATOR HOUSING CRACKED.						1	H	7	1 	3O				3A17
1998041700305	19980417	00305	NM  	1998	4	17	AU980241         	1	19980303	G	2910	AN81510D	UNION           			DHAV  	DHC8  	DHC8102     	2809003	NM  										HYDRAULIC MAIN	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) NR 1 HYDRAULIC SYSTEM PRESSURE MANIFOLD UNION FRACTURED.  LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T			RT	A13NM
1998041700306	19980417	00306	EU  	1998	4	17	AU980242         	1	19980226	G	5523		TRIM TAB        			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB STR	SEPARATED       	W				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) ELEVATOR TRIM TAB SEPARATED.  HINGE SEGMENTS TORN FROM ELEVATOR.  SUSPECT CAUSED BY AIRCRAFT OVERSPEED.						1	L	7	1 	3O			NT	A57EU
1998041700307	19980417	00307	EU  	1998	4	17	AU980243         	1	19980302	G	2750	8834K5	SWITCH          			BNORM 	BN2   	BN2A21      	1520221	EU  										TE FLAP CONTROL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP ACTUATION SWITCH BROKE APART DURING ACTUATION.						1	H	7	2 	3O				A17EU
1998041700308	19980417	00308	NM  	1998	4	17	AU980244         	1	19980225	G	3251		ACTUATOR        			BOEING	747   	747338      		NM  										STEERING UNIT	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RT BODY LANDING GEAR OUTBOARD STEERING ACTUATOR AFT END FORK FITTING SEPARATED FROM ACTUATOR BODY.						2	L	7	2 	4F			RT	A20WE
1998041700309	19980417	00309	CE  	1998	4	17	AU980245         	1	19980304	G	3320	PWFLC28	POWER SUPPLY    			BEECH 	200   	200BEECH    	1152920	CE  										PASSENGER COMPT	SHORTED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLUORESCENT LIGHTING POWER SUPPLY SHORT CIRCUITED.						1	L	7	2 	4T				A24CE
1998041700310	19980417	00310	CE  	1998	4	17	AU980246         	1	19980215	G	2612		DETECTOR        			BEECH 	200   	B200C       	1152924	CE  										FIRE DETECTION	CONTAMINATED    	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) LT ENGINE FIRE DETECTORS CONTAMINATED WITH MOISTURE.  FALSE FIRE WARNING RESULTED IN ENGINE SHUTDOWN AND FIRE BOTT	LE DISCHARGE.					1	L	7	2 	4T				A24CE
1998041700311	19980417	00311	CE  	1998	4	17	AU980247         	1	19980217	G	5743	1011201101	WEB             			BEECH 	200   	B200C       	1152924	CE  										LT MLG BRACE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT LANDING GEAR DRAG BRACE OUTBOARD ATTACHMENT WEB CORRODED.						1	L	7	2 	4T				A24CE
1998041700312	19980417	00312	CE  	1998	4	17	AU980248         	1	19980225	G	5730		SKIN            			BEECH 	200   	B200C       	1152924	CE  										LT WING	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING CENTER SECTION LOWER SKIN DEBONDED.						1	L	7	2 	4T				A24CE
1998041700313	19980417	00313	NM  	1998	4	17	AU980249         	1	19980302	G	5347		INSERT          		SL23344A7   	BOEING	737   	737376      		NM  										FLT ATTEND SEAT	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT FLIGHT ATTENDANT'S SEAT BULKHEAD ATTACHMENT INSERTS HAD PULLED OUT OF THE BULKHEAD.						2	L	7	2 	4F			RT	A16WE
1998041700314	19980417	00314	SW  	1998	4	17	AU980250         	1	19980311	G	2731	010A6117931	CONTROL CABLE   			MTSBSI	MU2   	MU2B30      	5780410	SW  										ELEVATOR TAB CON	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					527					(AUS) ELEVATOR TRIM CABLE FRAYED WITH ONLY ONE STRAND REMAINING . CABLE FAILED DURING REMOVAL.  AIRCRAFT WAS PREVIOUSLY 	REGISTERED ASVH-UZN.					1	H	7	2 	3T			 	A2PC
1998041700315	19980417	00315	CE  	1998	4	17	AU980251         	1	19980213	G	2730	1016100196	TORQUE TUBE     			BEECH 	200   	200BEECH    	1152920	CE  										RT ELEV	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT ELEVATOR TORQUE TUBE CONTAINED CORROSION AND DEEP PITTING IN THE AREA ADJACENT TO THE RIB ATTACHMENT BRACKET.						1	L	7	2 	4T				A24CE
1998041700316	19980417	00316	SO  	1998	4	17	AU980252         	1	19980304	G	5711		PLATE           			AYRES 	S2    	S2RT15NORMAL	0970105	SO  										WING SPAR STRUCT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR TOP PLATE CRACKED.						1	L	7	1 	3T				A3SW
1998041700317	19980417	00317	NE  	1998	4	17	AU980253         	2	19980218	G	7230	31042764	IMPELLER        	GARRTT      		JETAIR	JETSTM	JETSTM4101  	1500501	EU  	GARRTT	TPE331	TPE33114GR  	01514	NE  					TURB ENG COMP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P75052			(AUS) COMPRESSOR BLADE FAILED AND SEPARATED.  IMPELLER HAD SUFFERED A BIRDSTRIKE THIRTEEN DAYS EARLIER BUT INSPECTION FO	UND IMPACT DAMAGE TO BE WITHIN LIMITS.					2	L	7	2 	4T	4	T	RT	A41NM   	E18NE
1998041700318	19980417	00318	EU  	1998	4	17	AU980254         	1	19980311	G	2612	300139538243C7	FIRE WIRE       		801DRH      	STBROS	SD3   	SD360       	8100606	EU  										FIRE DETECTION	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		TO	TAKEOFF        	1			AU	S 					70185					(AUS) LT ENGINE FIRE WIRE FAULTY.						2	H	7	2 	4T				A41EU
1998041700319	19980417	00319	SO  	1998	4	17	AU980255         	2	19980223	G	8520	6419441048	STUD            			CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  					NR 4&5 CYL	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					350027		772890800218			(AUS) CRANKCASE LOWER THOUGH BOLT LOCATED BETWEEN NR 4 AND NR 5 CYLINDERS SHEARED OFF AT THE THREAD.						1	H	7	2 	3O	3	O		A6CE    	E1CE
1998041700320	19980417	00320	SW  	1998	4	17	AU980256         	1	19980308	G	2140	613112E2342	BOLT            		613112E2342 	FRCHLD	SA227 	SA227DC     	3377521	SW  										HEATING SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					DC848					(AUS) CABIN HEATING SYSTEM HOT AIR MIXING VALVE TO CABIN SUPPLY PIPE CLAMP SECURING BOLT SNAPPED.  SUSPECT BOLT WAS OVER	TORQUED.  PERSONNEL/MAINTENANCE ERROR.					2	L	7	2 	4T			RT	A18SW
1998041700321	19980417	00321	SO  	1998	4	17	AU980257         	1	19980306	G	2810		SEAL            			PIPER 	PA31  	PA31        	7103102	SO  										RT MAIN FUEL	MISSING         	W				K				NONE                    				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN FUEL TANK CAP SEAL MISSING.  AIRCRAFT FLEW THROUGH HEAVY RAIN ALLOWING WATER TO ENTER FUEL TANK.  RT ENGIN	E FAILED DUE TO WATER CONTAMINATION.  PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O				A20SO
1998041700322	19980417	00322	SW  	1998	4	17	AU980258         	1	19980201	G	6220	471201412	PIN             			BELL  	47    	47G3B1      	1181028	SW  										MAIN ROTOR HEAD	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B13259					(AUS) MAIN ROTOR HUB BEARING PINS DAMAGED DUE TO MAIN ROTOR STRIKE.  BEARINGS WERE ALSO UNSERVICEABLE.  FOUND DURING STR	IP OF MAIN ROTOR HUB FOR COMPLIANCE WITH AD/BELL47/92 AMDT4.					1	G	7	1 	3O				2H3
1998041700323	19980417	00323	EA  	1998	4	17	AU980259         	2	19980303	G	8520		STUD            			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	VO435A1F    	41516	EA  					ENG NR 5 CYL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L201552			(AUS) NR 5 CYLINDER HOLD DOWN STUDS FAILED.						1	G	7	1 	3O	3	O		2H3     	E279
1998041700324	19980417	00324		1998	4	17	AU980260         	1	19980221	G	7400		IGNITION SYSTEM 		912A        						ROTAX 	912   	ROTAX912    	55555	EU  					ENG IGNITION	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 							4410151			(AUS) ENGINE WOULD NOT START.  SUSPECT CAUSED BY WEAK IGNITION SYSTEM.											3	I			EXPE3I
1998042900015	19980429	00015	EU  	1998	4	29	AU980261         	1	19980307	G	3233	AIR86414	ACTUATOR        			SAAB  	SF340 	340B        	7860101	EU  										NLG ACTUATOR	FAULTY          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 					LK9000262					(AUS) NOSE LANDING GEAR ACTUATOR RESTRICTOR BLOCKED BY UNKNOWN FOREIGN MATERIAL.						2	L	7	2 	4T			RT	A52EU
1998041700325	19980417	00325	SW  	1998	4	17	AU980262         	1	19980213	G	6200		MAIN ROTOR SYS  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					DRIVE SYS	STOPPAGE        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR, TAIL ROTOR AND DRIVE SHAFT COMPONENTS -  SUSPECT FOLLOWING DYNAMIC ROLLOVER ON 2/13/98.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998041700326	19980417	00326	NM  	1998	4	17	AU980263         	1	19980123	G	5310		STRUCTURE       			BOEING	727   	7272J4      	1384006	NM  	PWA   	JT8   	JT8D17      	52049	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT STRUCTURE CORRODED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998041700327	19980417	00327	NM  	1998	4	17	AU980264         	1	19980115	G	5310		STRUCTURE       			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRCRAFT STRUCTURE CORRODED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1998042900016	19980429	00016	EU  	1998	4	29	AU980265         	1	19980308	G	2530	D2527410021000	ROD             			AIRBUS	320   	A320212     	       	EU  										RT GALLEY	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			DE	DESCENT        	1			AU	S 										(AUS) PASSENGER CABIN OXYGEN MASK PANEL LOCATED IN THE REAR GALLEY CEILING FAILED TO OPEN DURING AUTO-DEPLOYMENT DUE TO 	INTERFERENCE BY THE RT GALLEY CURTAIN RAIL P/N D2527410021000 WHICH HAD BEEN INCORRECTLY INSTALLED.					2	L	7	2 	4F			RT	A28NM
1998041700328	19980417	00328	NM  	1998	4	17	AU980266         	1	19980211	G	5312		WEB             			BOEING	737   	73733A      	1384673	NM  										FWD PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB SKIN CRACKED IN EIGHT PLACES.  FOUND DURING ULTRASONIC INSPECTION.						2	L	7	2 	4F			RT	A16WE
1998041700330	19980417	00330	NM  	1998	4	17	AU980268         	1	19980212	G	5312		CHORD           			BOEING	737   	73733A      	1384673	NM  										FWD PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD LT SIDE CHORD LOCATED AT WL 207 CRACKED.  CRACK LENGTH 38.1MM (1.5 INCH).  FOUND DURING 	VISUAL INSPECTION IAW ER B73-53-10-39C.					2	L	7	2 	4F			RT	A16WE
1998041700331	19980417	00331	NM  	1998	4	17	AU980269         	1	19980121	G	5312		WEB             			BOEING	737   	73733A      	1384673	NM  										FWD PRESS BLKHD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB SKIN CONTAINED SIX CRACKS.  FOUND DURING ULTRASONIC INSPECTION.						2	L	7	2 	4F			RT	A16WE
1998041700332	19980417	00332	NM  	1998	4	17	AU980270         	1	19980310	G	5312	651630084	BULKHEAD        			BOEING	737   	737476      		NM  										FWD PRESS WL 207	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD AT WL 207 CRACKED IN LT CHORD.  WEB ALSO CONTAINED THREE CRACKS.						2	L	7	2 	4F			RT	A16WE
1998041700333	19980417	00333	NM  	1998	4	17	AU980271         	1	19980226	G	5312	651630084	BULKHEAD        			BOEING	737   	737376      		NM  										BS 178	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED AT BS 178.  LT VERTICAL CHORD CRACKED IN TWO PLACES AND WEB CRACKED IN FIVE PLAC	ES.					2	L	7	2 	4F			RT	A16WE
1998041700334	19980417	00334	NM  	1998	4	17	AU980272         	1	19980306	G	3250	65C268333	VALVE           			BOEING	737   	7374Q8      		NM  										NLG STEERING	FAULTY          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 					FAH1648					(AUS) NOSE WHEEL STEERING DEPRESSURIZATION VALVE FAULTY.						2	L	7	2 	4F			RT	A16WE
1998041700335	19980417	00335	NM  	1998	4	17	AU980273         	1	19980225	G	5320	655507461	POST            			BOEING	737   	737376      		NM  										COCKPIT C-D POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT WINDOW POST `C-D' LT GUSSET CRACKED.  CRACK LENGTH 12.7MM (0.5 INCH).						2	L	7	2 	4F			RT	A16WE
1998041700336	19980417	00336		1998	4	17	AU980274         	4	19980205	G	3418	95001001F	SERVO           			SWRNGN	SA226 	SA226TC     	8780404	SW  										STALL WARNING	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					9816					(AUS) STALL WARNING SYSTEM SERVO CAPSTAN FAULTY DUE TO DRIED GREASE.						2	L	7	2 	4T			RT	A8SW
1998041700337	19980417	00337	EA  	1998	4	17	AU980275         	2	19980316	G	8550		FILTER          			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENG OIL	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L602761A			(AUS) ENGINE OIL FILTER CONTAMINATED WITH METAL.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998041700338	19980417	00338	SW  	1998	4	17	AU980276         	1	19980312	G	3243	400021	CLEVIS          			AIRTRC	AT802 	AT802       	0390305	SW  										LT BRAKE CYL	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT BRAKE MASTER CYLINDER CLEVIS BOLT FAILED.						1	L	7	1 	3T			NC	A19SW
1998041700339	19980417	00339	CE  	1998	4	17	AU980277         	1	19980314	G	2460	CM358950	MASTER SWITCH   			CESSNA	402   	402C        	207590R	CE  										DC POWER DISTRIB	BURNT OUT       	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			AU	S 										(AUS) AVIONICS MASTER SWITCH BURNED OUT.  SUSPECT CAUSED BY WATER INGRESS VIA THE WINDOW SEAL.						1	L	7	2 	3O				A7CE
1998041700340	19980417	00340	SW  	1998	4	17	AU980278         	1	19980311	G	6220	471301161	NUT             			BELL  	47    	47G3B       	1181026	SW  										MAIN ROTOR HEAD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1093 		0567					(AUS) MAIN ROTOR MAST NUT WORN.  SEAL EDGE LIP WORN INTO NUT FACE.						1	G	7	1 	3O				2H3
1998041700341	19980417	00341	CE  	1998	4	17	AU980279         	1	19980314	G	3234	99102251	VALVE           			CESSNA	402   	402C        	207590R	CE  										LANDING GEAR SEL	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR SELECTION VALVE FAULTY DUE TO HIGH RESISTANCE IN ELECTRICAL SOLENOID COIL.  CAUSED BY INGRESS OF HYDR	AULIC FLUID.					1	L	7	2 	3O				A7CE
1998041700342	19980417	00342	SO  	1998	4	17	AU980280         	2	19980204	G	8520		CRANKCASE       								CONT  	O360  	TSIO360E    	17025	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							237339R			(AUS) ENGINE CRANKCASE RT HALF CRACKED IN NR 4 MAIN BEARING TUNNEL AND LT HALF CRACKED IN NR 2 AND NR 3 MAIN BEARING TUN	NELS.  CRANKSHAFT CRACKED ON NR 4 MAIN BEARING.  CRACK LENGTH APPROXIMATELY 50.8MM (2 INCHES).										3	O			E9CE
1998041700343	19980417	00343	SW  	1998	4	17	AU980281         	1	19980311	G	7120	276202001	MOUNT           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ENG MOUNT SECT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE MOUNT TOP RT DIAGONAL BRACE HAD A HOLE WORN THROUGH BY THE TOP OF THE SWITCH ON THE ANTI-ICE VALVE P/N 3	19980-13-1.  SIZE OF HOLE APPROXIMATELY 4.762MM (0.1875 INCH).					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998041700344	19980417	00344	NM  	1998	4	17	AU980282         	1	19980105	G	5414		FASTENER        			BOEING	737   	737376      		NM  										LT PYLON ACCESS	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			LD	LANDING        	1			AU	S 										(AUS) LT PYLON AFT ACCESS FAIRING HAD NUMEROUS FASTENERS MISSING.  SUSPECT INCORRECT TORQUE.						2	L	7	2 	4F			RT	A16WE
1998041700345	19980417	00345	EA  	1998	4	17	AU980283         	2	19980211	G	7250		ENGINE          			PIPER 	PA42  	PA42        	7104202	SO  	PWA   	PT6   	PT6A41      	52043	EA  					TURBINE SECTION	FAILED          	W				K	E			NONE                    	ENGINE SHUTDOWN         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			5209 				85444			(AUS) ENGINE POWER SECTION FAILED.						1	L	7	2 	4T	4	T		A23SO   	E4EA
1998041700346	19980417	00346	CE  	1998	4	17	AU980284         	1	19980219	G	2612		FIRE DETECTOR   			BEECH 	200   	200BEECH    	1152920	CE  										FIRE DETECTION	FAULTY          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) LT ENGINE FIRE DETECTION SYSTEM FAULTY.  INVESTIGATION COULD FIND NO FAULTS WITH THE SYSTEM.  SUSPECT MOISTURE CON	TAMINATION OF DETECTORS.  LT ENGINE SHUT DOWN AND FIRE BOTTLE OPERATED.					1	L	7	2 	4T				A24CE
1998041700347	19980417	00347	CE  	1998	4	17	AU980285         	1	19980120	G	2460		PANEL           			BEECH 	200   	B200C       	1152924	CE  										DC POWER DISTRIB	SHORTED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) CIRCUIT BREAKER (CB) PANEL BUS FEEDER SHORT CIRCUITING TO AIRFRAME ADJACENT TO CBS.  SHORT CIRCUIT OCCURRED DUE TO	 WATER LEAKAGE FROM WINDOW.					1	L	7	2 	4T				A24CE
1998041700348	19980417	00348		1998	4	17	AU980286         	4	19980220	G	3418	861CAU2	SENSOR          			AMD   	FALC50	FALCON900   	2700160	EU  										STALL WARNING SY	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LT AND RT ANGLE OF ATTACK SENSORS OUT OF ADJUSTMENT.  THIS DEFECT WAS RECEIVED FROM NR 34 SQUADRON RAAF AND IS FOR	 INFORMATION ONLY.					2	L	7	3 	4F			RT	A46EU
1998041700349	19980417	00349	SW  	1998	4	17	AU980287         	1	19980318	G	6510	47644232101	DRIVE SHAFT     			BELL  	47    	47G3B       	1181026	SW  										TAIL ROTOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVE SHAFT COUPLING SPLINES WORN 0.3556MM (0.014 INCH) BELOW MINIMUM DIMENSIONS.						1	G	7	1 	3O				2H3
1998041700350	19980417	00350	SW  	1998	4	17	AU980288         	1	19980318	G	6710	476310871	BEARING         			BELL  	47    	47G3B       	1181026	SW  										M/R CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOTS COLLECTIVE LEVER BEARING WORN.  UNAPPROVED REPAIR HAD BEEN CARRIED OUT TO TAKE UP THE PLAY IN THE WORN SHAF	T AND BEARING.  UNAPPROVED REPAIR.  PERSONNEL/MAINTENANCE ERROR.					1	G	7	1 	3O			 	2H3
1998041700351	19980417	00351	EA  	1998	4	17	AU980289         	2	19980312	G	7314	B2680	SCREW           		RG34720A    	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL PUMP	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					B2680		PCE81596			(AUS) FUEL PUMP SCREWS FAILED TORQUE CHECK IAW ROMEC SB 101SB018.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998041700352	19980417	00352	SW  	1998	4	17	AU980290         	1	19980311	G	6220	471301161	NUT             			BELL  	47    	47G3B       	1181026	SW  										MAIN ROTOR HEAD	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1093 		0567					(AUS) MAIN ROTOR RETAINING NUT FACE WORN BY SEAL EDGE LIP.						1	G	7	1 	3O				2H3
1998041700353	19980417	00353	NE  	1998	4	17	AU980291         	2	19980303	G	8530	366249	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					NR 2 - 3 CYL EXH	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			10   							(AUS) NR 2 AND NR 3 CYLINDERS LEAKING PAST EXHAUST VALVES.						1	H	7	1 	3R	3	R		A815    	5E2
1998041700354	19980417	00354	NE  	1998	4	17	AU980292         	2	19980303	G	8530	366249	CYLINDER        		R134059     	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					NR 1 CYL	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			10   							(AUS) NR 1 CYLINDER LEAKING BETWEEN CYLINDER AND BARREL.						1	H	7	1 	3R	3	R		A815    	5E2
1998041700355	19980417	00355	SO  	1998	4	17	AU980293         	1	19980305	G	5320	4A14110716	CHANNEL         			EMB   	110   	EMB110P1    	3260122	SO  										STAB SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LT UPPER HORIZONTAL STABILIZER SUPPORT ATTACHMENT CHANNEL CRACKED THROUGH TWO BOLT HOLES.  FURTHER INVEST	IGATION FOUND SEVERE FRETTING ON THE LT CHANNEL TO REAR BULKHEAD ATTACHMENT FACE.					1	L	7	2 	4T				A21SO
1998041700356	19980417	00356	SO  	1998	4	17	AU980294         	1	19980308	G	5711	6244802	FITTING         		6244803     	PIPER 	PA28  	PA28R201    	7102816	SO  										LT RT AFT SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT REAR SPAR ATTACHMENT FITTINGS P/N 62448-02 (LT) AND P/N 62448-03 (RT) CORRODED.						1	L	7	1 	3O				2A13
1998041700357	19980417	00357		1998	4	17	AU980295         	4	19980305	G	3416	5934	ALTIMETER       			AYRES 	S2    	S2RT15NORMAL	0970105	SO  										COCKPIT	FRICTION        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTIMETER FAILED AD/INST/8 AMDT3.  EXCESSIVE FRICTION TRAVELLING UP AND DOWN SCALE.						1	L	7	1 	3T				A3SW
1998041700358	19980417	00358		1998	4	17	AU980296         	4	19980319	G	3424	5224TC	INDICATOR       			AYRES 	S2    	S2RT15NORMAL	0970105	SO  										TURN & BANK	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TURN AND SLIP INDICATOR FAULTY.  INDICATOR ROTOR WAS NOT SPINNING.  INSTRUMENT FAILED AD/INST/8 AMDT 3.						1	L	7	1 	3T				A3SW
1998041700359	19980417	00359	SO  	1998	4	17	AU980297         	1	19980318	G	3260	MS3470L8335	CONNECTOR       			EMB   	120   	EMB120      	3260201	SO  										GEAR POS	CORRODED        	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR UPLOCK PROXIMITY SENSOR `A' SYSTEM CONNECTOR IJ1548 CORRODED.						2	L	7	2 	4T			RT	A31SO
1998041700360	19980417	00360	EA  	1998	4	17	AU980298         	2	19980302	G	8540	LW10297	GEAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					CRANK IDLER	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 			1628 				L87968A			(AUS) CRANKSHAFT IDLER GEAR TEETH FAILED.  DAMAGE TO CAMSHAFT GEAR AND CRANKSHAFT GEAR.  LOSS OF DRIVE TO OIL PUMP AND M	AGNETO.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998041700361	19980417	00361	CE  	1998	4	17	AU980299         	1	19980304	G	5521		SPAR            			BEECH 	58    	58          	1152740	CE  						MCAULY				ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR SPAR CRACKED ACROSS SPAR WEB IN AREA OF OUTBOARD HINGE ATTACHMENT.  CRACK ORIGINATED AT THE HINGE ATTACHM	ENT BOLT HOLE AND PROPAGATED IN BOTH DIRECTIONS.  FACTORY FITTED DOUBLER ALSO CRACKED.					1	L	7	2 	3O				3A16
1998041700362	19980417	00362	CE  	1998	4	17	AU980300         	1	19980304	G	5511		DOUBLER         			BEECH 	58    	58          	1152740	CE  										HORIZ STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT TAILPLANE INBOARD RIB/REAR SPAR JOINT DOUBLER CRACKED.						1	L	7	2 	3O				3A16
1998041700363	19980417	00363	CE  	1998	4	17	AU980301         	1	19980209	G	5312	05121871	BULKHEAD        		05121872    	CESSNA	172   	172P        	2072436	CE  						MCAULY				DOOR POSTS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE AFT DOOR POSTS P/N 0512187-1 (LT) AND P/N 0512187-2 (RT) CRACKED.  FOUND DURING INSPECTION IAW CESSNA SB 	SEB 97-1.					1	H	7	1 	3O			NT	3A12
1998041700364	19980417	00364	CE  	1998	4	17	AU980302         	1	19980206	G	5312	05121871	BULKHEAD        		05121872    	CESSNA	172   	172P        	2072436	CE  										DOOR POSTS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LOWER AFT DOOR POST BULKHEADS P/N 0512187-1 AND P/N 0512187-2 CRACKED.  FOUND DURING INSPECTION IAW CESSN	A SB SEB97-1.					1	H	7	1 	3O			NT	3A12
1998041700365	19980417	00365		1998	4	17	AU980303         	1	19980322	G	7170		HOSE            								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE DRAINS	INCORRECT       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							438067			(AUS) CARBURETOR OVERFLOW DRAIN PIPE POSITIONING COULD CAUSE A FIRE HAZARD.											3	I			EXPE3I
1998041700366	19980417	00366	CE  	1998	4	17	AU980304         	1	19980311	G	3230	6046H39A	RELAY           			BEECH 	55    	D55         	1152730	CE  										GEAR RETRACT	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 			1650 							(AUS) LANDING GEAR RELAY FAULTY.  SUSPECT CAUSED BY INGRESS OF FOREIGN MATTER.						1	L	7	2 	3O				3A16
1998041700367	19980417	00367	EU  	1998	4	17	AU980305         	1	19980218	G	3230		VALVE           			BAG   	JETSTM	JETSTM3107  	1500215	EU  										GEAR RETRACT	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR EMERGENCY BYPASS VALVE BUTTON POPPED.						2	L	7	2 	4T			RT	BA15CAA
1998041700368	19980417	00368		1998	4	17	AU980306         	1	19980323	G	7602	115C6030	SUPPORT         								LYC   	O360  	O360A1F6    	41514	EA  					MIXTURE CONTROL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3482036A			(AUS) ENGINE MIXTURE CONTROL CABLE CLAMP SUPPORT CRACKED.											3	O			E286
1998041700369	19980417	00369	SO  	1998	4	17	AU980308         	2	19980325	G	8520		CRANKCASE       								CONT  	O520  	IO520M      	17032	SO  					ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							565121			(AUS) CRANKCASE TUNNELS OUT OF LIMITS.											3	O			E5CE
1998041700370	19980417	00370	SO  	1998	4	17	AU980309         	2	19980304	G	8540	537721	BEARING         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					ENG STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1069 				276251R			(AUS) STARTER SHAFT BEARING FAILED.  METAL CONTAMINATION OF OIL SYSTEM.						1	L	7	2 	3O	3	O		A25CE   	E7CE
1998041700371	19980417	00371	CE  	1998	4	17	AU980310         	1	19980313	G	3310	A350CNIWBKSH	CONNECTOR       	GRIMES      	A350CNIWBKSH	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520N    	17040	SO  					INST PANEL LITE	BURNT           	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) SPARE POST LIGHT CONNECTOR LOCATED BEHIND THE INSTRUMENT PANEL SHORT CIRCUITED AND BURNT.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998041700372	19980417	00372	EU  	1998	4	17	AU980311         	1	19980325	G	2750		VALVE           			JETAIR	JETSTM	JETSTM4101  	1500501	EU  	GARRTT	TPE331	TPE33114GR  	01514	NE  					TE FLAP CONTROL	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) FLAP CONTROL VALVE RESET IN ACTIVATED POSITION.  FLAPS WOULD NOT RETRACT.  FLAPS RESET AND SYSTEM OPERATED OK.						2	L	7	2 	4T	4	T	RT	A41NM   	E18NE
1998041700373	19980417	00373	CE  	1998	4	17	AU980312         	1	19980313	G	3260		BULB            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT GEAR POS	FAILED          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		DE	DESCENT        	1			AU	S 										(AUS) LT MAIN LANDING GEAR INDICATOR BULB BLOWN.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998041700374	19980417	00374	WP  	1998	4	17	AU980313         	2	19980327	G	7261	31035781	TUBE            		31080801    	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENGINE OIL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2647 				P44386			(AUS) REAR TURBINE OIL SUPPLY TUBE CHAFING ON UTS SYSTEM OIL SUPPLY TUBE.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998041700375	19980417	00375	CE  	1998	4	17	AU980314         	1	19980326	G	3213		TRUNNION        			CESSNA	421   	421B        	2076014	CE  										LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR TRUNNION FORWARD MOUNTING SUPPORT CRACKED.  RT MAIN LANDING GEAR TRUNNION SHOWS SIGNS OF A SI	MILAR DEFECT.					1	L	7	2 	3O				A7CE
1998041700376	19980417	00376	SO  	1998	4	17	AU980315         	1	19980308	G	5512		STABILIZER      			PIPER 	PA31  	PA31        	7103102	SO  										HORIZ STABILIZER	FOD             	W				K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) LT HORIZONTAL STABILIZER LEADING EDGE FOD.  DAMAGE LOCATED INBOARD OF STN 78.5.						1	L	7	2 	3O				A20SO
1998041700377	19980417	00377	EU  	1998	4	17	AU980316         	1	19980324	G	2611	72111211000	DETECTOR        			SAAB  	SF340 	340B        	7860101	EU  										SMOKE DETECTION	FAULTY          	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CR	CRUISE         	1			AU	S 										(AUS) CARGO SMOKE DETECTOR ACTIVATED.  INVESTIGATION COULD FIND NO EVIDENCE OF FIRE BUT FOUND THAT THE FLUORESCENT LIGHT	 IN THE LAVATORY HAD BEEN FLICKERING AND CAUSING EMI INTERFERENCE.					2	L	7	2 	4T			RT	A52EU
1998041700378	19980417	00378	EU  	1998	4	17	AU980317         	1	19980327	G	3411	6874017	HOSE            		6877519     	PARTEN	P68   	P68B        		EU  										PITOT/STATIC	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PITOT/STATIC SYSTEM HOSE DETERIORATED. SILICON HOSE APPEARS TO BE BREAKING DOWN AND EXUDING AN OILY FILM WHICH IS 	PARTIALLY BLOCKING THE STATIC AIR DISTRIBUTOR MANIFOLD.					1	H	7	2 	3O				A31EU
1998041700379	19980417	00379	EU  	1998	4	17	AU980318         	1	19980324	G	5414	68120237	SKIN            			PARTEN	P68   	P68B        		EU  										RT ENG NAC	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					136					(AUS) RT ENGINE LOWER NACELLE SKIN SEVERELY CORRODED INTERNALLY.  SKIN IS LOCATED ABOVE THE EXHAUST GAS STREAM.  PART OF	 THE NACELLE LATERAL BEAM WAS ALSO CORRODED.					1	H	7	2 	3O				A31EU
1998041700380	19980417	00380	SW  	1998	4	17	AU980320         	1	19980318	G	2720	701031	SPRING          			AIRTRC	AT500 	AT502       	0390303	SW  										RUDDER CONTROL	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) LT RUDDER/AILERON INTERCONNECT SPRING BROKEN.  THE SPRING FAILED ON THE HOOK APPROXIMATELY 10MM (0.393 INCH) FROM 	THE ATTACHMENT POINT.  INVESTIGATION FOUND THAT THE CRACK HAD BEEN PRESENT FOR SOME TIME BEFORE FAILURE.					1	L	7	1 	3T			NC	A9SW
1998041700381	19980417	00381	GL  	1998	4	17	AU980321         	3	19980325	G	6110		PROPELLER       													ROTOL	R333	R333482F12  	GL  	RT ENG	VIBRATION       	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 								DRG134785		(AUS) RT ENGINE VIBRATION.  PROPELLER CHANGED AS A PRECAUTION.																6	C	P61GL
1998041700382	19980417	00382	CE  	1998	4	17	AU980322         	1	19980320	G	5312	12113256	BULKHEAD        			CESSNA	210   	210M        	2073450	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LOWER CENTER SECTION FRAME/BULKHEAD CRACKED.  THE MAIN CRACKING WAS FROM THE OUTBOARD CUTOUT FOR THE RT M	AIN LANDING GEAR LEG.  CRACKING WAS ALSO COMMENCING ON THE OPPOSITE CUTOUT AND ALSO ON THE OUTER EDGE WHERE THE OUTBOARD	 CASTING BOLTS TO THE FRAMES.				1	H	7	1 	3O				3A21
1998041700383	19980417	00383	CE  	1998	4	17	AU980323         	1	19980324	G	3244	600X6	TIRE            	CLEVELAND   	4075B       	CESSNA	210   	210N        	2073453	CE  										LT MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR TIRE CUT DURING LANDING ON ROUGH STRIP.  TIRE DEFLATED.						1	H	7	1 	3O				3A21
1998041700384	19980417	00384	SO  	1998	4	17	AU980324         	2	19980218	G	7414	6210	MAGNETO         			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					LT MAG	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					88040262		567450			(AUS) LT MAGNETO FAULTY.						1	H	7	1 	3O	3	O		3A21    	E5CE
1998041700385	19980417	00385	SO  	1998	4	17	AU980325         	2	19980324	G	8530	653426A13	CYLINDER        			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					EXH VALVES	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							20R005			(AUS) ENGINE CYLINDERS HAD LOW COMPRESSION.  INVESTIGATION FOUND WORN EXHAUST VALVE GUIDES AND GLAZED AND OUT OF ROUND C	YLINDER BORES.					1	H	7	1 	3O	3	O		3A19    	E252
1998041700386	19980417	00386		1998	4	17	AU980326         	4	19980209	G	2562	9184	BATTERY         		E01         	PIPER 	PA32  	PA32300     	7103212	SO  										EMERG LOCATOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					9184					(AUS) ELT BATTERIES LEAKING.  BATTERIES WERE DURACELL MN1300 TYPE MADE IN THE USA.						1	L	7	1 	3O				A3SO
1998041700387	19980417	00387	EU  	1998	4	17	AU980327         	1	19980326	G	5711	6814001	SPAR            		6814002     	PARTEN	P68   	P68C        	6780105	EU  										LT RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING SPARS P/N 68-1.4001 AND P/N 68-1.4002 CONTAINED INTERGRANULAR AND EXFOLIATION CORROSION IN THE WEBS	 LOCATED BEHIND THE ENGINE FIREWALLS.					1	H	7	2 	3O				A31EU
1998041700388	19980417	00388	EU  	1998	4	17	AU980328         	1	19980326	G	2740	6853029	TORQUE TUBE     			PARTEN	P68   	P68C        	6780105	EU  										HORIZ STABILIZER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR TORQUE TUBE CORRODED.  INSPECTION FOUND RUST ON BOTH THE INTERNAL AND EXTERNAL SURFACES.						1	H	7	2 	3O				A31EU
1998041700389	19980417	00389	EA  	1998	4	17	AU980329         	2	19980321	G	8530	L347561A	CYLINDER        			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					LT ENG NR 1 CYL	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 							L347561A			(AUS) LT ENGINE NR 1 CYLINDER FAILED.  METAL CONTAMINATION OF OIL SYSTEM.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998041700390	19980417	00390	CE  	1998	4	17	AU980330         	1	19980323	G	3233	1053840023	ACTUATOR        		76          	BEECH 	76    	76          	1153005	CE  										LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LT MAIN LANDING GEAR ACTUATOR ROD BROKEN AT THE END OF THE THREADED SECTION.						1	L	7	2 	3O				A29CE
1998041700391	19980417	00391	EA  	1998	4	17	AU980331         	2	19980326	G	7322	229164	TUBE            	FACET       	MA3PA       						LYC   	O235  	O235H2C     	41505	EA  					CARBURETOR	SEPARATED       	W				K				NONE                    				E			VIBRATION/BUFFET          			LD	LANDING        	1			AU	S 			413  		DT31958		L24482815			(AUS) CARBURETOR ACCELERATOR PUMP DISCHARGE TUBE SEPARATED AND FELL INTO THE AIRBOX.											3	O			E223
1998041700392	19980417	00392	CE  	1998	4	17	AU980332         	1	19980317	G	5711	042240714	PLATE           		A152        	CESSNA	150   	A152        	2071836	CE  										WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR PLATE CONTAINED EXFOLIATION CORROSION BETWEEN SPAR FLANGE AND SPAR PLATE.  LENGTH OF CORROSION 35MM (1.3	7 INCH).					1	H	7	1 	3O				3A19
1998041700393	19980417	00393	GL  	1998	4	17	AU980333         	3	19980324	G	6114	C90	HUB             			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1182 					7710030		(AUS) PROPELLER HUB CRACKED ON FLANGE AREA.  INVESTIGATION ALSO FOUND THAT ALL THREE BLADE SOCKETS WERE FILLED WITH `SIL	ASTIC' SEALANT.  PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA
1998052200231	19980522	00231	SO  	1998	5	22	AU980334         	2	19980123	G	8530	643873	VALVE           		653443A13   	CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE EXHAUST	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							222760			(AUS) ENGINE EXHAUST VALVES P/N 643873 (3 OFF) AND VALVE GUIDE P/N 643767 (1 OFF) WORN BEYOND LIMITS.  CAM FOLLOWERS (5 	OFF) P/N 646277 (EXHAUST) AND P/N 628488 (INLET) CORRODED ON FACE.  PART TC:  171.					1	H	7	1 	3O	3	O	NT	TA13    	E273
1998052200232	19980522	00232	SO  	1998	5	22	AU980335         	2	19980123	G	8550	CH48104	FILTER          		653443A13   	CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470R       	17026	SO  					ENGINE OIL	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							222760			(AUS) OIL FILTER THREADED END INCOMPATIBLE WITH THE THREADS ON THE OIL FILTER HOUSING.						1	H	7	1 	3O	3	O	NT	TA13    	E273
1998052200233	19980522	00233	NM  	1998	5	22	AU980336         	1	19980217	G	5755	BN138	BRACKET         		651734748   	BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 2 SPOILER	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			417  		BN138					(AUS) LEFT NR 2 SPOILER ACTUATOR ATTACHMENT BRACKET FAILED.  SUSPECT CAUSED BY INCORRECT RIGGING.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1998052200234	19980522	00234	NM  	1998	5	22	AU980337         	1	19980119	G	2913	6507501	PUMP            			BOEING	727   	72777C      	1380420	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 1 HYD	FAILED          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 			8    							(AUS) NR 1 SYSTEM HYDRAULIC PUMP FAILED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1998052200235	19980522	00235	SO  	1998	5	22	AU980338         	2	19980330	G	7320	631329	HOUSING         			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					FUEL MANIFOLD	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					C029823CR					(AUS) FUEL MANIFOLD VALVE HOUSING DAMAGED IN SEAL RETAINING AREA ALLOWING FUEL TO LEAK PAST THE SEAL.						1	H	7	1 	3O	3	O		3A21    	E5CE
1998052200236	19980522	00236	NE  	1998	5	22	AU980339         	2	19980320	G	7250		LOCK            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	MISINSTALLED    	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LF05156			(AUS) NR 2 ENGINE 4TH TURBINE RETAINING NUT SEPARATED DUE TO INCORRECT CRIMPING OF THE LOCKING CUP.  PERSONNEL/MAINTENAN	CE ERROR.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998052200237	19980522	00237	EU  	1998	5	22	AU980340         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  										RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O			NT	A57EU
1998052200238	19980522	00238	EU  	1998	5	22	AU980341         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  					LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L24482815			(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223
1998052200239	19980522	00239	EU  	1998	5	22	AU980342         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223
1998052200240	19980522	00240	EU  	1998	5	22	AU980343         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  					LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223
1998052200241	19980522	00241	EU  	1998	5	22	AU980344         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223
1998052200242	19980522	00242		1998	5	22	AU980345         	1	19980319	G	7602	115C7102	CABLE           								LYC   	O360  	O360A1F6    	41514	EA  					MIXTURE CONTROL	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) MIXTURE CONTROL CABLE FAILED AT ENGINE END FITTING.											3	O			E286
1998052200243	19980522	00243	EU  	1998	5	22	AU980346         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223
1998052200244	19980522	00244	EU  	1998	5	22	AU980347         	1	19980320	G	3213		AXLE            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  					LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR AXLES CRACKED.						1	L	7	1 	3O	3	O	NT	A57EU   	E223
1998052200245	19980522	00245	EA  	1998	5	22	AU980348         	2	19980331	G	8530	LW15314	INLET VALVE     			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					NR 2 CYL	STICKING        	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							RL456276T			(AUS) NR 2 CYLINDER INLET VALVE STICKING DUE TO CARBON BUILD-UP ON THE VALVE STEM.  PUSHROD BENT.  PART TC:  8,302.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998052200246	19980522	00246		1998	5	22	AU980349         	1	19980318	G	7603	115C7100	CABLE           								LYC   	O360  	O360A1F6    	41514	EA  					POWER LEVER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THROTTLE CABLE OUTER GUIDE TUBE SEPARATED FROM INNER CABLE AT ENGINE END.  PART TC:  954.											3	O			E286
1998052200247	19980522	00247		1998	5	22	AU980350         	1	19980326	G	7160	11159	CABLE           								LYC   	O360  	O360A1F6    	41514	EA  					ENGINE AIR INTAK	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARBURETOR HEAT CABLE THREADED SHAFT BENT.  PART TC:  1,055.											3	O			E286
1998052200248	19980522	00248	CE  	1998	5	22	AU980351         	1	19980324	G	3213	1241110200	BEARING         			CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					LT MLG TRUNNION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR AFT TRUNNION SPHERICAL BEARING OUTER RACE SHATTERED.  INCORRECT BEARING FITTED.  A BUSH SHOUL	D BE FITTED IN THIS AREA AND NOT A SPHERICAL BEARING.  PERSONNEL/MAINTENANCE ERROR.  UNAPPROVED PART.					1	H	7	1 	3O	3	O	 	3A21    	E5CE
1998052200249	19980522	00249		1998	5	22	AU980352         	1	19980326	G	7603	115C7100	CABLE           								LYC   	O360  	O360A1F6    	41514	EA  					POWER LEVER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE THROTTLE CABLE OUTER GUIDE TUBE SEPARATED FROM INNER CABLE AT ENGINE END.  PART TC:  1,055.											3	O			E286
1998052200250	19980522	00250	CE  	1998	5	22	AU980353         	1	19980324	G	5711	21100015	SPAR            			CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					WING ATTACH LUG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR ASSEMBLY CONTAINED DEEP PITTING CORROSION ON THE LOWER WING ATTACHMENT LUG.  CAUSED BY A BROKEN AND RUST	Y SCAT HOSE WIRE RESTING ON THE SPAR.					1	H	7	1 	3O	3	O		3A21    	E5CE
1998052200251	19980522	00251	EU  	1998	5	22	AU980354         	1	19980330	G	3097		WIRE            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					WINDOW HEAT	SHORTED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) FIRST OFFICER'S SLIDING WINDOW HEATER CABLE ARCED AND BURNING.						2	L	7	2 	4F	4	F	RT	A35EU   	E23EA
1998052200252	19980522	00252	EU  	1998	5	22	AU980355         	1	19980331	G	3246	48290	BEARING         			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					NR 6 WHEEL	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) NR 6 WHEEL INNER BEARING COLLAPSED.  DAMAGE CAUSED TO AXLE.  PART TC:  227.						2	L	7	2 	4F	4	F		A35EU   	E23EA
1998052200253	19980522	00253	NE  	1998	5	22	AU980356         	1	19980330	G	6320	7635109082	CHIP DETECTOR   			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					M/R GEARBOX	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 					A2310000T					(AUS) MAIN GEARBOX LT CHIP DETECTOR FAULTY.						1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
1998052200254	19980522	00254	NE  	1998	5	22	AU980357         	2	19980325	G	7200		ENGINE          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 							LF05582A			(AUS) NR 4 ENGINE VIBRATING.  CHIP DETECTORS CONTAINED CONDITION TWO METAL CONTAMINATION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998052200255	19980522	00255	CE  	1998	5	22	AU980358         	1	19980323	G	5312		BULKHEAD        			CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					BS 209	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE BULKHEAD LOCATED AT STN 209 CRACKED.  BULKHEAD HAD BEEN INCORRECTLY REPAIRED PREVIOUSLY ALLOWING CRACKING	 AT HORIZONTAL STABILIZER ATTACHMENT POINTS.  PERSONNEL/MAINTENANCE ERROR.					1	H	7	1 	3O	3	O		3A21    	E5CE
1998052200256	19980522	00256	CE  	1998	5	22	AU980359         	1	19980324	G	2731	03103625	SCREW           			CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					ELEVATOR TAB	DISTORTED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM ACTUATOR SCREW BENT.						1	H	7	1 	3O	3	O		3A21    	E5CE
1998052200257	19980522	00257	CE  	1998	5	22	AU980360         	1	19980324	G	2731	1260759	CONTROL CABLE   		12607510    	CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					ELEVATOR TAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM CABLES P/N 126075-9 AND P/N 126075-10 CORRODED.						1	H	7	1 	3O	3	O	 	3A21    	E5CE
1998052200258	19980522	00258	NM  	1998	5	22	AU980361         	1	19980402	G	3250		CAM             			PIPER 	PA60  	PA60600A    	7106002	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					NLG  STEERING	INCORRECT FIT   	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) NOSE WHEEL CENTERING CAM INCORRECTLY INSTALLED PREVENTING CORRECT RETRACTION OF NOSE LANDING GEAR.  PERSONNEL/MAIN	TENANCE ERROR.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998052200259	19980522	00259	CE  	1998	5	22	AU980362         	1	19980223	G	3244	22X77510	TIRE            	GOODYEAR    	22X77510    	CESSNA	404   	404CESSNA   	2075901	CE  										TIRE	FAULTY          	W				K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		LD	LANDING        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR WOULD NOT EXTEND DUE TO TIRE CATCHING IN THE WHEEL WELL.  AIRCRAFT LANDED WITH THE RT MLG 	RETRACTED.  TIRE IS FROM A FAULTY BATCH AND APPEARS TO HAVE BECOME OVERSIZE DURING SERVICE.					1	L	7	2 	3O				A25CE
1998052200260	19980522	00260	EU  	1998	5	22	AU980363         	1	19980326	G	5610	CAP101018	WINDSHIELD      			MUDRY 	10    	CAP10B      		EU  	LYC   	O360  	AEIO360B2F  	41514	EA  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) FORWARD WINDSCREEN CRACKED.  CRACK ORIGINATED FROM A CRACK REPAIR CARRIED OUT IN JULY 1997.						1	L	7	1 	3O	3	O		A36EU   	1E10
1998052200261	19980522	00261	CE  	1998	5	22	AU980364         	1	19980225	G	2612	99120363	DETECTOR        			CESSNA	500   	500CESSNA   	2076602	CE  	PWA   	JT15  	JT15D1      	52060	NE  					FIRE DETECTION	BROKEN          	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) FIRE WIRE BROKEN GIVING FALSE FIRE INDICATION.						1	L	7	2 	4F	4	F		A22CE   	E1NE
1998052200262	19980522	00262	CE  	1998	5	22	AU980365         	1	19980220	G	5310		AIRCRAFT        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AIRCRAFT DESTROYED IN ACCIDENT.  NO FURTHER INFORMATION PROVIDED.						1	H	7	1 	3O	3	O		3A19    	E252
1998052200263	19980522	00263	CE  	1998	5	22	AU980366         	1	19980323	G	5311		FRAME           			CESSNA	188   	A188B       	2073005	CE  										FUSELAGE MAIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE TUBULAR FRAME CRACKED IN AREA OF RT OUTBOARD LANDING GEAR ATTACHMENT POINT.  PART TC:  2,150.						1	L	7	1 	3O				A9CE
1998052200264	19980522	00264	CE  	1998	5	22	AU980367         	1	19980323	G	5540	07311007	HINGE           			CESSNA	188   	A188B       	2073005	CE  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP RUDDER HINGE CRACKED FROM CORNER RADIUS.  PART TC:  2,150.						1	L	7	1 	3O				A9CE
1998052200265	19980522	00265	CE  	1998	5	22	AU980368         	1	19980323	G	5531	07310261	SPAR            			CESSNA	188   	A188B       	2073005	CE  										VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER REAR SPAR CRACKED BETWEEN TOP AND BOTTOM ATTACHMENT BOLTS.  SPAR HAD PREVIOUSLY BEEN CRACKED A	ND STOP DRILLED WITH CRACKING NOW CONTINUING PAST THE STOP DRILL HOLES.  CRACK LENGTHS APPROXIMATELY 12.7MM (0.5 INCH). 	 PART TC:  2,150.				1	L	7	1 	3O				A9CE
1998052200266	19980522	00266	CE  	1998	5	22	AU980369         	1	19980223	G	5540	07311007	HINGE           		07311009    	CESSNA	188   	A188B       	2073005	CE  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP AND MIDDLE RUDDER ATTACHMENT HINGES PN  0731100-7 AND PN  0731100-9 CRACKED.						1	L	7	1 	3O				A9CE
1998052200267	19980522	00267	CE  	1998	5	22	AU980370         	1	19980323	G	5551	07321008	HINGE           			CESSNA	188   	A188B       	2073005	CE  										ELEV RT OUTB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT OUTBOARD ELEVATOR HINGE CRACKED IN CORNER RADIUS.  PART TC:  2,150.						1	L	7	1 	3O				A9CE
1998052200268	19980522	00268	CE  	1998	5	22	AU980371         	1	19980323	G	5551	073210111	HINGE           		073210110   	CESSNA	188   	A188B       	2073005	CE  										HORIZONTAL STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAILPLANE AFT BOTTOM HINGE BOLTS LOOSE CAUSING HINGES PN 0732101-10 AND PN 0732101-11 TO WEAR BEYOND LIMITS.  PART	 TC:  2,150.					1	L	7	1 	3O				A9CE
1998052200269	19980522	00269	CE  	1998	5	22	AU980372         	1	19980406	G	3233	MS21242S4K	ROD END         			CESSNA	404   	404CESSNA   	2075901	CE  										NLG ACTUATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR ROD END FAILED DUE TO STRESS CORROSION IN THE AREA ADJACENT TO THE THREADED SECTION.  N	OSE LANDING GEAR COLLAPSED ON LANDING.					1	L	7	2 	3O				A25CE
1998052200270	19980522	00270		1998	5	22	AU980373         	1	19980308	G	3213	AN315A	BOLT            			AMTR  		KR2         												MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR BOLTS (4 OFF) SNAPPED OFF.									0
1998052200271	19980522	00271	SO  	1998	5	22	AU980374         	1	19980406	G	7120		MOUNT           			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH LOWER RUBBER ENGINE MOUNTS FITTED THE WRONG WAY AROUND.  PERSONNEL/MAINTENANCE ERROR.						1	L	7	1 	3O	3	O	 	2A13    	E274
1998052200272	19980522	00272	GL  	1998	5	22	AU980375         	3	19980331	G	6110	1C160DTM	PROPELLER       			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER ASSY	DAMAGED         	W				K				NONE                    				C			F.O.D.                    			LD	LANDING        	1			AU	S 										(AUS) PROPELLER CONTACTED GROUND SERVICING EQUIPMENT.  PROPELLER WRITTEN OFF AND ENGINE CRANKCASE CRACKED.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998052200273	19980522	00273	SW  	1998	5	22	AU980376         	1	19980406	G	2910	27810322755	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					HYDRAULIC	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) HYDRAULIC PIPE CRACKED AND LEAKING AT FLARED END.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
1998052200274	19980522	00274		1998	5	22	AU980377         	4	19980302	G	3457	1768001	GPS SYSTEM      		174500101010	CESSNA	500   	560CESSNA   	2076750	CE  										COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					255					(AUS) GNS-XES GIVES ERRATIC INFORMATION.						2	L	7	2 	4F			RT	A22CE
1998052200275	19980522	00275	EA  	1998	5	22	AU980378         	2	19980406	G	7320	LW120980100	PIPE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					RT ENG NR 4 INJ	FRACTURED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			2132 				L114761			(AUS) RT ENGINE NR 4 INJECTOR LINE FRACTURED ADJACENT TO THE INJECTOR NOZZLE.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998052200276	19980522	00276	CE  	1998	5	22	AU980379         	1	19980317	G	2435	03600907	BEARING         	LEARSIEGLER 		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					STARTER/GEN	COLLAPSED       	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CL	CLIMB          	1			AU	S 					1356					(AUS) RT ENGINE STARTER/GENERATOR FORWARD BEARING COLLAPSED.  PART TC:  1,010.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998052200277	19980522	00277	SO  	1998	5	22	AU980380         	2	19980217	G	8530	21935	ROCKER ARM      			CESSNA	172   	172E        	2072412	CE  	CONT  	O300  	O300C       	17022	SO  					NR 4 CYL INT VLV	BROKEN          	W				K				NONE                    				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			AU	S 							21935			(AUS) NR 4 CYLINDER INLET VALVE ROCKER ARM BROKEN AND PUSHROD BENT.   PART TC:  3,090.						1	H	7	1 	3O	3	O	NT	3A12    	E253
1998052200278	19980522	00278	NE  	1998	5	22	AU980381         	2	19980403	G	7250		TURBINE         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2 ENG	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							61412			(AUS) NR 2 ENGINE POWER SECTION FAILED.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998052200279	19980522	00279	GL  	1998	5	22	AU980382         	1	19980408	G	6220	281432015	BEARING         			ENSTRM	F28   	280C        	3300505	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					MAIN ROTOR HEAD	FAILED          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							L1723151A			(AUS) MAIN ROTOR HUB `LAMAFLEX' BEARING FAILED IN-FLIGHT.						1	G	7	1 	3O	3	O		H1CE    	1E10
1998052200280	19980522	00280	SO  	1998	5	22	AU980383         	2	19980406	G	8500	528021	ENGINE          		643986      	PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520B    	17040	SO  					ENGINE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			769  		528021		528021			(AUS) BROKEN MAIN BEARING PIECES FOUND IN SUMP.  AFTER ENGINE STRIP-DOWN, THE FOLLOWING DEFECTS WERE FOUND:  1.  OVERSIZ	ED PISTON AND CYLINDER ASSEMBLIES FITTED.  2.  SEVERE BEARING SADDLE FRETTING CAUSING MAIN BEARING MIGRATION.  3.  CRANK	CASE SEVERELY CRACKED AT NR 2 AND NR 3 MAIN BEARING  JOURNALS.  4.  PISTON PINS WORN BEYOND LIMITS.  5.  IT APPEARS DURI	NG LAST OVERHAUL, THE MAIN BEARING SADDLES WERE COATED WITH A GASKET COMPOUND AND CIRCLE OF SILK THREAD LAID  AROUND THE	 THROUGH BOLT HOLES.  PERSONNEL/MAINTENANCE ERROR.  UNAPPROVED PROCEDURE AND REPAIR.  PART TC:  2,297.		1	L	7	1 	3O	3	O	RT	A25SO   	E8CE
1998052200281	19980522	00281	NM  	1998	5	22	AU980384         	1	19980404	G	3230	4500221	SHAFT           			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR PIVOT SHAFT CRACKED.  PART TC:  5,760.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998052200282	19980522	00282	EA  	1998	5	22	AU980385         	2	19980318	G	8530	LW12425	VALVE GUIDE     		LW12425     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENG INLET	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ECNZ102921		L1405448A			(AUS) ENGINE INLET VALVE GUIDE FOUND LOOSE IN HEAD.						1	L	7	2 	3O	3	O		1A10    	1E4
1998052200283	19980522	00283	EA  	1998	5	22	AU980386         	2	19980403	G	8530	25288	POST            		72242       	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 3 CYL EXH VLV	BROKEN          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			1776 		25288		L538261A			(AUS) NR 3 CYLINDER EXHAUST VALVE ROCKER POST FAILED.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998052200284	19980522	00284	CE  	1998	5	22	AU980387         	1	19980407	G	2460	CM358950	CIRCUIT BREAKER 			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					DC POWER DISTRIB	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) AVIONICS CIRCUIT BREAKER SWITCH SMOKING.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998052200285	19980522	00285	SW  	1998	5	22	AU980388         	1	19980320	G	3221	AN12H15A	BOLT            			AIRTRC	AT500 	AT502       	0390303	SW  										TAIL WHEEL	SHEARED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) TAIL WHEEL SPRING TO SWIVEL ATTACHMENT BOLTS SHEARED DUE TO HEAVY LANDING.  PART TC:  534.						1	L	7	1 	3T			NC	A9SW
1998052200286	19980522	00286		1998	5	22	AU980389         	4	19980331	G	6122	210681	CSU             	WOODWARD    	210681      	SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROP GOV	DAMAGED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			1481 		1993841					(AUS) PROPELLER CSU LEAKING OIL.  INVESTIGATION FOUND THAT THE LOWER ENGINE COWL HAD WORN THROUGH THE CSU LOWER BODY.						1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920
1998052200287	19980522	00287	EU  	1998	5	22	AU980390         	1	19980326	G	3213	DRG225684DRG2	BEARING         	MESSIER     	200920003   	STBROS	SD3   	SD360       	8100606	EU  										MLG	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					DRG225684DRG					(AUS) DURING AD/SD3-60/48 (STUB WING SHEAR DECK AND RIB CORROSION INSPECTION), BOTH MAIN UNDERCARRIAGE SHOCK STRUT GLAND	 NUTS PN 200920604 WERE FOUND SHEARED.  FURTHER INVESTIGATION REVEALED THAT THE BEARING PN 200920638 HAD PREVIOUSLY BEEN	 FITTED UPSIDE DOWN.  THIS MEANT THAT THERE WAS NO RECESS FOR SCRAPER SEAL PN 511065-31.4 TO FIT INTO, THEREFORE, WHEN T	HE GLAND NUT WAS TIGHTENED UP AGAINST THE SCRAPER SEAL AND NOT THE SLEEVE PN 00920631, IT PRODUCED A LOAD ON THE INNER E	DGE OF THE FLANGE CAUSING THE FLANGE TO FAIL.  PERSONNEL/MAINTENANCE ERROR.		2	H	7	2 	4T			 	A41EU
1998052200288	19980522	00288	NE  	1998	5	22	AU980391         	2	19980409	G	7261		ENGINE          			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					LE ENG	OIL LOSS        	W				K				NONE                    				K	I		FLUID LOSS                	FLT. ATTITUDE INST.       		CL	CLIMB          	1			AU	S 							115399			(AUS) DURING CLIMB, THE LT ENGINE OIL PRESSURE FLUCTUATED, BUT DID NOT DROP TO ZERO.  ENGINE WAS REMOVED FOR INVESTIGATI	ON AND REPAIR FOR EXCESSIVE OIL CONSUMPTION FOLLOWING EXTENSIVE CHECKS AND GROUND RUNS.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998052200289	19980522	00289	CE  	1998	5	22	AU980392         	1	19980201	G	5511	12326241	STRUCTURE       			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520H    	17040	SO  					HORIZONTAL STAB	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER SPAR CAP CRACKED IN AREA OF THE LOWER REAR MOUNT BOLT HOLES.  CRACK LENGTHS 12.7MM (0.5 INCH	).  INVESTIGATION FOUND NEW PN 1232624-1 REINFORCEMENTS (SE 84-17) HAD BEEN FITTED IN AMERICA (29JUL84), BUT HAD BEEN IN	STALLED UPSIDE DOWN LEAVING THE LOWER SPAR CAP UNSUPPORTED AROUND THE BOLT HOLES.  PERSONNEL/MAINTENANCE ERROR.				1	H	7	1 	3O	3	O	 	3A21    	E8CE
1998052200290	19980522	00290	EA  	1998	5	22	AU980393         	2	19980226	G	8530	ECNZ9230F	SPARK PLUG      		76190       	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					LT ENG	SEPARATED       	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TX	TAXI/GRND HDL  	1			AU	S 					ECNZ9230F		L1373648			(AUS) LT ENGINE POWER DOWN DURING PRE TAKE-OFF CHECKS.  INVESTIGATION FOUND NR 4 CYLINDER UPPER SPARK PLUG HAD SEPARATED	 FROM THECYLINDER.  CAUSE APPEARS TO BE FROM EROSION OF THE SPARK PLUG HOLE UNDER THE HELICOIL.  SUSPECT FROM A VOID FOR	MED WHEN WELD REPAIRS WERE CARRIED OUT.				1	H	7	2 	3O	3	O		6A1     	1E4
1998052200291	19980522	00291	EA  	1998	5	22	AU980394         	2	19980326	G	8520	L3256836A	CRANKCASE       								LYC   	O360  	O360A4M     	41514	EA  					ENGINE	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L3256836A		L3256836A			(AUS) ENGINE CRANKCASE TUNNEL MEASUREMENTS OUT OF LIMITS.											3	O			E286
1998052200292	19980522	00292	NM  	1998	5	22	AU980395         	1	19980402	G	6310	V31001	SWITCH          			ROBSIN	R22   	R22BETA     		NM  										ENGINE/TRANS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1448					(AUS) CLUTCH ACTUATOR WOULD NOT ENGAGE.  SUSPECT UPLIMIT MICROSWITCHES.  PART TC:  1,458.						1	G	7	1 	3O				H10WE
1998052200293	19980522	00293	SW  	1998	5	22	AU980396         	1	19980409	G	3233	287784	O-RING          			SWRNGN	SA226 	SA226TC     	8780404	SW  										OUTB MLG ACT	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTBOARD MLG ACTUATOR BLANK LEAKING HYDRAULIC OIL DUE TO BROKEN O-RING SEAL.						2	L	7	2 	4T			RT	A8SW
1998052200294	19980522	00294	SO  	1998	5	22	AU980397         	1	19980327	G	3230	9529902	STUD            		9564307     	PIPER 	PA28  	PA28R201    	7102816	SO  										MLG BRACE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MLG SIDE BRACE STUD (1 OFF) CRACKED IN RADIUS.  FOUND DURING INSPECTION IAW AD/PA28/91.						1	L	7	1 	3O				2A13
1998052200295	19980522	00295	CE  	1998	5	22	AU980398         	1	19980324	G	2821	07560097	FILTER          			CESSNA	210   	210K        	2073446	CE  										ACFT FUEL FILTER	CRUSHED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL FILTER ASSEMBLY STRAINER FOUND CRUSHED ALLOWING UNFILTERED FUEL INTO FUEL PUMP AND ENGINE SYSTEM.  PERSONNEL/	MAINTENANCE ERROR.					1	H	7	1 	3O			 	3A21
1998052200296	19980522	00296	WP  	1998	5	22	AU980399         	2	19980404	G	7322	89778021	FCU             	WOODWARD    	89778021    						GARRTT	TPE331	TPE33110U   	01514	WP  					RT ENGINE	MALFUNCTIONED   	W				K				NONE                    				E	X		VIBRATION/BUFFET          	ENGINE FLAMEOUT           		LD	LANDING        	1			AU	S 					2123540					(AUS) RIGHT ENGINE FUEL CONTROL UNIT (FCU) FAULTY.											4	T			E4WE
1998052200297	19980522	00297	GL  	1998	5	22	AU980400         	3	19980414	G	6112	015	CONTACTOR       													ROTOL	R352	R3526123F1  	GL  	PROPELLER DE-ICE	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					015					(AUS) LEFT PROPELLER SPINNER ANTI-ICE SYSTEM CONTACTS FAULTY.																6	C	P16NG
1998052200298	19980522	00298	SO  	1998	5	22	AU980401         	1	19980319	G	8120	4091709001	COMPRESSOR BLADE	GARRTT      	4091709001  	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					EXHAUST TURBO	ERODED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			595  		IK0159		L42868A			(AUS) TURBOCHARGER COMPRESSOR BLADE LEADING EDGES SEVERELY ERODED.  DURING INVESTIGATION, AN AN363C-362 NUT WITH THE REM	AINS OF A SCREW STILL ATTACHED WAS FOUND ON THE TOP OF THE INDUCTION AIR FILTER BETWEEN THE FILTER AND THE TURBOCHARGER.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998052200299	19980522	00299	SO  	1998	5	22	AU980402         	2	19980324	G	8530	646286	VALVE           		639272PO10  	CESSNA	210   	T210L       	2073449	CE  	CONT  	O520  	TSIO520H    	17040	SO  					ENG EXH	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			304  		BT8458846084		506872			(AUS) THREE ENGINE CYLINDERS REMOVED DUE TO LOW COMPRESSION.  ALL EXHAUST VALVES PN 646286 AND VALVE GUIDES PN 636242 WE	RE FOUND TO BE WORN BEYOND LIMITS WITH 0.508MM (.020 INCH), 1.016MM (.041 INCH) AND 1.168MM (.046 INCH) CLEARANCES.					1	H	7	1 	3O	3	O		3A21    	E8CE
1998052200300	19980522	00300	SO  	1998	5	22	AU980403         	2	19980407	G	8550	632623	PUMP            			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					ENG OIL	SEIZED          	W				K	E			NONE                    	ENGINE SHUTDOWN         			O			OTHER                     			CL	CLIMB          	1			AU	S 			65   				276125R			(AUS) ENGINE OIL PUMP SEIZED.  SECONDARY DAMAGE CAUSED TO THE REST OF THE ENGINE.						1	L	7	2 	3O	3	O		A25CE   	E7CE
1998052200301	19980522	00301	EA  	1998	5	22	AU980404         	2	19980416	G	8530	LW11633	CYLINDER        			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					HEAD/BARREL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			385  				L1741215			(AUS) ENGINE CYLINDER LEAKING OIL AT BARREL TO HEAD JOINT AND BETWEEN FIRST AND SECOND BOTTOM FINS ON BARREL AREAS.  CYL	INDER WAS REMOVED AND A PENETRANT CHECK FOUND A CRACK 40MM (1.57 INCH) IN LENGTH (INSIDE) AT THE BARREL TO HEAD JOINT. P	ART TC:  1,327.				1	L	7	1 	3O	3	O		A18SO   	E223
1998052200302	19980522	00302	SO  	1998	5	22	AU980405         	1	19980417	G	7110	4183808	COWLING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					RT ENGINE	SEPARATED       	W				K				NONE                    				D			INFLIGHT SEPARATION       			CL	CLIMB          	1			AU	S 										(AUS) RIGHT ENGINE TOP COWL SEPARATED DURING FLIGHT.  INVESTIGATION FOUND ALL FASTENERS WERE IN PLACE AND IT APPEARS THA	T THE FIBREGLASS NOSE COWL UPPER SECTION DE-BONDED FROM THE ATTACHMENT ANGLE BRACKET RETAINING FASTENERS AT SECTION BEHI	ND THE PROPELLER.  DAMAGE CAUSED TO WING LEADING EDGE.  PERSONNEL/MAINTENANCE ERROR.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998052200303	19980522	00303	SO  	1998	5	22	AU980406         	1	19980119	G	5751	8639202	BRACKET         			PIPER 	PA32  	PA32R301    	7103218	SO  										AILERON HINGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON HINGE BRACKETS (4 OFF) CONTAINED SEVERE EXFOLIATION CORROSION.  PART TC:  1,627.						1	L	7	1 	3O				A3SO
1998052200304	19980522	00304	EA  	1998	5	22	AU980407         	2	19980325	G	7250	3026812	BLADE           			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  					TURBINE SECTION	SEPARATED       	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					90909					(AUS) ENGINE POWER TURBINE BLADE SEPARATED APPROXIMATELY 12.7MM (0.5 INCH) FROM THE BLADE ROOT.  ECONDARY DAMAGE TO OTHE	R BLADES AND EXHAUST DUCT ASSEMBLY.					1	L	7	2 	4T	4	T		A21SO   	E4EA
1998052200305	19980522	00305	CE  	1998	5	22	AU980408         	1	19980220	G	5312	05121871	BULKHEAD        		05121872    	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2G     	41508	EA  					LT RT DOOR POST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT LOWER AFT DOOR POST BULKHEADS (PN 0512187-1 LT AND PN 0512187-2 RT) CRACKED.  FOUND DURING INSPECTION IA	W SB SEB 97-1.  PART TC:  5,920.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998052200306	19980522	00306	CE  	1998	5	22	AU980409         	1	19980415	G	3213	5141001214	BARREL          			CESSNA	310   	310R        	2074245	CE  										RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR STRUT BARREL BROKEN.  RT MLG COLLAPSED DURING LANDING.						1	L	7	2 	3O				3A10
1998052200307	19980522	00307	NE  	1998	5	22	AU980410         	1	19980404	G	2422	7655003007	INVERTER        			SKRSKY	S76   	S76A        	8143006	NE  										AC INVERTER	FAILED          	W				K				NONE                    				J	H		WARNING INDICATION        	ELECT. POWER LOSS-50 PC   		CL	CLIMB          	1			AU	S 					2934					(AUS) INVERTER FAILED.  INVERTER FAIL LIGHT ILLUMINATED.  SHORTLY AFTERWARDS, THE AIRCRAFT GENERATOR WARNING ILLUMINATED	 CAUSING A COMPLETE LOSS OF AIRCRAFT SERVICES.  INVESTIGATION FOUND THE CAUSE OF THE FAILURE TO BE A FAULTY AC GENERATOR	 PLUG.				1	G	7	2 	3U				H1NE
1998052200308	19980522	00308	SO  	1998	5	22	AU980411         	1	19980326	G	2436		DIODE           			GULSTM	AA5   	AA5B        	3960105	SO  	LYC   	O360  	O360A4K     	41514	EA  					DC REGULATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) DURING CRUISE, THE 'OVER-VOLTAGE' PROTECTION ZENER DIODE FAILED, CAUSING EXTENSIVE FAILURE OF ELECTRICAL AND AVION	ICS EQUIPMENT.					1	L	7	1 	3O	3	O		A16EA   	E286
1998052200309	19980522	00309	CE  	1998	5	22	AU980412         	1	19980401	G	2810		CAP             		SK210136    	CESSNA	210   	210L        	2073448	CE  										FUEL STORAGE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING FUEL TANK CAP ALLOWING RAIN INGRESS.  SUSPECT CAUSED BY DEFORMATION OF THE RAISED AREA OF THE ADAPTER. A	DAPTER AND COVERPLATE REPLACED.					1	H	7	1 	3O				3A21
1998052200310	19980522	00310	GL  	1998	5	22	AU980413         	3	19980415	G	6114		FLYWEIGHT       			BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	PROPELLER HUB	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 			1430 					AU7713		(AUS) ON THE FIRST SHUTDOWN OF THE DAY, THE PROPELLER WOULD NOT LATCH AND WENT INTO FEATHER.  LATER IN THE DAY, THE PROP	ELLER FAILED TO ACHIEVE MAXIMUM RPM. THE PROPELLER WAS REMOVED AND INVESTIGATION AFTER REMOVING THE CYLINDER FOUND SUBST	ANTIAL DAMAGE TO THE INTERNAL COMPONENTS.  DUE TO THE DAMAGE IT WAS NOT POSSIBLE TO ESTABLISH THE CAUSE BUT IT IS SUSPEC	TED THAT THE WEIGHTS MAY HAVE FAILED DUE TO UNEVEN LOADING OR AS A RESULT OF IMPACT LOADS.			1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920
1998052200311	19980522	00311	CE  	1998	5	22	AU980414         	1	19980218	G	7820		PIPE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE EXH	BULGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE EXHAUST PIPES (BOTH ENGINES) HAVE SEVERE BULGING.  THREE OF THE FOUR PIPES HAVE IMPROPER PREVIOUS REPAIRS.						1	L	7	2 	3O	3	O		3A16    	E5CE
1998052200312	19980522	00312	CE  	1998	5	22	AU980416         	1	19980218	G	3230	3581512512	TUBE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					LANDING GEAR RET	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT LANDING GEAR DRIVE TUBE CREASED AT INBOARD FITTING (GEARBOX END).  THE CREASE WAS RUSTED AND APPEARS TO HAVE 	BEEN DAMAGED SOME TIME AGO AND WAS CLOSE TO FAILURE.					1	L	7	2 	3O	3	O		3A16    	E5CE
1998052200313	19980522	00313	CE  	1998	5	22	AU980417         	1	19980218	G	2710		CONTROL ARM     			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					AILERON CONTROL	MISRIGGED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL SYSTEM RIGGED INCORRECTLY. THE AILERON BELLCRANKS WERE NOT HITTING THE STOPS AND THE AILERONS WERE	 SHORT OF TRAVEL BY FIVE DEGREES.  PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O	 	3A16    	E5CE
1998052200314	19980522	00314	NM  	1998	5	22	AU980418         	1	19980331	G	2910	D10010D06	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HYDRAULIC SYS	CRACKED         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC LINE PERMASWAGE FITTING BROKEN.  THE COLLAR HAD CRACKED AND BROKEN APPROXIMATELY 4.76MM (0.1875 INCH) BE	LOW NUT.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998052200315	19980522	00315	NE  	1998	5	22	AU980419         	2	19980404	G	7261		CHIP DETECTOR   								CFMINT	CFM56 	CFM565A1    		NE  					ENG SCAV	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							731139			(AUS) REAR SCAVENGE CHIP DETECTOR FOUND WITH SIGNIFICANT `M50' METAL DEBRIS.											4	F			E29NE
1998053000003	19980530	00003	EU  	1998	5	30	AU980420         	1	19980411	G	4920	R138CANSETTSN0	COMPRESSOR      	GARRTT      	GTCP36300A  	AIRBUS	320   	A320212     		EU  										APU CORE ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				O	T	J	OTHER                     	ENGINE CASE PENETRATION   	WARNING INDICATION        	TX	TAXI/GRND HDL  	1			AU	S 					R138CANSETTS					(AUS) APU LOAD COMPRESSOR FAILED AT THE GROOVED SECTION OF THE AFT FACE DAMPING RING.  COMPRESSOR AND DIFFUSER PIECES HA	D EXITED THROUGH THE APU SCROLL CASING SEVERING AN OIL LINE. METAL DEBRIS HAD ALSO PUNCHED A 100MM (4 INCH) HOLE THROUGH	 THE LOWER APU ACCESS DOOR.  PART TC:  16,422.				2	L	7	2 	4F			RT	A28NM
1998052200316	19980522	00316	NE  	1998	5	22	AU980421         	2	19980405	G	7200		TURBINE ENGINE  			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE	FAILED          	W		A		K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LF05581A			(AUS) DURING ENGINE GROUND RUN, METALLIC SPARKS EMITTED FROM THE JETPIPE IN LARGE QUANTITIES.  UNDER INVESTIGATION.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998052200317	19980522	00317	CE  	1998	5	22	AU980422         	1	19980409	G	5312		BULKHEAD        			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470U      	17026	SO  					FWD FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FUSELAGE BULKHEAD AND BRACKET AT LOCATED AT STN 27.25 CRACKED.  BULKHEAD SUPPORTS THE PULLEYS FOR THE NOSE	 WHEEL STEERING CABLE.  PART TC:  6,445.					1	L	7	2 	3O	3	O		3A10    	3E1
1998052200318	19980522	00318	CE  	1998	5	22	AU980423         	1	19980323	G	2840	10038901823	SWITCH          	ITT         	980871103P  	BEECH 	200   	200BEECH    	1152920	CE  										LT FUEL IND	HIGH RESISTANCE 	W				K				NONE                    				P			NO WARNING INDICATION     			IN	INSP/MAINT     	1			AU	S 					6403					(AUS) LEFT FUEL LOW PRESSURE LIGHT NOT ILLUMINATING.  INVESTIGATION FOUND HIGH RESISTANCE AND CORROSION ON THE LOW PRESS	URE FUEL SWITCH PINS AND PLUG.					1	L	7	2 	4T				A24CE
1998052200319	19980522	00319	CE  	1998	5	22	AU980424         	1	19980417	G	3260		SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT MLG UP	OUT OF ADJUST   	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		CL	CLIMB          	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR `UP' POSITION MICROSWITCH OUT OF ADJUSTMENT.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998052200320	19980522	00320	CE  	1998	5	22	AU980425         	1	19980416	G	2750		SWITCH          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TE FLAP CONTROL	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) FLAP UPLIMIT MICROSWITCH OUT OF ADJUSTMENT CAUSING THE FLAP MOTOR TO FAIL.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998052200321	19980522	00321	CE  	1998	5	22	AU980427         	1	19980324	G	3300		LIGHT           			CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					LIGHTING SYSTEM	INOPERATIVE     	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AU	S 										(AUS) ROTATING BEACON, LANDING LIGHT, TAXI LIGHT AND PANEL LIGHTING INOPERATIVE.  PERSONNEL/MAINTENANCE ERROR.						1	H	7	1 	3O	3	O	 	3A21    	E5CE
1998052200322	19980522	00322	SO  	1998	5	22	AU980428         	2	19980324	G	7310		FITTING         			CESSNA	210   	210K        	2073446	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE FUEL DIST	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL PRESSURE FITTING ON ENGINE FUEL PUMP CHAFED THROUGH.						1	H	7	1 	3O	3	O		3A21    	E5CE
1998052200323	19980522	00323	CE  	1998	5	22	AU980429         	1	19980324	G	2410		BUSHING         			CESSNA	210   	210K        	2073446	CE  										ALT ATTACH	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR ATTACHMENT BUSHES VERY LOOSE AND EXCESSIVELY WORN.						1	H	7	1 	3O				3A21
1998052200324	19980522	00324	CE  	1998	5	22	AU980430         	1	19980324	G	5321		FLOOR           			CESSNA	210   	210K        	2073446	CE  										FUSELAGE FLOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BOTH PILOT'S AND COPILOT'S FLOOR SKINS BADLY CORRODED FORWARD OF DOOR.						1	H	7	1 	3O				3A21
1998052200325	19980522	00325	CE  	1998	5	22	AU980432         	1	19980324	G	2700		BEARING         			CESSNA	210   	210K        	2073446	CE  										EMPENNAGE STRUCT	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL ELEVATOR, ELEVATOR BELLCRANK AND RUDDER BEARINGS SEIZED.						1	H	7	1 	3O				3A21
1998052200326	19980522	00326	SW  	1998	5	22	AU980434         	1	19980415	G	3230		HYDRAULIC SYSTEM			FRCHLD	SA227 	SA227DC     	3377521	SW  										LANDING GEAR RET	MALFUNCTION     	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) DURING CLIMB, THE HYDRAULIC PRESSURE ANNUNCIATOR ILLUMINATED AND THE HYDRAULIC PRESSURE FELL TO 800 PSI.  THE LG I	NITIALLY WOULD NOT RETRACT, BUT RETRACTED AFTER APPROXIMATELY TWO MINUTES.  GROUND RETRACTION CHECKS COULD NOT DUPLICATE	 THE PROBLEM.  HYDRAULIC SYSTEM WAS BLED AND FUNCTIONAL CHECK OF HYDRAULIC SYSTEM CARRIED OUT AND AIRCRAFT RETURNED TO S	ERVICE.			2	L	7	2 	4T			RT	A18SW
1998052200327	19980522	00327	SO  	1998	5	22	AU980436         	1	19980407	G	3211	21418T005	BOLT            			AYRES 	S2    	S2RG10      		SO  										RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) RIGHT UNDERCARRIAGE BOLT BROKEN.  INSPECTION REVEALED THE BOLT MAY HAVE BEEN CRACKED FOR SOME TIME.  RIGHT FRONT B	USHING (WHERE BOLT FITS) CRACKED OUT OF BRACKET, THIS MAY HAVE CAUSED THE FAILURE.  LEFT BUSHING CRACKED BUT NOT SEPARAT	ED AND ITS BOLT WAS STILL INTACT.  PART TC:  1,446.				1	L	7	1 	3T			NC	A4SW
1998052200328	19980522	00328	SW  	1998	5	22	AU980437         	1	19980423	G	6320	2060400203	GEAR            		JR3TYPE     	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R GEARBOX	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			380  		BKW11302		CAE831527			(AUS) DURING A SCHEDULED INSPECTION, METAL WAS FOUND ON THE M/R TRANSMISSION'S CHIP DETECTORS.  ON TEAR DOWN INSPECTION,	 THE TRANSMISSION'S INPUT GEAR SHAFT WHICH FORMS THE INNER BEARING SURFACE FOR BEARING PN 206-040-031-107 RACE WAS FOUND	 TO HAVE SEVERE BRINELLING AND DESTRUCTIVE PITTING.  PART TC:  7,037.				1	G	7	1 	3U	3	U		H2SW    	E4CE
1998052200329	19980522	00329	NE  	1998	5	22	AU980438         	2	19980408	G	7230		FAN BLADE       								CFMINT	CFM56 	CFM565A1    		NE  					TURBINE ENGINE	BIRD STRIKE     	W				K				NONE                    				E	C		VIBRATION/BUFFET          	F.O.D.                    		TO	TAKEOFF        	1			AU	S 							731158			(AUS) RIGHT ENGINE BIRD STRIKE.  BORESCOPE INSPECTION FOUND DAMAGE TO EIGHT FAN BLADES, OUTLET GUIDE VANES, AND ACOUSTIC	 LINERS.										4	F			E29NE
1998052200330	19980522	00330	NE  	1998	5	22	AU980439         	2	19980330	G	7322	A5435ANSETTSN0	FCU             			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENG	FAULTY          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 			277  		A5435ANSETTS		LF05859A			(AUS) NR 1 ENGINE FUEL CONTROL UNIT FAULTY.   PART TC:  27,087.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998052200331	19980522	00331	NE  	1998	5	22	AU980440         	2	19980417	G	7200		ENGINE          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ENGINE NR 2	MAKING METAL    	W				K				NONE                    				O	R		OTHER                     	PARTIAL RPM/PWR LOSS      		NR	NOT REPORTED   	1			AU	S 							LF05880A			(AUS) NR 2 ENGINE OIL FILTERS FULL OF METAL.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998052200332	19980522	00332	SO  	1998	5	22	AU980441         	2	19980331	G	7322	63255531	LEVER           		6297032     	CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  					ENG THROTTLE	BROKEN          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 					C299451AR		270413			(AUS) ENGINE THROTTLE CONTROL LEVER BROKEN AT STEEL BUSH INSERT END.						1	H	7	1 	3O	3	O		3A21    	E5CE
1998052200333	19980522	00333	CE  	1998	5	22	AU980442         	1	19980422	G	5712	ME70	RIB             		B76         	BEECH 	76    	76          	1153005	CE  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ME70					(AUS) WING RIBS (3 OF 4) CRACKED.  PART TC:  7,731.						1	L	7	2 	3O				A29CE
1998052200334	19980522	00334	EU  	1998	5	22	AU980443         	1	19980414	G	5523	115C3551	TRIM TAB        			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB CRACKED IN AREA ADJACENT TO THE SECOND INBOARD HINGE SEGMENT.  PART TC:  977.						1	L	7	1 	3O			NT	A57EU
1998052200335	19980522	00335	EU  	1998	5	22	AU980444         	1	19980423	G	5523	115C3551	TRIM TAB        			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB CRACKED IN AREA ADJACENT TO THE SECOND INBOARD HINGE SEGMENT.  PART TC:  53.						1	L	7	1 	3O			NT	A57EU
1998052200336	19980522	00336	SO  	1998	5	22	AU980445         	1	19980326	G	3213	025992	TRUNNION        			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	RT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR TRUNNION HOUSING SHEARED IN AREA JUST BELOW THE PIVOT BEARING.  LANDING GEAR COLLAPSED DUR	ING LANDING.  THE PROPELLER CONTACTED THE GROUND CAUSING THE ENGINE TO STOP.					1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920
1998052200337	19980522	00337	SO  	1998	5	22	AU980446         	1	19980422	G	5210		DOOR            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					FWD ENTRY	NOT CLOSED      	W				K				NONE                    				O	J		OTHER                     	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) FORWARD ENTRY DOOR INCORRECTLY CLOSED DUE TO DOOR ALIGNMENT MARKS BEING WORN OFF.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998052200338	19980522	00338	CE  	1998	5	22	AU980447         	1	19980406	G	2731	53150971	TRIM JACK       			CESSNA	340   	340CESSNA   	2076404	CE  										ELEV TAB CONTROL	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 										(AUS) ELEVATOR TRIM ACTUATOR SHAFT SCREW SEPARATED FROM THE ACTIVATING ROD DUE TO WORN THREADS.						1	L	7	2 	3O				3A25
1998052200339	19980522	00339	CE  	1998	5	22	AU980448         	1	19980416	G	3230	MS24171D1	RELAY           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LANDING GEAR RET	SHORTED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) LANDING GEAR MOTOR POWER RELAY SHORT CIRCUITED AND BURNED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998052200340	19980522	00340		1998	5	22	AU980449         	1	19980402	G	7120	DC0051	MOUNT           								ROTAX 	912   	ROTAX912    	55555	EU  					LT RT ENG	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					050					(AUS) LEFT AND RIGHT ENGINE MOUNT FRAMES WORN BY CARBURETOR INLET SCAT HOSE IN FOUR AREAS PROTECTED BY SPIRAP.  AREAS AF	FECTED ARE 12.7MM WIDE BY 0.794MM DEEP (0.5 INCH WIDE BY 0.0312 INCH DEEP).  PART TC:  199.										3	I			EXPE3I
1998052200341	19980522	00341	CE  	1998	5	22	AU980450         	1	19980418	G	2435	23078019	STARTER/GEN     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67R     	52043	NE  					LT ENGINE	FIRE            	W				K				NONE                    				H	B		ELECT. POWER LOSS-50 PC   	SMOKE/FUMES/ODORS/SPARKS  		TO	TAKEOFF        	1			AU	S 			355  							(AUS) LEFT STARTER/GENERATOR FAULTY.  FLAMES SEEN EXITING THE UNIT.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998052200342	19980522	00342	CE  	1998	5	22	AU980451         	1	19980406	G	3260		WARNING SYSTEM  			CESSNA	402   	402C        	207590R	CE  										LANDING GEAR	FAULTY          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR WARNING HORN FAILED TO OPERATE CORRECTLY.  AIRCRAFT LANDED WITH GEAR IN THE `UP' POSITION.  INVESTIGA	TION COULD FIND NO FAULTS WITH THE SYSTEM.					1	L	7	2 	3O				A7CE
1998052200343	19980522	00343	SO  	1998	5	22	AU980452         	1	19980417	G	2730	54569002	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR CONTROL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL CABLE FROM AUTOPILOT FRAYED.  FOUR OF SEVEN STRANDS BROKEN.						1	L	7	2 	3O			 	A20SO
1998052200344	19980522	00344	SO  	1998	5	22	AU980453         	1	19980417	G	2710	55405002	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  										AIL RUD BAL	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON/RUDDER BALANCE CABLE FRAYED AT TERMINAL FITTING.						1	L	7	2 	3O			 	A20SO
1998052200345	19980522	00345	EU  	1998	5	22	AU980454         	1	19980424	G	5523	115C3551	TRIM TAB        			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB CRACKED IN AREA ADJACENT TO THE SECOND INBOARD HINGE SEGMENT.  PART TC:  1,142.						1	L	7	1 	3O			NT	A57EU
1998052200346	19980522	00346	EU  	1998	5	22	AU980455         	1	19980424	G	5523	115C3551	TRIM TAB        			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB CRACKED IN THE AREA ADJACENT TO THE SECOND INBOARD HINGE SEGMENT.  PART TC:  86.						1	L	7	1 	3O			NT	A57EU
1998052200347	19980522	00347	EU  	1998	5	22	AU980456         	1	19980424	G	5523	115C3551	TRIM TAB        			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB CRACKED IN AREA ADJACENT TO THE SECOND INBOARD HINGE SEGMENT.   PART TC:  1,672.						1	L	7	1 	3O			NT	A57EU
1998052200348	19980522	00348	NM  	1998	5	22	AU980457         	1	19980224	G	7830	P8077SPECNO60B	GEARBOX         			BOEING	747   	747312      	1384932	NM  	PWA   	JT9   	JT9D7R4G2   	52054	NE  					THRUST REVERSER	JAMMED          	W				K				NONE                    				J			WARNING INDICATION        			LD	LANDING        	1			AU	S 					P8077SPECNO6		P715100			(AUS) AFTER LANDING, THE NR 2 ENGINE THRUST REVERSER FAILED TO STOW.  GROUND INVESTIGATION FOUND THE THRUST REVERSER'S N	R 3 GEARBOX JAMMED AND DAMAGED.					2	L	7	4 	4F	4	F	RT	A20WE   	E3NE
1998053000004	19980530	00004	EU  	1998	5	30	AU980458         	1	19980308	G	2133	90231570301	VALVE           			AIRBUS	320   	A320212     		EU  										PRESSURE REG	FAULTY          	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DURING CRUISE, THE CABIN ALTITUDE CLIMBED SUDDENLY.  MANUAL PRESSURIZATION WAS SELECTED AND AN ATTEMPT WAS MADE TO	 CLOSE THE OUTFLOW VALVE BUT THIS COULD NOT BE ACHIEVED.  GROUND TEST FOUND THE OUTFLOW VALVE PN 9023-15703-81 BEHAVED E	RRATICALLY.				2	L	7	2 	4F			RT	A28NM
1998052200349	19980522	00349	EU  	1998	5	22	AU980459         	1	19980428	G	2550	BL7505	CABLE           	BREEZE      	BL16600120  	SNIAS 	350   	AS350B      	8680801	EU  										HOIST	SHEARED         	W				O				OTHER                   				O			OTHER                     			HO	HOVERING       	1			AU	S 					M135					(AUS) DURING THE FINAL 2-3 METERS OF A TRAINING LIFT, THE HOIST OPERATOR PHYSICALLY LIFTED THE REMAINING LENGTH OF CABLE	 INSIDE THE CABIN. THE OPERATOR THEN ACTUATED THE HOIST 'RAISE' SWITCH TO WIND THE REMAINING CABLE AND THE CABLE FAILED 	LEAVING THE HOOKED END AND APPROXIMATELY 1.5 METERS OF THE CABLE IN THE OPERATORS HAND.  INITIAL INVESTIGATION SUGGESTS 	THAT THE CABLE HAD 'BIRD CAGED' AND EFFECTIVELY INCREASED THE CABLE DIAMETER WHICH THEN JAMMED INSIDE THE CABLE GUIDE CA	USING THE FAILURE.		1	G	7	1 	3U			 	H9EU
1998052200350	19980522	00350	CE  	1998	5	22	AU980460         	1	19980401	G	5741	202200556	FITTING         			CESSNA	177   	177RG       	2073709	CE  										WING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INSPECTION OF WING FITTINGS REVEALED RELATIVE MOVEMENT BETWEEN FITTINGS AND SPAR.  THE AIRCRAFT HAD BEEN TREATED W	ITH 'BOESHIELD' IN FEB 93.  PART TC:  4,830.					1	H	7	1 	3O				A20CE
1998052200351	19980522	00351	NM  	1998	5	22	AU980461         	1	19980402	G	2780	65B840862	CONTROLLER      			BOEING	747   	747312      	1384932	NM  										LE FLAPS	MISRIGGED       	W				O				OTHER                   				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			AU	S 										(AUS) DURING AFTER-FLIGHT INSPECTION, THE NR 15 KRUEGER FLAP WAS FOUND SEVERELY DAMAGED WITH SURFACE AND STRUCTURE TORN 	APART.  THE LEADING EDGE FLAP TORQUE TUBE BETWEEN THE OFFSET GEARBOX AND THE NO 15 FLAP OUTBOARD ROTARY ACTUATOR WAS FOU	ND TO HAVE THE OUTBOARD END FITTING RIVETS SHEARED.  THE CAUSE APPEARS TO HAVE BEEN ASSOCIATED WITH THE BINDING OF NR 16	 KRUEGER FLAP WHICH WAS FOUND TO BE MISRIGGED - CURRENTLY UNDER INVESTIGATION BY OPERATOR.			2	L	7	4 	4F			RT	A20WE
1998052200352	19980522	00352	CE  	1998	5	22	AU980462         	1	19980227	G	7931		LINE            			CESSNA	310   	310L        	2074230	CE  	CONT  	O470  	IO470*      	17026	SO  					ENGINE OIL PRESS	SLUDGED         	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DURING FLIGHT, THE RT ENGINE GAUGE DISPLAYED LOW OIL PRESSURE.  ENGINE GROUND RUN WITH A CALIBRATED OIL PRESSURE G	AUGE PLUMBED INTO SYSTEM WAS CARRIED OUT WITH NO FAULT FOUND.  SUSPECTING IT COULD HAVE BEEN A SLUDGE PROBLEM IN THE PRE	SSURE LINE BETWEEN THE GAUGE AND ENGINE, THE LINE WAS PURGED AND REFILLED WITH CLEAN OIL.				1	L	7	2 	3O	3	O		3A10    	E1CE
1998052200353	19980522	00353	NM  	1998	5	22	AU980463         	1	19980416	G	2612		CONNECTOR       			BOEING	727   	7272J4      	1384006	NM  										FIRE DETECTION	LOOSE           	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) DURING CLIMB, A FIRE WARNING ON THE NR 1 ENGINE WAS EXPERIENCED.  GROUND INVESTIGATION FOUND A LOOSE CRIMP ON THE 	'B' LOOP FIREWALL FORWARD PLUG.					2	L	7	3 	4F			RT	A3WE
1998052200354	19980522	00354	SW  	1998	5	22	AU980464         	1	19980413	G	3241	944003	VALVE           			FRCHLD	SA227 	SA227DC     	3377521	SW  										BRAKE ANTI-SKID	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					944003					(AUS) DURING A PRE-FLIGHT INSPECTION, THE PILOT FOUND HYDRAULIC OIL ALONG THE LENGTH OF THE FUSELAGE FROM THE BRAKE OVER	FLOW PORT.  SYSTEM TROUBLESHOOTING FOUND THAT THE LHS ANTI-SKID VALVE WAS LEAKING, PUMPING HIGH PRESSURE HYDRAULIC OIL I	NTO THE LOW PRESSURE SYSTEM.				2	L	7	2 	4T			RT	A18SW
1998052200355	19980522	00355	EU  	1998	5	22	AU980465         	1	19980410	G	3297		WIRE            			BAG   	JETSTM	JETSTM3107  	1500215	EU  										MLG POSITION	OPEN            	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) MLG WOULD NOT RETRACT AFTER TAKEOFF.  GROUND INVESTIGATION FOUND A WIRING FAULT ON THE NOSE GEAR SQUAT SWITCH.						2	L	7	2 	4T			RT	BA15CAA
1998052200356	19980522	00356		1998	5	22	AU980466         	1	19980428	G	7333		TRANSMITTER     								GARRTT	TPE331	TPE33110U   	01514	WP  					LT ENG FUEL FLOW	FAILED          	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 							P42126			(AUS) DURING CLIMB, THE LT ENGINE FUEL FLOW INDICATION FAILED.  TRANSMITTER WAS REPLACED AND THE CONNECTOR PLUG CLEANED.											4	T			E4WE
1998052200357	19980522	00357	EU  	1998	5	22	AU980467         	1	19980428	G	2934		INDICATION      			FOKKER	F27   	F27MK50     		EU  										HYD QTY	MALFUNCTION     	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) DURING FLIGHT, THE PILOT REPORTED THE HYDRAULIC LOW QUANTITY LIGHT HAD ILLUMINATED.  THE HYDRAULIC QUANTITY AND IN	DICATING SYSTEM WERE CHECKED AND NIL DEFECTS FOUND.					2	H	7	2 	4T			RT	A817
1998052200358	19980522	00358	CE  	1998	5	22	AU980468         	1	19980422	G	3211		SCREW           			CESSNA	310   	310R        	2074245	CE  										MLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FORWARD AND AFT TRUNNIONS PN 0822720-3 ATTACHMENT SCREWS LOOSE AND FORWARD TRUNNION LOWER THREE RIVETS SHEARE	D.					1	L	7	2 	3O				3A10
1998052200359	19980522	00359	EU  	1998	5	22	AU980469         	1	19980425	G	5523	115C3551	HINGE           			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TAB	DISBONDED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB PN 115C-3551 HINGE APPEARS DISBONDED TO FIBER REINFORCED PLASTIC STRUCTURE SECOND INBOARD SEGMEN	T.  ALSO, AN OUTBOARD EDGE CRACK WAS DEVELOPING FROM SAME LOCATION.  PART TC:  171.					1	L	7	1 	3O			NT	A57EU
1998071700074	19980717	00074	EA  	1998	7	17	AU980470         	3	19980425	G	6111		BLADE           			WACO  	YMF   	YMF         	9600412	EA  	JACOBP	R755  	R755B2      	35007	SW  	SNSNCH	W96JB	W96JB       	EA  	PROPELLER	CRACKED         	H				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 								AD4765		(AUS) PROPELLER HAD SPLITS DEVELOPING AFT OF THE METAL LEADING EDGE AND BETWEEN LAMINATION MIDWAY ALONG THE CENTER OF BL	ADE.  FINE CRACKS WERE ALSO FOUND IN THE LEADING METAL SHEATH AT RADIUS OF STRESS RELIEVING POINTS.					1	Q	7	1 	3R	3	R		ATC542  	E237	5	N	P170
1998071700075	19980717	00075	SO  	1998	7	17	AU980471         	1	19980406	G	2823	757633	O-RING          	SCOTT       	236405      	PIPER 	PA34  	PA34200T    	7103406	SO  										FUEL SYS	DISINTEGRATED   	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					12731					(AUS) RT FUEL SELECTOR VALVE `O' RING SEALS DETERIORATED ALLOWING FUEL TO CROSSFEED FROM THE LT FUEL TANK TO THE RT ENGI	NE.					1	L	7	2 	3O				A7SO
1999012100006	19990121	00006	EU  	1999	1	21	AU980472         	1	19980427	G	7922		NUT             		53E22144    	SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  					THERMO BYPASS	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3206436A			(AUS) ENGINE THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) CRIMP NUT LOOSE.  NOTE:  VALVE P/N 53E22144 IS NOT MENTIO	NED IN SB 318A AS A PROBLEM.					1	L	7	1 	3O	3	O	NT	A51EU   	E286
1998072200003	19980722	00003	NE  	1998	7	22	AU980473         	2	19980421	G	7322	8063040	FCU             	WOODWARD    	8063040     	PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67      	52043	NE  					FUEL SYS	MALFUNCTIONED   	H				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 					11416011		110012			(AUS) FUEL CONTROL UNIT FAULTY.  NO FUEL FLOW INDICATION.  SUSPECT FUEL VALVE STUCK IN CLOSED POSITION.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
1998071700076	19980717	00076	CE  	1998	7	17	AU980474         	1	19980421	G	2701	NAS22014	SCREW           			CESSNA	182   	182         	2072702	CE  										RT CONT COLUMN	DISLODGED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT CONTROL COLUMN SCREW P/N NAS22014 WAS FOUND ADRIFT ALONG WITH GLIDE P/N 0760651-2 AND PLUG P/N 0760681-1.  THE 	LT CONTROL COLUMN WAS CHECKED AND ITS SCREW WAS ALSO FOUND TO BE LOOSE.					1	H	7	1 	3O			NT	3A13
1998071700077	19980717	00077	SW  	1998	7	17	AU980475         	1	19980417	G	2752	2736053001	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  										TE FLAP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					169					(AUS) FLAP ACTUATOR BODY CRACKED AROUND THE CIRCUMFERENCE APPROXIMATELY 8 MM (0.3 INCH) FROM AND PARALLEL TO THE BASE OF	 THE ACTUATOR.  CRACK LENGTH APPROXIMATELY 25.4 MM (1 INCH).					2	L	7	2 	4T			RT	A18SW
1998071700078	19980717	00078	EU  	1998	7	17	AU980476         	1	19980423	G	2611	7211121100	SMOKE DETECTOR  			SAAB  	SF340 	SF340A      	7850100	EU  										CARGO BAY	FAULTY          	H				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 					A2018					(AUS) CARGO SMOKE DETECTOR FAULTY.						2	L	7	2 	4T			RT	A52EU
1998071700079	19980717	00079		1998	7	17	AU980477         	1	19980429	G	7120	595104815	MOUNT           		60510021    						PWA   	PT6   	PT6A112     	52043	NE  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L12610R12611			(AUS) ENGINE MOUNT FOOT CRACKED.											3	T			E4EA
1998071700080	19980717	00080	CE  	1998	7	17	AU980478         	1	19980415	G	3250	571S096102CR	CONTROL CABLE   			CESSNA	441   	441         	2076020	CE  										NLG	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL STEERING SYSTEM RT AFT STEERING CABLE WORN WITH BROKEN STRANDS MID-LENGTH.						1	L	7	2 	3T			RT	A28CE
1998071700081	19980717	00081	SO  	1998	7	17	AU980479         	1	19980428	G	2821		FILTER          			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYS	CONTAMINATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING MAINTENANCE, BOTH MAIN FUEL FILTERS WERE FOUND HEAVILY CONTAMINATED BY A GREASY SUBSTANCE OVER THE FILTER W	AFERS.  THE SUBSTANCE WAS FOUND TO BE WATER SOLUBLE AND WHEN LEFT IN WATER PRODUCED (BY MULTIPLICATION), A GELATINOUS FU	NGUS LIKE SUBSTANCE.				1	L	7	2 	3O				A20SO
1998071700082	19980717	00082	SO  	1998	7	17	AU980480         	1	19980424	G	3260	MS243311	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	FAULTY          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR SAFETY MICROSWITCH WIRE INSULATION FAILED.						1	L	7	2 	3O				A20SO
1998071700083	19980717	00083	CE  	1998	7	17	AU980481         	1	19980409	G	5712	082217579	RIB             		082203846   	CESSNA	310   	310R        	2074245	CE  										WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0831					(AUS) LT WING RIB P/N 0822175-79 AND RT WING (REPAIRED) RIB P/N 0822175-75 CRACKED.  AIRCRAFT HAS FLOWN 1364.4 HOURS SIN	CE THE RT WING WAS REPAIRED IAW EO 95/490/DR.  FOUND DURING INSPECTION IAW AD/C310/56A1.					1	L	7	2 	3O				3A10
1998071700084	19980717	00084	CE  	1998	7	17	AU980482         	1	19980430	G	2810	50261024	FUEL TANK       	GOODYEAR    	50261024    	CESSNA	402   	402B        	207590P	CE  										LT WING	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					748721					(AUS) LT WING FUEL TANK LEAKING.  INVESTIGATION REVEALED A MOULDED-IN SPIGOT HAD TORN LOOSE FROM UNDER THE OUTER TANK OF	 THE RT AUXILIARY TANK SYSTEM.  THE INNER TANK WAS INSPECTED AND WAS FOUND TO BE CLOSE TO A SIMILAR FAILURE - BOTH TANKS	 WERE MANUFACTURED IN 1974.  THE SUBMITTER WAS CONCERNED AT THE SUDDENESS OF THE LEAK, THE MASSIVE FLOW, LACK OF ANY WAR	NING, AND THE FUEL LOSS AREA BEING VERY CLOSE TO THE TURBO EXHAUST.			1	L	7	2 	3O				A7CE
1998071700085	19980717	00085	CE  	1998	7	17	AU980483         	1	19980423	G	2810		VENT            			BEECH 	55    	D55         	1152730	CE  										FUEL BLADDER	BLOCKED         	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 										(AUS) DURING APPROACH, THE LT ENGINE LOST POWER.  THE MAIN FUEL GAUGE READ HALF FULL AND THE LT MAIN TANK SHOWED EMPTY. 	 INVESTIGATION FOUND THAT THE INBOARD FUEL VENT WAS BLOCKED CAUSING THE TANK FUEL BLADDER CELL TO COLLAPSE (SUCKED UP) A	ND PREVENTING THE FUEL QUANTITY TRANSMITTER FROM GOING TO EMPTY.				1	L	7	2 	3O				3A16
1998071700086	19980717	00086	SO  	1998	7	17	AU980484         	2	19980313	G	8530		GUIDE           			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					NR 3 CYL EXH	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							20R005			(AUS) NR 3 CYLINDER WAS REMOVED FOR LOW COMPRESSION.  THE EXHAUST VALVE GUIDE WAS FOUND TO BE WORN 0.483 MM (0.019 INCH)	.  THE REMAINING CYLINDERS WERE THEN REMOVED AND ALL WERE FOUND TO BE IN A SIMILAR CONDITION.  TIME IN SERVICE FOR THE C	YLINDERS WAS 55 HRS.				1	H	7	1 	3O	3	O		3A19    	E252
1998071700087	19980717	00087	SO  	1998	7	17	AU980485         	2	19980327	G	8530	652956	GUIDE           			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  					EXH VALVE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							247926R			(AUS) ENGINE CYLINDER REMOVED DUE TO LOW COMPRESSION.  EXHAUST VALVE P/N 636242 FOUND WORN 0.178 MM (0.007 INCH).  EXHAU	ST VALVE GUIDE P/N 652956 WORN 0.0432 MM (0.017 INCH).					1	H	7	1 	3O	3	O		A4CE    	E5CE
1998071700088	19980717	00088	EU  	1998	7	17	AU980486         	1	19980219	G	5320		WEB             			FOKKER	F28   	F28MK4000   	4990810	EU  										FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT NLG SIDE WALL WEB CRACKED AT STN 2650 LOCATED AT THE BEND LINE JUST ABOVE THE WEB CONNECTION TO THE LONGITUDINA	L BEAM.  FOUND DURING INSPECTION IAW ER F28-53-10-48B.  CRACK LENGTH APPROXIMATELY 38 MM (1.5 INCH).					2	L	7	2 	4F			RT	A20EU
1998071700089	19980717	00089	SO  	1998	7	17	AU980487         	2	19980301	G	8530		CYLINDER HEAD   			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  					NR 2	SEPARATED       	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 			358  				1214397B			(AUS) NR 2 CYLINDER HEAD SEPARATED FROM THE CYLINDER BARREL.						1	L	7	1 	3O	3	O		3A15    	E5CE
1998071700090	19980717	00090	SO  	1998	7	17	AU980488         	2	19980301	G	8520	629071629072	CRANKCASE       			BEECH 	35    	V35         	1151538	CE  	CONT  	O520  	IO520BA     	17032	SO  					NR 2 CYL PAD	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			358  		629071629072		1214397B			(AUS) AT ENGINE BULK STRIP, FOLLOWING THE SEPARATION OF NR 2 CYLINDER HEAD (REFER MDR 98/0488), A 127 MM (5 INCH) LONG C	RACK WAS FOUND IN THE CRANKCASE RUNNING FROM THE MATING FACE BACKBONE FLANGE DOWN TO THE NR 2 CYLINDER PAD.  THE CRACK W	AS OBSCURED BY THE LT MAGNETO AND HAD SILICON SEALANT SPREAD OVER ITS ENTIRE LENGTH.				1	L	7	1 	3O	3	O		3A15    	E5CE
1998071700091	19980717	00091	SO  	1998	7	17	AU980489         	2	19980421	G	8530	643767	GUIDE           			CESSNA	182   	182D        	2072710	CE  	CONT  	O470  	O470L       	17026	SO  					NR 4 EXH VALVE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING PERIODIC INSPECTION, NR 4 CYLINDER COMPRESSION WAS 20/80.  THE EXHAUST VALVE P/N 646286 WAS REMOVED AND FOU	ND TO BE WORN 0.203 MM (0.008 INCH) JUST ABOVE STEM NECK.  THE VALVE GUIDE P/N 643767 WAS WORN 0.457 MM (0.018 INCH) AT 	THE LOWER HALF AREA.				1	H	7	1 	3O	3	O	NT	3A13    	E273
1998071700092	19980717	00092	EU  	1998	7	17	AU980490         	1	19980427	G	5310		STRUCTURE       			FOKKER	F28   	F28MK4000   	4990810	EU  										FUSELAGE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING AIRCRAFT CORROSION INSPECTION AT `D1 CHECK', LEVEL TWO CORROSION AS DEFINED BY F.W.A. MAINTENANCE CONTROL M	ANUAL VOLUME 9 WAS FOUND.					2	L	7	2 	4F			RT	A20EU
1998071700093	19980717	00093	EA  	1998	7	17	AU980491         	2	19980418	G	8520	STD1065	DOWEL           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					CRANKSHAFT	SHEARED         	H				K				NONE                    				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CR	CRUISE         	1			AU	S 			585  		L1636736A		L1636736A			(AUS) CRANKSHAFT ACCESSORY DRIVE GEAR POSITIONING DOWEL SHEARED.  AIRCRAFT SUFFERED A LOSS OF POWER AND WAS DAMAGED DURI	NG A FORCED LANDING.  ENGINE HAD SUFFERED A PROPELLER STRIKE PRIOR TO THE LAST OVERHAUL AT WHICH THE DOWEL PIN WAS INSPE	CTED BUT NOT REPLACED.				1	L	7	1 	3O	3	O		2A13    	E286
1998071700094	19980717	00094	CE  	1998	7	17	AU980492         	1	19980304	G	5312		BULKHEAD        			CESSNA	210   	2105A       	2073406	CE  										DOOR POST	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT FUSELAGE DOORPOST BULKHEADS CRACKED.						1	H	7	1 	3O				3A21
1998071700095	19980717	00095	EU  	1998	7	17	AU980493         	1	19980216	G	2820	9949412B	COUPLING        		ST10106     	SNIAS 	AS332 	AS332L      	8680809	EU  										NR 2 ENG FUEL	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) NR 2 ENGINE FUEL SUPPLY LINE QUICK DISCONNECT FITTING LEAKING.  SUBMITTER SUSPECTS CAUSED BY A WORN COUPLING.						2	G	7	2 	4U				H4EU
1998071700096	19980717	00096	EU  	1998	7	17	AU980494         	1	19980103	G	2821	402B2511	FILTER          		4020P2511   	SNIAS 	AS332 	AS332L      	8680809	EU  										FUEL SYS	CONTAMINATED    	H				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		IN	INSP/MAINT     	1			AU	S 					41					(AUS) NR 2 ENGINE FUEL FILTER CONTAMINATED.						2	G	7	2 	4U				H4EU
1998071700097	19980717	00097	CE  	1998	7	17	AU980495         	1	19980501	G	3200		LANDING GEAR    			CESSNA	421   	421B        	2076014	CE  										NLG/RT MLG	SEPARATED       	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) AIRCRAFT CRASHED ON LANDING.  NOSE LANDING GEAR AND RT MAIN LANDING GEAR TORN FROM THE AIRCRAFT.  BOTH PROPELLERS 	STRUCK THE GROUND.					1	L	7	2 	3O				A7CE
1998071700098	19980717	00098	EA  	1998	7	17	AU980496         	1	19980416	G	5520		DOUBLER         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										ELEVATOR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR HINGE DOUBLER SEVERELY CORRODED.  LIGHT PITTING CORROSION FOUND ON THE SPAR.  FURTHER INVESTIGATION FO	UND SIMILAR CORROSION ON THE RT ELEVATOR.					1	H	7	1 	3R				A806
1998071700099	19980717	00099		1998	7	17	AU980497         	4	19980505	G	3442	MI5853512	INDICATOR       			DHAV  	DHC8  	DHC8*       		NM  										COCKPIT	FAULTY          	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 										(AUS) RADAR INDICATOR FAULTY.						2	H	7	2 	4T			RT	A13NM
1998071700100	19980717	00100	WP  	1998	7	17	AU980498         	1	19980404	G	6320	STD2209	BOLT            			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	SEPARATED       	H				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					L2518140A		L2518140A			(AUS) BOLT HEAD SEPARATED FROM THE SHANK.  DOWEL PIN SHEARED.						1	G	7	1 	3O	3	O		H11NM   	E295
1998071700101	19980717	00101	WP  	1998	7	17	AU980499         	1	19980426	G	6320	A6881	SWITCH          			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					M/R GRB TEMP	FAULTY          	H				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) MAIN ROTOR GEARBOX TEMPERATURE SWITCH FAULTY.						1	G	7	1 	3O	3	O		H11NM   	E295
1998071700102	19980717	00102	CE  	1998	7	17	AU980500         	1	19980501	G	2910	520010777	PIPE            			CESSNA	402   	402C        	207590R	CE  										HYDRAULIC SYSTEM	CRACKED         	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED BEHIND THE LT SIDE SPAR UNDER THE FLOOR SPLIT AND LEAKING.  LOSS OF HYDRAULIC FLUID.						1	L	7	2 	3O				A7CE
1998071700103	19980717	00103	CE  	1998	7	17	AU980501         	1	19980416	G	5320	05121871	CHANNEL         		05121872    	CESSNA	172   	172N        	2072434	CE  										FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOORPOST CHANNELS P/N 0512187-1 AND P/N 512187-2 CRACKED.						1	H	7	1 	3O			NT	3A12
1998071700104	19980717	00104		1998	7	17	AU980502         	4	19980504	G	3414	BK14A	INDICATOR       			AMTR  		JABIRUSK    												COCKPIT	OUT OF ADJUST   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1068					(AUS) AIRSPEED INDICATOR INACCURATE AT ALL SPEEDS.  FOUND DURING INSPECTION IAW AD/INST/8 AMDT3.									0
1998071700105	19980717	00105	EA  	1998	7	17	AU980503         	2	19980406	G	7414	M3333	IMPULSE COUPLING	SLICK       	6351        						LYC   	O540  	O540A1D5    	41532	EA  					MAGNETO	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					9508045		L805140			(AUS) MAGNETO IMPULSE COUPLING PAWL RIVETS LOOSE AND CLOSE TO FAILURE.  MAGNETO DRIVE SUPPORT BEARING CAGE BREAKING UP. 	 METAL FOUND IN OIL FILTER.										3	O			E295
1998071700106	19980717	00106	EA  	1998	7	17	AU980504         	2	19980504	G	7414	M3333	IMPULSE COUPLING	SLICK       	6351        						LYC   	O540  	O540A1D5    	41532	EA  					MAGNETO	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					97061910		L1862640A			(AUS) MAGNETO IMPULSE COUPLING PAWL RETAINING RIVETS LOOSE AND CLOSE TO FAILURE.											3	O			E295
1998071700107	19980717	00107	NE  	1998	7	17	AU980505         	2	19980505	G	7250		TURBINE         			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE	BURNED          	H				K				NONE                    				E	A		VIBRATION/BUFFET          	FLAME/FIRE                		IN	INSP/MAINT     	1			AU	S 							155442			(AUS) ENGINE CAUGHT FIRE DUE TO IGNITION OF FUEL VAPOR.  THE FIRE WAS CONCENTRATED EXTERNALLY AROUND THE TURBINE SECTION	.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
1998071700108	19980717	00108	EU  	1998	7	17	AU980506         	1	19980320	G	3213		BOLT            			AIRBUS	320   	A320212     		EU  										MLG	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR PINTLE PIN LOCK BOLT ROTATING.						2	L	7	2 	4F			RT	A28NM
1998071700109	19980717	00109	SW  	1998	7	17	AU980507         	1	19980507	G	5741	206931	ANGLE           			AIRTRC	AT500 	AT502B      	0390307	SW  										LT RT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING OUTER ATTACHMENT ANGLES CRACKED.  CRACK LENGTH APPROXIMATELY 25.4 MM (1 INCH).  FOUND DURING INSPEC	TION IAW AD/AT/16.  AIRCRAFT WAS PREVIOUSLY REGISTERED IN NEW ZEALAND AS ZK-SNO.					1	L	7	1 	3T			NC	A17SW
1998071700110	19980717	00110	CE  	1998	7	17	AU980508         	1	19980505	G	5343	071348560	BRACKET         			CESSNA	180   	180         	2072602	CE  										RT MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR INBOARD ATTACHMENT BRACKET AND BLOCK CONTAINED EXFOLIATION CORROSION. THE AIRCRAFT WAS RECENT	LY IMPORTED FROM THE USA.					1	H	7	1 	3O			NC	5A6
1998071700111	19980717	00111	CE  	1998	7	17	AU980509         	1	19980505	G	5341	0512122	BLOCK           			CESSNA	180   	180         	2072602	CE  										WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CARRY-THROUGH SPAR REAR WING ATTACHMENT BLOCKS (2OFF) CONTAINED SEVERE EXFOLIATION CORROSION.						1	H	7	1 	3O			NC	5A6
1998071700112	19980717	00112	EU  	1998	7	17	AU980510         	1	19980501	G	2621	1727ANSETTSNO0	FIRE BOTTLE     			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 4 ENG INBD	DISCHARGED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1727ANSETTSN					(AUS) NR 4 ENGINE INBOARD FIRE EXTINGUISHER BOTTLE EMPTY.  NO EVIDENCE OF INTENTIONAL OR THERMAL DISCHARGE.  FOUND DURIN	G REMOVAL IAW ER BA6-26-20-16.					2	H	7	4 	4F			RT	A49EU
1998071700113	19980717	00113	SO  	1998	7	17	AU980511         	1	19980408	G	5320		BRACKET         			PIPER 	PA38  	PA38112     	7103812	SO  										RUD TORQ TUBE	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER PEDAL TORQUE TUBE SUPPORT BRACKET FAULTY.						1	L	7	1 	3O				A18SO
1998071700114	19980717	00114	SO  	1998	7	17	AU980512         	1	19980408	G	5320		BRACKET         			PIPER 	PA38  	PA38112     	7103812	SO  										RUD TUBE TORQ	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER PEDAL TORQUE TUBE SUPPORT BRACKET FAULTY.  SEE MDR 98/0511FOR SIMILAR DEFECT.						1	L	7	1 	3O				A18SO
1998071700115	19980717	00115	SO  	1998	7	17	AU980513         	1	19980430	G	5753		FLAP            			PIPER 	PA28  	PA28180     	7102808	SO  										TE FLAP	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SEVERELY CORRODED IN NUMEROUS AREAS:  1. METAL HINGES AND ATTACHMENTS CORRODED.  2. NOSE RIBS CORRODED AWAY I	N SEVERAL AREAS.  3. LOWER SKINS BADLY CORRODED.					1	L	7	1 	3O				2A13
1998071700116	19980717	00116	SO  	1998	7	17	AU980514         	1	19980430	G	5540		BRACKET         			PIPER 	PA31  	PA31        	7103102	SO  										RUDDER	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER CORRODED.  WHEN THE RUDDER WAS REMOVED, THE TOP AND CENTER HINGE BRACKETS WERE FOUND TO BE CRACKED ON THE S	PARS AND DOUBLERS.					1	L	7	2 	3O				A20SO
1998071700117	19980717	00117		1998	7	17	AU980515         	4	19980512	G	3451	6222012012	INDICATOR       	COLLINS     	339F12A     	CESSNA	441   	441         	2076020	CE  										COCKPIT	FAULTY          	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 					1163					(AUS) DME INDICATOR FAULTY.  CIRCUIT BREAKER TRIPPED.						1	L	7	2 	3T			RT	A28CE
1998071700118	19980717	00118	WP  	1998	7	17	AU980516         	2	19980501	G	7261	31080261	PUMP            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					ENG OIL SCAV	FAILED          	H				K				NONE                    				E	B		VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  		DE	DESCENT        	1			AU	S 							P44005			(AUS) ENGINE TURBINE OIL SCAVENGE PUMP DRIVE GEAR TEETH MISSING.  TURBINE SEAL AND TURBINE ALSO DAMAGED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998071700119	19980717	00119	NM  	1998	7	17	AU980517         	1	19980506	G	2750	5256T00511	HOUSING         			BOEING	767   	767238      		NM  										TE FLAP	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 					124177					(AUS) FLAP CONTROL VALVE HOUSING LEAKING.  LOSS OF CENTER HYDRAULIC SYSTEM FLUID.						2	L	7	2 	4F			RT	A1NM
1998071700120	19980717	00120	NM  	1998	7	17	AU980518         	1	19980423	G	2497		WIRE            			BOEING	747   	747438      	       	NM  										DC SYS	WORN            	H				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) GALLEY POWER SYSTEM CABLES (4OFF) CHAFING AGAINST THE AFT GALLEY CHILLER AT THE FORWARD CONNECTION.  CABLE FROM PL	UG Y7LD001P HAD EVIDENCE OF ARCING.					2	L	7	4 	4F			RT	A20WE
1998071700121	19980717	00121	CE  	1998	7	17	AU980519         	1	19980312	G	3260	1013646289	SWITCH          		B200C       	BEECH 	200   	B200C       	1152924	CE  										NLG	FAULTY          	H				K				NONE                    				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR POSITION MICROSWITCH FAULTY.						1	L	7	2 	4T				A24CE
1998071700122	19980717	00122	NM  	1998	7	17	AU980520         	1	19980422	G	7931	APT761000	TRANSDUCER      			DHAV  	DHC8  	DHC8201     	2809001	NM  	PWA   	PW120 	PW123       		NE  					OIL SYS	FAULTY          	H				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 					54782520					(AUS) LT ENGINE OIL PRESSURE TRANSDUCER FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998071700123	19980717	00123	EA  	1998	7	17	AU980521         	2	19980507	G	7320	3033260	PIPE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					FUEL SYS	FAILED          	H				K	E			NONE                    	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 			1511 		PCE32165		PCE32165			(AUS) LT ENGINE P3 DISCHARGE PIPE FRACTURED AT THE FLARED END ATTACHEDTO THE P3 FILTER.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998071700124	19980717	00124	SO  	1998	7	17	AU980522         	1	19980513	G	7120	1178615	MOUNT           			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A3B     	41508	EA  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOP RT ENGINE MOUNT TUBE CRACKED IN AREA ADJACENT TO THE WELD.						1	H	7	1 	3O	3	O		1A6     	E274
1998071700125	19980717	00125	SW  	1998	7	17	AU980523         	1	19980513	G	6320	204040725003	BEARING         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TRANSMISSION	DETERIORATED    	H				K				NONE                    				J			WARNING INDICATION        			DE	DESCENT        	1			AU	S 					ABW40279					(AUS) MAIN TRANSMISSION BEARING DETERIORATED.  CHIP DETECTOR CONTAINED SIX PIECES OF FLAKED MAGNETIC MATERIAL.  THE TRAN	SMISSION WAS CHANGED.					1	G	7	2 	4U	4	U		H4SW    	E22EA
1998071700126	19980717	00126	SW  	1998	7	17	AU980524         	1	19980514	G	2721		CONTROL ROD     		010A24018   	MTSBSI	MU2   	MU2B30      	5780410	SW  										RUDDER TAB	BROKEN          	H				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRIM TAB CONTROL ROD BROKEN.  AD/MU-2/48 HAD NOT BEEN COMPLIED WITH.						1	H	7	2 	3T				A2PC
1998071700127	19980717	00127	CE  	1998	7	17	AU980525         	1	19980514	G	3230		ARM             			CESSNA	310   	310R        	2074245	CE  										RT MLG DOWNLOCK	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK ARM FAILED.  LANDING GEAR COLLAPSED.  AIRCRAFT WAS PREVIOUSLY REGISTERED AS VH-TXE.						1	L	7	2 	3O				3A10
1998071700128	19980717	00128	SO  	1998	7	17	AU980526         	1	19980507	G	2810	461715	TANK            			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL STORAGE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING AUXILIARY FUEL TANK DRAIN FAILED.  FUEL LEAKING INTO WING.  INVESTIGATION FOUND THAT THE RUBBER HAD BECOME	 BRITTLE AND HAD FAILED BENEATH THE SECURING CLAMP AT THE SUMP DRAIN VALVE.					1	L	7	2 	3O				A20SO
1998071700129	19980717	00129	CE  	1998	7	17	AU980527         	1	19980502	G	3000	101HS1	SWITCH          			BEECH 	200   	B200C       	1152924	CE  										DE-ICE SYS	FAILED          	H				K				NONE                    				P			NO WARNING INDICATION     			CR	CRUISE         	1			AU	S 										(AUS) ICE VANE MICROSWITCH FAILED INTERNALLY.						1	L	7	2 	4T				A24CE
1998071700130	19980717	00130	SO  	1998	7	17	AU980528         	1	19980506	G	3230	4198301	DOWNLOCK        			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	LACK OF LUBE    	H				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK HOOK STIFF IN OPERATION DUE TO A BUILD-UP OF CONTAMINATION.						1	L	7	2 	3O				A20SO
1998071700131	19980717	00131	NE  	1998	7	17	AU980529         	2	19980119	G	7250	311983802	BOLT            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7126 				PCE115622			(AUS) HIGH PRESSURE TURBINE DISC NR 5 BOLT CRACKED (VISIBLE TO THE NAKED EYE).  THE REMAINING FOUR BOLTS WERE NDT INSPEC	TED WITH TWO BOLTS SHOWING CRACK INDICATIONS.  FOUND DURING INSPECTION IAW PRATT AND WHITNEY CANADA SIL PW100-56.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998071700132	19980717	00132	SO  	1998	7	17	AU980530         	1	19980408	G	2810		TANK            			PIPER 	PA32  	PA32300     	7103212	SO  										FUEL STORAGE	CONTAMINATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK CONTAMINATED WITH GEL COAT TYPE MATERIAL.						1	L	7	1 	3O				A3SO
1998071700133	19980717	00133	EU  	1998	7	17	AU980531         	1	19980326	G	5720	HLT900BV2022	FASTENER        			AIRBUS	320   	A320212     		EU  										WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING TOP SKIN GEAR SUPPORT RIB HI-LOCK FASTENER HEAD SHEARED.  HEAD OF FASTENER ON THE LT SIDE WAS CRACKED.  FU	RTHER, INVESTIGATION FOUND ALL REMAINING FASTENERS IN THE AREA TO HAVE VARYING DEGREES OF DISHING.					2	L	7	2 	4F			RT	A28NM
1998071700134	19980717	00134	NM  	1998	7	17	AU980532         	1	19980329	G	2782	167ANSETTSNO00	PDU             			BOEING	767   	767277      		NM  										LE FLAP	FAULTY          	H				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 			39209		167ANSETTSNO					(AUS) OUTBOARD LEADING EDGE SLAT POWER DRIVE UNIT (PDU), ELECTRIC MOTOR FAULTY.						2	L	7	2 	4F			RT	A1NM
1998071700135	19980717	00135	NM  	1998	7	17	AU980533         	1	19980125	G	2760		CONTROL CABLE   			BOEING	737   	737377      	       	NM  										SPOILER	FRAYED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING FLIGHT SPOILER CABLES CONTAINED BROKEN STRANDS IN THE AREA ADJACENT TO PULLEY AT STN 230:  LT WS B1-3, P/N BA	CC2A3A02794EG.  WS B2-3, P/N BACC2A3A03216FG.  WS A2-3, P/N BACC2A3A01853FG.  WS A1-3, P/N BACC2A3A02428EG.  RT WS B1-4,	 P/N BACC2A3A02625FG.  WS B2-4, P/N BACC2A3A03051FG.				2	L	7	2 	4F			RT	A16WE
1998071700136	19980717	00136	CE  	1998	7	17	AU980534         	1	19980514	G	3230	HYH5001	ELECTRIC MOTOR  			BEECH 	76    	76          	1153005	CE  										MLG	FAULTY          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR ELECTRIC MOTOR FAULTY.  INVESTIGATION FOUND POOR CONTACT WITH THE THERMAL TRIP FITTED IN SERIES TO TH	E MOTOR BRUSH HOLDER.					1	L	7	2 	3O				A29CE
1998071700137	19980717	00137		1998	7	17	AU980535         	4	19980325	G	2565	603220193J	ASPIRATOR       			AIRBUS	320   	A320212     		EU  										SLIDE	FRACTURED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4904 		C0010ANSETTT					(AUS) RT AFT ESCAPE SLIDE ASPIRATOR NOZZLE DAMAGED DUE TO INCORRECT POSITIONING OF THE ASPIRATOR DURING PACKING.  INVEST	IGATION FOUND THAT THE LOWER CHAMBER ASPIRATOR P/N 60322-103J WAS DISTORTED AND OUT OF SHAPE RESULTING IN THE FRACTURE O	F THE NOZZLE MANIFOLD WHERE IT ATTACHES TO THE WALL.				2	L	7	2 	4F			RT	A28NM
1998071700138	19980717	00138	EA  	1998	7	17	AU980536         	2	19980513	G	8520	LW12186	NUT             								LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CONNECTING ROD NUT INCORRECTLY MACHINED AT FACTORY.											3	O			E14EA
1998071700139	19980717	00139	NM  	1998	7	17	AU980537         	1	19980218	G	5220	655670	WINDOW          			BOEING	737   	737377      		NM  										CABIN	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT EMERGENCY EXIT HATCH WINDOW OUTER PANEL DELAMINATED AND CRACKED FROM THE LOWER FORWARD CORNER VERTICALLY UP THE	 REAR EDGE TO THE TOP REAR CORNER.					2	L	7	2 	4F			RT	A16WE
1998071700140	19980717	00140	SO  	1998	7	17	AU980538         	2	19980518	G	8520	282116R	CRANKCASE       								CONT  	O520  	IO520C      	17032	SO  					ENGINE	OUT OF LIMITS   	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					282116R		282116R			(AUS) ENGINE CRANKCASE TUNNEL MEASUREMENTS OUT OF LIMITS.											3	O			E5CE
1998071700141	19980717	00141	EU  	1998	7	17	AU980539         	1	19980228	G	2913	42038	PUMP            			BAG   	BAE146	BAE146200A  	1500266	EU  										HYD SYS	FAILED          	H		A		K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 			21245		S19ANSETTSN0					(AUS) POWER TRANSFER UNIT HYDRAULIC PUMP FAILED.  ON STRIP-DOWN OF THE PUMP, FOUND THE CYLINDER BARREL INNER RACE BEARIN	G P/N 40963 WAS BROKEN CAUSING DAMAGE TO THE BEARING ROLLERS.  BRONZE  METAL CONTAMINATION OF THE YELLOW HYDRAULIC SYSTE	M FILTER.				2	H	7	4 	4F			RT	A49EU
1998071700142	19980717	00142	CE  	1998	7	17	AU980540         	1	19980508	G	3250	50420101	LINK            			CESSNA	310   	310R        	2074245	CE  										NLG	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE WHEEL STEERING LINK BROKEN.						1	L	7	2 	3O				3A10
1998071700143	19980717	00143	SO  	1998	7	17	AU980541         	1	19980311	G	2434		WIRE            			PIPER 	PA28  	PA28180     	7102808	SO  										ALTERNATOR	BROKEN          	H				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) ALTERNATOR FIELD WIRE BROKEN.						1	L	7	1 	3O			 	2A13
1998071700144	19980717	00144	EA  	1998	7	17	AU980542         	2	19980513	G	7414	103910881	COIL            	BENDIX      	S1200       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MAGNETO	FAILED          	H				K				NONE                    				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			AU	S 			5    							(AUS) MAGNETO COIL CASE SHORT CIRCUITING TO MAGNETO FRAME.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998071700145	19980717	00145	SO  	1998	7	17	AU980543         	1	19980502	G	3230	752383	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	SEIZED          	H				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOWNLOCK ACTUATOR ROD END BEARING DIRTY AND PARTIALLY SEIZED.						1	L	7	2 	3O				A20SO
1998071700146	19980717	00146	SW  	1998	7	17	AU980544         	1	19980401	G	2510	ANCRA4171312	SWIVEL          		0572300207  	BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					249835					(AUS) SEAT BELT HINGED ATTACHMENT SWIVEL FAILED.						1	G	7	2 	4U				H4SW
1998071700147	19980717	00147	CE  	1998	7	17	AU980545         	1	19980508	G	5741	08113507	FITTING         		340         	CESSNA	340   	340CESSNA   	2076404	CE  										WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0050					(AUS) LT AND RT UPPER AND LOWER STUB WING ATTACHMENT FITTINGS P/N  0811350-7 AND P/N 0811350-8 CONTAINED SEVERE EXFOLIAT	ION CORROSION.					1	L	7	2 	3O				3A25
1998072200004	19980722	00004	NE  	1998	7	22	AU980546         	2	19980517	G	7320	3352528060	PIPE            								GE    	CFM56 	CFM56*      	13802	NE  					NR 1 ENG FUEL	LOOSE           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							725496			(AUS) NR 1 ENGINE 9TH STAGE FUEL LINE (TC2 SENSE LINE) TO TURBINE, CLEARANCE CONTROL VALVE `B' NUT LOOSE.											4	F			E2GL
1998071700148	19980717	00148	EA  	1998	7	17	AU980547         	2	19980429	G	7414	M3485SLICK	BEARING         	SLICK       	4370        						LYC   	O360  	O360C1F     	41514	EA  					MAGNETO	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					92090338					(AUS) MAGNETO BEARING SPINNING IN CAP.											3	O			E286
1998071700149	19980717	00149	SW  	1998	7	17	AU980548         	1	19980519	G	5711		SPAR            			SWRNGN	SA226 	SA226TC     	8780404	SW  										WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING MAIN SPAR CRACKED IN TWO PLACES. OUTBOARD CRACK LENGTH 82.55 MM (3.25 INCH).  INBOARD CRACK LENGTH 57.15 MM (	2.25 INCH).  FOUND DURING INSPECTION IAW SA226 MANUAL ST-UN-M002.					2	L	7	2 	4T			RT	A8SW
1998071700150	19980717	00150		1998	7	17	AU980549         	4	19980511	G	2330		HARNESS         			BOEING	767   	767338      		NM  										CABIN	WORN            	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) PASSENGER ENTERTAINMENT SYSTEM WIRING HARNESS CHAFED THROUGH AND ARCING AGAINST THE LIFE RAFT STOWAGE AND FOOT RES	T.  THE HARNESS WAS FOUND TO BE ROUTED OUTSIDE THE CABLE TRACKS AND THE CARPET.					2	L	7	2 	4F			RT	A1NM
1998071700151	19980717	00151	CE  	1998	7	17	AU980550         	1	19980521	G	2710		CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										RT AILERON	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CABLE IN RT WING IS ROUTED OVER THE AUTOPILOT SERVO PULLEY AND OVER THE AILERON CABLE PULLEY RESULTING IN 	THE CABLE BEING PULLED OUT OF ALIGNMENT CAUSING A LARGE CABLE DEFLECTION THAT HAS THE CABLE RIDING ON THE COTTER PIN CAB	LE KEEPER INSTEAD OF ON THE PULLEY.  THIS DEFECT WAS FOUND ON AIRCRAFT SERIAL NUMBERS 17280337, 17280345 AND 17280354.				1	H	7	1 	3O			NT	3A12
1998071700152	19980717	00152	CE  	1998	7	17	AU980551         	1	19980521	G	3260	GE327	BULB            			BEECH 	58    	58          	1152740	CE  										NLG DOWNLOCK	FAILED          	H				K				NONE                    				P			NO WARNING INDICATION     			DE	DESCENT        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK INDICATOR BULB BLOWN.						1	L	7	2 	3O				3A16
1998071700153	19980717	00153	NM  	1998	7	17	AU980552         	1	19980519	G	3211	85311176005	FITTING         			DHAV  	DHC8  	DHC8102     	2809003	NM  										MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR FITTING FORWARD ATTACHMENT LUG CRACKED FROM FLANGE RADIUS TO FORWARD FLANGE FASTENER HOLE.  CRACK LEN	GTH 12.7 MM (0.5 INCH).					2	H	7	2 	4T			RT	A13NM
1998071700154	19980717	00154	WP  	1998	7	17	AU980553         	2	19980519	G	7320	2762026223	PIPE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					FUEL SYS	CRACKED         	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			AU	S 							P44495C			(AUS) DP/P TRANSDUCER RIGID SUPPLY PIPE CRACKED AROUND BEND RADIUS.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998071700155	19980717	00155	CE  	1998	7	17	AU980554         	1	19980521	G	2710		CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										RT AILERON	MISINSTALLED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CABLE IN RT WING IS ROUTED OVER THE AUTOPILOT SERVO PULLEY AND OVER THE AILERON CABLE PULLEY RESULTING IN 	THE CABLE BEING PULLED OUT OF ALIGNMENT CAUSING A LARGE CABLE DEFLECTION THAT HAS THE CABLE RIDING ON THE COTTER PIN CAB	LE KEEPER INSTEAD OF ON THE PULLEY.				1	H	7	1 	3O			NT	3A12
1998071700156	19980717	00156	SO  	1998	7	17	AU980555         	1	19980519	G	5744	AN526C1032R	SCREW           			PIPER 	PA28  	PA28160     	7102806	SO  										AILERON	IMPROPER PART   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT HARDWARE WAS USED TO FIT THE AILERONS TO THE AIRCRAFT FOLLOWING PAINTING.  INCORRECT TYPE P/N  AN526C103	2R SCREWS WERE USED INSTEAD OF THE CORRECT P/N MS20365-1-10 SCREWS.  UNAPPROVED PART.					1	L	7	1 	3O			 	2A13
1998071700157	19980717	00157	CE  	1998	7	17	AU980556         	1	19980515	G	2436	C6110010102	REGULATOR       			CESSNA	182   	182P        	2075816	CE  										DC SYS	FAILED          	H				K				NONE                    				B	H		SMOKE/FUMES/ODORS/SPARKS  	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			AU	S 										(AUS) VOLTAGE REGULATOR FAILED.  OVERVOLT SENSOR FAILED TO TRIP CAUSING DAMAGE TO ELECTRICAL COMPONENTS.						1	H	7	1 	3O			NT	TA13
1998071700158	19980717	00158	EU  	1998	7	17	AU980557         	1	19980420	G	5720	NB201909	ANGLE           			BNORM 	BN2   	BN2A26      	1520226	EU  										LT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3004					(AUS) LT WING/NACELLE ANGLE CRACKED THROUGH VERTICAL BOLT HOLES.  BOLTS APPEAR TO BE LOOSE AND WORKING.  ON REMOVAL OF T	HE VERTICAL BOLTS, TRACES OF DRY CHROMATE JOINING COMPOUND WERE FOUND IN THE THREADS.					1	H	7	2 	3O				A17EU
1998071700159	19980717	00159	CE  	1998	7	17	AU980558         	1	19980521	G	2710		CONTROL CABLE   			CESSNA	172   	172R        	2072401	CE  										RT AILERON	MISINSTALLED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CABLE IN RT WING IS ROUTED OVER THE AUTOPILOT SERVO PULLEY AND OVER THE AILERON CABLE PULLEY RESULTING IN 	THE CABLE BEING PULLED OUT OF ALIGNMENT CAUSING A LARGE CABLE DEFLECTION THAT HAS THE CABLE RIDING ON THE COTTER PIN CAB	LE KEEPER INSTEAD OF ON THE PULLEY.				1	H	7	1 	3O			NT	3A12
1998071700160	19980717	00160	CE  	1998	7	17	AU980559         	1	19980521	G	2731		TRIM TAB        			CESSNA	172   	172R        	2072401	CE  										ELEVATOR TAB	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM OPERATES IN REVERSE SENSE.  SUSPECT CAUSED WHEN THE AIRCRAFT IS REASSEMBLED IN AUSTRALIA FOLLOWING R	ECEIPT FROM THE FACTORY USING THE ILLUSTRATION IN THE MAINTENANCE MANUAL AS A GUIDE.  MANUFACTURING ERROR.					1	H	7	1 	3O			NT	3A12
1998071700161	19980717	00161	EA  	1998	7	17	AU980560         	2	19980521	G	7414	M3485	BEARING         	SLICK       	4371        						LYC   	O360  	O360A4K     	41514	EA  					MAGNETO	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					92070557					(AUS) MAGNETO BEARING SPINNING IN PLATE.											3	O			E286
1998071700162	19980717	00162	EU  	1998	7	17	AU980561         	1	19980521	G	3241		VALVE           			BAG   	BAE146	BAE146200A  	1500266	EU  										BRAKE	FAULTY          	H				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) NR 4 DUAL ADAPTIVE ANTI-SKID VALVE FAULTY.						2	H	7	4 	4F			RT	A49EU
1998071700163	19980717	00163	EA  	1998	7	17	AU980562         	2	19980521	G	8520	L721061A	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					LT ENG NR 6 CYL	FAILED          	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			1572 		L721061A		L721061A			(AUS) LT ENGINE NR 6 CYLINDER HOLD-DOWN BOLTS/STUDS (6OFF) BROKEN.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998071700164	19980717	00164	CE  	1998	7	17	AU980563         	1	19980515	G	2810	1003810051	SEAL            		1003810051  	BEECH 	200   	200BEECH    	1152920	CE  										FUEL TANK	DETERIORATED    	H				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 										(AUS) LT MAIN FUEL TANK CAP SEAL DETERIORATED.						1	L	7	2 	4T				A24CE
1998071700165	19980717	00165	CE  	1998	7	17	AU980564         	1	19980511	G	7603		ARM             			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT POWER LEVER	LOOSE           	H				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 										(AUS) LT ENGINE POWER LEVER INPUT ARM MOVING ON THE INPUT SHAFT.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998071700166	19980717	00166	CE  	1998	7	17	AU980565         	1	19980517	G	3230	HMX5FG	ROD END         			BEECH 	36    	A36         	1151604	CE  										NLG	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR OUTER ROD END HOUSING FAILED ACROSS THE GREASE NIPPLE ORIFICE.						1	L	7	1 	3O				3A15
1998071700167	19980717	00167	EU  	1998	7	17	AU980566         	1	19980420	G	5741	NB201909	ANGLE           			BNORM 	BN2   	BN2A26      	1520226	EU  										RT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3004					(AUS) RH WING ANGLE BRACKET CRACKED AT OUTER VERTICAL BOLT POSITIONS.  ALL VERTICAL BOLTS FRETTING UNDER THE HEADS.  DRI	ED CHROMATE JOINING PASTE FOUND IN BOLT/NUT ASSEMBLIES.					1	H	7	2 	3O				A17EU
1998071700168	19980717	00168	EU  	1998	7	17	AU980567         	1	19980420	G	5741	NB201819	ANGLE           			BNORM 	BN2   	BN2A26      	1520226	EU  										LT YWING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3004					(AUS) LT WING ATTACHMENT ANGLE SUSPECT CRACKED AND MOUNTING BOLTS LOOSE.  FOLLOWING REMOVAL AND INSPECTION, NO CRACK WAS	 FOUND IN THE ANGLE, HOWEVER, FRETTING WAS FOUND ON THE ANGLE MOUNTING FACES.  CHROMATE JOINING COMPOUND WAS FOUND TO HA	VE DRIED OUT.				1	H	7	2 	3O				A17EU
1998071700169	19980717	00169	EA  	1998	7	17	AU980568         	2	19980527	G	8530	LW14995	SPRING          			BEECH 	76    	76          	1153005	CE  	LYC   	O360  	O360A1G     	41514	EA  					NR 2 CYL INT	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L2850836A			(AUS) LT ENGINE, NR 2 CYLINDER INLET VALVE PUSHROD SHROUD TUBE RETAINING SPRING BROKEN IN HALF AND LYING IN THE BOTTOM O	F THE ROCKER BOX.					1	L	7	2 	3O	3	O		A29CE   	E286
1998071700170	19980717	00170		1998	7	17	AU980569         	4	19980522	G	2213	258668911AP	CONTROLLER      			DOUG  	DC9   	DC933F      	302207A	WP  										AFCS	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					04771805					(AUS) AUTOPILOT CONTROLLER FAULTY.						2	L	7	2 	4F				A6WE
1998071700171	19980717	00171	EU  	1998	7	17	AU980570         	1	19980420	G	5741	NB201819	ANGLE           			BNORM 	BN2   	BN2A26      	1520226	EU  										RT WING	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3004					(AUS) RT WING ATTACHMENT ANGLE BROKEN THROUGH THE UPPER BOLT HOLE.  ALL ATTACHMENT BOLTS FRETTING.  FRETTING ALSO FOUND 	ON THE ANGLE TO SPAR INTERFACE.  THE VERTICAL BOLT/NUT ASSEMBLIES CONTAINED DRIED CHROMATE JOINING PASTE.					1	H	7	2 	3O				A17EU
1998071700172	19980717	00172	SO  	1998	7	17	AU980571         	1	19980508	G	3230	3252700	HOUSING         			PIPER 	PA23  	PA23250     	7102308	SO  										MLG	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR LOWER DRAG LINK BROKEN AWAY FROM THE UPPER TRUNNION.  INVESTIGATION FOUND THE FAILURE WAS DUE TO	 A HEAVY LANDING.					1	L	7	2 	3O				1A10
1998071700309	19980717	00309	EU  	1998	7	17	AU980572         	1	19980303	G	3260		SENSOR          			AIRBUS	320   	A320212     		EU  										RT MLG	OUT OF ADJ      	H				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOOR PROXIMITY SENSOR 34GA OUT OF ADJUSTMENT.						2	L	7	2 	4F			RT	A28NM
1998071700310	19980717	00310	CE  	1998	7	17	AU980573         	1	19980528	G	3244	650X10X8PLY	TIRE            			CESSNA	402   	402C        	207590R	CE  										MLG	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TIRE FAULTY.  SIDEWALLS TOO SOFT AND SCRUBBING ON THE BRAKES.  TIRE TREAD TOO SOFT.  WITH THE CORRECT INFLATION PR	ESSURE, THE TIRE LOOKS FLAT.					1	L	7	2 	3O				A7CE
1998071700311	19980717	00311		1998	7	17	AU980574         	4	19980217	G	2562	4520130	ELT             		ELT1104     	CESSNA	210   	210N        	2073453	CE  										CABIN	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT CASE CRACKED AND CORRODED.  MOUNTING TRAY ALSO CORRODED.  INVESTIGATION FOUND SEVERAL OF THE BATTERIES EXTENSI	VELY CORRODED ALONG WITH THE ELECTRICAL CONNECTOR AND MOUNTING POSTS.					1	H	7	1 	3O				3A21
1998071700312	19980717	00312	EU  	1998	7	17	AU980575         	2	19980527	G	7230	720481	BEARING         	GE          	CDM563C1    						CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1 ENGINE	FAILED          	H				K	E			NONE                    	ENGINE SHUTDOWN         			E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CR	CRUISE         	1			AU	S 			28929		720481		720481			(AUS) NR 1 ENGINE FAILED.  SUSPECT CAUSED BY FAILURE OF NR 4 BEARING.  PART TC:  28,929.											4	F			E21EU
1998071700313	19980717	00313	NM  	1998	7	17	AU980576         	1	19980125	G	2150	1254591ANSETTS	BEARING         			BOEING	737   	737377      		NM  										AIR CONDITIONING	FAILED          	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			10289		1254591ANSET					(AUS) LT AIR CONDITIONING SYSTEM AIR CYCLE MACHINE FAILED.  SUSPECT CAUSED BY FAILURE OF THE AIR CYCLE MACHINE COMPRESSO	R BEARING CAUSING THE ACM TO SEIZE.  THE RT RAM AIR CONTROL MODULE P\N 607518-2 FAILED SHORTLY AFTER DUE TO BREAKING DOW	N OF THE THRISTOR CR17.  PART TC:  28,268.				2	L	7	2 	4F			RT	A16WE
1998071700314	19980717	00314	EU  	1998	7	17	AU980577         	1	19980530	G	2910	SA7670006	HOSE            			BAG   	BAE146	BAE146100A  	1500260	EU  										HYDRAULIC SYSTEM	FAILED          	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 										(AUS) LT LANDING GEAR RETRACTION ACTUATOR PRESSURE HOSE FAILED.  LOSS OF GREEN SYSTEM HYDRAULIC FLUID.						2	H	7	4 	4F			RT	A49EU
1998071700315	19980717	00315	EA  	1998	7	17	AU980578         	2	19980415	G	7421	REM40E	SPARK PLUG      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH				ENGINE	FAILED          	H				K				NONE                    				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		LD	LANDING        	1			AU	S 							L731339A			(AUS) NR 3 CYLINDER TOP SPARK PLUG CENTER ELECTRODE CERAMIC BROKEN.  NR 3 CYLINDER LOWER SPARK PLUG FOULED.						1	L	7	1 	3O	3	O		2A13    	E274
1998071700316	19980717	00316	EU  	1998	7	17	AU980579         	1	19980528	G	6121		ACTUATOR        			STBROS	SD3   	SD360       	8100606	EU  										PROP CONTROL	FAILED          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LT PROPELLER SYNCHRONIZATION SYSTEM FAILED.  PROPELLER CONTROL ACTUATOR FULLY WOUND ONE WAY PREVENTING THE GOVERNO	R ARM FROM REACHING THE MAXIMUM RPM STOP.					2	H	7	2 	4T				A41EU
1998071700317	19980717	00317	EU  	1998	7	17	AU980580         	1	19980526	G	3270		SUPPORT         			STBROS	SD3   	SD360       	8100606	EU  										TAIL	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			TO	TAKEOFF        	1			AU	S 										(AUS) AIRCRAFT TAIL SUPPORT STRUT (POGO STICK) NOT REMOVED AND STOWED BEFORE THE AIRCRAFT DEPARTED.						2	H	7	2 	4T			 	A41EU
1998071700318	19980717	00318	SO  	1998	7	17	AU980581         	1	19980529	G	5341		FITTING         			PIPER 	PA25  	PA25235     	7102504	SO  						MCAULY				RT/LT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING/FUSELAGE ATTACHMENT FITTING CLUSTERS CRACKED IN THE FOLLOWING LOCATIONS:  LT FORWARD CLUSTER CONTAI	NED ONE 3MM (0.118 INCH) CRACK IN THE FORWARD LUG LOWER SURFACE AND ONE 7MM (0.275 INCH) CRACK IN THE AFT LUG LOWER SURF	ACE.  RT FORWARD CLUSTER CONTAINED ONE 7MM (0.275 INCH) CRACK IN THE AFT LUG LOWER SURFACE.				1	L	7	1 	3O				2A10
1998071700319	19980717	00319	SO  	1998	7	17	AU980582         	1	19980529	G	5711	2020343L	SPAR CAP        			AYRES 	S2    	S2RR1820    	0970215	SO  										LT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SPAR CAP CRACKED AT SPLICE ATTACHMENT BOLT HOLE.						1	L	7	1 	4R				A4SW
1998071700320	19980717	00320		1998	7	17	AU980583         	4	19980515	G	2350		TRANSMITTER     	NARCO       	MARK12D     	CESSNA	150   	150M        	2071830	CE  										COCKPIT	FAULTY          	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) TRANSMIT INTERLOCK FAULTY.						1	H	7	1 	3O				3A19
1998071700321	19980717	00321	SO  	1998	7	17	AU980584         	1	19980520	G	5730		SKIN            			PIPER 	PA31  	PA31350     	7103110	SO  										WS 77	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING LOWER SKIN CORRODED IN AREA OF STN 77.50.						1	L	7	2 	3O				A20SO
1998071700322	19980717	00322	SO  	1998	7	17	AU980585         	2	19980525	G	7322	46A65	VENTURI         	FACET       	IO4439      	CESSNA	172   	172B        	2072406	CE  	CONT  	O300  	O300C       	17022	SO  	MCAULY				CARBURETOR	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			679  		53B2657		30R057			(AUS) CARBURETOR VENTURI LOOSE.						1	H	7	1 	3O	3	O	NT	3A12    	E253
1998071700323	19980717	00323	SW  	1998	7	17	AU980586         	1	19980525	G	2910	212076162001	PIPE            			BELL  	412   	412         	1182202	SW  										HYDRAULIC SYSTEM	DAMAGED         	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) NR 2 HYDRAULIC SYSTEM PIPE FAILED.  A SECOND PIPE WAS FOUND TO BE DAMAGED.  BOTH PIPES WERE DAMAGED DUE TO POOR RO	UTING AND CHAFING AND ARE LOCATED IN THE HELL HOLE AREA BEHIND THE LIFT BEAM.  PART TC:  1,087.					1	G	7	2 	4U			 	H4SW
1998071700324	19980717	00324	SW  	1998	7	17	AU980587         	1	19980512	G	2742	2719008002	ACTUATOR        			SWRNGN	SA227 	SA227AC     	8780603	SW  										HORIZONTAL STAB	CONTAMINATED    	H				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 					205					(AUS) PITCH TRIM ACTUATOR CONTAMINATED WITH WATER.						2	L	7	2 	4T			RT	A8SW
1998071700325	19980717	00325		1998	7	17	AU980588         	4	19980112	G	6113	AEP8	BACKPLATE       																	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNER BACKPLATE CRACKED AROUND THE CIRCUMFERENCE OF THE PROPELLER FLANGE AND THE BOLT HOLES ELONGATED.	  PART TC:  130.
1998071700326	19980717	00326		1998	7	17	AU980589         	4	19980501	G	6113	AEP8	BACKPLATE       																	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNER BACKPLATE CRACKED AROUND THE CIRCUMFERENCE OF THE PROPELLER FLANGE AND THE BOLT HOLES ELONGATED.	 BOLT HOLES INTHE PROPELLER ARE ALSO SHOWING SIGNS OF ELONGATION.  PART TC:  66
1998071700327	19980717	00327		1998	7	17	AU980590         	4	19980519	G	6113	AEP8	BACKPLATE       																	PROPELLER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PROPELLER SPINNER BACKPLATE CRACKED AROUND THE CIRCUMFERENCE AND BOLT HOLES ELONGATED.  BOLT HOLES IN THE PROPELLE	R ARE ALSO STARTING TO SHOW SIGNS OF ELONGATION.
1998071700328	19980717	00328		1998	7	17	AU980591         	4	19980526	G	3442	7008470912	ANTENNA         			FOKKER	F27   	F27MK50     		EU  										RADAR	CONTAMINATED    	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					86100188					(AUS) RADAR ANTENNA/TRANSCEIVER FAILED.  SUSPECT CAUSED BY WATER INGRESS.						2	H	7	2 	4T			RT	A817
1998071700329	19980717	00329	EU  	1998	7	17	AU980592         	1	19980524	G	2842	TWAS1024U182	TRANSMITTER     			BAG   	JETSTM	JETSTM3107  	1500215	EU  										FUEL SYSTEM	FAILED          	H				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) RT FUEL TRANSMITTER FAILED.						2	L	7	2 	4T			RT	BA15CAA
1998071700330	19980717	00330	EA  	1998	7	17	AU980594         	1	19980602	G	3244	256K433	TIRE            		6008512315  	CNDAIR	CL600 	CL6002B16   	1900305	EA  										LT MLG	FAILED          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					OCT890133					(AUS) LT INNER TIRE FAILED DURING TAKEOFF. LT OUTER TIRE FAILED ON LANDING.						2	L	7	2 	4F			RT	A21EA
1998071700331	19980717	00331	SO  	1998	7	17	AU980595         	1	19980525	G	7922	53E19600	THERMO VALVE    			MAULE 	MX7   	MX7180      	5460185	SO  						HARTZL				ENGINE	NUT LOOSE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L3206136A		L3206136A			(AUS) THERMOSTATIC OIL COOLER BYPASS VALVE (VERNATHERM) SHAFT NUT LOOSE.  FOUND DURING INSPECTION IAW AD/LYC/78 AMDT5. P	ART TC:  770.					1	H	7	1 	3O			NC	3A23
1998071700332	19980717	00332	CE  	1998	7	17	AU980597         	1	19980527	G	5751		FITTING         			CESSNA	500   	S550        	2076607	CE  										RT AILERON	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A00600072					(AUS) RT AILERON HINGE FITTINGS CONTAINED INTERGRANNULAR CORROSION.  PART TC:  7,910.						1	L	7	2 	4F			RT	A22CE
1998071700333	19980717	00333	CE  	1998	7	17	AU980598         	1	19980525	G	5751		HINGE           			CESSNA	500   	S550        	2076607	CE  										LT AILERON	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A00100083					(AUS) LT AILERON HINGE FLANGE BROKEN.  INTERGRANNULAR CORROSION WAS ALSO FOUND IN THE HINGES.  PART TC:  7,910.						1	L	7	2 	4F			RT	A22CE
1998071700334	19980717	00334	CE  	1998	7	17	AU980599         	1	19980526	G	3230	3581507714	BRACKET         			BEECH 	33    	35C33       	1151408	CE  										LT MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR UPLOCK BRACKET CORRODED IN THE AREA OF THE UPLOCK PIVOT POINT.  PART 5,634.						1	L	7	1 	3O				3A15
1998071700335	19980717	00335	SO  	1998	7	17	AU980601         	2	19980505	G	8520	537290	CRANKSHAFT      			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY				ENGINE	PITTED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1788 		712355		132305	712355		(AUS) CRANKSHAFT PITTED IN AREA OF CRANKSHAFT FELT SEAL.  THE DEPTH OF THE PITTING WAS 0.127MM TO 0.254MM (0.005 INCH TO	 0.010 INCH).  SUSPECT CAUSED BY MOISTURE RETENTION OF THE FELT SEAL.					1	H	7	1 	3O	3	O	NT	3A13    	E273
1998071700336	19980717	00336	NM  	1998	7	17	AU980602         	1	19980523	G	2612	87858101	CONNECTOR       			BOEING	737   	737377      		NM  										APU FIRE DETECT	SHORTED         	H				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) APU FIRE DETECTOR LOOP CONNECTOR SHORT CIRCUITED BETWEEN THE CENTER PIN AND THE OUTER SHELL.  FALSE APU FIRE WARNI	NG RESULTED IN THE FIRE BOTTLE BEING DISCHARGED.					2	L	7	2 	4F			RT	A16WE
1998071700337	19980717	00337		1998	7	17	AU980603         	4	19980531	G	3425		EFI SYSTEM      			BAG   	BAE146	BAE146200A  	1500266	EU  										E/E BAY	SHORTED         	H				K				NONE                    				F	G		FLT CONT AFFECTED         	MULTIPLE FAILURE          		TO	TAKEOFF        	1			AU	S 										(AUS) E/E BAY CONTAMINATED WITH WATER LEAKING FROM THE GALLEY.  LOSS OF ALL FOUR EFIS SCREENS.						2	H	7	4 	4F			RT	A49EU
1998071700338	19980717	00338	SO  	1998	7	17	AU980604         	1	19980511	G	2140	90D382	HEATER          	JANITROL    	90D382      	PIPER 	PA44  	PA44180T    	7104404	SO  										CABIN	FAULTY          	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 			36   		11801045					(AUS) CABIN HEATER SMOKING.  INVESTIGATION COULD FIND NO PROBLEMS.  SUSPECT FOREIGN OBJECT ENTERED THE HEATER AND BURNED	 UP.  PART TC:  6,261.					1	L	7	2 	3O				A19SO
1998071700339	19980717	00339	CE  	1998	7	17	AU980605         	1	19980526	G	3221	12430097	TRUNNION        			CESSNA	210   	T210N       	2073456	CE  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR LOWER TRUNNION CRACKED ON THE SIDE BRACE ATTACHMENT LUGS.  CRACKING INITIATED IN THE MACHINING R	ADIUS.  PART TC:  3,647.					1	H	7	1 	3O				3A21
1998071700340	19980717	00340	CE  	1998	7	17	AU980606         	1	19980526	G	3222	12430097	TORQUE LINK     		12430097    	CESSNA	210   	T210N       	2073456	CE  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR UPPER TORQUE LINK CONTAINED THREE CRACKS IN THE AREA ADJACENT TO THE SQUAT SWITCH MOUNT HOLES. P	ART TC:  3,467.					1	H	7	1 	3O				3A21
1998071700341	19980717	00341	CE  	1998	7	17	AU980607         	1	19980526	G	7160		CLAMP           		05540061    	CESSNA	172   	172N        	2072434	CE  						MCAULY				ENGINE	BROKEN          	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		DE	DESCENT        	1			AU	S 			450  							(AUS) CARBURETOR HEAT SHROUD ATTACHMENT CLAMP BROKEN.  A PIECE OF THE CLAMP FELL INTO THE HEAT DUCT AND LODGED UNDER THE	 ALTERNATE AIRDOOR BEFORE ENTERING THE CARBURETOR VENTURI.  THE SAFETY MESH WAS MISSING FROM THE HOT AIR INTAKE OF THE C	ARBURETOR HEAT SHROUD.				1	H	7	1 	3O			NT	3A12
1998071700342	19980717	00342		1998	7	17	AU980608         	4	19980505	G	2210	7002800914	ACTUATOR        			AMD   	FALC50	FALCON900   	2700160	EU  										AFCS	FAULTY          	H				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 										(AUS) YAW DAMPER LINEAR ACTUATOR FAULTY.						2	L	7	3 	4F			RT	A46EU
1998071700343	19980717	00343	CE  	1998	7	17	AU980611         	1	19980512	G	7722	89720524	COMPENSATOR     			CESSNA	441   	441         	2076020	CE  										ENGINE EGT	FAULTY          	H				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 										(AUS) ENGINE EGT COMPENSATOR FAULTY.						1	L	7	2 	3T			RT	A28CE
1998071700344	19980717	00344	NE  	1998	7	17	AU980612         	2	19980130	G	7313	PHC1088Y	NOZZLE          								GE    	CF6   	CF680A      	30025	NE  					FUEL INJECTOR	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					PHC1088Y		580242			(AUS) NR 1 ENGINE FUEL NOZZLE ELBOW CRACKED AND LEAKING FUEL.  THE NOZZLE WAS LOCATED AT APPROXIMATELY THE 1 O'CLOCK POS	ITION.  THE ELBOW WAS IDENTIFIED AS AN OLD TYPE CAST ELBOW WHICH HAD BEEN FOUND TO BE PRONE TO POROSITY.										4	F			E13NE
1998071700345	19980717	00345		1998	7	17	AU980613         	1	19980411	G	3213		STRUT           			AMTR  		JABIRUSK    												MLG	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LT LANDING GEAR LEG FAILED IN AREA OF MAIN BOLT HOLE.  MAINSHACKLE `U' BOLT FRACTURED.  THIS DEFECT WAS RECEIVED F	ROM THE AUF AND IS FOR INFORMATION ONLY.								0
1998071700346	19980717	00346	NE  	1998	7	17	AU980614         	2	19980125	G	7321	GEJN0236ANSETTS	FCU             								CFMINT	CFM56 	CFM565A1    		NE  					FUEL SYSTEM	FAILED          	H				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		NR	NOT REPORTED   	1			AU	S 			894  		GEJN0236ANSE		731159			(AUS) NR 2 ENGINE ELECTRONIC FUEL CONTROL UNIT (EFU) FAULTY.  WORKSHOP INVESTIGATION FOUND THE UNIT FAILED PRESSURE SUB-	SYSTEM CHANNEL `A' TEST.  PART TC:  21,089.										4	F			E29NE
1998071700347	19980717	00347	SO  	1998	7	17	AU980615         	1	19980529	G	5711		SPAR CAP        			AYRES 	S2    	S2RT15NORMAL	0970105	SO  										RT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING LOWER SPAR CAP CRACKED IN THE BOLT HOLE.  FOUND USING EDDY CURRENT AND MAGNETIC PARTICLE INSPECTION TECHNI	QUES.  REF:  MDR98/0643.  PART TC:  22,176.					1	L	7	1 	3T				A3SW
1998071700348	19980717	00348	SO  	1998	7	17	AU980616         	1	19980529	G	5711	20207T901	SPAR CAP        		S2RT15      	AYRES 	S2    	S2RT15NORMAL	0970105	SO  										LT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					027					(AUS) LT WING LOWER SPAR CAP CRACKED IN HOLE.  FOUND DURING MAGNETIC PARTICLE INSPECTION.  PART TC:  4,879.  PART TC:  4	,879.					1	L	7	1 	3T				A3SW
1998071700349	19980717	00349	SO  	1998	7	17	AU980617         	1	19980529	G	5711	20207T902	SPAR CAP        	AYRES       	S2RT15      	AYRES 	S2    	S2RT15NORMAL	0970105	SO  										RT WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					027					(AUS) RT WING LOWER SPAR CAP CRACKED IN BOLT HOLES.  FOUND DURING MAGNETIC PARTICLE INSPECTION IAW AYRES SB-AG-39 AND AD	/AC-SNOW/24 AMDT1.PART TC:  4,879.					1	L	7	1 	3T				A3SW
1998071700350	19980717	00350	CE  	1998	7	17	AU980618         	1	19980609	G	2910		PIPE            			CESSNA	404   	404CESSNA   	2075901	CE  										HYDRAULIC SYSTEM	CORRODED        	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED UNDER THE CABIN FLOOR CONTAINED A SERIES OF PIN HOLES DUE TO CORROSION. THE AREA OF CORROSI	ON WAS LOCATED OVER A 100MM (4 INCH) LENGTH.  PIPE WAS ORIGINAL FITTING.  PART TC:  23,430.					1	L	7	2 	3O				A25CE
1998071700351	19980717	00351	CE  	1998	7	17	AU980619         	1	19980606	G	2750	511523716	REDUCTION GEAR  			CESSNA	402   	402C        	207590R	CE  										TE FLAP CONTROL	FAILED          	H				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 					UK					(AUS) FLAP GEARBOX ASSEMBLY NOISY.  STRIP INSPECTION FOUND THE REDUCTION GEAR TEETH STRIPPED.						1	L	7	2 	3O				A7CE
1998071700352	19980717	00352	WP  	1998	7	17	AU980620         	2	19980608	G	7322	3499034	SHAFT           	WOODWARD    	89778025    	FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY				FCU	STRIPPED        	H				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 			3325 		2173792		P70162			(AUS) LT ENGINE FUEL CONTROL UNIT (FCU) DRIVESHAFT INTERNAL SPLINES STRIPPED.  PART TC:  3,325.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
1998071700353	19980717	00353	CE  	1998	7	17	AU980621         	1	19980520	G	5741	351150583	FITTING         		200         	BEECH 	200   	200BEECH    	1152920	CE  										RT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT WING LOWER REAR FITTINGS CORRODED.						1	L	7	2 	4T				A24CE
1998071700354	19980717	00354	SO  	1998	7	17	AU980622         	2	19980522	G	8530	653446	CYLINDER        			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY				ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					175939R		175939R	931708		(AUS) ENGINE CYLINDER CRACKED BETWEEN THE EXHAUST VALVE AND THE LOWER SPARK PLUG HOLE.  PART TC:  1,680.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998071700355	19980717	00355	CE  	1998	7	17	AU980623         	1	19980609	G	5520	NAS682A3	NUT PLATE       			CESSNA	150   	150L        	2071826	CE  										RT ELEVATOR	FAULTY          	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) RT ELEVATOR OUTBOARD HINGE BOLT NUTPLATE LOCKING FUNCTION FAILED TO LOCK THE BOLT ALLOWING THE BOLT TO FALL OUT. T	HE BOLT WAS FOUND IN THE TIP FAIRING.					1	H	7	1 	3O				3A19
1998071700356	19980717	00356	SW  	1998	7	17	AU980624         	1	19980522	G	3233	AN415	BOLT            			GULSTM	112   	114         	7630314	SW  										NLG	BROKEN          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR ACTUATOR UPPER ATTACHMENT BOLT SHEARED.						1	L	7	1 	3O				A12SO
1998071700357	19980717	00357	NE  	1998	7	17	AU980625         	2	19980606	G	7320	3016724	LINE            								PWA   	PT6   	PT6A112     	52043	NE  					RT ENGINE	BROKEN          	H				K				NONE                    				W			INADEQUATE Q C            			LD	LANDING        	1			AU	S 							PCE12575			(AUS) RT ENGINE P3 LINE FOUND BROKEN AT COMPRESSOR CASE FLANGE END.  SUSPECT CAUSED BY CONTINUALLY DISCONNECTING AND REC	ONNECTING THE LINE FOR ENGINE COMPRESSOR WASHES.										3	T			E4EA
1998072200005	19980722	00005	NE  	1998	7	22	AU980626         	2	19980529	G	7200		INDICATORS      			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67      	52043	NE  					ENGINE	FLUCTUATE       	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 							110042			(AUS) ENGINE INSTRUMENTS FLUCTUATING.  INSPECTION OF THE ENGINE AND THE OIL FILTER FOLLOWED BY GROUND RUNS AND TEST FLIG	HT COULD NOT CONFIRM THE DEFECT.					1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
1998071700358	19980717	00358	SW  	1998	7	17	AU980627         	1	19980527	G	5743	730090002	SUPPORT         			GULSTM	690TP 	695B        	3970610	SW  										RT MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LANDING GEAR SUPPORT ASSEMBLY CRACKED.						1	H	7	2 	4T			RT	2A4
1998071700359	19980717	00359	EU  	1998	7	17	AU980628         	1	19980603	G	2612	1734362450	FIRE DETECTOR   			SAAB  	SF340 	340B        	7860101	EU  										RT ENGINE	CONTAMINATED    	H				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) RT ENGINE FIRE DETECTORS CONTAMINATED WITH MOISTURE.  PART TC:  12,329.						2	L	7	2 	4T			RT	A52EU
1998071700360	19980717	00360	SO  	1998	7	17	AU980629         	1	19980424	G	3260	MS243311	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	FAULTY          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR SAFETY MICROSWITCH WIRING INSULATION FAULTY.						1	L	7	2 	3O				A20SO
1998071700361	19980717	00361	SO  	1998	7	17	AU980630         	1	19980610	G	3230	41789000	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	DAMAGED         	H				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 					317552104					(AUS) RT MAIN LANDING GEAR RETRACTION LINK FORK BOLT BENT PREVENTING CORRECT LANDING GEAR INDICATIONS.						1	L	7	2 	3O				A20SO
1998071700362	19980717	00362	SO  	1998	7	17	AU980631         	1	19980612	G	5510	42235	HINGE           			PIPER 	PA31  	PA31350     	7103110	SO  										LT HORIZ STAB	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT HORIZONTAL STABILIZER OUTBOARD HINGE ASSEMBLY CRACKED.						1	L	7	2 	3O				A20SO
1998071700363	19980717	00363	SO  	1998	7	17	AU980632         	1	19980612	G	5521		SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  										LT ELEVATOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ELEVATOR SPAR CRACKED IN AREA OF ATTACHMENT FOR THE ELEVATOR TORQUE TUBE ASSEMBLY.  FOUND DURING INSPECTION IAW	 PIPER SB 1008.  PART TC:  9,523.					1	L	7	2 	3O				A20SO
1998071700364	19980717	00364	WP  	1998	7	17	AU980633         	2	19980611	G	7322	89737524	FCU             								GARRTT	TPE331	TPE33111U   	01514	WP  					FUEL SYSTEM	FAULTY          	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			5988 		2173576		44709			(AUS) ENGINE FUEL CONTROL UNIT FAULTY.											4	T			E4WE
1998071700365	19980717	00365	EU  	1998	7	17	AU980634         	1	19980529	G	5243		BLADES          			AIRBUS	300   	A300B4203   	3930306	EU  										RAM AIR TURBINE	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RAM AIR TURBINE BLADES DAMAGED.  INVESTIGATION FOUND THAT THE INBOARD DOOR HAD NOT DEPLOYED TO THE CORRECT POSITIO	N DUE TO STIFF DEPLOYMENT CRANK OPERATION.  FURTHER DAMAGE FOUND TO THE BLADE LOCK PIN AND PIN ENGAGEMENT AREA.					2	L	7	2 	4F				A35EU
1998071700366	19980717	00366	CE  	1998	7	17	AU980635         	1	19980505	G	5343	3580961	BRACKET         		3580962     	CESSNA	185   	A185E       	2072818	CE  										FLOAT ATTACH	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT AFT FLOAT STRUT ATTACHMENT FITTINGS P/N 35-8096-1 AND P/N 35-8096-2 CRACKED AND CORRODED.  PART TC:  4,8	25.					1	H	7	1 	3O				3A24
1998071700367	19980717	00367	EU  	1998	7	17	AU980636         	1	19980322	G	3250	MF171ANSETTSN	CONTROL UNIT    			AIRBUS	320   	A320212     		EU  										LG STEERING	FAULTY          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			8998 		MF171ANSETTS					(AUS) BRAKE STEERING CONTROL UNIT K5 RELAY FAILED.  ELECTRO/HYDRAULIC STEERING MODULE ALSO FAULTY.  PART TC:  12,636.						2	L	7	2 	4F			RT	A28NM
1998071700368	19980717	00368	SO  	1998	7	17	AU980637         	1	19980609	G	5343	M18	PLATE           			MAULE 	M7    	M7235       	5460170	SO  										LT MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) FORWARD LT CROSS BRACE PLATE CORRODED ALLOWING THE ATTACHMENT PIN TO PULL THROUGH THE PLATE.						1	H	7	1 	3O			NC	3A23
1998071700369	19980717	00369	CE  	1998	7	17	AU980638         	1	19980505	G	5343	071349561	BRACKET         			CESSNA	185   	A185E       	2072818	CE  										MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR SUPPORT BRACKET CORRODED.  AIRCRAFT IS A FLOAT PLANE OPERATING IN A SALT LADEN ENVIRONMENT.  PART TC:	  7,399.					1	H	7	1 	3O				3A24
1998071700370	19980717	00370	CE  	1998	7	17	AU980639         	1	19980608	G	3244	184410	TIRE            			CESSNA	500   	550         	2076604	CE  										NLG	FAILED          	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE WHEEL TIRE BLEW OUT WHILE BEING INFLATED TO APPROXIMATELY 60 PSI.						1	L	7	2 	4F			 	A22CE
1998071700371	19980717	00371	EA  	1998	7	17	AU980640         	2	19980602	G	7314	RG9080J4A	PUMP            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					RT ENGINE	SEIZED          	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AU	S 			1748 		L484861A		L484861A			(AUS) RT ENGINE DRIVEN FUEL PUMP FAILED INTERNALLY.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998071700372	19980717	00372	NE  	1998	7	17	AU980641         	2	19980612	G	7250		BOLT            			AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  					ENGINE	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							PCE57337			(AUS) ENGINE COMPRESSOR TURBINE AIR SEAL STATOR ATTACHMENT BOLTS (8OFF) LOOSE.  BOLTS WERE FITTED WITH TAB WASHERS WHICH	 HAD NOT BEEN LOCKED.  SIXTEEN OTHER BOLTS WERE FOUND TO BE TIGHT BUT NOT FITTED WITH TAB WASHERS.  FOUND DURING DISASSE	MBLY FOR OVERHAUL.				1	L	7	1 	3T	4	T		A3SW    	E4EA
1998071700373	19980717	00373	SO  	1998	7	17	AU980642         	2	19980611	G	7320	630626	BRACKET         			CESSNA	182   	182A        	2072704	CE  	CONT  	O470  	O470L       	17026	SO  					BALANCE TUBE	BROKEN          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							069769R			(AUS) ENGINE INDUCTION SYSTEM BALANCE TUBE SUPPORT BRACKET BROKEN.  ENGINE BACKFIRE CAUSED BALANCE TUBE TO COME OUT OF R	UBBERS.					1	H	7	1 	3O	3	O	NT	3A13    	E273
1998071700374	19980717	00374	SO  	1998	7	17	AU980643         	1	19980529	G	5711	20207T90I	SPAR CAP        			AYRES 	S2    	S2RT15NORMAL	0970105	SO  										SPAR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SPAR CAP CRACKED.						1	L	7	1 	3T				A3SW
1998071700375	19980717	00375	WP  	1998	7	17	AU980644         	1	19980618	G	5753	241609	LUG             			FLTCHR	24    	FU24AAIRPTS 	3530204	WP  										TE FLAP HORN	BROKEN          	H				K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			AU	S 										(AUS) LT FLAP CONTROL HORN LUG FAILED.						1	L	7	1 	3O				4A12
1998071700376	19980717	00376	NE  	1998	7	17	AU980645         	3	19980615	G	6110		PROPELLER       			EMB   	120   	EMB120      	3260201	SO  						HAMSTD	14RF	14RF9       	NE  	RT ENGINE	FOD             	H				K				NONE                    				C	F		F.O.D.                    	FLT CONT AFFECTED         		LD	LANDING        	1			AU	S 										(AUS) RT PROPELLER CONTACTED A LARGE KANGAROO DURING LANDING.  INVESTIGATION FOUND ONE PROPELLER BLADE DAMAGED AND THE B	LADE RETAINING CLAMPS BROKEN.  RT ENGINE AND PROPELLER REPLACED.					2	L	7	2 	4T			RT	A31SO   		6	C	P11NE
1998071700377	19980717	00377	EA  	1998	7	17	AU980646         	2	19980611	G	7420	50383	IGNITOR LEAD    		103815501E  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL				RT ENGINE	BROKEN          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					10276					(AUS) RT ENGINE IGNITOR LEAD BROKEN.  THE FOLLOWING DEFECTS IN THE IGNITION SYSTEM WERE ALSO FOUND:  1.  RELAY P/N 50-38	0048-1.  2.  FUEL INDICATION CB PANEL CONNECTOR J108 CONTAMINATED WITH MOISTURE AND CORROSION.  3. IGNITOR BOX P/N 10-38	1550.				1	L	7	2 	4T	4	T		A24CE   	E4EA
1998071700378	19980717	00378	SW  	1998	7	17	AU980647         	1	19980616	G	2720	705245	CABLES          			AIRTRC	AT802 	AT802       	0390305	SW  										RUDDER CONTROL	FRAYED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT RUDDER CONTROL CABLES BADLY FRAYED AND CLOSE TO FAILURE IN THE AREA WHERE THEY PASS THROUGH THE FAIRLEAD	S IN THE AFT SEAL BULKHEAD.  PART TC:  382.					1	L	7	1 	3T			NC	A19SW
1998071700379	19980717	00379	NM  	1998	7	17	AU980648         	1	19980610	G	2751		TRANSMITTER     			BOEING	757   	757200      	1384950	NM  										TE FLAP	FAULTY          	H				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) TE FLAP INDICATING SYSTEM SUSPECT FAULTY.  INVESTIGATION FOUND THE LT WING FLAP POSITION TRANSMITTER OUT OF LIMITS	.					2	L	7	2 	4F			RT	A2NM
1998071700380	19980717	00380	GL  	1998	7	17	AU980649         	3	19980610	G	6110	3A32C76SM	O-RING          			BEECH 	36    	A36         	1151604	CE  						MCAULY	3A32C	3A32C76     	GL  	PROP ASSEMBLY	IMPROPER PART   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			1460 		787474					(AUS) PROPELLER BLADE RETENTION NUT `O' RING SEALS WERE THE INCORRECT PART.  TWO FERRULES P/N C4451 WERE LOOSE.  ONE FER	RULE HAD BEEN INCORRECTLY DRILLED.  PROPELLER FULL OF CORROSION.  UNAPPROVED PART.PART TC:  4,431.					1	L	7	1 	3O			 	3A15    		5	C	P21EA
1998071700381	19980717	00381	NE  	1998	7	17	AU980650         	2	19980602	G	7322	A34712	O-RING          	BENDIX      	324473512   	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					FCU	DAMAGED         	H				K				NONE                    				K			FLUID LOSS                			HO	HOVERING       	1			AU	S 					A34712		CPPS63295			(AUS) NR 1 ENGINE FUEL CONTROL UNIT `O' RING SEAL DAMAGED.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998071700382	19980717	00382	SO  	1998	7	17	AU980651         	2	19980204	G	8530		CYLINDER        			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							65861	B1002		(AUS) NR 2 CYLINDER WORN BEYOND LIMITS.						1	H	7	1 	3O	3	O		3A19    	E252
1998071700383	19980717	00383	SO  	1998	7	17	AU980652         	1	19980322	G	2824	756227	VALVE           		PA39        	PIPER 	PA30  	PA39        	7103902	SO  										FUEL TRANSFER	CONTAMINATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT TIP TANK FUEL TRANSFER SOLENOID VALVE FAULTY.  PART TC:  7,363.						1	L	7	2 	3O				A1EA
1998071700384	19980717	00384	EU  	1998	7	17	AU980653         	1	19980115	G	2820		PIPE            			PARTEN	P68   	P68B        		EU  										FUEL SYSTEM	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT FUEL SELECTOR PIPE TO TANK LOOSE.						1	H	7	2 	3O				A31EU
1998071700385	19980717	00385	EU  	1998	7	17	AU980654         	1	19980323	G	2752	D5757030500200	STRUT           			AIRBUS	320   	A320212     		EU  										TE FLAP ACTUATOR	DEFECTIVE       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					G061ANSSNO02					(AUS) FLAP ACTUATOR STRUT FAULTY.  INVESTIGATION FOUND THE CONNECTING STRUT IN VERY POOR CONDITION WITH SEVERAL PARTS DA	MAGED.  PART TC:  27,357.					2	L	7	2 	4F			RT	A28NM
1998071700386	19980717	00386	NE  	1998	7	17	AU980655         	2	19980212	G	7230	3968007	MOTOR           								CFMINT	CFM56 	CFM565A1    		NE  					COMPRESSOR	FAILED          	H				K				NONE                    				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			AU	S 			23691		2794ANSSNO03					(AUS) COMPRESSOR GUIDE VANE MOTOR FAULTY.  PART TC:  23,691.											4	F			E29NE
1998071700387	19980717	00387	EU  	1998	7	17	AU980656         	1	19980330	G	2760	831A000005	SLAT            			AIRBUS	320   	A320212     		EU  										WINGS	JAMMED          	H				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 					2685ANSSNO00					(AUS) WING SLATS JAMMED.  INVESTIGATION FOUND LT WING TIP BRAKE VERY TIGHT IN OPERATION.  PART TC:  5,190.						2	L	7	2 	4F			RT	A28NM
1998071700388	19980717	00388	EU  	1998	7	17	AU980657         	1	19980615	G	5270		SWITCH          			FOKKER	F28   	F28MK4000   	4990810	EU  										PASS DOOR	FAULTY          	H				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) PASSENGER DOOR LOCK MICROSWITCH FAULTY.						2	L	7	2 	4F			RT	A20EU
1998071700389	19980717	00389	EU  	1998	7	17	AU980658         	1	19980614	G	3230		ACTUATOR        			FOKKER	F28   	F28MK4000   	4990810	EU  										RT MLG	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK ACTUATOR LEAKING.						2	L	7	2 	4F			RT	A20EU
1998071700390	19980717	00390	EU  	1998	7	17	AU980659         	1	19980614	G	2752		GEARBOX         			FOKKER	F28   	F28MK4000   	4990810	EU  										TE FLAP ACTUATOR	FAILED          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAP MAIN DRIVE GEARBOX FAILED.						2	L	7	2 	4F			RT	A20EU
1998071700391	19980717	00391	SO  	1998	7	17	AU980660         	2	19980515	G	8550		HOSE            			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	TSIO520R    	17040	SO  					TURBOCHARGER	BURNT           	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							293517R			(AUS) FLEXIBLE OIL SUPPLY LINES TO TURBOCHARGER AND OIL PRESSURE HOSE BURNT DUE TO BEING ROUTED UNDER THE REAR EXHAUST P	IPE.  ONE HOSE HAD BEEN BURNT SUFFICIENTLY FOR OIL LEAKAGE TO OCCUR.					1	H	7	1 	3O	3	O		3A21    	E8CE
1998071700392	19980717	00392	SW  	1998	7	17	AU980661         	1	19980609	G	6410	206010765001	BEARING         		206016201   	BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			640  		CS13431131					(AUS) TAIL ROTOR BLADE FEATHER BEARING CRACKED.  PART TC:  640.						1	G	7	1 	3U				H2SW
1998071700393	19980717	00393	EU  	1998	7	17	AU980662         	1	19980515	G	5523	1153551	HINGE           			GROB  	G115  	G115C       	1660303	EU  										ELEVATOR TRIM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM TAB FORWARD HINGE CRACKED AT THE LT FORWARD EDGE.  CRACK LENGTH 3MM (0.118 INCH).  PART TC:  2,815.						1	L	7	1 	3O			NT	A57EU
1999012100007	19990121	00007	EU  	1999	1	21	AU980663         	1	19980421	G	5320	TB1021029765	STIFFENER       			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  										CABIN	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN FLOOR STIFFENER CRACKED IN AREA OF FLAP CONTROL TORQUE TUBE SUPPORT REAR ANCHOR NUT HOLE.  PART TC:  6,271.						1	L	7	1 	3O			NT	A51EU
1998071700394	19980717	00394	CE  	1998	7	17	AU980664         	1	19980608	G	3260	ISEI3	SWITCH          			CESSNA	310   	310R        	2074245	CE  										LT MLG	FAULTY          	H				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) LT MAIN LANDING GEAR MICROSWITCH FAULTY.  PART TC:  6,400.						1	L	7	2 	3O				3A10
1998071700395	19980717	00395	EU  	1998	7	17	AU980667         	1	19980616	G	3213	AIR830644	STRUT           			SAAB  	SF340 	340B        	7860101	EU  										LT MLG	STICKING        	H				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 			8904 							(AUS) LT MAIN LANDING GEAR OLEO STRUT STICKING AND NOT EXTENDING WHEN THE WEIGHT WAS TAKEN OFF.  PART TC:  19,380.						2	L	7	2 	4T			RT	A52EU
1998071700396	19980717	00396	NM  	1998	7	17	AU980668         	1	19980504	G	5312		PRESS BULKHEAD  			BOEING	737   	737377      		NM  										FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB FORWARD FACE CONTAINED A TOTAL OF FIVE CRACKS.  A CRACK WAS ALSO FOUND IN THE RADIUS	 OF THE VERTICAL CHORD OF THE BULKHEAD AT LBL 5.7 LEVEL WITH THE HORIZONTAL STIFFENER AT WL 184.  FOUND DURING EDDY CURR	ENT INSPECTION IAW ER B73-53-10-39A.				2	L	7	2 	4F			RT	A16WE
1998071700397	19980717	00397	NM  	1998	7	17	AU980669         	1	19980409	G	5312		PRESS BULKHEAD  			BOEING	737   	73733A      	1384673	NM  										FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD WEB FORWARD FACE CONTAINED SIX CRACKS.  FOUND DURING EDDY CURRENT INSPECTION IAW ER B73-	53-10-39A.					2	L	7	2 	4F			RT	A16WE
1998071700398	19980717	00398	SW  	1998	7	17	AU980671         	1	19980612	G	6420	B1212	BEARING         	BELL        		BELL  	206   	206L3       	1182108	SW  										TAIL ROTOR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AFS5010					(AUS) TAIL ROTOR HUB BEARING SEIZED AND FULL OF RUST.  DURING REMOVAL, THE BEARING DISINTEGRATED.  INVESTIGATION FOUND B	RINELLING ON THE INNER AND OUTER RACES CONSISTENT WITH ONE NEEDLE ROLLER BEING ABSENT FROM THE BEARING.					1	G	7	1 	3U				H2SW
1998071700399	19980717	00399	NM  	1998	7	17	AU980672         	1	19980525	G	2920	6510SERNO6608B	SWITCH          			BOEING	767   	767338      		NM  										RAM AIR TURBINE	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RAM AIR TURBINE (RAT) AIRSPEED SWITCH FAULTY.  RAT FAILED TO DEPLOY DURING TEST IAW AD/B767/93.						2	L	7	2 	4F			RT	A1NM
1998071700400	19980717	00400		1998	7	17	AU980673         	1	19980517	G	8011	43176AC	CLAMP           																	NR2 STARTER	BROKEN          	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE STARTER MIGRATED PART OF THE WAY OUT OF THE GEARBOX SPLINES DUE TO A BROKEN STARTER CLAMP.  THE STARTE	R ADAPTER TO THE GEARBOX WAS WORN AND OIL LOSS OCCURRED.
1998071700401	19980717	00401	NM  	1998	7	17	AU980675         	1	19980602	G	2782	1267621	PDU             			BOEING	747   	747438      		NM  										LE FLAP ACTUATOR	FAULTY          	H				K				NONE                    				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) GROUP 1 LEADING EDGE FLAP POWER DRIVE UNIT (PDU) FAULTY.						2	L	7	4 	4F			RT	A20WE
1998071700402	19980717	00402		1998	7	17	AU980676         	4	19980518	G	2565	4A303715	REGULATOR       			BOEING	747   	747238B     	1384828	NM  										ESCAPE SLIDE	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					G4651					(AUS) NR 3 LT OFFWING ESCAPE SLIDE SLOW TO DEPLOY.  INVESTIGATION FOUND THAT THE INFLATION CYLINDER REGULATOR WAS AFFECT	ED BY `O' RING FRICTION.					2	L	7	4 	4F				A20WE
1998071700403	19980717	00403	SO  	1998	7	17	AU980677         	1	19980612	G	2140	FR45070ZEL	HEATER          	JANITROL    	FR45070ZEL  	PIPER 	PA23  	PA23250     	7102308	SO  										CABIN	FAILED          	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 			51   		A96050011					(AUS) CABIN HEATER FAILED.						1	L	7	2 	3O				1A10
1998071700404	19980717	00404	SW  	1998	7	17	AU980678         	1	19980610	G	5711	0933	SPAR            			GULSTM	500   	500S        	0141107	SW  										WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					0933					(AUS) WING LOWER SPAR CRACKED IN LT RADIUS.  FOUND DURING INSPECTION IAW AD/AC/42.  PART TC:  2,039.						1	H	7	2 	3O				6A1
1998071700405	19980717	00405	NM  	1998	7	17	AU980679         	1	19980625	G	3231	83231020003	SPRING          			DHAV  	DHC8  	DHC8102     	2809003	NM  										MLG DOOR	FRACTURED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AFT MAIN LANDING GEAR DOOR OPEN ASSIST SPRING BROKEN.						2	H	7	2 	4T			RT	A13NM
1999012100008	19990121	00008	EA  	1999	1	21	AU980680         	2	19980616	G	8530	LW14995	SPRING          			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL				ENGINE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3357136A			(AUS) NR 2 AND NR 3 CYLINDER PUSHROD RETAINING SPRINGS BROKEN.  PART TC:  532.						1	L	7	1 	3O	3	O	NT	A51EU   	E286
1998071700406	19980717	00406	NM  	1998	7	17	AU980681         	1	19980111	G	2822	60B9260318	PUMP            			BOEING	747   	747312      	1384932	NM  										FUEL SYSTEM	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 MAIN OUTBOARD OVERBOARD/JETTISON BOOST PUMP FAILED.  INVESTIGATION FOUND THAT THE FAULT WAS DUE TO CONDUCTIVE	 CORROSION AT THE WIRE TERMINAL ASSEMBLY.  PART TC:  64,376.					2	L	7	4 	4F			RT	A20WE
1998071700407	19980717	00407	NM  	1998	7	17	AU980682         	1	19980111	G	2822	60B890049	PUMP            			BOEING	747   	747312      	1384932	NM  										FUEL SYSTEM	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 MAIN FORWARD BOOST PUMP FAILED.  INVESTIGATION FOUND THE CAUSE OF THE FAILURE TO BE INSULATION FAILURE DUE TO	 CONDUCTIVE CORROSION AT THE WIRE TERMINAL ASSEMBLY.   PART TC:  65,844.					2	L	7	4 	4F			RT	A20WE
1998071700408	19980717	00408	NE  	1998	7	17	AU980683         	2	19980403	G	7250	3017600	ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2 ENGINE	FAILED          	H				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			E	H	X	VIBRATION/BUFFET          	ELECT. POWER LOSS-50 PC   	ENGINE FLAMEOUT           	NR	NOT REPORTED   	1			AU	S 			19046		CPPS61412		CPRS61412			(AUS) NR 2 ENGINE SURGED TWICE BEFORE SHUTTING ITSELF DOWN.  INVESTIGATION FOUND HEAT DAMAGE AROUND THE WIRING LOOM AND 	SOOT AROUND THE FUEL CONTROLS.   BOTH FIRE BOTTLES WERE DISCHARGED.  PART TC:  6,482.					1	G	7	2 	4U	4	U		H4SW    	E22EA
1998071700409	19980717	00409	CE  	1998	7	17	AU980684         	1	19980505	G	3243	8000016	O-RING          			CESSNA	210   	210L        	2073448	CE  										LT BRAKE CYL	FAILED          	H				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) LT BRAKE CYLINDER `O' RING SEAL LEAKING.   PART TC:  4,407.						1	H	7	1 	3O				3A21
1998071700410	19980717	00410	SO  	1998	7	17	AU980685         	1	19980602	G	8120	4708183	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL				RT TURBOCHARGER	WARPED          	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 			2279 		GLO106		L279268A			(AUS) RT ENGINE TURBOCHARGER WASTEGATE BUTTERFLY VALVE WARPED CAUSING THE VALVE TO STAY OPEN.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998071700411	19980717	00411	SO  	1998	7	17	AU980686         	1	19980511	G	2910		HOSE            			EMB   	120   	EMB120      	3260201	SO  										HYDRAULIC SYSTEM	LOOSE           	H				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		CL	CLIMB          	1			AU	S 										(AUS) RT ENGINE DRIVEN HYDRAULIC PUMP SUCTION HOSE LOOSE.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T			RT	A31SO
1998071700412	19980717	00412	CE  	1998	7	17	AU980687         	1	19980611	G	5743		FITTING         			CESSNA	310   	310R        	2074245	CE  										RT/LT MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR SIDE BRACE RIB ATTACHMENT AREAS CRACKED.						1	L	7	2 	3O				3A10
1998071700413	19980717	00413		1998	7	17	AU980688         	1	19980614	G	3222	U603	STRUT           			AMTR  		RV6         												NLG	FAILED          	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR LEG FAILED IN AREA OF UPPER ATTACHMENT. SUSPECT MANUFACTURING DEFECT.									0
1998071700414	19980717	00414	SW  	1998	7	17	AU980689         	1	19980506	G	6310	206040205005	BEARING         			BELL  	206   	206B        	1181511	SW  										FREEWHEEL ASSY	SEIZED          	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					BMB53041					(AUS) FREEWHEEL ASSEMBLY FORWARD BEARING P/N 206-040-205-005 AND SHAFT P/N 206-040-222-005 BEARING SURFACE FAILED. SUSPE	CT CAUSED BY OIL STARVATION DUE TO A BLOCKED ORIFICE IN THE OIL PRESSURE LINE LOCATED ON THE TRANSMISSION DECK.  DEBRIS 	FOUND IS SUSPECTED TO BE PART OF THE TRANSMISSION OIL FILTER ELEMENT.				1	G	7	1 	3U				H2SW
1998071700415	19980717	00415	EA  	1998	7	17	AU980690         	2	19980506	G	8530		CYLINDER        		O4351       	STNSON	L5    	L5B         	8630204	NE  	LYC   	O435  	O4351       	41516	EA  					ENGINE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							L0033868			(AUS) NR 5 CYLINDER LEAKING FROM BARREL/HEAD JOINT.  ENGINE WAS ON THE FIRST TEST FLIGHT FOLLOWING AN ENGINE REBUILD.						1	H	7	1 	3O	3	O		A764    	E228
1998071700416	19980717	00416		1998	7	17	AU980691         	1	19980611	G	3060	RA45185	TERMINAL        																	PROP DE-ICE	DIRTY           	H				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) RT PROPELLER ANTI-ICE SYSTEM CONTACTS BETWEEN BACKPLATE AND SPINNER DIRTY.
1998080700686	19980807	00686	SW  	1998	8	7	AU980692         	1	19980626	G	2612		DETECTOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	MALFUNCTIONED   	H				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			N			FALSE WARNING             			CR	CRUISE         	1			AU	S 							P70166			(AUS) LEFT ENGINE FIRE DETECTOR SUSPECT FAULTY.  ENGINE SHUT DOWN AND FIRE BOTTLE DISCHARGED.  INVESTIGATION COULD FIND 	NO CAUSE FOR THE FIRE WARNING SYSTEM ACTIVATION.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998080700687	19980807	00687	EU  	1998	8	7	AU980693         	1	19980627	G	2110	139005	SUPERCHARGER    		AUXGEARBOX  	FOKKER	F27   	F27MK100    	4990617	EU  	RROYCE	DART  	DART5147    		EU  	ROTOL	R4304	R1934304    	EU  	RT ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					NAF03					(AUS) RIGHT ENGINE DRIVEN CABIN SUPERCHARGER FAILED.  GEARBOX CHIP DETECTOR CONTAMINATED WITH METAL.  PART TOTAL CYCLES:	  1,611.					2	H	7	2 	4T	4	T		A817    	E283	6	C	P899
1998080700688	19980807	00688	EU  	1998	8	7	AU980694         	1	19980617	G	5610	0900041919	WINDSHIELD      			FOKKER	F27   	F27MK100    	4990617	EU  	RROYCE	DART  	DART5147    		EU  	ROTOL	R4304	R1934304    	EU  	COCKPIT	CRACKED         	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) PILOT'S WINDSCREEN OUTER PANEL CRACKED.						2	H	7	2 	4T	4	T		A817    	E283	6	C	P899
1998080700689	19980807	00689	NM  	1998	8	7	AU980695         	1	19980603	G	5210	720B	VALVE           			DHAV  	DHC8  	DHC8202     	2809007	NM  										PASSENGER DOOR	FAILED          	H				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) MAIN CABIN DOOR SEAL AIR PRESSURE ACCUMULATOR DRAIN VALVE FAULTY.  PART TOTAL CYCLES:  1,646.						2	H	7	2 	4T			RT	A13NM
1998080700690	19980807	00690	NM  	1998	8	7	AU980698         	1	19980614	G	2560		GIRT BAR        			BOEING	747   	747238B     	1384828	NM  										CABIN	DETACHED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 RIGHT DOOR GIRT BAR AFT END NOT ENGAGED.  GIRT BAR AFT SLIDER NOT POSITIONED BY THE ARMING MECHANISM.						2	L	7	4 	4F				A20WE
1998080700691	19980807	00691	NE  	1998	8	7	AU980699         	2	19980610	G	7310	K16738	COUPLING        		LK53830     						RROYCE	RB211 	RB211524G19 		NE  					FUEL SYSTEM	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 AND NR 4 ENGINE FUEL SUPPLY PIPES P/N LK80877 BETWEEN THE LP FUEL FILTER AND THE FUEL PUMP CONTAINED FRETTING	 CAUSING THE LINES TO LEAK AT THE END COUPLINGS P/N LK53830 AND P/N K16738.										4	F			E30NE
1998080700692	19980807	00692	CE  	1998	8	7	AU980700         	1	19980610	G	2434	ALV9510R	ALTERNATOR      			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	DC SYSTEM	FAILED          	H				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			IN	INSP/MAINT     	1			AU	S 	6763R		696  			4040686				(AUS) ALTERNATOR ROTOR FAILED.  SUSPECT CAUSED BY CONTINUAL TURNING OFF OF THE ALTERNATOR DURING SURVEY OPERATIONS.  SEE	 MDR 98/0701 FOR SIMILAR DEFECT.  AIRCRAFT IS USA REGISTERED N6763R.					1	L	7	2 	3O				A25CE   		5	C	P45GL
1998080700693	19980807	00693	CE  	1998	8	7	AU980701         	1	19980525	G	2434	ALV9510R	ALTERNATOR      			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	DC SYSTEM	FAILED          	H				K				NONE                    				H	E		ELECT. POWER LOSS-50 PC   	VIBRATION/BUFFET          		CL	CLIMB          	1			AU	S 			212  							(AUS) RIGHT ALTERNATOR FAILED.  INVESTIGATION FOUND THE ROTOR HALF SECURING SCREWS MISSING OR WITH STRIPPED THREADS.  TH	E UNBALANCED ROTOR THEN WORE THE ROTOR SHAFT UNTIL THE DRIVING GEAR CAME OUT OF MESH AND DAMAGED THE DRIVE CHAIN AND RED	UCTION GEARBOX.  SEE MDR98/0700 FOR SIMILAR DEFECT.				1	L	7	2 	3O				A25CE   		5	C	P45GL
1998080700694	19980807	00694	SO  	1998	8	7	AU980703         	2	19980503	G	7322	104894	CARBURETOR      			CESSNA	150   	150F        	2071814	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A100	1A100MCM    	GL  	ENGINE	OUT OF ADJUST   	H				K				NONE                    				R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	LD	LANDING        	1			AU	S 							24R604			(AUS) CARBURETOR OUT OF ADJUSTMENT.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998080700695	19980807	00695	NE  	1998	8	7	AU980704         	2	19980623	G	7200		ENGINE          			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1	FAILED          	H				O				OTHER                   				E	R	Y	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	CL	CLIMB          	1			AU	S 							LF05545A			(AUS) NR 1 ENGINE FAILED.  LIMITED INFORMATION PROVIDED.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700696	19980807	00696	CE  	1998	8	7	AU980706         	1	19980624	G	2820	1014	HOSE            		1016        	BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A2B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	FUEL SYSTEM	DETERIORATED    	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FLEXIBLE HOSES NOT CHANGED DURING ENGINE CHANGE.  NO TAGS WERE PRESENT ON MOST OF THE AIRFRAME HOSES.  THE 	TWO FUEL TANK HOSES WERE TAGGED 1973 AND THE FITTINGS WERE BADLY CORRODED.					1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P7EA
1998080700697	19980807	00697	CE  	1998	8	7	AU980707         	1	19980420	G	2434		ALTERNATOR      			BEECH 	23    	A2324       	1151226	CE  	LYC   	O360  	IO360A2B    	41514	EA  	MCAULY	2D34C	2D34C9      	GL  	DC SYSTEM	IMPROPER PART   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							L1405651A			(AUS) INCORRECT ALTERNATOR FITTED. PERSONNEL/MAINTENANCE ERROR.  UNAPPROVED PART.						1	L	7	1 	3O	3	O	 	A1CE    	1E10	5	C	P7EA
1998080700698	19980807	00698	SO  	1998	8	7	AU980708         	1	19980626	G	5730		SKIN            			PIPER 	PA38  	PA38112     	7103812	SO  						SNSNCH	72C	72CK        	EA  	WINGS	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								K2651		(AUS) LOWER WING SKINS REMOVED FOR INSPECTION AND REPLACED USING BOLTS AND NUTS.						1	L	7	1 	3O				A18SO   		5	N	P9045
1998080700699	19980807	00699	CE  	1998	8	7	AU980709         	1	19980622	G	3230	00282001631	BUSHING         			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	NLG	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR UPPER DRAG BRACE RIGHT BUSHING LOOSE.  PART TOTAL CYCLES:  1,870.						1	L	7	2 	3O				3A16    		5	C	P22EA
1998080700700	19980807	00700	CE  	1998	8	7	AU980710         	1	19980623	G	3230	12434262	LINK            			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR UPPER TORQUE LINK CRACKED.  CRACKS APPEAR TO ORIGINATE FROM CORROSION PITTING.  PART TOTAL CYCLE	S:  5,150.					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA
1998080700701	19980807	00701	CE  	1998	8	7	AU980711         	1	19980622	G	5520	365241075	MOUNT           			BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	ELEVATOR	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CONTROL SYSTEM BOB WEIGHTS LOOSE DUE TO P/N AN 960-416 WASHERS LOCATED UNDER THE HEAD OF THE WEIGHT ATTAC	HING BOLTS EMBEDDING THEMSELVES INTO THE WORN MOUNT.  PART TOTAL CYCLES:  1,870.					1	L	7	2 	3O				3A16    		5	C	P22EA
1998080700702	19980807	00702	CE  	1998	8	7	AU980712         	1	19980625	G	3244	277K061	TIRE            	CLEVELAND   	WHEEL       	CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	LT MLG	FAILED          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			154  		0023					(AUS) LEFT MAIN WHEEL TIRE BURST.  SUSPECT CAUSED BY AN UNDER-INFLATED TIRE COMBINED WITH HEAVY BRAKING.  PART TOTAL CYC	LES:  180.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998080700703	19980807	00703	SW  	1998	8	7	AU980713         	1	19980619	G	5414		KEELSON         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT/RT NACELLES	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT NACELLE LEFT OUTBOARD KEELSON CRACKED FROM THE EDGE OF THE SKIN THROUGH THE LAST RIVET OF THE STIFFENER AND C	ONTINUES OUT AT AN ANGLE OF APPROXIMATELY 45 DEGREES.  CRACK LENGTH 76.2 MM (3 INCHES).  PART TOTAL CYCLES:  29,529.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998080700704	19980807	00704	SW  	1998	8	7	AU980714         	1	19980619	G	3230	OAS55011	DRAG BRACE      			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	MLG	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					515					(AUS) MAIN LANDING GEAR DRAG BRACE ASSEMBLY CENTER TORQUE SHAFT SUPPORT LUGS BROKEN.  TORQUE SHAFT BENT AND BROKEN.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998080700705	19980807	00705	CE  	1998	8	7	AU980715         	1	19980622	G	3030	CM35897	SWITCH          			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	COCKPIT	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT PITOT HEAT SWITCH FAULTY.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998080700706	19980807	00706	NM  	1998	8	7	AU980716         	1	19980330	G	2612	894481	CONNECTOR       			BOEING	737   	737377      		NM  										FIRE LOOP	CONTAMINATED    	H				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) APU FIRE DETECTOR FAULTY.  INVESTIGATION FOUND OIL IN THE CONNECTOR BODY.						2	L	7	2 	4F			RT	A16WE
1998080700707	19980807	00707	EU  	1998	8	7	AU980717         	1	19980623	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 5 ENGINE	DISCHARGED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8187 		1500					(AUS) NR 54 ENGINE OUTBOARD FIRE EXTINGUISHER BOTTLE EMPTY.  FOUND DURING RE-WEIGH INSPECTION IAW ER BA6-26-20-15.  SUSP	ECT CAUSED BY INTERNAL HEAD CORROSION.  PART TOTAL CYCLES:  17,999.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700708	19980807	00708	CE  	1998	8	7	AU980721         	1	19980620	G	7603		THROTTLE CABLE  			BBAVIA	7     	7KCAB       	21101P3	CE  	LYC   	O320  	IO320E2A    	41508	EA  					THROTTLE	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L381155A			(AUS) THROTTLE CONTROL CABLE BROKEN AT THROTTLE LEVER.  PART TOTAL CYCLES:  1,552.						1	H	7	1 	3O	3	O	 	A759    	1E12
1998080700709	19980807	00709	GL  	1998	8	7	AU980722         	1	19980629	G	3213		STRUT           			AMTR  	MAXAIR	XP503       	9570746	GL  										MLG	DAMAGED         	H				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR STRUT BENT DURING FORCED LANDING.  SLIGHT DAMAGE TO PROPELLER.						1	H	7	1 	3I			NT	EXPA1H71
1998080700710	19980807	00710	EU  	1998	8	7	AU980723         	1	19980614	G	2910	FGFB751505149	PIPE            			AMD   	FALC50	FALCON900   	2700160	EU  										HYDRAULIC SYSTEM	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC SYSTEM PIPE LOCATED AT THE FORWARD BULKHEAD OF THE REAR SERVICING COMPARTMENT LEAKING FROM A FRACTURE IN	 THE PIPE.  WHEN THE PIPE WAS REMOVED, IT FAILED AT THE FRACTURE.  INVESTIGATION FOUND THE FAILURE WAS CAUSED BY AN INCL	USION IN THE PIPE SUSPECT EXISTING SINCE MANUFACTURE.				2	L	7	3 	4F			RT	A46EU
1998080700711	19980807	00711	EU  	1998	8	7	AU980727         	1	19980104	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 ENGINE	DISCHARGED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4138 		CM6512					(AUS) NR 1 ENGINE OUTBOARD FIRE EXTINGUISHER BOTTLE EMPTY.  SUSPECT CAUSED BY CORROSION OF THE HEAD ASSEMBLY AND LEAKAGE	 AT THE HEAD TO CYLINDER JOINT.  FOUND DURING INSPECTION IAW ER BA6-26-20-15.  PART TOTAL CYCLES:  12,839.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700712	19980807	00712	EU  	1998	8	7	AU980728         	1	19980116	G	5730		SKIN            			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT/RT WINGS	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TOP SKIN LOWER SURFACE CONTAINED NUMEROUS DRILL MARKS IN THE AREA AT RIB ZERO AND RIB 2, LT AND RT SIDES.  FO	UND DURING INSPECTION IAW ER BA6-57-10-9A (AD/BAE146/066).  SUSPECT MANUFACTURING FAULT.					2	H	7	4 	4F	4	F	 	A49EU   	E6NE
1998080700713	19980807	00713	NM  	1998	8	7	AU980729         	1	19980608	G	5330		SKIN            			BOEING	747   	747312      	1384932	NM  										BS 340-400	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE LAP SPLICE CRACKED ON THE LEFT SIDE BETWEEN BS 340 AND BS400 ADJACENT TO STRINGER 6L. CRA CK LENGTH 0.508	 MM (0.020 INCHES).  FOUND DURING HIGH FREQUENCY EDDY CURRENT INSPECTION.					2	L	7	4 	4F			RT	A20WE
1998080700714	19980807	00714	CE  	1998	8	7	AU980730         	1	19980612	G	6120	310047501	CONTROL CABLE   		310047503   	BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PROP CONTROL	CONTAMINATED    	H				O				OTHER                   				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			2863 		PCE32164		PCE32164			(AUS) PROPELLER BETA CABLE CONTAMINATED AND STICKING.  PART TOTAL CYCLES:  18,161.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
1998080700715	19980807	00715	CE  	1998	8	7	AU980731         	1	19980624	G	3250	993880047	ACTUATOR        	ELECTROMECH 	ACTUATOR    	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG STEERING	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					308					(AUS) NOSE WHEEL STEERING SYSTEM DISCONNECT LINEAR ACTUATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998080700716	19980807	00716	EA  	1998	8	7	AU980732         	2	19980703	G	8520	TIO540	CRANKCASE       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			689  				L10668A			(AUS) RIGHT ENGINE CRANKCASE CRACKED.  CRACK STARTED AT NR 6 CYLINDER TOP STUD.  CRACK LENGTH 50.8 MM (2 INCHES).						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998080700717	19980807	00717	WP  	1998	8	7	AU980734         	1	19980630	G	6320	269A51045	GEAR            	HUGHES      		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					M/R GEARBOX	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					235					(AUS) MAIN ROTOR TRANSMISSION RING GEAR TEETH BRINELLED IN AREA INDICATED IN SB B 244-3.  PART TOTAL CYCLES:  896.						1	G	7	1 	3O	3	O		4H12    	1E10
1998080700718	19980807	00718	WP  	1998	8	7	AU980735         	1	19980630	G	6320	269A510341	PINION          	HUGHES      		HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					M/R GEARBOX	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					235					(AUS) MAIN ROTOR TRANSMISSION PINION GEAR TEETH BRINELLED IN AREA INDICATED IN SB B 244-3.  PART TOTAL CYCLES:  896.						1	G	7	1 	3O	3	O		4H12    	1E10
1998080700719	19980807	00719	NM  	1998	8	7	AU980736         	1	19980705	G	2910	DSL3461	HOSE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HYDRAULIC SYSTEM	LEAKING         	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			AU	S 										(AUS) NR 2 ENGINE DRIVEN HYDRAULIC PUMP HOSE LEAKING.  LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998080700720	19980807	00720	EU  	1998	8	7	AU980737         	1	19980209	G	5752	HC576C0145000	BRACKET         		HC576C014500	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					AILERON	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AILERON TRIM TAB INBOARD AND OUTBOARD DRIVE BRACKETS P/N HC576C0145-000 AND P/N HC576C0145-001 CORRODED.  PAR	T TOTAL CYCLES:  11,817.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700721	19980807	00721	NM  	1998	8	7	AU980738         	1	19980623	G	3260	88825	TARGET          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					NLG WW	MISSING         	H				K				NONE                    				N			FALSE WARNING             			TO	TAKEOFF        	1			AU	S 										(AUS) NLG WEIGHT ON WHEELS SENSOR TARGET SEPARATED.  SUSPECT CAUSED BY FAILURE OF ADHESIVE.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998080700722	19980807	00722	SW  	1998	8	7	AU980739         	1	19980617	G	3240	3272006003	PUSHROD         			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	RT MLG	BROKEN          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOT'S RT BRAKE PEDAL PUSH ROD BROKEN IN THREADED SECTION.  PART TOTAL CYCLES:  8,800.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998080700723	19980807	00723	SW  	1998	8	7	AU980740         	1	19980613	G	3210		MLG             			GULSTM	690TP 	690         	0141720	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	FUSELAGE	COLLAPSED       	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN LANDING GEAR COLLAPSED DURING RT ENGINE START.  INVESTIGATION COULD FIND NO CONCLUSIVE CAUSE OF THE DEFECT.						1	H	7	2 	3T				2A4     		6	C	P15EA
1998080700724	19980807	00724	CE  	1998	8	7	AU980742         	1	19980618	G	7922	639305	VALVE           			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RT ENGINE	FAILED          	H				K				NONE                    				K	M		FLUID LOSS                	OVER TEMP                 		CL	CLIMB          	1			AU	S 			242  		276338		276338			(AUS) RIGHT ENGINE OIL TEMPERATURE VALVE FAILED.						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL
1998080700725	19980807	00725	SW  	1998	8	7	AU980743         	1	19980612	G	6420	B1212	BEARING         		Y           	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAIL ROTOR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AFS5010		CAE890259			(AUS) TAIL ROTOR BEARING SEIZED DUE TO RUST.  DURING REMOVAL, THE BEARING DISINTEGRATED.  EVIDENCE OF BRINELLING ON THE 	INNER AND OUTER RACES CONSISTENT WITH A MISSING NEEDLE ROLLER.  THE AIRCRAFT FLIES THROUGH RAIN ON A REGULAR (DAILY) BAS	IS.				1	G	7	1 	3U	3	U		H2SW    	E1GL
1998080700726	19980807	00726	SW  	1998	8	7	AU980744         	1	19980609	G	6410	206010765001	BEARING         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					TAIL ROTOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			640  		CS13431131		CAE890259			(AUS) TAIL ROTOR BLADE FEATHERING BEARING CRACKED.  PART TOTAL CYCLES:  640.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998080700727	19980807	00727	SO  	1998	8	7	AU980747         	1	19980511	G	2822	RG15980L	SPLINE DRIVE    	ROMEC       	RG17678     	AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  	HARTZL	HCB3T	HCB3TN3     	GL  	PUMP SHAFT	SEPARATED       	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					D2418		PCE56484			(AUS) FUEL SYSTEM BOOST PUMP SPLINED DRIVE SEPARATED FROM THE PUMP SHAFT. SUSPECT CAUSED BY LACK OF LUBRICATION.  PART T	OTAL CYCLES:  2,720.					1	L	7	1 	3T	4	T		A3SW    	E4EA	6	C	P15EA
1998080700728	19980807	00728	NM  	1998	8	7	AU980748         	1	19980618	G	2910	AS133900624	PIPE            			BOEING	767   	767338      		NM  										HYDRAULIC SYSTEM	LEAKING         	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR DOWN SYSTEM HYDRAULIC PIPE LEAKING.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F			RT	A1NM
1998080700729	19980807	00729		1998	8	7	AU980749         	1	19980622	G	5280	65C2811121	SKIN            																	NLG DOOR	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT NOSE LANDING GEAR DOOR DAMAGED DURING TOWING. THE TOW BAR BROKE WHEN THE TUG JACK KNIFED CAUSING THE DAMAGE. 	 THE AIRCRAFT IS NEW ZEALAND REGISTERED ZK-FDM.
1998080700730	19980807	00730	SW  	1998	8	7	AU980750         	1	19980629	G	5311	31003265	FRAME           			GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  					FUSELAGE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME CRACKED.  FOUND DURING INSPECTION IAW AD/AC/93.						1	H	7	2 	3O	3	O		6A1     	1E4
1998080700731	19980807	00731	CE  	1998	8	7	AU980751         	1	19980423	G	5610	1013840257	WINDSHIELD      		B200C       	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COCKPIT	CRACKED         	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					BL126					(AUS) PILOT'S WINDSCREEN OUTER PLY CRACKED.  PART TOTAL CYCLES:  1,967.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998080700732	19980807	00732	EU  	1998	8	7	AU980752         	1	19980211	G	5713		STRINGER        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CHAFED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TOP SKIN LOWER SURFACE CONTAINED NUMEROUS BARE METAL AREAS ON STRINGERS LOCATED AT RIB ZERO AND RIB 2 LT AND 	RT.  NO EVIDENCEOF CORROSION PRESENT.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700733	19980807	00733	EU  	1998	8	7	AU980753         	1	19980630	G	3234	HTE210014	ACTUATOR        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAILED          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			160  		190GB188H					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR FAULTY.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700734	19980807	00734	EU  	1998	8	7	AU980754         	1	19980414	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	DISCHARGED      	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1428					(AUS) NR 2 ENGINE INBOARD FIRE EXTINGUISHER UNDERWEIGHT.  INVESTIGATION FOUND CORROSION AROUND THE HEAD AND EVIDENCE OF 	LEAKAGE.  FOUND DURING INSPECTION IAW ER BA6-26-20-15.  PART TOTAL CYCLES:  18,961.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700735	19980807	00735	NM  	1998	8	7	AU980755         	1	19980704	G	6123		SWITCH          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	PROP FEATHER	MALFUNCTIONED   	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) AUTOFEATHER SYSTEM WOULD NOT ARM FOR TAKEOFF.  POWER WAS SWITCHED OFF AND THEN ON AGAIN AND PROBLEM DID NOT RECUR.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
1998080700736	19980807	00736	NM  	1998	8	7	AU980756         	1	19980705	G	6123	6121S13	SWITCH          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	PROP  FEATHER	DAMAGED         	H				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AUTOFEATHERING SYSTEM WIRING AND SWITCH DAMAGED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
1998080700737	19980807	00737	CE  	1998	8	7	AU980758         	1	19980630	G	6123	9696001115	PIPE            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	CSU	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE CSU TO UNFEATHERING SYSTEM PIPE BROKEN AT CSU FITTING.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA
1998080700738	19980807	00738	CE  	1998	8	7	AU980759         	1	19980630	G	5312	FS2579	BULKHEAD        		27192       	BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF2    	GL  	BS 257	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BULKHEAD LOCATED AT FS 257.6 CRACKED.  PART TOTAL CYCLES:  4,996.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P36EA
1998080700739	19980807	00739	SO  	1998	8	7	AU980761         	1	19980627	G	2910	MS2192D5	FITTING         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	HYD SYSTEM	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 										(AUS) HYDRAULIC PUMP PRESSURE SYSTEM ALUMINUM `T' FITTING LOCATED ON LT FIREWALL CRACKED.  FITTING HAS AN INTERNAL FLARE	 SEAL.  LOSS OF HYDRAULIC FLUID.  PART TOTAL CYCLES:  18,318.					1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
1998080700740	19980807	00740	EU  	1998	8	7	AU980762         	1	19980626	G	7922	75944	VALVE           			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	OIL TEMP	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL TEMPERATURE CONTROL VALVE FACE WORN EXCESSIVELY.  FOUND DURING INSPECTION IAW AD/LYC/78.  PART TOTAL CY	CLES:  1,830.					1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920
1998080700741	19980807	00741	SO  	1998	8	7	AU980763         	2	19980707	G	7322	6297032	FCU             		63135117A6  	CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	FAULTY          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							2548952			(AUS) ENGINE FUEL CONTROL UNIT P/N 629703-2 AND FUEL FLOW DIVIDER P/N 631351-17A6 FITTED TO FACTORY.  REMANUFACTURED ENG	INE SUSPECT FAULTY.					1	H	7	1 	3O	3	O		3A21    	E5CE
1998080700742	19980807	00742	SO  	1998	8	7	AU980764         	2	19980620	G	8550		HOSE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RT ENGINE	LEAKING         	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) RIGHT ENGINE OIL PUMP OUTLET TO OIL FILTER HOSE LEAKING FROM HOSE FITTING.						1	L	7	2 	3O	3	O		A7CE    	E7CE	5	C	P45GL
1998080700743	19980807	00743	EU  	1998	8	7	AU980765         	1	19980707	G	3242	SD3490541	BRAKE CABLE     			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	BRAKE ASSY	SEPARATED       	H				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) EMERGENCY BRAKE ACCUMULATOR CABLE SEPARATED FROM THE ACTUATING HANDLE CAUSING THE EMERGENCY BRAKE SYSTEM TO REMAIN	 ACTIVATED.  PART TOTAL CYCLES:  7,293.					2	H	7	2 	4T	4	T	 	A41EU   	E26NE	6	C	P14NE
1998080700744	19980807	00744	WP  	1998	8	7	AU980766         	2	19980630	G	7261		FILTER          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	CONTAMINATED    	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P31325			(AUS) ENGINE OIL SYSTEM CONTAMINATED WITH METAL PARTICLES.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
1998080700745	19980807	00745	WP  	1998	8	7	AU980769         	1	19980630	G	6310	269A5490	FITTING         			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					TRANSMISSION	IMPROPER PART   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CLUTCH ACTUATOR FITTING INCORRECT PART.  FITTING P/N 269A5490 IS USED ON 269A AND 269B MODELS ONLY.  FITTING P/N 2	69A5491-5 IS USED ON 269C MODELS.  PERSONNEL/MAINTENANCE ERROR.  UNAPPROVED PART.					1	G	7	1 	3O	3	O	 	4H12    	1E10
1998080700746	19980807	00746	WP  	1998	8	7	AU980770         	1	19980630	G	6720	269A60445	CONTROL ROD     			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					TAIL ROTOR	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR CONTROL ROD RUBBING ON `POP' RIVET TAIL.  THE RIVET HAD BEEN INSTALLED SOME TIME IN THE PREVIOUS TWO YE	ARS TO SECURE A BRACKET UNDER THE TAIL BOOM FOR SECURING THE STATIC SYSTEM TUBE.  PART TOTAL CYCLES:  161.					1	G	7	1 	3O	3	O		4H12    	1E10
1998080700747	19980807	00747	NM  	1998	8	7	AU980771         	1	19980709	G	5711	20000803	SPAR CAP        			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	TIO540S1AD  	41532	EA  					LT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING FORWARD MAIN SPAR CAP CONTAINED INTERGRANULAR CORROSION IN AREA ADJACENT TO THE INBOARD AND OUTBOARD EDG	ES OF THE ENGINE NACELLES.  PART TOTAL CYCLES:  2,011.					1	M	7	2 	3O	3	O	RT	A17WE   	E14EA
1998080700748	19980807	00748	EU  	1998	8	7	AU980772         	1	19980702	G	3234	HTE94902	VALVE           			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR SELECTOR VALVE LEAKING FROM THE GLAND SEAL.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998080700749	19980807	00749	EU  	1998	8	7	AU980773         	1	19980630	G	3234	643500100	SELECTOR        			BAC   	146   	146100A     	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAULTY          	H				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LANDING GEAR SELECTOR HANDLE FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998081900039	19980819	00039	NE  	1998	8	19	AU980774         	2	19980629	G	7261	3038336	RELIEF VALVE    			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67      	52043	NE  					ENGINE	STICKING        	H				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 							110025			(AUS) ENGINE OIL PRESSURE RELIEF VALVE SUSPECT STICKING.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
1998080700750	19980807	00750	SW  	1998	8	7	AU980775         	1	19980701	G	2612		FIRE LOOP       			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	LT ENGINE	FAULTY          	H				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) LEFT ENGINE FIRE DETECTION SYSTEM FAULTY.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998080700751	19980807	00751	EA  	1998	8	7	AU980776         	2	19980101	G	8550	78528	PUMP            			BNORM 	BN2   	BN2A        	1520204	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	FOD             	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2126 				L2102848A			(AUS) ENGINE OIL PUMP BODY CRACKED DUE TO INGESTION OF FOREIGN OBJECT INTO THE OIL PUMP.  ADDITIONAL DAMAGE CAUSED TO DR	IVE SHAFT (CRACKED), IMPELLERS AND ACCESSORY HOUSING.  SUSPECT FOD WAS A STOP PIN FROM A MAGNETO.					1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920
1998080700752	19980807	00752	SO  	1998	8	7	AU980777         	1	19980706	G	3230	38040	DOWNLOCK        			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK ASSEMBLY BROKEN AT BUSHING AT PIVOT POINT.  SUSPECT CRACK HAD BEEN PRESENT FOR SOME TIM	E.  PART TOTAL CYCLES:  7,184.					1	L	7	1 	3O	3	O		A3SO    	1E4
1998080700753	19980807	00753	CE  	1998	8	7	AU980778         	1	19980625	G	5321		FLOOR PANEL     			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	BS 56	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLOOR PAN LOCATED ON THE TOP OF THE RT MAIN LANDING GEAR BOX STRUCTURE AT STN 56.69 CONTAINED SEVERAL CRACKS (APPR	OXIMATELY SIX) UP TO 52.8 MM (2 INCHES) LONG BETWEEN THE RIVETS ON TOP OF THE BULKHEAD AT THE REAR OF THE CABIN SEATS. S	USPECT CAUSED BY HEAVY LANDING.				1	H	7	1 	3O			NT	3A19    		5	N	P50GL
1998080700754	19980807	00754	CE  	1998	8	7	AU980779         	1	19980629	G	3260	1003810061	SWITCH          			BEECH 	76    	76          	1153005	CE  										NLG	FAILED          	H				K				NONE                    				P			NO WARNING INDICATION     			LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWN MICROSWITCH FAULTY.						1	L	7	2 	3O				A29CE
1998080700755	19980807	00755	SW  	1998	8	7	AU980780         	1	19980302	G	6520	206340103101	SEAL            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					AFS2056					(AUS) TAIL ROTOR GEARBOX INPUT SEAL LEAKING.  PART TOTAL CYCLES:  15.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998080700756	19980807	00756	NE  	1998	8	7	AU980781         	2	19980401	G	7210	230307203	SEAL            			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 1 ENGINE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							LE45885E			(AUS) NR 1 ENGINE OUTPUT SHAFT SEAL LEAKING.  PART TOTAL CYCLES:  147.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998080700757	19980807	00757	NE  	1998	8	7	AU980782         	2	19980401	G	7210	230307203	SEAL            			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 1 ENGINE	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 							LE45885E			(AUS) NR 1 ENGINE OUTPUT SHAFT SEAL LEAKING.  PART TOTAL CYCLES:  62.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998080700758	19980807	00758	SW  	1998	8	7	AU980783         	1	19980605	G	6520	206340103101	SEAL            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					T/R GEARBOX	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					ALO12512					(AUS) TAIL ROTOR GEARBOX INPUT SEAL LEAKING.  PART TOTAL CYCLES:  27.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998080700759	19980807	00759	CE  	1998	8	7	AU980784         	1	19980523	G	3211	S21381	BOLT            			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	RT MLG	SHEARED         	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR ATTACHMENT BOLT SHEARED.  MLG STRUT ROTATED IN ITS HOUSING AND THEN COLLAPSED. BOLT SHEARE	D DURING LANDING WHEN THE AIRCRAFT STRUCK A PILE OF GRAVEL.  SUSPECT BOLT HAD ALREADY BEEN DAMAGED ALLOWING IT TO EASILY	 SHEAR WITHOUT CAUSING DAMAGE TO THE ATTACHMENT STRUCTURE.				1	H	7	1 	3O			NT	3A12    		5	N	P910
1998080700760	19980807	00760	SO  	1998	8	7	AU980785         	1	19980705	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	CONTAMINATED    	H				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWN MICROSWITCH FAILED.  SUSPECT CAUSED BY CONTAMINATION DUE TO MUD/DEBRIS IN WET CONDITIONS.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998080700761	19980807	00761	CE  	1998	8	7	AU980786         	1	19980702	G	3233	1158100291	NUT             			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT MLG	SEPARATED       	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 			138  		97B279					(AUS) RIGHT MAIN LANDING GEAR ACTUATOR WORM DRIVE ASSEMBLY SEPARATED FROM INNER BORE OF SHAFT.  SIGNS OF RUST ON SHAFT I	NNER BORE.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998080700762	19980807	00762	NM  	1998	8	7	AU980787         	1	19980422	G	2750	113T225213	COLLAR          			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					LT TE FLAP	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					00213					(AUS) LEFT INBOARD FLAP INBOARD TORQUE TUBE COLLAR CRACKED AND TORQUE TUBE HEAVILY CORRODED.  RIGHT SIDE FLAP COLLARS AN	D TORQUE TUBE ALSO CORRODED.  PART TOTAL CYCLES:  39,633.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998080700763	19980807	00763	EU  	1998	8	7	AU980788         	1	19980130	G	5551		FITTING         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HORIZ  STAB	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILISER ATTACHMENT FITTING INNER FACES AND ADJOINING VERTICAL STABILIZER LUGS CONTAINED AREAS OF MIN	OR CORROSION AND DAMAGE ON SEVERAL LUGS.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700764	19980807	00764	NE  	1998	8	7	AU980789         	2	19980121	G	7310	216362033	MANIFOLD        			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1441		LF05173			(AUS) NR 3 ENGINE RIGHT FUEL MANIFOLD SEGMENT CRACKED.  FOUND DURING EDDY CURRENT INSPECTION IAW ER ALF-73-10-20 PART 2B	.  PART TOTAL CYCLES:  17,119.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700765	19980807	00765	NM  	1998	8	7	AU980790         	1	19980703	G	3221	10621954	BEARING         			BOEING	737   	737376      		NM  										NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT NOSE LANDING GEAR TRUNNION BEARING HOUSING CRACKED.						2	L	7	2 	4F			RT	A16WE
1998080700766	19980807	00766	SO  	1998	8	7	AU980791         	2	19980709	G	7322	6158704	FILTER          	FACET       	4104895     	CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	CARBURETOR	CONTAMINATED    	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			AU	S 			1880 		6158704		25598DR	QA047		(AUS) CARBURETOR FINGER FILTER CONTAMINATED WITH LINT TYPE MATERIAL.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
1998080700767	19980807	00767		1998	8	7	AU980794         	4	19980313	G	2565	D31865103	STRIP           			AIRBUS	320   	A320212     		EU  										LT ESCAPE SLIDE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					C0088					(AUS) LEFT OVERWING ESCAPE SLIDE CONTAINED EXTENSIVE CORROSION ALONG THE EDGE OF THE REINFORCEMENT STRIP WITH A LARGE AR	EA OF DELAMINATION ALONG THE LOWER EDGE OF THE PACKBOARD.  PART TOTAL CYCLES:  26,474.					2	L	7	2 	4F			RT	A28NM
1998080700768	19980807	00768		1998	8	7	AU980795         	4	19980313	G	2565	D31865104	PACKBOARD       			AIRBUS	320   	A320212     		EU  										RT ESCAPE SLIDE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A6108					(AUS) RIGHT OVERWING ESCAPE SLIDE CONTAINED MINOR CORROSION ON THE PACKBOARD AND SMALL AREAS OF CORROSION.  SEE MDR 98/0	794 FOR SIMILAR DEFECT ON LT SLIDE.  PART TOTAL CYCLES:  23,395.					2	L	7	2 	4F			RT	A28NM
1998080700769	19980807	00769	EU  	1998	8	7	AU980796         	1	19980408	G	5551		FITTING         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					HORIZ  STAB	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER TO VERTICAL STABILIZER ATTACHMENT LUG INNER FACES CONTAINED MINOR CORROSION ON UPPER FORK EN	D FITTING TANGS.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700770	19980807	00770	NM  	1998	8	7	AU980797         	1	19980511	G	2750	65B100591	DRUM            			BOEING	747   	747312      	1384932	NM  										RT TE FLAP	BROKEN          	H				K				NONE                    				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) RIGHT INBOARD FLAP TRANSMITTER CABLE DRUM FLANGE BROKEN.						2	L	7	4 	4F			RT	A20WE
1998080700771	19980807	00771	NM  	1998	8	7	AU980798         	1	19980511	G	2750	BACS30EM55	SWITCH          			BOEING	747   	747312      	1384932	NM  										TE FLAP	FAULTY          	H				K				NONE                    				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) INBOARD TRAILING EDGE FLAP ALTERNATE FLAP CONTROL MODULE ARMING SWITCH FAULTY.						2	L	7	4 	4F			RT	A20WE
1998080700772	19980807	00772	EU  	1998	8	7	AU980799         	1	19980703	G	2752	CHA1069	ACTUATOR        			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	TE FLAP	FAILED          	H				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 					J1910					(AUS) HYDRAULIC FLAP ACTUATOR FAILED.						2	H	7	2 	4T	4	T		A41EU   	E26NE	6	C	P14NE
1998080700773	19980807	00773	NM  	1998	8	7	AU980800         	1	19980609	G	5311	65B13386	WEB             			BOEING	747   	747312      	1384932	NM  										BS 1265	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME WEB LOCATED AT BS 1265 WL 200 LT AND RT SIDES CRACKED.  FOUND DURING HF EDDY CURRENT INSPECTION IAW	 SB 747-53A2416.					2	L	7	4 	4F			RT	A20WE
1998080700774	19980807	00774	NM  	1998	8	7	AU980801         	1	19980629	G	2520	SICMA	LINK            			BOEING	737   	737377      		NM  										PAX SEAT	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SEAT 8A RECLINE LIMIT LINK WORN.						2	L	7	2 	4F			RT	A16WE
1998080700775	19980807	00775	EA  	1998	8	7	AU980802         	2	19980421	G	8520	LW74309	BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	NR 4 CYL ROD	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1777361A			(AUS) NR 4 CYLINDER CONNECTING ROD BEARING FAILED.  METAL CONTAMINATION OF OIL SYSTEM.  SUSPECT CAUSED BY INCORRECT CRAN	KSHAFT BEING INSTALLED IN THE ENGINE.  LTIO-540-J2BD CRANKSHAFT INSTALLED INSTEAD OF TIO-540-J2BD CRANKSHAFT.  CRANKSHAF	TS HAVE THE OIL PASSAGES FOR THE CONNECTING RODS IN DIFFERENT LOCATIONS.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998080700776	19980807	00776	NM  	1998	8	7	AU980803         	1	19980710	G	5730	65454877	PANEL           			BOEING	737   	737476      		NM  										RT WING	SEPARATED       	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING CENTER FUEL BOOST PUMP ACCESS PANEL MISSING.						2	L	7	2 	4F			RT	A16WE
1998080700777	19980807	00777	SO  	1998	8	7	AU980804         	1	19980707	G	3260	487862	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	FAULTY          	H				K				NONE                    				O	P		OTHER                     	NO WARNING INDICATION     		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK MICROSWITCH CONTAMINATED WITH DIRT AND GRIT.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998080700778	19980807	00778	CE  	1998	8	7	AU980805         	1	19980702	G	3233		ACTUATOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RT MLG	FAILED          	H				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR ACTUATOR FAILED DURING LANDING GEAR RETRACTION CAUSING DAMAGE TO THE GEARBOX.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998080700779	19980807	00779	SO  	1998	8	7	AU980806         	1	19980707	G	2435	230721125	CLAMP           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	START/GEN	LOOSE           	H				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RIGHT ENGINE STARTER-GENERATOR `V' BAND CLAMP NUT MISSING AND CLAMP MOVED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998080700780	19980807	00780	SO  	1998	8	7	AU980807         	1	19980718	G	7820	68717	MUFFLER         			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	SEPARATED       	H				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			AU	S 										(AUS) MUFFLER EXHAUST OUTLET PIPE SEPARATED FROM THE MUFFLER.						1	L	7	1 	3O	3	O		A3SO    	E295	5	C	P920
1998080700781	19980807	00781	SO  	1998	8	7	AU980808         	1	19980604	G	2910	40839	PIPE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	HYD SYSTEM	CORRODED        	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC PIPE LOCATED IN THE LOWER FUSELAGE ADJACENT TO THE SPAR CONTAINED A CORROSION PIN HOLE IN THE AREA BELOW	 THE PIPE IDENTIFICATION TAG.  PART TOTAL CYCLES:  19,729.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998080700782	19980807	00782	EA  	1998	8	7	AU980809         	2	19980717	G	8530	LW12993	CYLINDER        			ENSTRM	F28   	F28A        	3300406	GL  	LYC   	O360  	HIO360C1A   	41514	EA  					ENGINE	CRACKED         	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AU	S 			80   				L1243251A			(AUS) CYLINDER HEAD SEPARATED FROM BARREL AT THE SECOND THREAD FROM THE TOP.						1	G	7	1 	3O	3	O		H1CE    	1E10
1998080700783	19980807	00783	SO  	1998	8	7	AU980810         	1	19980505	G	2910	4085400	PIPE            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	HYD SYSTEM	CRACKED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) POWER PACK HYDRAULIC PIPE CRACKED AND LEAKING.  PART TOTAL CYCLES:  44						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998080700784	19980807	00784	EU  	1998	8	7	AU980811         	1	19980715	G	5270		DOOR            			REIMS 	406   	F406        		EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	COCKPIT	WARNING         	H				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) DOOR UNLOCKED WARNING LIGHT ILLUMINATED.  LIMITED INFORMATION PROVIDED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
1998080700785	19980807	00785		1998	8	7	AU980812         	4	19980710	G	3414		INDICATOR       			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	COCKPIT	MALFUNCTIONED   	H				K				NONE                    				I			FLT. ATTITUDE INST.       			TO	TAKEOFF        	1			AU	S 										(AUS) AIR SPEED INDICATOR SUSPECTED FAULTY.						1	L	7	2 	3O				A25CE   		5	C	P45GL
1998080700786	19980807	00786	GL  	1998	8	7	AU980813         	2	19980228	G	7250		TURBINE         								GE    	CF6   	CF680C      	 	GL  					RT ENGINE	FOD             	H				C	E	D		ABORTED TAKEOFF         	ENGINE SHUTDOWN         	RETURN TO BLOCK         		W	X		INADEQUATE Q C            	ENGINE FLAMEOUT           		TO	TAKEOFF        	1			AU	S 							695456			(AUS) RIGHT ENGINE COMPRESSOR AND TURBINE SEVERELY DAMAGED.  ENGINE STRIP AND INSPECTION FOUND SEVERE FOD TO ALL COMPRES	SOR AND TURBINE STAGES DUE TO A 1/4 INCH HEXAGONAL DRIVE NR 2 PHILLIPS BIT.  FROM THE LOCATION OF THE DAMAGE, IT WAS DET	ERMINED THAT THE FOD ENTERED THE ENGINE GAS PATH THROUGH A BLEED DUCT OPENING WHEN THE THRUST REVERSERS WERE OPEN DURING	 A PREVIOUS MAINTENANCE VISIT.  FOD.  PERSONNEL/MAINTENANCE ERROR.								4	F			E23EA
1998080700787	19980807	00787	NE  	1998	8	7	AU980814         	2	19980630	G	7310		PIPE            								RROYCE	RB211 	RB211524D419	54555	NE  					FUEL SYSTEM	LEAKING         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE HIGH PRESSURE FUEL LINE LOCATED BETWEEN THE FFR AND THE HP SHUTOFF VALVE LEAKING AT THE SHUTOFF VALVE END.											4	F			E12EU
1998080700788	19980807	00788	SO  	1998	8	7	AU980815         	1	19980624	G	7922	53E22144	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	OIL TEMP	FAULTY          	H				A				UNSCHED LANDING         				K	M	J	FLUID LOSS                	OVER TEMP                 	WARNING INDICATION        	CL	CLIMB          	1			AU	S 					L810361A		L810361A			(AUS) ENGINE OIL TEMPERATURE VALVE (VERNATHERM) FAULTY.  PART TOTAL CYCLES:  334.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998080700789	19980807	00789	NM  	1998	8	7	AU980816         	1	19980716	G	2920	NAS16126	O-RING          	VICKERS     	MPEV301125  	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HYD SYSTEM	DAMAGED         	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 STANDBY HYDRAULIC POWER UNIT PRESSURE OUTPUT FITTING LOOSE.  FITTING `O' RING SEAL DAMAGED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998080700790	19980807	00790		1998	8	7	AU980817         	1	19980517	G	7820	MA1L	MUFFLER         								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 							4076079			(AUS) LEFT MUFFLER CRACKED AND SECTION MISSING FROM AREA LOCATED BEHIND THE CARBURETOR HEATING PLATE.											3	I			EXPE3I
1998080700791	19980807	00791	SO  	1998	8	7	AU980818         	1	19980721	G	5553	6350104	FITTING         			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	VERT STAB	LOOSE           	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER REAR ATTACHMENT FITTING RIVETS SHEARED AND FITTING LOOSE.						1	L	7	2 	3O				A7SO    		5	C	P920
1998080700792	19980807	00792	NM  	1998	8	7	AU980819         	1	19980704	G	3244	A01721967	TIRE            		161U00011   	BOEING	747   	747438      		NM  										RT MLG	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A01721967					(AUS) NR 5 RT MAIN WHEEL TIRE TREAD SEPARATION. MINOR DAMAGE TO ADJACENT FAIRINGS.						2	L	7	4 	4F			RT	A20WE
1998080700793	19980807	00793	GL  	1998	8	7	AU980820         	3	19980714	G	6114	DP54	HUB             	HARTZL      		PIPER 	PA30  	PA39        	7103902	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROP	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					DP54			DP54		(AUS) PROPELLER HUB DAMAGED ON ENGINE HALF SIDE FOLLOWING A GROUND STRIKE.   HUB WAS RETURNED TO SERVICE CONTRARY TO INS	TRUCTIONS IN THE MANUAL.  PERSONNEL/MAINTENANCE ERROR.					1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA
1998080700794	19980807	00794	NM  	1998	8	7	AU980821         	1	19980306	G	5415	311T31021	PIN             			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					LT ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE MID SPAR INBOARD FUSE PIN INNER BORE CONTAINED TWO LONGITUDINAL CRACKS. TOTAL CRACK LENGTH 8.89 MM (0.35	 INCHES).  FOUND DURING EDDY CURRENT INSPECTION IAW ER B76-54-40-4I.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998080700795	19980807	00795	NM  	1998	8	7	AU980822         	1	19980618	G	5350	000347	RADOME          		B767        	BOEING	767   	767         	UTILUSE	NM  										FUSELAGE	MISMANUFACTURED 	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					000347					(AUS) RADOME FAILED TO MEET THE REQUIREMENTS OF RTCA/00-213 FOR A CLASS B RADOME. (TRANSMISSION EFFICIENCY).						2	L	7	2 	4F			RT	A1NM
1998080700796	19980807	00796	SO  	1998	8	7	AU980823         	1	19980630	G	2721	6345703	ARM             			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1A5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	RUDDER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRIM ARM ASSEMBLY CRACKED.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1998080700797	19980807	00797	SO  	1998	8	7	AU980824         	2	19980528	G	8520	629340	BOLT            			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	CONNECTING ROD	BROKEN          	H				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			AU	S 			1315 		282453		282453R			(AUS) ENGINE CONNECTING ROD BOLT FAILED.  PART TOTAL CYCLES:  1,315.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998080700798	19980807	00798	SO  	1998	8	7	AU980825         	1	19980626	G	2820	6770079	LINE            			PIPER 	PA28  	PA28161     	7102803	SO  										FUEL SYSTEM	CORRODED        	H				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL LINES CORRODED AND LEAKING IN AREAS UNDERNEATH CLAMPS.  PIPES ARE LOCATED UNDER TRIM PANELS.  PART TOTAL CYCL	ES:  7,539.					1	L	7	1 	3O				2A13
1998080700799	19980807	00799	SO  	1998	8	7	AU980826         	1	19980515	G	5751	8639802	RIB             			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AILERON	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON NOSE RIBS CRACKED.  FOUND DURING INSPECTION IAW PIPER SB 1011.  PART TOTAL CYCLES:  1,879.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1998080700800	19980807	00800	SO  	1998	8	7	AU980827         	1	19980515	G	5751	8639803	RIB             			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	AILERON	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON NOSE RIBS CRACKED.  FOUND DURING INSPECTION IAW PIPER SB 1011.  PART TOTAL CYCLES:  1,879.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1998080700801	19980807	00801	CE  	1998	8	7	AU980828         	1	19980721	G	5753	052323113	ROLLER          			CESSNA	172   	172N        	2072434	CE  						MCAULY	1C160	1C160DTM    	GL  	TE FLAP	WORN            	H				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAP ROLLERS WORN AND CORRODED.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998080700802	19980807	00802	CE  	1998	8	7	AU980829         	1	19980721	G	5753	05239211	TRACK           			CESSNA	172   	172N        	2072434	CE  						MCAULY	1C160	1C160DTM    	GL  	TE FLAP	WORN            	H				K				NONE                    				F			FLT CONT AFFECTED         			DE	DESCENT        	1			AU	S 										(AUS) FLAP TRACKS WORN.   SEE MDR 98/0828 FOR ADDITIONAL INFORMATION.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998080700803	19980807	00803	CE  	1998	8	7	AU980830         	1	19980716	G	5311		FRAME           			CESSNA	188   	A188B       	2073005	CE  						MCAULY	2A34C	D2A34C98    	GL  	FUSELAGE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE, REAR SPAR AND STUB WING TUBE FRAMES CONTAINED CORROSION PITTING.						1	L	7	1 	3O				A9CE    		5	C	P3EA
1998080700805	19980807	00805	SW  	1998	8	7	AU980832         	1	19980713	G	2910	27810322682	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYD SYSTEM	CHAFED          	H				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			AU	S 							P70215			(AUS) HYDRAULIC PIPE CHAFING ON OIL TANK.  LOSS OF HYDRAULIC FLUID.  PART TOTAL CYCLES:  4,378.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998080700806	19980807	00806		1998	8	7	AU980833         	4	19980715	G	6122	D20268	HOUSING         	MCAULY      		CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	HARTZL	HCJ3Y	PHCJ3YF1    	GL  	PROP GOVERNOR	DAMAGED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					742039					(AUS) PROPELLER GOVERNOR BODY DAMAGED DURING PROPELLER GROUND STRIKE.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P36EA
1998080700807	19980807	00807	EU  	1998	8	7	AU980834         	1	19980711	G	2750	9787320013	CONTROL UNIT    		FCNU952     	PILATS	PC12  	PC12        	7090550	EU  										TE FLAP	FAILED          	H				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			174  		3234					(AUS) FLAP CONTROL UNIT INTERNAL POWER SUPPLY FAILED.						1	L	7	1 	3T			RT	A78EU
1998080700808	19980807	00808	EA  	1998	8	7	AU980835         	1	19980703	G	5520	C6TPM102129	BRACKET         			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR HINGE BRACKET CORRODED.  FOUND DURING INSPECTION IAWAD/DHC-6/70.						1	H	7	2 	3T	4	T		A9EA    	E4EA	6	C	P15EA
1998080700809	19980807	00809	SW  	1998	8	7	AU980836         	1	19980719	G	8200		CAP             			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	TANK	MISSING         	H				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		CL	CLIMB          	1			AU	S 										(AUS) CONTINUOUS ALCOHOL WATER INJECTION TANK CAP MISSING.  SUSPECT CAP INCORRECTLY SECURED FOLLOWING SERVICING.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998080700810	19980807	00810	NM  	1998	8	7	AU980837         	1	19980721	G	5260	85210275001	BRACKET         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					AIRSTAIR DOOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AIRSTAIR DOOR STOP BRACKET CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998080700811	19980807	00811	CE  	1998	8	7	AU980838         	1	19980719	G	5712	05230273	RIB             			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1C160	1C160DTM    	GL  	LT/RT WS 32	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT WING NR 2 NOSE RIBS LOCATED AT STN 32.75 ADJACENT TO THE LEADING EDGE CABIN AIR DUCTS SEVERELY CORRODED.	  PART TOTAL CYCLES:  12,704.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P910
1998080700812	19980807	00812	SW  	1998	8	7	AU980839         	1	19980721	G	6220	206011113103	TRUNNION        			BELL  	206   	206A        	1181508	SW  	ALLSN 	250C  	250C20      	03013	GL  					MAIN ROTOR	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					GDLM11766		CAE821499			(AUS) MAIN ROTOR TRUNNION CRACKED IN TWO PLACES.  FOUND DURING MAGNETIC PARTICLE INSPECTION FOLLOWING HEAVY LANDING.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998080700813	19980807	00813	NM  	1998	8	7	AU980840         	1	19980718	G	2752	793T1005	TRANSMISSION    			BOEING	747   	747338      		NM  										TE FLAP	FAILED          	H				K				NONE                    				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 					2590					(AUS) NR 8 OUTBOARD TRAILING EDGE FLAP DRIVE TRANSMISSION LOCKED UP.						2	L	7	2 	4F			RT	A20WE
1998080700814	19980807	00814	NE  	1998	8	7	AU980841         	2	19980720	G	7321		CONNECTOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					EEC/HMU	CONTAMINATED    	H				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			AU	S 										(AUS) HMU AND EEC CONNECTIONS CONTAMINATED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998080700815	19980807	00815	NE  	1998	8	7	AU980842         	2	19980711	G	7310		LINE            								PWA   	JT9   	JT9D7R4E    	52054	NE  					FUEL SYSTEM	IMPROPER PART   	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE NR 18 PRIMARY FUEL NOZZLE SUPPLY LINE WAS AN INCORRECT PART.  THE LINE WAS CHAFING AGAINST THE NR 17 PRIMAR	Y FUEL NOZZLE SUPPLY LINE.  UNAPPROVED PART.  PERSONNEL/MAINTENANCE ERROR.										4	F			E3NE
1998080700816	19980807	00816	CE  	1998	8	7	AU980843         	1	19980719	G	5730	05230803	SKIN            			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1C160	1C160DTM    	GL  	LT WS 100	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED IN THREE PLACES ADJACENT TO THE RIVETS SECURING THE SKIN TO THE WING RIB AT STN 100.0	.  MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCHES).  PART TOTAL CYCLES:  12,704.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P910
1998080700817	19980807	00817	CE  	1998	8	7	AU980844         	1	19980719	G	5730	05230804	SKIN            			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1C160	1C160DTM    	GL  	RT WS 100	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING UPPER SKIN CRACKED IN THREE PLACES ADJACENT TO THE RIVETS SECURING THE SKIN TO THE WING RIB AT STN 100.	0.  MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCHES).  PART TOTAL CYCLES:  12,704.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P910
1998080700818	19980807	00818	SW  	1998	8	7	AU980845         	1	19980708	G	3220	2752543001	CAM             			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	NLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR CENTERING CAM CRACKED AROUND BOTH ROLLER MOUNTING LUGS.  PART TOTAL CYCLES:  5,781.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998080700819	19980807	00819	SW  	1998	8	7	AU980846         	1	19980714	G	3213	54510051	YOKE            	OZONE       	BA545315    	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	RT/LT MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					KAL055KAL066					(AUS) LEFT AND RIGHT MAIN LANDING GEAR YOKES CRACKED.  FOUND DURING ULTRASONIC INSPECTION IAW AD/SWSA226/74-A3.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998080700820	19980807	00820	EU  	1998	8	7	AU980847         	1	19980721	G	7120	6862003B	MOUNT           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	ENGINE	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1847851A			(AUS) RIGHT LOWER ENGINE MOUNT TUBE CRACKED.						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920
1998080700821	19980807	00821	CE  	1998	8	7	AU980848         	1	19980703	G	5730	05230803	SKIN            			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	LT WS 100	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED IN THREE PLACES IN AREA ADJACENT TO RIVETS SECURING THE SKIN TO WING RIBS AT STN 100.	0.  CRACK LENGTHS 4 MM (0.157 INCHES).  PART TOTAL CYCLES:  12,650.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857
1998080700822	19980807	00822	CE  	1998	8	7	AU980849         	1	19980703	G	5730	05230804	SKIN            			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	RT WS 100	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING UPPER SKIN CRACKED IN TWO PLACES IN AREA ADJACENT TO RIVETS ATTACHING SKIN TO WING RIB AT STN 100.0.  M	AXIMUM CRACK LENGTH 3MM (0.118 INCHES).    PART TOTAL CYCLES:  12,650.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857
1998080700823	19980807	00823	EA  	1998	8	7	AU980850         	1	19980629	G	5720	C6W10057	STRUT           			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING STRUT LINK ATTACHMENT FLANGES CONTAINED EXFOLIATION CORROSION.  PART TOTAL CYCLES:  21,550.						1	H	7	2 	3T	4	T		A9EA    	E4EA	6	C	P15EA
1998080700824	19980807	00824	CE  	1998	8	7	AU980851         	1	19980703	G	5712	05230273	RIB             			CESSNA	172   	172P        	2072436	CE  	LYC   	O360  	O360A4M     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	LT/RT WS 32	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT WING NR 2 NOSE RIBS LOCATED AT STN 32.75 ADJACENT TO THE LEADING EDGE CABIN AIR DUCTS SEVERELY CORR	ODED.  PART TOTAL CYCLES:  12,650.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P857
1998080700825	19980807	00825	WP  	1998	8	7	AU980852         	2	19980721	G	7261	8696012	RELIEF VALVE    	GARRTT      		GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	STICKING        	H				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 			3305 		PO6140		PO6140			(AUS) ENGINE OIL PRESSURE RELIEF VALVE FAULTY.  PART TOTAL CYCLES:  6,199.						1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P15EA
1998080700826	19980807	00826	NM  	1998	8	7	AU980853         	1	19980717	G	2722	654486111	PCU             			BOEING	737   	737376      		NM  										RUDDER	FAILED          	H		A		K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) RUDDER PCU SUSPECT FAULTY.  PART TOTAL CYCLES:  3,637.						2	L	7	2 	4F			RT	A16WE
1998080700827	19980807	00827	EU  	1998	8	7	AU980855         	1	19980122	G	5311		FRAME           			AIRBUS	320   	A320212     		EU  										BS 1810	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTER FUSELAGE FRAME 41 AT STN 1810 CRACKED IN THE TOP HOLE OF THE FLANGE CAP IN AREA ADJACENT TO STRINGER 24 RT.	  CRACK LENGTH 4.762 MM (0.1875 INCHES).  FOUND DURING EDDY CURRENT INSPECTION IAW ER A32-53-10B.					2	L	7	2 	4F			RT	A28NM
1998080700828	19980807	00828	EU  	1998	8	7	AU980856         	1	19980409	G	3230		BRACKET         			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT & RT MLG	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT AND RT MAIN LANDING GEAR FORWARD HINGE BRACKETS CORRODED.  FOUND DURING INSPECTION IAW ER BA6-32-10-30F.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998080700829	19980807	00829	NM  	1998	8	7	AU980857         	1	19980722	G	5610	5893543130	WINDSHIELD      			BOEING	737   	737376      		NM  										COCKPIT	SHATTERED       	H				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) R1 WINDSCREEN INNER AND OUTER PANES SHATTERED.  PART TOTAL CYCLES:  10.						2	L	7	2 	4F			RT	A16WE
1998080700830	19980807	00830	EU  	1998	8	7	AU980858         	1	19980422	G	5311		FRAME           			AIRBUS	320   	A320212     		EU  										BS 1753	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 40 LOCATED AT STN 1753 CRACKED FROM INBOARD FROM HOLE TO RADIUS OF FRAME ADJACENT TO STRINGER 23 RT	.  CRACK LENGTH 8MM (0.314 INCHES).  FOUND DURING EDDY CURRENT INSPECTION IAW ERA32-53-10-30B.					2	L	7	2 	4F			RT	A28NM
1998080700831	19980807	00831	GL  	1998	8	7	AU980859         	1	19980721	G	5542		SKIN            			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  	LYC   	O360  	IO360B1B    	41514	EA  					RUDDER	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L898939A			(AUS) RUDDER CONTAINED FOUR CRACKS IN THE AREA OF THE TOP PIVOT.  FURTHER INVESTIGATION FOUND DELAMINATION AND LOW STREN	GTH IN THE MATERIAL.  SUSPECT CAUSED BY THE USE OF TIME EXPIRED MATERIALS.  PART TOTAL CYCLES:  397.					1	L	7	1 	3O	3	O	RT	EXPA1L71	1E10
1998080700832	19980807	00832	EU  	1998	8	7	AU980860         	1	19980601	G	5730		SKIN            			BAC   	146   	146300A     	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					WING	DAMAGED         	H				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) WING TOP SKIN AT RIB ZERO, RIB 2 LT AND RIB 2 RT CONTAINED NUMEROUS DRILL MARKS.  FOUND DURING INSPECTION IAW ER B	A6-57-10-9A.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998080700833	19980807	00833	CE  	1998	8	7	AU980861         	1	19980714	G	3242		DISC            			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	RT BRAKE	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							21105	731811		(AUS) RT BRAKE DISC SEVERELY RUSTED AND CRACKED AROUND THE DISC AT THE DISC TO SUPPORT HUB WELD.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
1998080700834	19980807	00834	CE  	1998	8	7	AU980862         	1	19980714	G	5711		SPAR            			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	WING	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							21105	731811		(AUS) WING REAR SPAR CRACKED IN WEB RADIUS. THE CRACK WAS CONFIRMED USING DYE PENETRANT NDI.  PART TOTAL CYCLES:  5,343.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
1998080700835	19980807	00835	CE  	1998	8	7	AU980863         	1	19980714	G	5751		FITTING         			CESSNA	172   	172F        	2072414	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	AILERON	CORRODED        	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							21105	731811		(AUS) LT AND RT AILERON BALANCE WEIGHT ATTACHMENT AREA CORRODED.  ALL BALANCE WEIGHT ATTACHMENT RIVETS WERE REMOVED AND 	'AN' NUTS AND BOLTS INSTALLED.  PART TOTAL CYCLES:  5,343.					1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
1998080700836	19980807	00836	SO  	1998	8	7	AU980864         	1	19980726	G	5280	12036438002	HINGE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	LT MLG	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT MAIN LANDING GEAR DOOR REAR HINGE BROKEN.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998091800170	19980918	00170	EA  	1998	9	18	AU980867         	2	19980714	G	8520	A516511	CAMSHAFT        			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L699576		L699576	MA034		(AUS) CAMSHAFT LOBES WORN EXCESSIVELY DUE TO TAPPET BODY SPALLING.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998091800171	19980918	00171	EA  	1998	9	18	AU980868         	2	19980714	G	8520	LW16586	TAPPET          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L699576		L699576	MA034		(AUS) TAPPET BODIES SPALLED.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998091800172	19980918	00172	CE  	1998	9	18	AU980875         	1	19980721	G	3260	99100801	HORN            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR WARNING HORN INTERNAL CONTACT BETWEEN THE LEAF SPRING AND THE DIAPHRAGM HAD FALLEN OFF.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998091800173	19980918	00173	CE  	1998	9	18	AU980878         	1	19980610	G	2450	7271830	CIRCUIT BREAKER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					AC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 AVIONICS MASTER CIRCUIT BREAKER FAULTY.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800174	19980918	00174	SO  	1998	9	18	AU980879         	2	19980528	G	8530		EXHAUST VALVE   			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 6 CYLINDER EXHAUST VALVE FAILED.  VALVE CONTACTED PISTON RESULTING IN SMALL METAL FRAGMENTS PASSING INTO THE TU	RBOCHARGER CAUSING IT TO SEIZE.					1	L	7	2 	3O	3	O		A7SO    	E9CE
1998091800175	19980918	00175	NM  	1998	9	18	AU980882         	1	19980706	G	2761		CAP             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					SPOILER	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 OUTBOARD GROUND SPOILER ACTUATOR BLANKING CAP LEAKING.  LOSS OF HYDRAULIC FLUID.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998091800176	19980918	00176	GL  	1998	9	18	AU980883         	3	19980727	G	6111	C1301	CLAMP           													HARTZL	HC92Z	HC92ZK8     	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U1405			1143F		(AUS) NR 1 BLADE CLAMP CRACKED.  FOUND DURING MAGNETIC PARTICLE INSPECTION.																5	C	P892
1998091800177	19980918	00177	NE  	1998	9	18	AU980884         	3	19980723	G	6111	6951A20	BLADE           													HAMSTD	43D	43D50       	NE  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					N800485N8004			N228461		(AUS) PROPELLER BLADE LEADING EDGE CRACKED FROM STN 44 TO THE BLADE TIP.  CRACK LENGTH 304.8MM (12 INCHES).  INSPECTION 	OF THE OTHER TWO BLADES FOUND SIMILAR, BUT SMALLER CRACKS.  CRACKING WAS CONFIRMED USING DYE PENETRANT AND EDDY CURRENT 	INSPECTION.  FOUND DURING INSPECTION IAW AD/DNS/10 AMDT 1.														6	C	P8879
1998091800178	19980918	00178	SO  	1998	9	18	AU980885         	1	19980717	G	2752	3LD3001007	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					1115					(AUS) LEFT OUTBOARD FLAP ACTUATOR FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998091800179	19980918	00179	NE  	1998	9	18	AU980886         	2	19980723	G	7260	GD202	DRIVESHAFT      			FOKKER	F27   	F27MK600    	4990706	EU  	RROYCE	DART  	DART5327R   	54509	NE  					RT GEARBOX	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			3618 		13330					(AUS) RIGHT ENGINE GEARBOX DRIVESHAFT FAILED AT THE FORWARD UNIVERSAL JOINT DAMAGING THE ENGINE `W' STRUT AND NR 1 AND N	R 2 COMBUSTION CHAMBERS.					2	H	7	2 	4T	4	T		A817    	E297
1998091800180	19980918	00180	GL  	1998	9	18	AU980887         	2	19980701	G	7230	23004514	RING            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					CAC90506		CAC90506			(AUS) COMPRESSOR NR 1 BEARING CARBON SEAL MATING RING WEARING ON IMPELLER BEARING SPINDLE.  SPINDLE WAS WORN TO APPROXIM	ATELY 33 PERCENT OF ITS ORIGINAL DIAMETER.  METAL CONTAMINATION.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998091800181	19980918	00181	SO  	1998	9	18	AU980888         	1	19980722	G	5711	20207T902	SPAR CAP        	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  					RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					130DC					(AUS) RIGHT WING LOWER SPAR CAP CRACKED.  CRACK LENGTH 6.35MM (0.25 INCHES).						1	L	7	1 	3T	4	T		A3SW    	E4EA
1998091800182	19980918	00182	SO  	1998	9	18	AU980889         	1	19980722	G	5711	20207T901	SPAR CAP        	AYRES       		AYRES 	S2    	S2RT34NORMAL	0970106	SO  	PWA   	PT6   	PT6A34AG    	52053	NE  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					130DC					(AUS) LEFT WING LOWER SPAR CAP CRACKED.						1	L	7	1 	3T	4	T		A3SW    	E4EA
1998091800183	19980918	00183	SW  	1998	9	18	AU980890         	1	19980721	G	2436	E15971	REGULATOR       			GULSTM	690TP 	690A        	0141722	SW  										DC SYSTEM	FAILED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 					5143715					(AUS) LEFT VOLTAGE REGULATOR FAILED.  HIGH VOLTAGE OUTPUT CAUSED BATTERIES TO BOIL WITH CONSEQUENT ACID SPILLAGE.						1	H	7	2 	3T				2A4
1998091800184	19980918	00184		1998	9	18	AU980891         	1	19980707	G	5341	W225	BOLTS           			AMTR  		RV4         												WING FITTING	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					W225					(AUS) WING SPAR TO FUSELAGE ATTACHMENT FITTING BOLTS MISSING.  1.  AN4-17A - 4 BOLTS MISSING.  2.  AN3-16A - 6 BOLTS MIS	SING.  3.  AN3-17A - 9 BOLTS MISSING.  PERSONNEL/MAINTENANCE ERROR.								0
1998091800185	19980918	00185		1998	9	18	AU980892         	1	19980707	G	2460		BATTERY CABLE   			AMTR  		RV4         												DC SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN BATTERY CABLE CUT THROUGH AND ARCING.  CABLE RAN THROUGH A JAGGED HOLE IN THE STAINLESS STEEEL FIREWALL WITH 	NO SUPPORT OR GROMMET FITTED.  PERSONNEL/MAINTENANCE ERROR.								0
1998091800186	19980918	00186		1998	9	18	AU980894         	1	19980707	G	3242		DISC            			AMTR  		RV4         												BRAKE	RUBBING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BRAKE DISCS RUBBING ON SPAT BACKPLATES.									0
1998091800187	19980918	00187		1998	9	18	AU980895         	1	19980707	G	5720	W225	SPLICE          			AMTR  		RV4         												WS 420	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					W225					(AUS) LOWER SPAR SPLICE PLATES LOCATED AT W420 TRANSPOSED FRONT TO REAR.  SHARP EDGES MARKED THE BULKHEAD.  PERSONNEL/MA	INTENANCE ERROR.								0
1998091800188	19980918	00188		1998	9	18	AU980896         	1	19980707	G	7120		BOLTS           			AMTR  		RV4         												ENGINE MOUNT	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FRONT ENGINE MOUNT TO CENTER CONSOLE TUNNEL ANGLE AND BOLTS NOT INSTALLED DURING CONSTRUCTION.  PERSONNEL/MAINTENA	NCE ERROR.								0
1998091800189	19980918	00189	SO  	1998	9	18	AU980897         	1	19980723	G	2820		FUEL SYSTEM     			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  					LT & RT ENGINE	MALFUNCTIONED   	W				O				OTHER                   				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			AU	S 							320173319102			(AUS) LEFT AND RIGHT ENGINES CUT OUT.  SUSPECT LEAN CUT-OUT DUE TO FUEL STARVATION.						1	L	7	2 	3O	3	O		A7SO    	E9CE
1998091800190	19980918	00190		1998	9	18	AU980898         	1	19980707	G	7120		BOLT            			AMTR  		RV4         			LYC   		O320E2D     							ENGINE MOUNT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE DYNAFOCAL MOUNT BOLTS THREAD-BOUND RESULTING IN A 0.794MM (0.0312 INCH) GAP BETWEEN THE RUBBER MOUNTS AND T	HE ENGINE.								0
1998091800191	19980918	00191	CE  	1998	9	18	AU980899         	1	19980721	G	8010		RELAY           			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STARTER RELAY FAILED TO DISENGAGE AFTER START-UP. THE MASTER RELAY FAILED TO DISENGAGE CAUSING BATTERY OVERHEATING	.					1	H	7	1 	3O	3	O	RT	3A13    	E295
1998091800192	19980918	00192	CE  	1998	9	18	AU980900         	1	19980730	G	5347	CM37101	SEAT TRACK      			CESSNA	441   	441         	2076020	CE  										BS 235-290	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL FOUR SEAT TRACKS LOCATED BETWEEN FS 235.75 AND FS 290.0 CONTAIN EXFOLIATION CORROSION.						1	L	7	2 	3T			RT	A28CE
1998091800193	19980918	00193	CE  	1998	9	18	AU980901         	1	19980625	G	5512	57321051	SKIN            			CESSNA	441   	441         	2076020	CE  										HORIZ STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT HORIZONTAL STABILIZER LOWER SKIN CORRODED IN AREA 63.5MM (2.5 INCHES) OUTBOARD OF THE FUSELAGE AND 127MM (5 	INCHES) AFT FROM THE LEADING EDGE SKIN.					1	L	7	2 	3T			RT	A28CE
1998091800194	19980918	00194	WP  	1998	9	18	AU980902         	2	19980626	G	7261		FILTER          			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  					RT ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1321 				P31597			(AUS) RIGHT ENGINE OIL FILTER CONTAMINATED WITH METAL.						1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
1998091800195	19980918	00195	SW  	1998	9	18	AU980903         	1	19980707	G	3241	60064911	VALVE           			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					RT BRAKE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 					94060009					(AUS) RIGHT BRAKE ANTI-SKID CONTROL VALVE INTERNAL LEAKAGE.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
1998091800196	19980918	00196	CE  	1998	9	18	AU980904         	1	19980625	G	5320	501111035	FRAME           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					PAX DOORWAY	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD CABIN DOOR FRAME CONTAINED SEVERE EXFOLIATION CORROSION IN THE AREA OF THE UPPER DOOR STRIKER PLATE.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998091800197	19980918	00197	CE  	1998	9	18	AU980905         	1	19980716	G	3260	ICHI6	SWITCH          			CESSNA	441   	441         	2076020	CE  										RT MLG	INTERMITTENT    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR MICROSWITCH INTERMITTENT OPERATION.						1	L	7	2 	3T			RT	A28CE
1998091800198	19980918	00198	CE  	1998	9	18	AU980911         	1	19980729	G	5720	08227904	BRACKET         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	TSIO520B    	17040	SO  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING BRACKET CRACKED.						1	L	7	2 	3O	3	O		3A10    	E8CE
1998091800199	19980918	00199	WP  	1998	9	18	AU980912         	2	19980722	G	7321	89778025	FCU             			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  					LT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					2170230					(AUS) LEFT ENGINE FUEL CONTROL UNIT FAULTY.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE
1998091800200	19980918	00200	CE  	1998	9	18	AU980913         	1	19980712	G	5711	05230414	SPAR            			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					RT WING	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING REAR SPAR TOP FLANGE AND SPAR WEB BUCKLED.  SUSPECT CAUSED BY A WING TIP STRIKE.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998091800201	19980918	00201	SW  	1998	9	18	AU980914         	1	19980727	G	3310	2719115	PANEL           			FRCHLD	SA227 	SA227DC     	3377521	SW  										COCKPIT	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FORWARD DC CIRCUIT BREAKER LIGHTING PANEL CONTAMINATED BY AN UNIDENTIFIED LIQUID AND WAS DAMAGED DUE TO OVER	HEATING.					2	L	7	2 	4T			RT	A18SW
1998091800202	19980918	00202	NM  	1998	9	18	AU980915         	1	19980707	G	3213	AN3106	NUT             			PIPER 	PA60  	PA60600     	7106001	NM  	LYC   	O540  	IO540K1F5   	41532	EA  					RT MLG	STRIPPED        	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT LANDING GEAR TORQUE LINK NUT STRIPPED OFF THE BOLT ALLOWING THE NUT TO SEPARATE.  SPLIT PIN HAD BEEN SHEARED	.					1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998091800203	19980918	00203	NM  	1998	9	18	AU980916         	1	19980728	G	2710	600050513	PUSHROD         			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					AILERON	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4031 							(AUS) AILERON CONTROL SYSTEM PUSHROD LOWER END FITTING RIVETS LOOSE.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998091800204	19980918	00204	SO  	1998	9	18	AU980917         	1	19980730	G	2750	3075001017	CONTROL UNIT    			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					0186					(AUS) FLAP CONTROL UNIT FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998092600006	19980926	00006	EU  	1998	9	26	AU980918         	1	19980509	G	3310	561408BVL2	BALLAST         			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT GLARESHIELD RED FLUORESCENT TUBE BALLAST UNIT (LG16) INTERNAL SHORT CIRCUIT.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998091800205	19980918	00205	EU  	1998	9	18	AU980919         	1	19980725	G	2530	8001050000	OVEN            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					GALLEY	MALFUNCTIONED   	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 					81043138					(AUS) FORWARD GALLEY OVEN FAULTY.  SMOKE FROM THE OVEN NECESSITATED USE OF A FIRE EXTINGUISHER.						2	L	7	2 	4F	4	F		A35EU   	E23EA
1998091800206	19980918	00206	NM  	1998	9	18	AU980921         	1	19980529	G	2120	65B409311	DUCT            			BOEING	747   	747312      	1384932	NM  										AIR DISTRIBUTION	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 AIR CYCLE MACHINE INLET DUCT RUPTURED AT THE `Y' SECTION.						2	L	7	4 	4F			RT	A20WE
1998091800207	19980918	00207	NM  	1998	9	18	AU980922         	1	19980730	G	6520	AO211	GEARBOX         			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					TAIL ROTOR	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			462  		2508					(AUS) TAIL ROTOR GEARBOX CHIP DETECTOR CONTAINED SMALL METAL FLAKES.						1	G	7	1 	3O	3	O		H10WE   	E274
1998091800208	19980918	00208	SO  	1998	9	18	AU980923         	2	19980620	G	8550	CM3758F162OOOS	HOSE            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  					ENGINE OIL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL HOSE LOCATED ADJACENT TO THE EXHAUST PIPE FAILED DUE TO HEAT DETERIORATION.						1	L	7	2 	3O	3	O		A7CE    	E7CE
1998091800209	19980918	00209	SO  	1998	9	18	AU980924         	1	19980804	G	5511		TUBE            		M7          	MAULE 	M7    	M7235       	5460170	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT TAILPLANE LEADING EDGE TUBE CRACKED FOR APPROXIMATELY 60 PERCENT OF THE CIRCUMFERENCE. AIRCRAFT OPERATES AS 	A FLOAT PLANE.					1	H	7	1 	3O	3	O	NC	3A23    	1E4
1998091800210	19980918	00210	NM  	1998	9	18	AU980925         	1	19980711	G	5246	LJ39208	PANEL           			BOEING	747   	747438      		NM  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					13044					(AUS) NR 4 ENGINE OIL ACCESS DOOR SEPARATED.						2	L	7	4 	4F			RT	A20WE
1998091800211	19980918	00211	SO  	1998	9	18	AU980927         	2	19980731	G	8520		CRANKCASE       			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							502934			(AUS) RIGHT ENGINE CRANKCASE CRACKED IN AREA OF NR 1 CYLINDER MOUNT PAD.  CRACK LENGTH 50.8MM (2 INCHES).						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998091800212	19980918	00212	SO  	1998	9	18	AU980928         	2	19980731	G	8530		ENGINE CYLINDER 			CESSNA	402   	402B        	207590P	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							502934			(AUS) NR 2, NR 3, AND NR 5 CYLINDERS CRACKED BETWEEN TOP SPARK PLUG HOLE AND INJECTOR NOZZLE HOLE.						1	L	7	2 	3O	3	O		A7CE    	E8CE
1998091800213	19980918	00213	SW  	1998	9	18	AU980929         	1	19980702	G	6510	476442149	DRIVESHAFT      			BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					TAIL ROTOR	MISALIGNED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVE SHAFT AND BEARINGS OUT OF ALIGNMENT. GREASE DISCOLOURED AT NR 1, NR 2, NR 7, AND NR 8 BEARINGS. A	LL BEARINGS SHOWED SIGNS OF HEAVY WEAR.					1	G	7	1 	3O	3	O		2H3     	1E13
1998091800214	19980918	00214	EA  	1998	9	18	AU980930         	2	19980719	G	7421	STD1102	SPARK PLUG      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							L1914527A			(AUS) NR 1 CYLINDER SPARK PLUGS (2 OFF) DAMAGED BY FOD.  CYLINDER AND PISTON ALSO CONTAINED SMALL DENTS.  FOD WAS FOUND 	TO BE A MISSING BLANKING PLUG FROM THE CYLINDER PRIMER POSITION.  THE PLUG WAS FINALLY LOCATED IN THE NR 2 CYLINDER INDU	CTION TUBE.				1	L	7	1 	3O	3	O		2A13    	E274
1998091800215	19980918	00215	CE  	1998	9	18	AU980931         	1	19980404	G	3230	3581507710	BRACKET         			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					LT MLG	WORN            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					TC1124		272978R	736273		(AUS) LEFT MAIN LANDING GEAR JAMMED DURING RETRACTION.  AIRCRAFT LANDED WITH LEFT MLG RETRACTED CAUSING DAMAGE TO THE LT	 WINGTIP, LT FLAP , LT AILERON, LT STABILATOR, LT PROPELLER, AND LT ENGINE.					1	L	7	2 	3O	3	O	RT	3A16    	3E1
1998091800216	19980918	00216	SO  	1998	9	18	AU980932         	1	19980708	G	3230	4198301	HOOK            			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					317852104					(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK HOOK TO ACTUATING ROD ATTACHMENT RIVETS SHEARED.						1	L	7	2 	3O				A20SO
1998091800217	19980918	00217	CE  	1998	9	18	AU980934         	1	19980730	G	5330	TC1124	RIVET           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					FUSELAGE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			7234 		TC1124					(AUS) RIVETS MISSING FROM FUSELAGE IN AREA FROM DORSAL FIN FORWARD TO FIN STERN POST.  SUSPECT RIVETS CORRODED.  SKIN LA	P JOINTS HAVE SEPARATED OVER A LENGTH OF APPROXIMATELY 2.1 METRES (7 FEET).					1	L	7	2 	3O	3	O	RT	3A16    	3E1
1998091800218	19980918	00218	EU  	1998	9	18	AU980935         	1	19980615	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 AND R1 SERVICE DOOR LOWER CONNECTION LINK BUSHES AND L2 AND R2 UPPER AND LOWER CONNECTION LINK BUSHES MIGRATED.	  FOUND DURING INSPECTION IAW ER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1998091800219	19980918	00219	EU  	1998	9	18	AU980936         	1	19980630	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) R2 SERVICE DOOR UPPER CONTROL ARM SHOULDERED BUSH MIGRATED.  FOUND DURING INSPECTION IAW ER A32-52-10-7C.						2	L	7	2 	4F			RT	A28NM
1998091800220	19980918	00220	EU  	1998	9	18	AU980937         	1	19980316	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 SERVICE DOOR LOWER CONNECTION LINK BUSH AND L2 SERVICE DOORUPPER CONNECTION LINK BUSH MIGRATED.  FOUND DURING I	NSPECTION IAWER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1998091800221	19980918	00221	EU  	1998	9	18	AU980938         	1	19980304	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 SERVICE DOOR UPPER AND LOWER CONNECTION LINK BUSHES AND R1 DOOR LOWER CONNECTION LINK BUSH MIGRATED. FOUN D DUR	ING INSPECTION IAW ER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1998091800222	19980918	00222	EU  	1998	9	18	AU980939         	1	19980130	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) R2 SERVICE DOOR UPPER AND LOWER CONNECTION LINK BUSHES AND L2 SERVICE DOOR LOWER CONNECTION LINK BUSH MIGRATED.  F	OUND DURING INSPECTION IAW ER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1998091800223	19980918	00223	EU  	1998	9	18	AU980940         	1	19980624	G	3246	5010488	WHEEL           			SAAB  	SF340 	SF340A      	7850100	EU  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THREE WHEEL ASSEMBLIES FOUND TO BE CRACKED IN THE BEAD SEAT AREA.						2	L	7	2 	4T			RT	A52EU
1998091800224	19980918	00224	EU  	1998	9	18	AU980942         	1	19980623	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 AND R1 SERVICE DOOR LOWER CONNECTION LINK BUSHES AND R2 SERVICE DOOR UPPER CONNECTION LINK BUSHES MIGRATED.  FO	UND DURING INSPECTION IAW ER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1998091800225	19980918	00225	EU  	1998	9	18	AU980943         	1	19980726	G	3411	IH2419	MANIFOLD        	AIRBORNE    	IH2419      	REIMS 	406   	F406        		EU  	PWA   	PT6   	PT6A112     	52043	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GYRO PRESSURE MANIFOLD CORRODED.  MANIFOLD IS CONSTRUCTED FROM CADMIUM PLATED STEEL.  STEEL ELBOW ALSO CORRODED.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA
1998091800226	19980918	00226	CE  	1998	9	18	AU980944         	1	19980805	G	5711	052301144	RIVET           		052301144   	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					WING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING LOWER SPAR CAP HAD NUMEROUS RIVETS MISSING.  RIVETS HAVE A CROSS ON THE HEAD POSSIBLY INDICATING MAGNESIUM MA	NUFACTURE.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998091800227	19980918	00227	SO  	1998	9	18	AU980945         	1	19980709	G	3260	MS272402	SWITCH          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					RT MLG	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR MICROSWITCH STICKING.						1	L	7	2 	4T	4	T		A21SO   	E4EA
1998091800228	19980918	00228	EA  	1998	9	18	AU980946         	2	19980515	G	7320	3027974	PY LINE         			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ENG FUEL SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					056605		056605			(AUS) ENGINE PY LINE CRACKED AT END FITTING FERRULE.						1	L	7	2 	4T	4	T		A21SO   	E4EA
1998091800229	19980918	00229	SO  	1998	9	18	AU980947         	2	19980803	G	8540	539568	GEAR            			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1970 		286072R		286072R			(AUS) STARTER SHAFT GEAR TOOTH CRACKED.  SUSPECT CAUSED BT BACKFIRE DURING START.  FOUND USING NDT.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998091800230	19980918	00230	SO  	1998	9	18	AU980948         	2	19980803	G	8520	535661	CAMSHAFT        			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1970 		286072R		286072R			(AUS) CAMSHAFT FRONT LOBE WORN.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998091800231	19980918	00231	SO  	1998	9	18	AU980949         	2	19980803	G	8550	629218	PUMP            			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					286072R		286072R			(AUS) ENGINE OIL PUMP GEAR BUSHES WORN CAUSING THE GEARS TO RUB AGAINST THE PUMP BODY AND CAUSE WEAR TO THE HOUSING.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998091800232	19980918	00232	WP  	1998	9	18	AU980950         	2	19980715	G	8530	VETL0218	PISTON RING     			DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					ENGINE	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					441		441			(AUS) NR 1 CYLINDER PISTON SEIZED.  SIGNS OF IMPENDING SEIZURE ON THE OTHER CYLINDERS.  INVESTIGATION FOUND INSUFFICIENT	 CLEARANCE ON NEWLY FITTED OIL CONTROL RINGS.					1	Q	7	1 	3I	3	I		A8EU    	A8EU
1998091800233	19980918	00233	SO  	1998	9	18	AU980951         	1	19980717	G	5720	IAS	SEAL            			PIPER 	PA34  	PA34200T    	7103406	SO  										WING	ICED            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AILERONS BINDING.  FAULT WAS TRACED TO ICE FORMING BETWEEN THE GAP SEALS AND THE AILERON.						1	L	7	2 	3O				A7SO
1998091800234	19980918	00234	NM  	1998	9	18	AU980952         	1	19980729	G	5610		WINDOW          			BOEING	737   	737376      		NM  										COCKPIT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) N 2 RT COCKPIT WINDOW EMERGENCY OPENING MECHANISM OUT OF ADJUSTMENT.						2	L	7	2 	4F			RT	A16WE
1998091800235	19980918	00235	NM  	1998	9	18	AU980953         	1	19980801	G	2913	GENM29501011	PUMP            			BOEING	737   	737476      		NM  										HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4504 							(AUS) SYSTEM `B' ELECTRIC HYDRAULIC PUMP FAULTY.  PART TC:  20,942.						2	L	7	2 	4F			RT	A16WE
1998091800236	19980918	00236	EU  	1998	9	18	AU980954         	1	19980708	G	5311		FRAME           			AIRBUS	320   	A320211     	3930320	EU  										BS 43	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 43 AT STN 1023 CONTAINED CRACKS IN THE FASTENER HOLES OF THE FLOORBEAM FLANGES Y-765RH AND Y-1292RH	.  FOUND DURING EDDY CURRENT INSPECTION IAW SB A320-53-10-08.					2	L	7	2 	4F			RT	A28NM
1998091800237	19980918	00237	CE  	1998	9	18	AU980955         	1	19980803	G	7120	9691001057	MOUNT           			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  					ENGINE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			400  							(AUS) ENGINE MOUNT ASSEMBLY WRAPPED WITH `SPEED TAPE'.  WHEN THE TAPE WAS REMOVED IT WAS FOUND THAT THE MOUNT HAD BEEN S	EVERELY CHAFED BY SCAT HOSE WIRES.					1	L	7	2 	3O	3	O		3A16    	E5CE
1998091800238	19980918	00238	EU  	1998	9	18	AU980956         	1	19980519	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L1 AND L2 SERVICE DOOR LOWER CONNECTION LINK BUSHES MIGRATED.  FOUND DURING INSPECTION IAW ER A32-52-10-7C.						2	L	7	2 	4F			RT	A28NM
1998091800239	19980918	00239	EU  	1998	9	18	AU980957         	1	19980624	G	5240		BUSHING         			AIRBUS	320   	A320211     	3930320	EU  										SERVICE DOOR	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) R1, R2, AND L2 CABIN DOOR LOWER CONNECTION LINK BUSHINGS MIGRATED.  FOUND DURING INSPECTION IAW ER A32-52-10-7C.						2	L	7	2 	4F			RT	A28NM
1998091800240	19980918	00240		1998	9	18	AU980958         	4	19980806	G	2562	E01	CASE            			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30      	03013	GL  					ELT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELT TRANSMITTER AND BATTERY HOUSING BODIES BADLY CRACKED IN SEVERAL PLACES.  SUSPECT CAUSED BY OVERTORQUE OF THE M	AIN BODY SCREWS DURING MANUFACTURE.  PART TC:  187.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998091800241	19980918	00241	EU  	1998	9	18	AU980960         	1	19980806	G	3040	XW21121	GEAR            			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					WINDSHIELD WIPER	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WINDSCREEN WIPER CONVERTER DRIVE GEAR STRIPPED ALLOWING THE MOTOR TO OVERSPEED.  PART TC:  7,961.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6
1998091800242	19980918	00242	EA  	1998	9	18	AU980961         	2	19980401	G	8520	LW19341	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2160 		L279268A		L279268A			(AUS) CAMSHAFT CSU DRIVE GEAR TOOTH FAILED.  METAL CONTAMINATION OF OIL SYSTEM.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998091800243	19980918	00243	CE  	1998	9	18	AU980962         	1	19980812	G	3211	S21381	BOLT            			CESSNA	172   	172M        	2072418	CE  										RT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR RETAINING BOLT FAILED.  INVESTIGATION FOUND THAT THE BOLT HAD BEEN BROKEN FOR SOME TIME. R	IGHT MLG LEG COLLAPSED.					1	H	7	1 	3O			NT	3A12
1998091800244	19980918	00244	CE  	1998	9	18	AU980963         	1	19980812	G	3211	S21381	BOLT            			CESSNA	172   	172M        	2072418	CE  										LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR RETAINING BOLT CRACKED.  FOUND USING MAGNETIC PARTICLE INSPECTION FOLLOWING FAILURE OF THE 	SIMILIAR BOLT ON THE RIGHT MAIN LANDING GEAR.  SEE MDR 98/0962.					1	H	7	1 	3O			NT	3A12
1998091800245	19980918	00245	CE  	1998	9	18	AU980964         	1	19980804	G	3230	727725	CIRCUIT BREAKER 			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR CONTROL CIRCUIT BREAKER FAULTY.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800246	19980918	00246	WP  	1998	9	18	AU980965         	1	19980806	G	6520	A0211	GEARBOX         			ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					TAIL ROTOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			980  		0262					(AUS) TAIL ROTOR GEARBOX FAULTY.  GEARBOX OIL BLACK.  EVIDENCE OF GEAR SLIPPAGE.						1	G	7	1 	3O	3	O		H10WE   	E274
1998091800247	19980918	00247	EA  	1998	9	18	AU980967         	1	19980804	G	2910	72980010249	PIPE            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					HYDRAULIC SYS	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					056					(AUS) NR 2 HYDRAULIC SYSTEM CASE DRAIN PIPE CORRODED.						2	H	7	4 	4T	4	T		A20EA   	E4EA
1998091800248	19980918	00248	EU  	1998	9	18	AU980969         	1	19980811	G	3260		SWITCH          			BAG   	JETSTM	JETSTM3107  	1500215	EU  										RT MLG	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR UPLOCK SWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4T			RT	BA15CAA
1998091800249	19980918	00249	EA  	1998	9	18	AU980970         	2	19980806	G	7322	13662	BRACKET         		MA45        						LYC   	O360  	O360A1F6    	41514	EA  					CARBURETOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					75058401		L3528436A			(AUS) CARBURETOR FLOAT BRACKET BROKEN.  PART TC:  208.											3	O			E286
1998091800250	19980918	00250	WP  	1998	9	18	AU980971         	1	19980806	G	6220	369A12103	STRAP           			HUGHES	369   	369C        	4470704	WP  	ALLSN 	250C  	250C18A     	03011	GL  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			582  		3452					(AUS) MAIN ROTOR STRAPS CRACKED IN AREA OUTBOARD OF THE STRAP RETAINING BOLT.  PART TC:  582.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998091800251	19980918	00251		1998	9	18	AU980972         	1	19980627	G	7120	LK25239	PIN             								RROYCE	RB211 	RB211524G19 		NE  					MOUNT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE AFT ENGINE MOUNT FAILSAFE PIN SHEARED.											4	F			E30NE
1998091800252	19980918	00252	EU  	1998	9	18	AU980974         	1	19980502	G	2910	201042094	HOSE            			AIRBUS	320   	A320211     	3930320	EU  										HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC HOSE FAILED.  LOSS OF `GREEN' HYDRAULIC SYSTEM.  INVESTIGATION FOUND THE RIGHT MAIN LANDING GEAR DOWNLOC	K ACTUATOR HOSE HAD FAILED ADJACENT TO THE LOWER SWIVEL FITTING.  PART TC:  18,828					2	L	7	2 	4F			RT	A28NM
1998092600007	19980926	00007	WP  	1998	9	26	AU980975         	2	19980806	G	7200		ENGINE          								GARRTT	TPE331	TPE33110U   	01514	WP  					RT NACELLE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT ENGINE WOULD NOT ACHEIVE TARGET TORQUE OF 104.5 PERCENT.  MAXIMUM TORQUE ACHIEVED 99 PERCENT.											4	T			E4WE
1998091800253	19980918	00253	SO  	1998	9	18	AU980978         	1	19980304	G	2731	41734078	CONTROL CABLE   			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR TAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR ELEVATOR TRIM CABLE BROKEN IN THE AREA OF THE SERVO MOTOR.						1	L	7	2 	3O			 	A20SO
1998091800254	19980918	00254	CE  	1998	9	18	AU980979         	1	19980501	G	3260		SWITCH          			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					RT MLG	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK MICROSWITCH STIFF DUE TO LACK OF LUBRICATION.						1	L	7	2 	3T	3	T		3A20    	E4EA
1998091800255	19980918	00255	NE  	1998	9	18	AU980980         	2	19980806	G	7510	12034409002	RECEIVER        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					DE-ICE SYSTEM	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT DEICE SYSTEM PRESSURE REGULATOR EXHAUST AIR RECEIVER LOOSE ALLOWING HOT AIR LEAKAGE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998091800256	19980918	00256	SW  	1998	9	18	AU980983         	1	19980814	G	3243	1023A	NUT             		1023A       	AIRTRC	AT300 	AT301       	0390103	SW  										BRAKE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1283					(AUS) BRAKE MASTER CYLINDER PISTON TO SHAFT SECURING NUT MISSING.						1	L	7	1 	3R				A9SW
1998091800257	19980918	00257	NM  	1998	9	18	AU980984         	1	19980520	G	2782	65447581	STUD            			BOEING	737   	737377      		NM  										TE FLAP	FRACTURED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			1176 		0368ANSSNO00					(AUS) LT OUTBOARD NR 1 LEADING EDGE SLAT ACTUATOR STUD LOCKING ASSEMBLY END FITTING FRACTURED AND JAMMED UNDER THE HEAD 	OF THE INNER PISTON P\N 65-44757-1 AND THE END OF THE TRANSFER TUBE P\N 65-44768-1 PREVENTING CORRECT OPERATION OF THE A	CTUATOR.  PART TC:  30,320.				2	L	7	2 	4F			RT	A16WE
1998091800258	19980918	00258	EU  	1998	9	18	AU980985         	1	19980811	G	5350	A5351008700201	PANEL           			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					FUSELAGE	SEPARATED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LT AND RT WING TO FUSELAGE PANELS SEPARATED FROM THE AIRCRAFT.  PART TC:  33,163.						2	L	7	2 	4F	4	F		A35EU   	E23EA
1998091800259	19980918	00259	NM  	1998	9	18	AU980986         	1	19980423	G	3830	C0086ANSSNO031	VALVE           			BOEING	737   	737377      		NM  										LAVATORY	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					C0086ANSSNO0					(AUS) FORWARD TOILET DRAIN VALVE LEAKING DURING VACUUM TEST IAW ERB73-38-11 PT2.  PART TC:  3,325.						2	L	7	2 	4F			RT	A16WE
1998091800260	19980918	00260	EU  	1998	9	18	AU980987         	1	19980309	G	2510	010890005	INERTIA REEL    		010810615   	BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CORRODED        	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) CAPTAIN'S SHOULDER HARNESS INERTIA REEL JAMMED DUE TO INTERNAL CORROSION.  DATE OF MANUFACTURE 3Q84.						2	H	7	4 	4F	4	F		A49EU   	E6NE
1998091800261	19980918	00261	EU  	1998	9	18	AU980988         	1	19980606	G	3232	AE2463921G0181	HOSE            			AIRBUS	320   	A320211     	3930320	EU  										LT MLG	FAILED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOOR ACTUATOR HOSE FAILED ADJACENT TO THEINBOARD END FITTING.  LOSS OF `GREEN' SYSTEM HYDRA	ULIC FLUID.					2	L	7	2 	4F			RT	A28NM
1998091800262	19980918	00262	EU  	1998	9	18	AU980989         	1	19980506	G	2760	831A000002	BRAKE           			AIRBUS	320   	A320211     	3930320	EU  										RT WING	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					00600ANSSNO0					(AUS) RIGHT WING TIP BRAKE UNIT FAULTY.  SUSPECT DUE TO MOISTURE INGRESS.						2	L	7	2 	4F			RT	A28NM
1998091800263	19980918	00263	SW  	1998	9	18	AU980990         	1	19980503	G	6210	206010200033	BLADE           			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE LEADING EDGE UPPER SURFACES PEELING AWAY.  FURTHER INSPECTION FOUND INTERGRANULAR CORROSION ON TH	E LOWER SURFACE. EDDY CURRENT INSPECTION CONFIRMED INTERNAL CORROSION.  PART TC:  2,209.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998091800264	19980918	00264	SW  	1998	9	18	AU980991         	1	19980601	G	5532	206020113191	SKIN            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL FIN ASSEMBLY SKIN CORRODED.  PART TC:  7,193.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998091800265	19980918	00265	SW  	1998	9	18	AU980992         	1	19980428	G	5415	206033201167	STIFFENER       			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					PYLON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT STIFFENER LOCATED ON THE FORWARD RT SIDE CRACKED.  PART TC:  7,193.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998091800266	19980918	00266	SW  	1998	9	18	AU980993         	1	19980428	G	6720		CONTROL         			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	MISRIGGED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR CONTROLS INCORRECTLY RIGGED ALLOWING TAIL ROTOR CONTROL TUBE P\N 206-001-020-033 TO RUB ON BULKHEAD P\N	 206-031-200-51.  PART TC:  7,193.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998091800267	19980918	00267	NE  	1998	9	18	AU980994         	2	19980713	G	7260	430124102	SEAL            			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					START/GEN	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LE45885E			(AUS) ENGINE ACCESSORY GEARBOX STARTER/GENERATOR SEAL LEAKING.  PART TC:  54.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998091800268	19980918	00268	NE  	1998	9	18	AU980995         	2	19980713	G	7210	230307203	SEAL            		HOUSING     	BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					LT & RT ENGINES	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LE45885ELE45			(AUS) LEFT ENGINE AND RIGHT ENGINE OUTPUT SEALS LEAKING.  PART TC:  88.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998091800269	19980918	00269	EU  	1998	9	18	AU980998         	1	19980803	G	6730	ACM28592	SERVO           	DUNLOP      	AC67244     	SNIAS 	350   	AS350D      	8680803	EU  	ALLSN 	250C  	250C30      	03013	GL  					CYCLIC	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			853  		EW330					(AUS) CYCLIC SERVO EXTENSION P\N ACM28592 CORRODED INTERNALLY RESTRICTING PISTON ROD P\N ACM28591.						1	G	7	1 	3U	3	U		H9EU    	E1GL
1998091800270	19980918	00270	SO  	1998	9	18	AU980999         	2	19980804	G	8530	SA4000SC7POI5	PISTON RING     			CESSNA	210   	2105        	2073404	CE  	CONT  	O470  	IO470S      	17026	SO  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							109330			(AUS) NR 2 AND NR 4 CYLINDER OIL CONTROL RINGS BROKEN.  PART TC:  89.						1	H	7	1 	3O	3	O		3A21    	3E1
1998091800271	19980918	00271	CE  	1998	9	18	AU981000         	1	19980815	G	3260		HARNESS         			CESSNA	402   	402B        	207590P	CE  										RT MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT MAIN LANDING GEAR DOWNLOCK SWITCH WIRING LOOM FOULED IN GEAR LINKAGE DURING LANDING GEAR DOWN SELECTION CAUSING	 THE WIRING LOOM TO BE TORN OUT OF THE DOWNLOCK SWITCH.					1	L	7	2 	3O				A7CE
1998091800272	19980918	00272	EU  	1998	9	18	AU981001         	1	19980509	G	6230	350A37118322	LOCKPLATE       		350A3710760 	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					M/R MAST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					M2970					(AUS) MAIN ROTOR MAST BEARING LOCKPLATE CRACKED.  SUSPECT LOSS OF TORQUE LOADING ON MAST BEARING CAUSED VIBRATION LEADIN	G TO THE LOOSE AND SHEARED RIVETS ON THE SWASHPLATE SUPPORT.					1	G	7	1 	3U	3	U		H9EU    	E19EU
1998091800273	19980918	00273	SO  	1998	9	18	AU981002         	1	19980817	G	2140	3751047	VALVE           	JANITROL    	HEATER      	PIPER 	PA31  	PA31350     	7103110	SO  										HEATING SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					3751047					(AUS) CABIN HEATER FUEL VALVE WOULD NOT SHUT OFF PREVENTING HEATER FROM BEING TURNED OFF.						1	L	7	2 	3O				A20SO
1998091800274	19980918	00274	CE  	1998	9	18	AU981003         	1	19980814	G	3222	108820010603	FORK            			BEECH 	77    	77          	1153007	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK CRACKED.  FOUND DURING INSPECTION IAW SB 2241.						1	L	7	1 	3O				A30CE
1998091800275	19980918	00275	CE  	1998	9	18	AU981004         	1	19980814	G	3222	108820010603	FORK            			BEECH 	77    	77          	1153007	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK CRACKED.  FOUND DURING INSPECTION IAW SB2241.						1	L	7	1 	3O				A30CE
1998091800276	19980918	00276	CE  	1998	9	18	AU981005         	1	19980814	G	3222	102820010603	FORK            			BEECH 	77    	77          	1153007	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK CRACKED.  FOUND DURING INSPECTION IAW SB2241.						1	L	7	1 	3O				A30CE
1998091800277	19980918	00277	EA  	1998	9	18	AU981006         	2	19980714	G	8520	LW19332	ROD             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			346  		L87461A		L87461A			(AUS) NR 3 CYLINDER CONNECTING ROD CRACKED.  FOUND USING FLUORESCENT MAGNETIC PARTICLE TECHNIQUE.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998091800278	19980918	00278		1998	9	18	AU981008         	4	19980812	G	2562	E01	BATTERY         			CESSNA	402   	402CESSNA   	207590K	CE  										ELT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1420					(AUS) ELT BATTERIES LEAKING ELECTROLYTE.  BEACON MODULATION INCORRECT.						1	L	7	2 	3O				A7CE
1998091800279	19980918	00279	CE  	1998	9	18	AU981009         	1	19980813	G	5610	1013840257	WINDSHIELD      			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	BIRD STRIKE     	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT WINDSHIELD OUTER PANE EXTENSIVELY CRACKED DUE TO BIRDSTRIKE.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800280	19980918	00280	SO  	1998	9	18	AU981010         	1	19980626	G	3211	6792631	TRUNNION        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR TRUNNION BROKEN IN THE LOWER AREA OF THE FILLET AS REFERENCED IN AD/PA34/44 AMDT1.  RT MAI	N LANDING GEAR COLLAPSED ON LANDING.					1	L	7	1 	3O	3	O		A3SO    	1E4
1998091800281	19980918	00281	EU  	1998	9	18	AU981012         	1	19980625	G	2621	57333012	FIRE BOTTLE     			BAC   	146   	146200A     	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					1502					(AUS) NR 2 ENGINE OUTBOARD FIRE EXTINGUISHER BOTTLE LEAKING.  CORROSION FOUND ON THE BOTTLE HEAD.  FOUND DURING INSPECTI	ON IAW ER BA6-26-20-15.					2	H	7	4 	4F	4	F		A49EU   	E6NE
1998091800282	19980918	00282	SO  	1998	9	18	AU981013         	1	19980809	G	5270		LOCK            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					DOOR	MALFUNCTIONED   	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) FORWARD DOOR WARNING LIGHT ILLUMINATED IN-FLIGHT.  INSPECTION OF THE DOOR LOCKING MECHANISM COULD FIND NO FAULT.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998091800283	19980918	00283	EU  	1998	9	18	AU981014         	1	19980806	G	3230		VALVE           			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR RELEASE VALVE NEEDED RE-SETTING.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE
1998091800284	19980918	00284	NE  	1998	9	18	AU981015         	2	19980521	G	7250	3112696	BEARING         			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					LT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					94559		PLE94559			(AUS) LEFT ENGINE NR 4 BEARING CAGE FAILED.  METAL CONTAMINATION OF OIL SYSTEM.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800285	19980918	00285	NE  	1998	9	18	AU981016         	2	19980812	G	7322	0164348640	FCU             			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 2 ENGINE	FAULTY          	W				K				NONE                    				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 			521  		15082		15082			(AUS) NR 2 ENGINE FUEL CONTROL UNIT INTERNAL FAULT.  PART TC:  521.						1	G	7	2 	3U	3	U		H1NE    	E19EU
1998091800286	19980918	00286	EU  	1998	9	18	AU981017         	1	19980701	G	6120	RA68741	SWITCH          	ROTOL       	C488        	FOKKER	F27   	F27MK600    	4990706	EU  	RROYCE	DART  	DART5327R   	54509	NE  					PROP CONTROL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 			2756 		081		13330			(AUS) NR 2 ENGINE PROPELLER CONTROL UNIT PRESSURE SWITCH LEAKING OIL.						2	H	7	2 	4T	4	T		A817    	E297
1998091800287	19980918	00287	WP  	1998	9	18	AU981018         	2	19980720	G	7414	X21937	SLIP RING       	BTH         	AG46        	DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					MAGNETO	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					X21937					(AUS) MAGNETO DRIVE END BEARING FITTED TO THE HOUSING WITH NO INSULATION RESULTING IN POLING OF THE ARMATURE.  METAL CON	TAMINATION.  IMPULSE COUPLING MAGNETIZED SLIP RING SUSPECT UNAPPROVED PART.  PERSONNEL/MAINTENANCE ERROR.					1	Q	7	1 	3I	3	I		A8EU    	A8EU
1998091800288	19980918	00288	EA  	1998	9	18	AU981019         	2	19980707	G	8520		STUD            			PIPER 	PA22  	PA22150     	7102210	SO  	LYC   	O320  	O320A2B     	41508	EA  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 CYLINDER HOLDDOWN STUDS BROKEN OR LOOSE.						1	H	7	1 	3O	3	O		1A6     	E274
1998091800289	19980918	00289	EA  	1998	9	18	AU981020         	2	19980720	G	8530	LW13622	INLET VALVE     			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			1919 		L1720048A		L1720048A			(AUS) NR 6 CYLINDER INLET VALVE HEAD SEPARATED FROM THE VALVE STEM.  CRANKCASE CRACKED AND SEVERE INTERNAL DAMAGE TO THE	 ENGINE.  PART TC:  4,097.					1	L	7	1 	3O	3	O		A3SO    	1E4
1998091800290	19980918	00290	NE  	1998	9	18	AU981021         	2	19980720	G	7322	0164448560	FCU             								TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					NR 1 ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			8    		A312B		663			(AUS) NR 1 ENGINE FUEL CONTROL UNIT INTERNAL FAULT.  PART TC:  8,965											3	U			E19EU
1998091800291	19980918	00291		1998	9	18	AU981022         	4	19980725	G	3425	6226198003	HPU             			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					542					(AUS) NR 2 HSI HEADING PROCESSOR UNIT FAILED.						2	H	7	2 	4T	4	T		A41EU   	E26NE
1998091800292	19980918	00292	EU  	1998	9	18	AU981023         	1	19980722	G	3244	900X6X12PLY	TIRE            			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  					NLG	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE WHEEL TIRE BALANCE PATCH SEPARATED FROM THE INSIDE WALL OF THE TIRE.						2	H	7	2 	4T	4	T		A41EU   	E26NE
1998091800293	19980918	00293	CE  	1998	9	18	AU981024         	1	19980726	G	5711		SPAR            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTER WING SPAR LOWER SPAR CAP DELAMINATED FOR APPROXIMATELY 609.6MM (24 INCHES).  PART TC:  1,710.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800294	19980918	00294	CE  	1998	9	18	AU981025         	1	19980801	G	2432	40576	BATTERY         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  					E/E BAY	OVERTEMP        	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 					075534					(AUS) BATTERY OVERHEATED.  SUSPECT CAUSED BY NUMEROUS STARTS.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800295	19980918	00295	CE  	1998	9	18	AU981026         	1	19980805	G	7603	509660763	LEVER           			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					COCKPIT	LOOSE           	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ENGINE POWER LEVER ARM SLIPPING ON THE GROOVED PIN OF THE REVERSING MECHANISM.  SUSPECT LEVER ARM CLAMPING BOLT AN	D NUT INSUFFICIENTLY TORQUED DURING INSTALLATION 47.2 HOURS PREVIOUSLY.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800296	19980918	00296	CE  	1998	9	18	AU981027         	1	19980805	G	7603	8011094	PIN             			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					POWER LEVER	DEFECTIVE       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) POWER LEVER GROOVED PIN IS IMPRESSING GROOVES INTO LIGHT ALLOY OF POWER LEVER ARM.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998091800297	19980918	00297	SO  	1998	9	18	AU981028         	1	19980821	G	5753	658988049	BRACKET         			PIPER 	PA28  	PA28140     	7102802	SO  										TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP HANGER BRACKET CONTAINED SEVERE EXFOLIATION CORROSION.  PART TC:  7,247.						1	L	7	1 	3O				2A13
1998091800298	19980918	00298	EU  	1998	9	18	AU981029         	1	19980719	G	2750		FLAP            			BAC   	146   	AVRO146RJ70A	1500095	EU  										TE FLAP	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) FLAP SYSTEM FAULTY.						2	H	7	4 	4F			RT	A49EU
1998091800299	19980918	00299	NE  	1998	9	18	AU981030         	2	19980818	G	7261	2028419	FILTER          			PILATS	PC12  	PC12        	7090550	EU  	PWA   	PT6   	PT6A67D     		NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							110042			(AUS) ENGINE OIL FILTER SUSPECT FAULTY.  PART TC:  9,847.						1	L	7	1 	3T	4	T	RT	A78EU   	E26NE
1998091800300	19980918	00300	CE  	1998	9	18	AU981031         	1	19980803	G	5711		FITTING         			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RT LOWER SPAR FITTING CRACKED.						1	L	7	2 	3O	3	O		3A16    	E5CE
1998091800301	19980918	00301	NE  	1998	9	18	AU981032         	2	19980809	G	7314	371900	PUMP            			DOUG  	DC9   	DC933F      	302207A	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			6182 				666886			(AUS) NR 2 ENGINE DRIVEN FUEL PUMP DRIVE SPLINE SHEARED.						2	L	7	2 	4F	4	F		A6WE    	E2EA
1998091800302	19980918	00302	GL  	1998	9	18	AU981033         	3	19980723	G	6114	D4237C81	HUB             			CESSNA	310   	310K        	2074228	CE  	CONT  	O470  	IO470U      	17026	SO  	MCAULY	2AF34C	D2AF34C81   	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			860  		710802			710802		(AUS) PROPELLER HUB CRACKED THROUGH THE THREADS IN NR 2 BLADE SOCKET.  CRACK LENGTH APPROXIMATELY 50.8MM (2 INCHES).  CR	ACK DOES NOT FOLLOW THE THREADS AROUND THE SOCKET.					1	L	7	2 	3O	3	O		3A10    	3E1	5	C	P5EA
1998091800303	19980918	00303	EA  	1998	9	18	AU981035         	1	19980807	G	5730		SKIN            			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							23112			(AUS) LEFT WING LEADING EDGE DAMAGED BY CONTACT WITH A YACHT DURING A STORM.  AIRCRAFT IS A FLOAT PLANE.						1	H	7	1 	3R	3	R		A806    	5E1
1998091800304	19980918	00304	WP  	1998	9	18	AU981036         	1	19980724	G	6410	269A603523	BLADE           			HUGHES	269   	269C        	4470504	WP  	LYC   	O360  	HIO360D1A   	41514	EA  					TAIL ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					S1402					(AUS) TAIL ROTOR BLADE LEADING EDGE ABRASION STRIP DEBONDED.  AREA OF DELAMINATION APPROXIMATELY 50.8MM BY 25.4MM (2 INC	HES BY 1 INCH).  PART TC:  2,267.					1	G	7	1 	3O	3	O		4H12    	1E10
1998091800305	19980918	00305	EU  	1998	9	18	AU981037         	1	19980811	G	3246	AHA1236	WHEEL           			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  					RT MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					LJ191					(AUS) RIGHT MAIN LANDING GEAR WHEEL OUTER RIM GROUND AWAY WHEN TIRE FAILED FOLLOWING BRAKE LOCK-UP.						2	H	7	2 	4T	4	T		A41EU   	E4EA
1998091800306	19980918	00306	EU  	1998	9	18	AU981038         	1	19980810	G	3246	AHA1236	WHEEL           	DUNLOP      	AHA1236     	STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A65R     	52043	EA  					RT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			144  		KR02B					(AUS) RIGHT MAIN WHEEL OUTER RIM SECTION MISSING.						2	H	7	2 	4T	4	T		A41EU   	E4EA
1998091800307	19980918	00307	EU  	1998	9	18	AU981039         	1	19980812	G	3246	SEEATTACHEDLIST	WHEEL           			AIRBUS	320   	A320211     	3930320	EU  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					SEEATTACHEDL					(AUS) MAIN WHEEL ASSEMBLY INBOARD HALF HUBS (28 OFF) CRACKED.   FOUND DURING EDDY CURRENT INSPECTION.						2	L	7	2 	4F			RT	A28NM
1998091800308	19980918	00308	EU  	1998	9	18	AU981040         	1	19980825	G	5720	68140131	ANGLE           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) SPAR CAP ANGLE CRACKED BEYOND THE STOP DRILL HOLE.  PART TC:  7,384.						1	H	7	2 	3O	3	O		A31EU   	1E10
1999012100004	19990121	00004	EU  	1999	1	21	AU981041         	1	19980813	G	5210		DOOR            			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  					CABIN	MALFUNCTIONED   	W				K				NONE                    				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			AU	S 							L3344536A	CH30517		(AUS) RIGHT DOOR OPENED IN-FLIGHT. INVESTIGATION COULD FIND NO FAULTS WITH THE LATCHES OR LOCKING MECHANISM.						1	L	7	1 	3O	3	O	NT	A51EU   	E286
1998091800309	19980918	00309	NE  	1998	9	18	AU981042         	3	19980814	G	6110	660710398	BOLT            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R390	R3904123F27 	NE  	PROPELLER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							785480	DAP0059		(AUS) PROPELLER FLANGE MOUNT BOLT SHEARED IN THE AREA WHERE THE SHANK JOINS THE HEAD WHEN TORQUED DURING PROPELLER FITTI	NG.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P31NE
1998091800310	19980918	00310	SW  	1998	9	18	AU981043         	1	19980819	G	6510	47645239103	BEARING         			BELL  	47    	47          	1180602	SW  										T/R DRIVE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR DRIVE SHAFT BEARINGS ROUGH.  THE BEARINGS ARE NEW ITEMS AND WERE BEING INSPECTED PRIOR TO USE.  FIVE OF	 ELEVEN BEARINGS SUPPLIED WERE FAULTY.					1	G	7	1 	3O				H1
1998091800311	19980918	00311	CE  	1998	9	18	AU981044         	1	19980814	G	5730	082203713	SKIN            			CESSNA	402   	402A        	207590M	CE  										LT & RT WINGS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT WING LOWER INBOARD SKINS CRACKED IN AREA OF OUTBOARD WHEEL WELL CUTOUTS BELOW THE FORWARD LANDING G	EAR SUPPORT ATTACHMENTS.					1	L	7	2 	3O				A7CE
1998091800312	19980918	00312	CE  	1998	9	18	AU981045         	1	19980814	G	5712	082217565	RIB             			CESSNA	402   	402A        	207590M	CE  										LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING RIB DOUBLER REPAIR CRACKED.						1	L	7	2 	3O				A7CE
1998091800313	19980918	00313	CE  	1998	9	18	AU981046         	1	19980814	G	5712	082217565	RIB             			CESSNA	402   	402A        	207590M	CE  										RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING RIB DOUBLER CRACKED.  CRACK LENGTH APPROXIMATELY 9.525MM (0.375 INCH).						1	L	7	2 	3O				A7CE
1998091800314	19980918	00314	CE  	1998	9	18	AU981047         	1	19980811	G	2437		BULB            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AIRCRAFT SUFFERED A COMPLETE ELECTRICAL FAILURE.  INVESTIGATION FOUND THAT THE ALTERNATOR WARNING LIGHT BULB HAD B	LOWN.					1	H	7	1 	3O	3	O	RT	3A13    	E295
1998091800315	19980918	00315	NM  	1998	9	18	AU981048         	1	19980723	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										BS 178	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD LOCATED AT STN 178 CRACKED IN THE FOLLOWING AREAS:  1.  FORWARD FACE WEB CRACKED IN FIVE	 POSITIONS ADJACENT TO THE  RADAR MOUNT POINTS.   2.  WL217 CONTAINED TWO CRACKS IN THE AREA BETWEEN LBL 5.7 AND  LBL 17	 3.  LT SIDE CHORD LOCATED AT WL 207 - CRACK LENGTH 15.24MM (0.6 INCH).  4.  LBL 5.7 VERTICAL CHORD ON THE AFT FACE OF T	HE BULKHEAD AT WL 184 FOUND DURING INSPECTION IAW ER B73-53-10-39D.			2	L	7	2 	4F			RT	A16WE
1999012100005	19990121	00005	NM  	1999	1	21	AU981049         	1	19980803	G	2730	2287	ACTUATOR        			BOEING	767   	767216      	1385121	NM  	GE    	CF6   	CF680A      	30025	NE  					ELEVATOR	FAILED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 			3809 		2287					(AUS) LEFT ELEVATOR POWER CONTROL ACTUATOR LEAKING FROM CHECK VALVE END CAP. LOSS OF RT HYDRAULIC SYSTEM FLUID. INVESTIG	ATION FOUND THE CHECK VALVE INNER AND BACKUP `O' RING SEALS MISSING FROM THREE CHECK VALVE END CAPS.  PERSONNEL/MAINTENA	NCE ERROR.  PART TC:  32,529.				2	L	7	2 	4F	4	F	TC	A2NM    	E13NE
1998091800316	19980918	00316	WP  	1998	9	18	AU981050         	2	19980825	G	7397		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  					LT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT ENGINE TEMPERATURE LIMITER PLUG P107 HAD THE WIRES TO PINS `U', `N', AND `L' WORN THROUGH DUE TO CHAFING ON P	LUG P128 TO THE CONTROL UNIT P\N 32-82010-011 MOUNTED ON THE AVIONICS SHELF.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE
1998091800317	19980918	00317	CE  	1998	9	18	AU981051         	1	19980816	G	3213	04425061	TORQUE LINK     			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300C       	17022	SO  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LANDING GEAR TORQUE LINK SIDE WEBS CRACKED IN FIVE PLACES.						1	H	7	1 	3O	3	O	NT	3A12    	E253
1998091800318	19980918	00318	SO  	1998	9	18	AU981052         	2	19980815	G	8530	648005P005	PISTON RING     			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) REPLACEMENT PISTON RINGS FOUND TO BE DEFECTIVE WHEN INSPECTED BEFORE INSTALLATION.  OIL CONTROL RING P/N 654717P00	5-1 HAD A PIECE MISSING. TOP NR 1 RING P/N 648005P005 HAS A MANUFACTURING DEFECT.  MANUFACTURING ERROR.					1	L	7	2 	3O	3	O		A25CE   	E7CE
1998091800319	19980918	00319	SO  	1998	9	18	AU981053         	2	19980815	G	8530	654717P0051	PISTON RING     			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  					ENGINE	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) REPLACEMENT PISTON RINGS FOUND TO BE FAULTY DURING INSPECTION BEFORE INSTALLATION.  OIL CONTROL RING P/N 654717P00	5-1 HAD A PIECE MISSING.  TOP NR 1 RING P/N 648005P005 HAS A MANUFACTURING FAULT.					1	L	7	2 	3O	3	O		A25CE   	E7CE
1998091800320	19980918	00320	SO  	1998	9	18	AU981054         	2	19980817	G	8530	648044	PISTON          		648044      	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  					ENGINE	IMPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							554303			(AUS) INCORRECT PART NUMBER PISTONS FITTED.  PISTONS WERE APPLICABLE TO TSIO520 ENGINES ONLY. UNAPPROVED PART.  PERSONNE	L/MAINTENANCE ERROR.  PART TC:  669.					1	H	7	1 	3O	3	O		3A21    	E5CE
1998091800321	19980918	00321	EU  	1998	9	18	AU981055         	1	19980807	G	2612	1734362450	DETECTOR        			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  					ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							785480			(AUS) ENGINE TAIL PIPE HEAT DETECTION SENSORS AND CONNECTORS CONTAMINATED WITH MOISTURE.  PART TC:  7,001.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998091800322	19980918	00322	CE  	1998	9	18	AU981057         	1	19980817	G	2810	50T3890348	FUEL CELL       			BEECH 	80    	65B80       	1152812	CE  	LYC   	O540  	IGSO540A1D  	41532	EA  					FUSELAGE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT INBOARD FUEL CELL LEAKING IN AREA ADJACENT TO THE RT ENGINE NACELLE.						1	L	7	2 	3O	3	O		3A20    	1E7
1998091800323	19980918	00323	CE  	1998	9	18	AU981058         	1	19980817	G	2810	509215528	FUEL CELL       			BEECH 	80    	65B80       	1152812	CE  	LYC   	O540  	IGSO540A1D  	41532	EA  					FUSELAGE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR OUTBOARD AND LEADING EDGE FUEL TANKS P/N 50T389034-8 AND P/N 50-921552-8 LEAKING.						1	L	7	2 	3O	3	O		3A20    	1E7
1998091800324	19980918	00324	SO  	1998	9	18	AU981059         	1	19980820	G	3230	3034	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR ACTUATOR `UP' HYDRAULIC HOSE LEAKING AROUND CENTER SECTION.  PART TC:  2,514.						1	L	7	2 	3O				A20SO
1998091800325	19980918	00325	NM  	1998	9	18	AU981060         	1	19980806	G	3520		OXYGEN BOTTLE   			BOEING	747   	747438      		NM  										CABIN	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER OXYGEN BOTTLES (6 OFF) LOCATED IN THE CEILING OF THE FORWARD CARGO HOLD HAD THE LOCKWIRE BROKEN AND WERE	 TURNED OFF.					2	L	7	4 	4F			RT	A20WE
1998091800326	19980918	00326	SO  	1998	9	18	AU981061         	1	19980807	G	2913	WTC21351	POWER PACK      			PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC PUMP	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 								DJ10751A		(AUS) LANDING GEAR POWER PACK FAULTY.  INVESTIGATION FOUND WORN `O' RING SEALS AND A STICKY TIME DELAY VALVE.  PART TC: 	 9,639.					1	L	7	2 	3O				A20SO
1998091800327	19980918	00327	SO  	1998	9	18	AU981063         	2	19980817	G	7413	1038280824	VIBRATOR        	BENDIX      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			271  		925					(AUS) ENGINE START SYSTEM VIBRATOR FAULTY.  INVESTIGATION FOUND THE CONTACT PO INTS FAILED CLOSED DUE TO A FAULTY CONDEN	SER.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900714	19981009	00714	SO  	1998	10	9	AU981066         	1	19980820	G	3213	65319004	STRUT           			PIPER 	PA28  	PA28151     	7102805	SO  						SNSNCH	74D	74DM        	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR LEG CRACKED IN AREA OF TORQUE LINK MOUNT LUGS.   PART TC:  9,360.						1	L	7	1 	3O				2A13    		5	N	P88614
1998100900715	19981009	00715	SO  	1998	10	9	AU981067         	1	19980820	G	3213	78738002	LUG             			PIPER 	PA28  	PA28151     	7102805	SO  						SNSNCH	74D	74DM        	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR AXLE STUD LUGS CRACKED IN AREA OF TORQUE LINK ATTACHMENT.   PART TC:  9,360.						1	L	7	1 	3O				2A13    		5	N	P88614
1998100900716	19981009	00716	SO  	1998	10	9	AU981068         	1	19980820	G	3213	78738003	LUG             			PIPER 	PA28  	PA28151     	7102805	SO  						SNSNCH	74D	74DM        	EA  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR AXLE STUD LUGS CRACKED IN AREA OF TORQUE LINK ATTACHMENT.   PART TC:  9,360.						1	L	7	1 	3O				2A13    		5	N	P88614
1998100900717	19981009	00717	SO  	1998	10	9	AU981072         	1	19980816	G	2823	492111	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE FUEL SHUTOFF VALVE STIFF TO OPERATE.  THE VALVE COULD NOT BE COMPLETELY OPENED CAUSING RESTRICTED FUEL	 FLOW.   PART TC:  9,693.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998100900718	19981009	00718	NM  	1998	10	9	AU981073         	1	19980815	G	2497	LJ37495	WIRE            			BOEING	757   	757200      	1384950	NM  										AC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT GENERATOR (IDG) FEED CABLES SHORT-CIRCUITED AND BURNT THROUGH AT THE UPPER ENGINE TO PYLON DISCONNECT PLUG.						2	L	7	2 	4F			RT	A2NM
1998100900719	19981009	00719	SO  	1998	10	9	AU981074         	2	19980811	G	7414	10357586	GEAR            	BENDIX      	S6RN205     	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MAGNETO	STRIPPED        	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			1087 		0058813ER		278318R			(AUS) RIGHT ENGINE MAGNETO DISTRIBUTOR GEAR TEETH STRIPPED.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998100900720	19981009	00720	CE  	1998	10	9	AU981075         	1	19980803	G	5280		RIB             			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR DOOR RIBS AND ADJACENT STRUCTURE CRACKED.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998100900721	19981009	00721	CE  	1998	10	9	AU981076         	1	19980803	G	5711		RIVET           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	WING SPAR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOOSE AND WORKING RIVETS LOCATED IN AREA OF RIGHT WING INBOARD SPAR SECTION.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998100900722	19981009	00722	CE  	1998	10	9	AU981077         	1	19980803	G	5511		RIVET           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	HORIZ STAB	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIVETS MISSING FROM RIGHT HORIZONTAL STABILIZER SPAR.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998100900723	19981009	00723	GL  	1998	10	9	AU981078         	2	19980819	G	7250	6877092	TURBINE         								ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAT34271		CAE831591			(AUS) SECOND STAGE TURBINE WHEEL CRACKED IN THREE PLACES.  CRACK LENGTHS APPROXIMATELY 25.4 MM (1 INCH).   PART TC:  1,6	21.										3	U			E4CE
1998100900724	19981009	00724	SO  	1998	10	9	AU981079         	1	19980816	G	5243	12007993613	DOOR            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					HYD COMP	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT HYDRAULIC BAY DOOR MISSING.  LEFT ELECTRIC HYDRAULIC PUMP SUCTION PIPE BENT.  DOOR HINGE SLIGHTLY DAMAGED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998100900725	19981009	00725	GL  	1998	10	9	AU981080         	3	19980827	G	6114	1A170FFA7563	HUB             		1A170FFA7563						LYC   	O360  	O360A4K     	41514	EA  	MCAULY	1A170	1A170FFA    	GL  	PROPELLER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1413 					P80976		(AUS) PROPELLER HUB CRACKED IN TWO AREAS.  FOUND DURING INSPECTION IAW AD/PFP/13 AMDT3.											3	O			E286	5	N	P857
1998100900726	19981009	00726		1998	10	9	AU981081         	4	19980821	G	2340		LOOM            			BOEING	767   	767238      		NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					INTERPHONE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WIRING LOOM LOCATED IN THE AREA ABOVE DOOR L1 WORN THROUGH DUE TO CHAFING ON THE AIRCRAFT STRUCTURE.						2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
1998100900727	19981009	00727	WP  	1998	10	9	AU981082         	2	19980801	G	7230	3101668	PLENUM          								GARRTT	TPE331	TPE33110U   	01514	WP  	ROTOL	R333	R333482F12  	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			5491 		P63099		P63099	DRG20878		(AUS) NR 2 ENGINE PLENUM CASE CRACKED IN THE 9 O'CLOCK POSITION.  LEAKING P3 AIR CAUSED HEAT DAMAGE TO ELECTRICAL WIRING	 INSULATION AND PAINT.   PART TC:  17,403.										4	T			E4WE	6	C	P61GL
1998100900728	19981009	00728	NE  	1998	10	9	AU981083         	2	19980806	G	7510	12034409002	RECEIVER        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					DE-ICE SYSTEM	LOOSE           	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) RIGHT DE-ICE SYSTEM PRESSURE REGULATOR EXHAUST AIR RECEIVER LOOSE ALLOWING HOT AIR TO BLOW ONTO THE LEAK DETECTOR.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998100900729	19981009	00729	SO  	1998	10	9	AU981084         	2	19980820	G	8530	T1641370	CYLINDER        			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					T1641370		352293			(AUS) NR 2 CYLINDER ROCKER ARM SHEARED OFF AT ATTACHMENT POINT.						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
1998100900730	19981009	00730	SW  	1998	10	9	AU981085         	1	19980820	G	5411		KEELSON         			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	LT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT NACELLE STRUCTURE INBOARD KEELSON CRACKED.   PART TC:  29,623.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998100900731	19981009	00731	SO  	1998	10	9	AU981086         	1	19980824	G	5712		RIB             			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	LT WING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING RIBS LOCATED IN THE LEFT WHEEL WELL DISTORTED AND RIVETS SHEARED.						1	L	7	2 	3O				A7SO    		5	C	P920
1998100900732	19981009	00732	EU  	1998	10	9	AU981087         	1	19980818	G	6210	709010301101	BLADE           			AGUSTA	A109  	A109C       	0260118	EU  										MAIN ROTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					EM0126					(AUS) MAIN ROTOR BLADES FAULTY.  BLADES FAILED TO MEET THE REQUIREMENTS OF B.T. NR 109-106.   PART TC:  2,760.						1	G	7	2 	3U				H7EU
1998100900733	19981009	00733	EU  	1998	10	9	AU981088         	1	19980818	G	6210	709010301101	BLADE           			AGUSTA	A109  	A109C       	0260118	EU  										MAIN ROTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					EM0416					(AUS) MAIN ROTOR BLADES FAULTY.  BLADES FAILED TO MEET THE REQUIREMENTS OF ALERT B.T. NR 109-106.   PART TC:  3,196.						1	G	7	2 	3U				H7EU
1998100900734	19981009	00734	CE  	1998	10	9	AU981089         	1	19980825	G	2910	CM3690C60100	HOSE            			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HYDRAULIC SYS	DETERIORATED    	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR EXTENSION HYDRAULIC HOSE DETERIORATED AND HOLED.  LOSS OF HYDRAULIC FLUID.  PART TC:  7.941	.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998100900735	19981009	00735	CE  	1998	10	9	AU981090         	1	19980824	G	3211	12416111	BOLT            			CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							294729R	902665		(AUS) LEFT MAIN LANDING GEAR ATTACHMENT BOLT CRACKED.   PART TC:  5,350.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL
1998100900736	19981009	00736	CE  	1998	10	9	AU981091         	1	19980814	G	2140	09883011	COMBUSTOR       	JANITROL    	CABINHEATER 	BEECH 	58    	58          	1152740	CE  						MCAULY	3AF32C	3AF32C512   	GL  	HEATER	CRACKED         	W				K				NONE                    				A			FLAME/FIRE                			CR	CRUISE         	1			AU	S 					09883011					(AUS) CABIN HEATER COMBUSTION CAN CRACKED AND LEAKING CARBON MONOXIDE INTO THE CABIN.						1	L	7	2 	3O				3A16    		5	C	P22EA
1998100900737	19981009	00737	SO  	1998	10	9	AU981092         	1	19980810	G	5415		PLATE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE INBOARD ENGINE MOUNT PLATE LOOSE AND RIVETS MISSING.  PART TC:  9,754.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998101700022	19981017	00022	EA  	1998	10	17	AU981093         	2	19980823	G	8530		COVER           			LKHEED	1049  	C121C       	5262118	WP  	WRIGHT	R3350 	R3350*      	67040	EA  	HAMSTD	43E	43E60       	NE  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			CL	CLIMB          	1			AU	S 							W560143			(AUS) ENGINE CYLINDER ROCKER COVER CRACKED AND LEAKING.						2	L	7	4 	4R	4	R		6A5     	E272	6	C	P871
1998100900738	19981009	00738	NM  	1998	10	9	AU981094         	1	19980709	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD CRACKED IN THE FOLLOWING AREAS:  SIDE CHORDS AT WL 207 LT AND WL 207 RT (2 CRACKS).  VER	TICAL CHORD AT LBL 5.7 AFT FACE 3.  INTERCOSTALS AT WL 197 LT AND WL 195 RT (2 CRACKS).  FOUND DURING EDDY CURRENT INSPE	CTION.				2	L	7	2 	4F			RT	A16WE
1998100900739	19981009	00739	NM  	1998	10	9	AU981095         	1	19980710	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FUSELAGE BULKHEAD FORWARD FACE CONTAINED SIX WEB CRACKS.  FOUND DURING ULTRASONIC INSPECTION.						2	L	7	2 	4F			RT	A16WE
1998100900740	19981009	00740	NM  	1998	10	9	AU981097         	1	19980617	G	2913	223422	FILTER          			BOEING	737   	73733A      	1384673	NM  										HYD PUMP	MISINSTALLED    	W				K				NONE                    				K	J	W	FLUID LOSS                	WARNING INDICATION        	INADEQUATE Q C            	DE	DESCENT        	1			AU	S 					223422					(AUS) HYDRAULIC SYSTEM `A' HYDRAULIC PUMP CASE DRAIN FILTER INSTALLED IN REVERSE CAUSING LOW HYDRAULIC PRESSURE AND DAMA	GE TO THE PUMP.					2	L	7	2 	4F			RT	A16WE
1998100900741	19981009	00741	NM  	1998	10	9	AU981098         	1	19980106	G	2612	710165	FIRE DETECTOR   	WHITTAKER   	801RDS      	BOEING	767   	767324      		NM  	GE    	CF6   	CF680C2B7   		NE  					LT ENGINE	FAULTY          	W				K				NONE                    				B	N		SMOKE/FUMES/ODORS/SPARKS  	FALSE WARNING             		CR	CRUISE         	1			AU	S 					332					(AUS) LT ENGINE FIRE DETECTION SYSTEM FAULTY DUE TO DECREASED INSULATION RESISTANCE BETWEEN ACTIVE ELEMENTS WITHIN THE D	ETECTOR CAUSED BY MIGRATION OF METAL PARTICLES FROM THE SENSOR CORE.   PART TC:4,199.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900742	19981009	00742	CE  	1998	10	9	AU981099         	1	19980825	G	3230	HYH5001	MOTOR           			BEECH 	76    	76          	1153005	CE  										MLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) LANDING GEAR ELECTRIC MOTOR FAULTY. INVESTIGATION FOUND WORN BRUSHES.   PART TC:  7,900.						1	L	7	2 	3O				A29CE
1998100900743	19981009	00743	WP  	1998	10	9	AU981101         	2	19980828	G	7397		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT NACELLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE TEMPERATURE LIMITER PLUG P107 RUBBING ON PLUG P128 OF THE INVERTER CONTROL UNIT P/N 32-82010-011 LOCAT	ED ON THE REAR AVIONICS SHELF.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998100900744	19981009	00744	SW  	1998	10	9	AU981102         	1	19980826	G	3213	2751540003	SHAFT           			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	RT MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR TORQUE LINK SHAFT SHEARED THROUGH ONE OF THE LOCKING PIN HOLES.   PART TC:  6,563.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998100900745	19981009	00745	EU  	1998	10	9	AU981103         	1	19980828	G	5311		FRAME           			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BS 18	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME 18 CONTAINED STRESS CORROSION AND CRACKING IN FLANGES.  A HOLE MEASURING 63.5 MM BY 25.4 MM (2.5 IN	CHES BY 1 INCH) WAS FOUND JUST BELOW FLOOR LEVEL AT THE RT SERVICE DOOR.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998100900746	19981009	00746	NM  	1998	10	9	AU981104         	1	19980812	G	5610	9567H9612	WINDOW          			BOEING	737   	737476      		NM  										COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					9567H9612					(AUS) FIRST OFFICER'S NR 2 WINDOW OPERATING MECHANISM FAULTY.  WINDOW FAILED TO OPEN WHEN THE EXTERNAL EMERGENCY HANDLE 	WAS OPERATED.					2	L	7	2 	4F			RT	A16WE
1998100900747	19981009	00747	NM  	1998	10	9	AU981105         	1	19980106	G	2120	1190A	VALVE           			BOEING	767   	767324      		NM  	GE    	CF6   	CF680C2B7   		NE  					AIR DISTRIBUTION	STICKING        	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					1190A					(AUS) EQUIPMENT COOLING OVERRIDE/SMOKE CLEARANCE VALVE STUCK IN THE CLOSED POSITION.   PART TC:  8,350.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900748	19981009	00748	NM  	1998	10	9	AU981106         	1	19980811	G	5511		SPAR            			BOEING	737   	73733A      	1384673	NM  										HORIZ STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT HORIZONTAL STABILIZER REAR SPAR UPPER CHORD AND TRAILING EDGE BEAM UPPER COVER PLATE CONTAINED EXFOLIATION CO	RROSION.  REAR SPAR CORROSION LOCATED AT STA 138 WAS APPROXIMATELY 1.27 MM (0.050 INCH DEEP.					2	L	7	2 	4F			RT	A16WE
1998100900749	19981009	00749	NM  	1998	10	9	AU981107         	1	19980901	G	3230	450007501	ROD             			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540G1B5   	41532	EA  					NLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR BUNGEE ROD CORRODED AND BINDING.  NOSE LANDING GEAR COLLAPSED.						1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998100900750	19981009	00750	EU  	1998	10	9	AU981108         	1	19980828	G	5313		LONGERON        			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR BAGGAGE BAY MAIN LONGERON CONTAINED EXTENSIVE STRESS CORROSION AT ALL FRAME INTERSECTIONS.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998100900751	19981009	00751	WP  	1998	10	9	AU981109         	2	19980828	G	7397		WIRE            			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LT NACELLE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE TEMPERATURE LIMITER PLUG P107 CHAFING ON PLUG P128 OF THE INVERTER CONTROL UNIT P/N 32-82010-011 LOCAT	ED ON THE REAR AVIONICS SHELF.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998100900752	19981009	00752	SO  	1998	10	9	AU981110         	1	19980718	G	5541	D514	SPAR            			MAULE 	M7    	M7235       	5460170	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L258924811			(AUS) RUDDER POST CORRODED INTERNALLY.  AIRCRAFT IS A FLOAT PLANE AND THE SALT WATER ENTERS THE RUDDER POST THROUGH THE 	RUDDER TAB CABLE CASING.   PART TC:  390.					1	H	7	1 	3O	3	O	NC	3A23    	1E4
1998100900753	19981009	00753	SO  	1998	10	9	AU981111         	1	19980718	G	5531	B21	SPAR            			MAULE 	M7    	M7235       	5460170	SO  	LYC   	O540  	IO540W1A5   	41532	NE  					VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L258924811			(AUS) FIN POST SUSPECT INTERNAL CORROSION.  WATER CAN ENTER THE POST VIA THE TRIM TAB CONTROL CONDUIT.  AIRCRAFT OPERATE	S AS A FLOAT PLANE.   PART TC:  390.					1	H	7	1 	3O	3	O	NC	3A23    	1E4
1998100900754	19981009	00754		1998	10	9	AU981112         	1	19980809	G	7603	847740	SLEEVE          		6432394     						ROTAX 	912   	ROTAX912    	55555	EU  					POWER LEVER	CORRODED        	W				K				NONE                    				E			VIBRATION/BUFFET          			DE	DESCENT        	1			AU	S 							4410104			(AUS) LEFT THROTTLE CONTROL BROKEN AT THROTTLE ARM.  INVESTIGATION FOUND THAT THE CABLE PIVOT IN THE THROTTLE ARM SEIZED	 DUE TO CORROSION.  AIRCRAFT OPERATES IN A SALT LADEN ENVIRONMENT.   PART TC:  231.										3	I			EXPE3I
1998100900755	19981009	00755	CE  	1998	10	9	AU981113         	1	19980904	G	2750	1013800006	CONTROL CABLE   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  					TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT OUTBOARD FLAP DRIVE CABLE WORN AT THE MOTOR END.  PART TC:  9,693.						1	L	7	2 	4T	4	T	 	A24CE   	E4EA
1998100900756	19981009	00756	CE  	1998	10	9	AU981114         	1	19980831	G	5510	12326231	SUPPORT         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U206066016		810235R	931915		(AUS) HORIZONTAL STABILIZER REINFORCEMENT CRACKED.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
1998100900757	19981009	00757	CE  	1998	10	9	AU981115         	1	19980901	G	5510	12326241	SUPPORT         			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HORIZONTAL STABILIZER REAR LEFT REINFORCEMENT BRACKET CRACKED IN TWO PLACES.   PART TC:  3,108.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL
1998100900758	19981009	00758	SW  	1998	10	9	AU981116         	1	19980813	G	2430	880014501	SUPPRESSOR      			MOONEY	M20   	M20J        	5870219	SW  	LYC   	O360  	IO360A3B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	DC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALTERNATOR NOISE SUPPRESSOR RFI (RADIO FREQUENCY INTERFERENCE) UNIT FAULTY.						1	L	7	1 	3O	3	O		2A3     	1E10	5	C	P920
1998100900759	19981009	00759	SO  	1998	10	9	AU981118         	1	19980831	G	7810	LW16620	EXHAUST STACK   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L88668A		L88668A			(AUS) RIGHT ENGINE REAR EXHAUST SEGMENT CRACKED FOR 75 PERCENT OF THE CIRCUMFERENCE OF THE FLANGE.   PART TC:  1,971.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998100900760	19981009	00760	SO  	1998	10	9	AU981119         	1	19980831	G	8120	LW12435	BRACKET         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	TURBOCHARGER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1484 		L871861A		L871861A			(AUS) ENGINE TURBOCHARGER SUPPORT BRACKET BROKEN BETWEEN THE SUPPORT STAY AND THE BRACKET.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998100900761	19981009	00761	EU  	1998	10	9	AU981120         	1	19980725	G	2530	81043138	OVEN            			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					GALLEY	FIRE            	W				F				ACTIVATE FIRE EXT.      				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			AU	S 					81043138					(AUS) FORWARD GALLEY OVEN CAUGHT FIRE DUE TO FOOD OIL SPILLED ONTO TRAY.  FIRE EXTINGUISHER DISCHARGED.						2	L	7	2 	4F	4	F		A35EU   	E23EA
1998100900762	19981009	00762	CE  	1998	10	9	AU981121         	1	19980828	G	5531	9664000037	SPAR            			BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCC3Y	PHCC3YF2    	GL  	VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER SPAR CORRODED.						1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P25EA
1998100900763	19981009	00763	NE  	1998	10	9	AU981122         	2	19980714	G	7250		BEARING         								LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	FAILED          	W				O				OTHER                   				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CR	CRUISE         	1			AU	S 							LFO5788			(AUS) NR 2 ENGINE 4/5 BEARING SUSPECT FAULTY.											4	F			E6NE
1998100900764	19981009	00764	WP  	1998	10	9	AU981123         	1	19980901	G	5543	4N33150	TRIM TAB        			GOVT  	N22   	N24A        		WP  	ALLSN 	250B  	250B17B     	03010	GL  	HARTZL	HCA3V	HCA3VF7     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRIM TAB CRACKED.						1	H	7	2 	3T	3	T		A7PC    	E10CE	5	C	P6EA
1998100900765	19981009	00765	EU  	1998	10	9	AU981124         	1	19980904	G	6220		BEARING         	AEROSP      	332AB1000106	SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					MAIN ROTOR HEAD	LOOSE           	W				K				NONE                    				O	F		OTHER                     	FLT CONT AFFECTED         		IN	INSP/MAINT     	1			AU	S 					M117					(AUS) MAIN ROTOR HEAD TEFLON BEARINGS HAD EXCESSIVE PLAY.   PART TC:  1,142.						2	G	7	2 	4U	4	U		H4EU    	E12NE
1998100900766	19981009	00766	NM  	1998	10	9	AU981125         	1	19980904	G	3230	10800113	UPLOCK          			DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	PW121 	PW121       	52124	NE  					RT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) RT MAIN LANDING GEAR UPLOCK HOOK WORN AND CORRODED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998100900767	19981009	00767	EU  	1998	10	9	AU981126         	1	19980821	G	3340	019042	CLUTCH          		SX16        	AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					SPOTLIGHT	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 					3					(AUS) NITESUN LIGHT CLUTCH OUT OF ADJUSTMENT.  NITESUN MOUNTS DEFECTIVE.   PART TC:  24.						1	G	7	2 	3U	3	U		H10EU   	E19EU
1998100900768	19981009	00768	CE  	1998	10	9	AU981127         	1	19980817	G	5711	051212478	SPAR            			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTER SECTION CARRY THROUGH SPAR CORRODED AND RIVET HEAD MISSING.  RIVET HEAD HAD BEEN MISSING PRIOR TO RECE	NT RE-PAINT.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1998100900769	19981009	00769	CE  	1998	10	9	AU981128         	1	19980817	G	2700		CONTROL CABLE   			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	FLIGHT CONTROL	CORRODED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) FLIGHT CONTROL CABLES CORRODED AND WORN.  SUBMITTER SUSPECTS CORROSION (RUST) IS A DIRECT RESULT OF THE RECENT STR	IP AND RE-PAINT OF THE AIRCRAFT DUE TO CONTAMINATION BY THE PAINT STRIPPING CHEMICALS.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1998100900770	19981009	00770	CE  	1998	10	9	AU981129         	1	19980817	G	7922	75944	VALVE           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	OIL TEMP	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L4387627A			(AUS) ENGINE OIL SYSTEM THERMAL BYPASS VALVE MISSING.  VALVE BODY WAS FITTED TO THE OIL FILTER ADAPTER AS A PLUG.  FOUND	 DURING INSPECTION IAW AD/LYC/78 AMDT 5.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998100900771	19981009	00771	SW  	1998	10	9	AU981132         	1	19980828	G	2720	OIOA61636	ROD FORK        			MTSBSI	MU2   	MU2B30      	5780410	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	RUDDER CONTROL	FAILED          	W				K				NONE                    				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) RUDDER CONTROL ROD FORK END ROTATED AND CAUSED RESTRICTED MOVEMENT WHICH EVENTUALLY SNAPPED THE FORK.  INVESTIGATI	ON FOUND THAT THE LOCKNUT HAD WORKED LOOSE.					1	H	7	2 	3T				A2PC    		6	C	P15EA
1998100900772	19981009	00772	SO  	1998	10	9	AU981133         	1	19980904	G	5320	6345100	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  						SNSNCH	74DM	M74DM       	EA  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER BAR SUPPORT ASSEMBLY CRACKED FROM ALL FOUR MOUNT BOLT HOLES.   PART TC:  7,247.						1	L	7	1 	3O				2A13    		5	N	P88614
1998100900773	19981009	00773		1998	10	9	AU981134         	4	19980427	G	2565	7A144710	SLIDE           			BOEING	747   	747338      		NM  										PAX DOOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR L1 LEFT SIDE ESCAPE SLIDE SLOW TO DEPLOY DURING TEST.   SUBMITTER SUSPECTS CAUSED BY STICKING OF THE SLIDE RE	GULATOR PISTON.					2	L	7	2 	4F			RT	A20WE
1998100900774	19981009	00774	NE  	1998	10	9	AU981135         	2	19980903	G	7250	825601	TURBINE DISC    								PWA   	JT9   	JT9D7R4E    	52054	NE  					RT ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT ENGINE FIRST STAGE HIGH PRESSURE TURBINE BLADE TIPS CRACKED.  FURTHER INVESTIGATION FOUND A RADIAL CRACK ON 	THE FORWARD FACE OF THE FIRST STAGE DISC.  THE LENGTH OF THE CRACK WAS APPROXIMATELY 100 MM (4 INCHES) EXTENDING APPROXI	MATELY 50.8 MM (2 INCHES) RADIALLY IN EACH DIRECTION FROM A COOLING AIR HOLE.  THE MANUFACTURER HAS REVIEWED THE DATA ON	 THE CRACK AND HAS FOUND THAT THE MULTIPLE SMALL CRACKS ACCOMPANYING THE MAIN CRACK AT THE COOLING AIR HOLE SUPPORT THE 	THEORY THAT THE DAMAGE WAS CAUSED BY A MANUFACTURING ANOMALY KNOWN AS A `SEVERELY WORKED LAYER' OR `ABUSIVE MACHINING' O	F THE MATERIAL SURROUNDING THE HOLE.						4	F			E3NE
1998100900775	19981009	00775	NM  	1998	10	9	AU981136         	1	19980907	G	5350	65B1079110	FAIRING         			BOEING	747   	747SP38     		NM  										FUSELAGE	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 20 BULLNOSE FAIRING MISSING.  CAMBER LINK AND OTHER LINKS BROKEN AND ARM CRACKED.						2	L	7	4 	4F			RT	A20WE
1998100900776	19981009	00776	NM  	1998	10	9	AU981137         	1	19980906	G	3040	60B100285	WINDOW          			BOEING	747   	747SP38     		NM  										COCKPIT	OVERHEAT        	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) NR 1 COCKPIT WINDOW OVERHEATED.						2	L	7	4 	4F			RT	A20WE
1998100900777	19981009	00777	SO  	1998	10	9	AU981138         	1	19980813	G	3230		MOTOR           			PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	MLG	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR MOTOR COMMUTATOR SEGMENT HAD OPEN CIRCUIT.						1	L	7	2 	3O	3	O		A7SO    	1E10	5	C	P920
1998100900778	19981009	00778		1998	10	9	AU981139         	4	19980816	G	2312		CONTROLLER      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					VHF COMM	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 										(AUS) NR 2 VHF SYSTEM CONTROLLER FAULTY.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900779	19981009	00779	EA  	1998	10	9	AU981140         	2	19980812	G	7230		BLADE           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					COMPRESSOR	DAMAGED         	W				K				NONE                    				C			F.O.D.                    			CR	CRUISE         	1			AU	S 							PCE32212			(AUS) LEFT ENGINE FIRST STAGE COMPRESSOR BLADES (8 OFF) SUFFERED REPAIRABLE FOD DAMAGE.  THE FOD WAS THEN DEFLECTED BACK	 THROUGH THE INLET SCREEN.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998100900780	19981009	00780	SW  	1998	10	9	AU981141         	1	19980902	G	6520	206030446ODF	MOUNT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR GEARBOX MOUNT FORGING CRACKED IN AREA OF THE LEFT REAR STUD HOLE.  PART TC:  10,168.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998100900781	19981009	00781	EU  	1998	10	9	AU981142         	1	19980906	G	2910	TB2047000011	PIPE            			SOCATA	TB20  	TB20TRINIDAD	8680695	EU  	LYC   	O540  	IO540C4D5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 										(AUS) LANDING GEAR EMERGENCY VALVE FORWARD PIPE LEAKING FLUID FROM A PIN HOLE IN A CURVED SECTION OF THE PIPE.  LOSS OF 	HYDRAULIC FLUID.   PART TC:  3,439.					1	L	7	1 	3O	3	O	RT	A51EU   	1E4	5	C	P920
1999012100003	19990121	00003	EU  	1999	1	21	AU981143         	1	19980827	G	5510	TB2034021102	BEARING         			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILATOR RIGHT HINGE BEARING CRACKED FROM THE BORE HOLE TO THE BOTTOM FLANGE OF THE HINGE.  CRACK LENGTH 9 MM (0	.35 INCH).   PART TC:  6,109.					1	L	7	1 	3O	3	O	NT	A51EU   	E286	5	C	P920
1998100900782	19981009	00782	NM  	1998	10	9	AU981144         	1	19980828	G	5730	654548716	PANEL           			BOEING	737   	737476      		NM  										WING	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 FUEL TANK OUTBOARD BOOST PUMP ACCESS PANEL MISSING.   PART TC:  18,986.						2	L	7	2 	4F			RT	A16WE
1998100900783	19981009	00783	NE  	1998	10	9	AU981145         	3	19980906	G	6110		PROPELLER       			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14SF	14SF*       	NE  	LT PROP	OVERSPEED       	W				K				NONE                    				O			OTHER                     			DE	DESCENT        	1			AU	S 										(AUS) LEFT PROPELLER SUSPECT OVERSPEED BEYOND 112 PERCENT.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P7NE
1998100900784	19981009	00784	NM  	1998	10	9	AU981146         	1	19980903	G	4920		TURBINE         	GARRTT      	GTCP8512K   	BOEING	737   	737476      		NM  										APU	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1932 							(AUS) APU TURBINE FAILURE.   PART TC:  19,004.						2	L	7	2 	4F			RT	A16WE
1998100900785	19981009	00785	EU  	1998	10	9	AU981147         	2	19980831	G	7321	8063210	FCU             								CFMINT	CFM56 	CFM563C     	13802	EU  					NR 1 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					WYG65228					(AUS) NR 1 ENGINE FUEL CONTROL UNIT SUSPECT FAULTY.											4	F			E21EU
1998100900786	19981009	00786	EU  	1998	10	9	AU981148         	1	19980808	G	5743		SUPPORT         			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					LT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR SUPPORT STRUCTURE CORRODED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998100900787	19981009	00787	SO  	1998	10	9	AU981149         	1	19980831	G	3230	12038594001	CONTROL BOX     			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					MLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					120116					(AUS) LANDING GEAR CONTROL BOX SUSPECT FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998100900788	19981009	00788		1998	10	9	AU981150         	4	19980604	G	2565	B732560133	LANYARD         			BOEING	737   	73733A      	1384673	NM  										ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR L2 ESCAPE SLIDE COVER RELEASE CABLE FRAYED.  FOUND DURING INSPECTION IAW AD/B737/42.						2	L	7	2 	4F			RT	A16WE
1998100900789	19981009	00789		1998	10	9	AU981151         	4	19980721	G	2565	65C1990115	LANYARD         			BOEING	737   	737377      		NM  										ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ESCAPE SLIDE COVER RELEASE CABLES FRAYED AT BOTH AFT DOORS.  FOUND DURING INSPECTION IAW AD/B737/42.						2	L	7	2 	4F			RT	A16WE
1998100900790	19981009	00790	NM  	1998	10	9	AU981152         	1	19980811	G	5754		SLAT            			BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					WING	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 2 LEADING EDGE SLAT TRAILING EDGE WEDGE DELAMINATED IN FOUR AREAS.  FOUND DURING INSPECTION IAW AD/B767/73.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900791	19981009	00791	CE  	1998	10	9	AU981153         	1	19980907	G	2932	991028710	SWITCH          		99101881    	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	HYD PRESSURE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) HYDRAULIC PRESSURE SWITCH LEAKING FROM SWITCH BODY.  SUSPECT FAILURE OF INTERNAL DIAPHRAGM.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998100900792	19981009	00792	SW  	1998	10	9	AU981154         	1	19980908	G	2731	2719008002	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	ELEVATOR TAB	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 					293					(AUS) PITCH TRIM ACTUATOR FAULTY.   PART TC:  6,048.						2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998100900793	19981009	00793	CE  	1998	10	9	AU981155         	1	19980911	G	5730	042240136	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED IN THREE LOCATIONS BETWEEN THE FRONT AND REAR SPARS.   CRACKS ORIGINATE FROM THE RIVE	TS ATTACHING THE SKIN TO THE WING RIB AT STN 102.  MAXIMUM CRACK LENGTH 4 MM (0.157 INCHES).   PART TC:  7,047.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998100900794	19981009	00794	NM  	1998	10	9	AU981156         	1	19980901	G	2510		SPRING          		3A0900021010	BOEING	737   	737376      		NM  										COCKPIT SEAT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CAPTAIN'S SEAT LOCKING PAWL SPRING SEPARATED.   PART TC:  33,669.						2	L	7	2 	4F			RT	A16WE
1998100900795	19981009	00795	EU  	1998	10	9	AU981157         	1	19980614	G	3230	012	ACTUATOR        		200498005   	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					RT MLG	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 					012					(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK ACTUATOR LEAKING.  LOSS OF SYSTEM 1 HYDRAULIC FLUID. INVESTIGATION FOUND SPRING A	CTUATOR BACKUP RING P/N 130036365 DAMAGED.   PART TC:  55,277.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998100900796	19981009	00796	EU  	1998	10	9	AU981158         	1	19980614	G	2750	007	WASHER          		130507      	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					TE FLAP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					007					(AUS) FLAP DRIVE CENTER GEARBOX CONE CLUTCH POSITION WASHERS FAILED.   PART TC:  62,175.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998100900797	19981009	00797	SO  	1998	10	9	AU981159         	2	19980905	G	7322	IO4849	CARBURETOR      			CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			1700 		4022240		254714			(AUS) CARBURETOR CONTAMINATED WITH CORROSION PARTICLES.  DURING INVERTED FLIGHT, THE CORROSION IN THE CARBURETOR BOWL WA	S DISLODGED AND ENTERED THE CARBURETOR MAIN JET CAUSING A PARTIAL POWER LOSS.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P50GL
1998100900798	19981009	00798		1998	10	9	AU981160         	4	19980821	G	2565	B732560135	LANYARD         			BOEING	737   	737377      		NM  										ESCAPE SLIDE	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) L2 PASSENGER DOOR ESCAPE SLIDE COVER RELEASE CABLE FRAYED.  FOUND DURING INSPECTION IAW AD/B737/42.						2	L	7	2 	4F			RT	A16WE
1998100900799	19981009	00799	GL  	1998	10	9	AU981161         	3	19980902	G	6111		NUT             			PIPER 	PA34  	PA34200T    	7103406	SO  						HARTZL	HCC2Y	BHCC2YF2    	GL  	PROPELLER BLADE	STRIPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								AN2006		(AUS) PROPELLER PITCH CHANGE PISTON RETENTION NUT THREADS STRIPPED.  NUT WAS A NYLOCK TYPE NUT. THE CORRECT HARTZELL P/N	 B3807 NUT IS A METAL LOCK NUT.  SUBMITTER SUSPECTS UNAPPROVED PART.					1	L	7	2 	3O				A7SO    		5	C	P920
1998101700023	19981017	00023	EU  	1998	10	17	AU981162         	2	19980911	G	7250	0301527950	HARNESS         		MAKILA1A1   	SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2712 		2516		2516			(AUS) NR 1 ENGINE NTL HARNESS FAULTY.   PART TC:  6,171.						2	G	7	2 	4U	4	U		H4EU    	E12NE
1998100900800	19981009	00800	NE  	1998	10	9	AU981163         	1	19980904	G	7714	9580115910	SENSOR          			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					ENGINE RPM	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					3061		3061			(AUS) NR 1 ENGINE OVERSPEED SENSOR FAULTY.   PART TC:  900.						1	G	7	2 	3U	3	U		H1NE    	E19EU
1998100900801	19981009	00801	CE  	1998	10	9	AU981164         	1	19980911	G	7922	75944	VALVE           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE OIL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3963627			(AUS) ENGINE OIL COOLER THERMOSTATIC BYPASS VALVE NOT FITTED TO THE ENGINE WITH THE HOLE BLANKED OFF BY A PLUG.  FOUND D	URING INSPECTION IAW AD/LYC/78 AMDT 5.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998100900802	19981009	00802	EA  	1998	10	9	AU981165         	2	19980911	G	8520		CRANKSHAFT      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3963627			(AUS) CRANKSHAFT INTERNAL INSPECTION FOUND THAT THE CRANKSHAFT WAS CORRODED BEYOND LIMITS.  FOUND DURING INSPECTION IAW 	AD/LYC/102AMDT 1.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998100900803	19981009	00803	NM  	1998	10	9	AU981166         	1	19980910	G	3230	BACB10BW33	BEARING         			BOEING	737   	737376      		NM  										NLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR SYSTEM BEARINGS (2 OFF) SEIZED.						2	L	7	2 	4F			RT	A16WE
1998100900804	19981009	00804	SO  	1998	10	9	AU981167         	1	19980910	G	2820	412300	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				O	K		OTHER                     	FLUID LOSS                		IN	INSP/MAINT     	1			AU	S 										(AUS) TEFLON FUEL HOSE LOCATED IN THE LEFT WING ROOT LEAKING.  SUSPECT INTERNAL FAILURE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998100900805	19981009	00805	SO  	1998	10	9	AU981168         	1	19980914	G	5751	4019017	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT AILERON SPAR CRACKED BENEATH THE INBOARD ATTACHMENT BRACKET.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998100900806	19981009	00806	SO  	1998	10	9	AU981169         	1	19980914	G	5751	4019016	SPAR            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AILERON SPAR CRACKED BENEATH THE INBOARD ATTACHMENT BRACKET.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998100900807	19981009	00807	NM  	1998	10	9	AU981170         	1	19980812	G	2520	502755E2256	SEAT BELT       			BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					CABIN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER SEAT BELTS LOCATED AT 19D, 23E, 30C, 32E, 33E AND 34C AS WELL AS THE FIRST OFFICER'S SEAT BELT HAD MISSI	NG ID LABELS.  FOUND DURING INSPECTION IAW ER Z1-25-00-10J (AD/RES/29).					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900808	19981009	00808	CE  	1998	10	9	AU981171         	1	19980916	G	2140	762	COMBUSTOR       		8259JR2     	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	HEATER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			520  		762					(AUS) CABIN HEATER COMBUSTION CHAMBER CRACKED IN PREVIOUSLY WELD REPAIRED AREA.   PART TC:  660.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998100900809	19981009	00809	CE  	1998	10	9	AU981172         	1	19980816	G	5220	0221	WINDOW          			CESSNA	401   	401B        	207590E	CE  						MCAULY	3AF32C	3AF32C87    	GL  	EMERGENCY EXIT	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			AU	S 					0221					(AUS) EMERGENCY EXIT WINDOW SEPARATED FROM THE AIRCRAFT.  WINDOW HAD BEEN REMOVED AND RE-FITTED DURING AN EXTENDED 100-H	OUR INSPECTION THAT HAD TAKEN SEVERAL MONTHS.  AT SOME TIME BETWEEN THE FITTING OF THE WINDOW AND THE WINDOW SEPARATION,	 THE EMERGENCY EXIT HANDLE HAD BEEN ACTIVATED THEN RESTOWED.   PART TC:  2,258.				1	L	7	2 	3O				A7CE    		5	C	P22EA
1998100900810	19981009	00810	SO  	1998	10	9	AU981173         	1	19980915	G	3060	2061501	CONNECTOR       	BFGOODRICH  	4E11883     	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP DE-ICE	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) PROPELLER DE-ICE SYSTEM CONNECTORS E461 AND E462 DAMAGED.   PART TC:  4,543.						1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA
1998100900811	19981009	00811	SO  	1998	10	9	AU981174         	1	19980915	G	3060	2061512	CONNECTOR       	BFGOODRICH  	4E11883     	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP DE-ICE	BURNT           	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 										(AUS) PROPELLER DE-ICE SYSTEM CONNECTOR E461 AND E462 DAMAGED.  SEE ALSO MDR AU981173.   PART TC:  4,543.						1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA
1998100900812	19981009	00812	SO  	1998	10	9	AU981175         	2	19980708	G	8520	642720	BEARING         			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1618 		286559R		286559R			(AUS) MAIN CRANKSHAFT BEARING BROKEN.  CRANKCASE THROUGH BOLT P/N 641931-10-75 BROKEN.  ALL CYLINDER FLANGE NUTS LOOSE. 	 CRANKCASE MATING FACES FRETTED AND CRANKCASE CRACKED.  METAL CONTAMINATION OF OIL FILTER.   PART TC:  1,618.					1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998100900813	19981009	00813	EA  	1998	10	9	AU981176         	2	19980908	G	7314	476088	PUMP            	FACET       	574A        						LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRIC FUEL PUMP LEAKING FROM THE TOP END CAP.  PART TC:  99.											3	O			E286	5	C	P27EA
1998100900814	19981009	00814	CE  	1998	10	9	AU981177         	1	19980917	G	5730	042240136	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) UPPER LEFT WING SKIN CRACKED IN TWO AREAS BETWEEN THE FRONT AND REAR SPARS.  UPPER RIGHT WING SKIN CRACKED IN TWO 	AREAS STARTING FROM THE RIVETS ATTACHING THE SKIN TO THE WING RIB AT WS 102.  MAXIMUM CRACK LENGTH 3 MM (0.118 INCH).  P	ART TC:  9,847.				1	H	7	1 	3O				3A19    		5	N	P50GL
1998100900815	19981009	00815	SO  	1998	10	9	AU981178         	1	19980908	G	2750	62820000	SPRING          			PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	TE FLAP	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					327740092					(AUS) FLAP SPRING BROKEN.  SUBMITTER SUSPECTED UNAPPROVED PART.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1998100900816	19981009	00816	EA  	1998	10	9	AU981179         	2	19980825	G	7314	LW15472	PUMP            			CESSNA	182   	R182        	2072734	CE  	LYC   	O540  	O540J3C5    	41532	EA  	MCAULY	3D32C	B3D32C407   	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L2329540A	815242		(AUS) ENGINE DRIVEN FUEL PUMP LEAKING.  INVESTIGATION FOUND THAT THE DIAPHRAGM PLATE TO PUMP BODY ATTACHMENT SCREWS WERE	 LOOSE.   PART TC:  1,835.					1	H	7	1 	3O	3	O	RT	3A13    	E295	5	C	EXPP5C
1998100900817	19981009	00817	CE  	1998	10	9	AU981180         	1	19980918	G	5730	042240127RH	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING UPPER SKIN CRACKED IN TWO PLACES FROM SKIN TO RIB ATTACHMENT RIVETS:  ONE CRACK AT STN 102.0.  ONE CRAC	K AT STN 84.0.  MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCH).   PART TC:  15,720.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998100900818	19981009	00818	CE  	1998	10	9	AU981181         	1	19980918	G	5730	042240136LH	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED IN THREE PLACES FROM SKIN TO RIB ATTACHMENT RIVETS:  TWO CRACKS AT STN 102.0 .  ONE C	RACK AT STN 84.0.  MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCH).  PART TC:  15,720.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998100900819	19981009	00819	CE  	1998	10	9	AU981182         	1	19980602	G	5341	07116066LH	FITTING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U20604939					(AUS) FUSELAGE TO LEFT WING REAR ATTACHMENT FITTING CONTAINED INTERGRANNULAR CORROSION BETWEEN THE FITTING AND THE CARRY	-THROUGH SPAR.   PART TC:  11,194.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
1998100900820	19981009	00820	CE  	1998	10	9	AU981183         	1	19980602	G	5341	07116069RH	FITTING         			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					U20604939					(AUS) FUSELAGE TO RIGHT WING REAR ATTACHMENT FITTING CONTAINED INTERGRANNULAR CORROSION BETWEEN THE FITTING AND THE CARR	Y-THROUGH SPAR.   PART TC:  11,194.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
1998100900821	19981009	00821	CE  	1998	10	9	AU981184         	1	19980916	G	3260	1SE13	SWITCH          			CESSNA	402   	402B        	207590P	CE  						MCAULY	3AF32C	3AF32C87    	GL  	RT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR DOWNLOCK MICROSWITCH FAULTY.						1	L	7	2 	3O				A7CE    		5	C	P22EA
1998100900822	19981009	00822	SO  	1998	10	9	AU981185         	1	19980902	G	3260	487933	SWITCH          			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	RT MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					317405447					(AUS) RIGHT MAIN LANDING GEAR DOOR SWITCH FAULTY.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998100900823	19981009	00823	NM  	1998	10	9	AU981186         	1	19980915	G	5620	65457912	WINDOW          			BOEING	737   	737476      		NM  										CABIN	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PASSENGER WINDOW LOCATED AT ROW 8A HAD TWO ATTACHMENT CLIPS AND SCREWS MISSING.   PART TC:  3,320.						2	L	7	2 	4F			RT	A16WE
1998100900824	19981009	00824	EU  	1998	10	9	AU981187         	1	19980623	G	2823	6871007	VALVE           			PARTEN	P68   	P68B        		EU  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	LT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1306251A			(AUS) LEFT ENGINE FUEL SELECTOR VALVE WOULD NOT COMPLETELY OPEN.   PART TC:  7,649.						1	H	7	2 	3O	3	O		A31EU   	1E10	5	C	P920
1998100900825	19981009	00825	NM  	1998	10	9	AU981188         	1	19980918	G	5512	CAP033	SKIN            	DHAV        	85510001001 	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HORIZ STAB	DISBONDED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1586 		CAP033					(AUS) HORIZONTAL STABILIZER SKIN DISBONDED.   PART TC:  26,068.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998100900826	19981009	00826	CE  	1998	10	9	AU981189         	1	19980921	G	7120	57510061	TRUSS           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN3     	GL  	ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT HORIZONTAL TUBE CRACKED AT UPPER LEFT ATTACHMENT POINT.  CRACKING CONFIRMED USING DYE PENETRANT AND M	AGNETIC PARTICLE INSPECTION.   CRACK LENGTH APPROXIMATELY 9.525 MM (0.375 INCH).   PART TC:  8,052.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
1998100900827	19981009	00827	CE  	1998	10	9	AU981190         	1	19980921	G	5730	042240127	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED FROM THE RIVETS ATTACHING THE SKIN TO THE RIBS AT THE FOLLOWING LOCATIONS:  TWO CRACK	S LOCATED AT STN 102.02.  ONE CRACK LOCATED AT STN 84.0.  MAXIMUM LENGTH OF CRACKS 4 MM (0.157 INCH).    14,010.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998100900828	19981009	00828	CE  	1998	10	9	AU981191         	1	19980921	G	5730	042240136	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT UPPER WING SKIN CRACKED FROM THE RIVETS ATTACHING THE SKIN TO THE RIBS AT THE FOLLOWING LOCATION:  THREE CRA	CKS LOCATED AT STN 102.0.  MAXIMUM CRACK LENGTH 4 MM (0.157 INCH).   PART TC:  14,010.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998100900829	19981009	00829	SO  	1998	10	9	AU981192         	1	19980909	G	3220	5079150811	SPRING          			AYRES 	S2    	S2RG10      		SO  	GARRTT	TPE331	TPE33110    	01514	WP  	HARTZL	HCB4T	HCB4TN5     	GL  	TAIL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							P36412	CDA3616		(AUS) AIRCRAFT TAILSPRING CRACKED AND BROKEN.  AIRCRAFT HAD BEEN PARKED OVERNIGHT WITH A FULL HOPPER.   PART TC: 1,775.						1	L	7	1 	3T	4	T	NC	A4SW    	E4WE	6	C	P40EA
1998100900830	19981009	00830	SW  	1998	10	9	AU981193         	1	19980914	G	2731	2719008002	ACTUATOR        			FRCHLD	SA227 	SA227DC     	3377521	SW  										ELEVATOR TAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					193					(AUS) PITCH TRIM ACTUATOR LEFT OUTPUT SHAFT END FLOAT APPROXIMATELY 1.587 MM (0.0625 INCH).  FOUND DURING INSPECTION IAW	 AD/SWSA226/68 (SL 021).   PART TC:  4,377.					2	L	7	2 	4T			RT	A18SW
1998100900831	19981009	00831	EA  	1998	10	9	AU981194         	2	19980921	G	7414	M3548	ROTOR           	SLICK       	4370        	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	MAGNETO	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					94060483		L917239A			(AUS) MAGNETO ROTOR BROKEN INTO TWO PIECES.   PART TC:  1,900.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
1998100900832	19981009	00832	SW  	1998	10	9	AU981195         	1	19980901	G	3213	AN17420	BOLT            	ELECTROL    	400139      	GULSTM	500   	500S        	0141107	SW  	LYC   	O540  	IO540E1B5   	41532	EA  	HARTZL	HCA3V	HCA3VK2     	GL  	MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) MAIN LANDING GEAR SCISSORS BOLT FAILED.  PART TC:  16.   PART TC:  16.						1	H	7	2 	3O	3	O		6A1     	1E4	5	C	P6EA
1998100900833	19981009	00833	SO  	1998	10	9	AU981196         	1	19980918	G	3211	77388003	FITTING         			PIPER 	PA38  	PA38112     	7103812	SO  						SNSNCH	72C	72CK        	EA  	LT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								K4722		(AUS) LEFT MAIN LANDING GEAR INBOARD ATTACHMENT FITTING SEVERELY CORRODED ALLOWING THE LEFT MLG INBOARD ATTACHMENT BOLT 	TO PULL OUT OF THE WING.  RIGHT MLG FITTING CORRODED TO A LESSER DEGREE.   PART TC:  8,079.					1	L	7	1 	3O				A18SO   		5	N	P9045
1998100900834	19981009	00834	CE  	1998	10	9	AU981197         	1	19980701	G	5720	082255022	FITTING         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING SPAR FITTING CRACKED AND CORRODED.   PART TC:  12,500.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998100900835	19981009	00835	CE  	1998	10	9	AU981198         	1	19980701	G	5720	082255024	FITTING         			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING SPAR FITTING CRACKED AND CORRODED.   PART TC:  12,500.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998100900836	19981009	00836	CE  	1998	10	9	AU981199         	1	19980901	G	3231	NAS464P4A10	BOLT            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR RETRACTION LINKAGE BOLT SHEARED.  BOLT WAS FOUND TO BE CRACKED AROUND THE THREAD.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998100900837	19981009	00837	EA  	1998	10	9	AU981200         	2	19980916	G	8520	CW11853	CRANKSHAFT      			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L4557427A		L4557427A			(AUS) CRANKSHAFT FAILED TO MEET DIMENSIONAL LIMITS FOLLOWING REWORK IAW AD/LYC/102 AMDT 1 (LYC SB 05) (HAWKER PACIFIC EN	GINEERING ORDER ENG 1627/2).					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
1998100900838	19981009	00838	SO  	1998	10	9	AU981201         	2	19980728	G	8520	649898	CRANKSHAFT      			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					227475R		227475R			(AUS) CRANKSHAFT FRONT MAIN BEARING JOURNAL SHOWED EVIDENCE OF ARCING FOLLOWING BULK STRIP FOR LIGHTNING STRIKE INSPECTI	ON.					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998100900839	19981009	00839	SO  	1998	10	9	AU981202         	2	19980922	G	8530	640941	ROCKER ARM      			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			917  				234315R			(AUS) NR 4 CYLINDER EXHAUST VALVE ROCKER ARM BROKEN AT THE BALL SOCKET.						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL
1998100900840	19981009	00840	EA  	1998	10	9	AU981203         	2	19980907	G	7322	233614	NEEDLE          	FACET       	MA6         	PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	CARBURETOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			840  		CH172618		L29577T			(AUS) CARBURETOR FLOAT NEEDLE AND SEAT WORN.  CARBURETOR FLOODING CAUSED A POST SHUTDOWN ENGINE FIRE.   PART TC:  4,105.						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920
1998100900841	19981009	00841	CE  	1998	10	9	AU981204         	1	19980918	G	7997		WIRE            			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE OIL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ENGINE OIL PRESSURE LIGHT SIGNAL WIRE E120A20 INSULATION WORN THROUGH IN AN AREA LOCATED UNDER THE FLOOR BELO	W THE PILOT'S SEAT.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
1998100900842	19981009	00842	EU  	1998	10	9	AU981205         	1	19980921	G	2760		WARNING SYSTEM  			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					SPOILER	ACTIVATED       	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) MANUAL SPOILER FAULT LIGHT ILLUMINATED.  SYSTEM CHECKED, BUT NO REASON FOR THE FAULT COULD BE FOUND.  DEFECT HAS N	OT OCCURRED SINCE.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998100900843	19981009	00843	NM  	1998	10	9	AU981206         	1	19980918	G	5512	85510001001	SKIN            		STABILIZER  	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HORIZ STAB	DEBONDED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					027					(AUS) RIGHT HORIZONTAL STABILIZER LOWER SKIN DEBONDING.   PART TC:  27,742.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998100900844	19981009	00844	SW  	1998	10	9	AU981207         	1	19980622	G	2910	2781006069	PIPE            			SWRNGN	SA226 	SA226TC     	8780404	SW  						HARTZL	HCB3T	HCB3TN5     	GL  	HYDRAULIC SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			TO	TAKEOFF        	1			AU	S 										(AUS) HYDRAULIC PIPE FAILED.  SUBMITTER STATED LIMITED INFORMATION PROVIDED.   PART TC:  7,863.						2	L	7	2 	4T			RT	A8SW    		6	C	P15EA
1998100900845	19981009	00845	NM  	1998	10	9	AU981208         	1	19980720	G	5410		FITTING         			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					RT NACELLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT PYLON CONTAINED EXFOLIATION CORROSION ON THE UPPER SURFACES OF THE UPPER WEB OF THE TORQUE BOX ADJACENT TO T	HE UPPER LINK ATTACHMENT BEAM EITHER SIDE OF AND RUNNING UNDER THE FORWARD UPPER STRUT FITTING.  CORROSION HAD PENETRATE	D THROUGH THE WEB WITH CRACKING RUNNING THROUGH THE RIVET LINE.  AREA OF CORROSION 100 MM BY 63.5 MM (4 INCHES BY 2.5 IN	CHES) AND 63.5 MM BY 19.05MM (2.5 INCHES BY 0.75 INCH).			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900846	19981009	00846	NM  	1998	10	9	AU981209         	1	19980720	G	5410		FITTING         			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					LT NACELLE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT PYLON CONTAINED EXFOLIATION CORROSION ON THE UPPER SURFACES OF THE UPPER WEB OF THE TORQUE BOX ADJACENT TO TH	E UPPER LINK ATTACHMENT BEAM OUTBOARD OF AND RUNNING UNDER THE STRUT FITTING.  CORROSION HAD PENETRATED TO A DEPTH OF 1.	778 MM (0.070 INCH) WITH CRACKING ALONG THE RIVET LINE.  AREA OF CORROSION 88.9 MM BY 63.5 MM (3.5 INCHES BY 2.5 INCHES)	.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900847	19981009	00847	NM  	1998	10	9	AU981210         	1	19980728	G	5744	113T13571	FITTING         			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					WS 906	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING DEFLECTION CONTROL SUPPORT FITTING LOWER ATTACHMENT LUG FRACTURED THROUGH THE BEARING HOUSING.  FITTING 	IS LOCATED AT WS 906.20.   PART TC:  41,421.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998100900848	19981009	00848	EU  	1998	10	9	AU981211         	1	19980507	G	5610	NP1701022	WINDSHIELD      			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			CL	CLIMB          	1			AU	S 					NP1701022					(AUS) FIRST OFFICER'S `B' WINDSHIELD EXTERNAL PANE SHATTERED.  SUBMITTED SUSPECTS CAUSED BY MOISTURE INGRESS INTO CONDUC	TIVE LAYER CAUSING ARCING AND CRACKING.   PART TC:13,956.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998100900849	19981009	00849	EU  	1998	10	9	AU981212         	1	19980806	G	3230	C23005303C	DAMPER          			AIRBUS	300   	A300B4203   	3930306	EU  	GE    	CF6   	CF650C2     	30018	NE  					RT MLG	LEAKING         	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR PITCH DAMPER LEAKING PREVENTING THE BOGIE FROM OBTAINING THE CORRECT ANGLE FOR RETRACTION.	   PART TC:  12,130.					2	L	7	2 	4F	4	F		A35EU   	E23EA
1998100900850	19981009	00850	NE  	1998	10	9	AU981213         	1	19980320	G	5711	21610401	SPAR            			CONAER	LA4   	LA4250      	5110320	NE  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	LT WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L2435848A	FM728		(AUS) SUBMITTER STATED INCORRECT STEEL WASHERS (CORRECT TYPE ALUMINIUM) USED UNDER THE LEFT WING ATTACHMENT NUTS CAUSED 	CORROSION OF THE WING SPAR.  AIRCRAFT IS AN AMPHIBIAN AND OPERATES IN A SALT LADEN ENVIRONMENT.  1,301.					1	H	7	1 	3O	3	O		1A13    	1E4	5	C	P33EA
1998111300278	19981113	00278	EA  	1998	11	13	AU981214         	1	19980921	G	2450	MS3120E2039	CONNECTOR       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AC SYSTEM	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			NR	NOT REPORTED   	1			AU	S 										(AUS) ELECTRICAL CONNECTOR J31/P31 LOCATED IN OVERHEAD PANEL MELTED.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
1998111300279	19981113	00279	EA  	1998	11	13	AU981215         	1	19980921	G	2450	MS3126E2039P	CONNECTOR       			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AC SYSTEM	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			AU	S 										(AUS) ELECTRICAL CONNECTOR J31/P31 LOCATED IN OVERHEAD PANEL MELTED.  SEE MDR 98/1214 FOR ADDITIONAL INFORMATION.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
1998111300280	19981113	00280	NM  	1998	11	13	AU981216         	1	19980917	G	5522	65C2578331	PANEL           			BOEING	737   	737476      		NM  										ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT ELEVATOR NOSE HINGE INBOARD BALANCE PANEL HAD THREE BOLTS MISSING AND ANOTHER THREE BOLTS LOOSE.						2	L	7	2 	4F			RT	A16WE
1998111300281	19981113	00281	NE  	1998	11	13	AU981217         	2	19980924	G	7261		ENGINE          			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					RT NACELLE	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							120014			(AUS) RIGHT ENGINE OIL QUANTITY LOW. TWO QUARTS OF OIL ADDED.  SUBMITTER SUSPECTED CAUSE AS MISREADING OF THE OIL SIGHT 	GAUGE.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998111300282	19981113	00282		1998	11	13	AU981218         	4	19980918	G	3441	HG1050AD04	IRU             			BOEING	737   	737376      		NM  										E/E BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 					201501					(AUS) RIGHT INERTIAL REFERENCE UNIT FAULTY.						2	L	7	2 	4F			RT	A16WE
1998111300283	19981113	00283	SO  	1998	11	13	AU981219         	1	19980918	G	5753	6232800	RIB             		6232801     	PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP RIB CORRODED IN AREA OF STEEL HINGE BRACKET ATTACHMENT.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
1998111300284	19981113	00284	CE  	1998	11	13	AU981220         	1	19980627	G	3260	1003810761	SWITCH          			BEECH 	76    	76          	1153005	CE  										NLG	INTERMITTENT    	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) NLG DOWN LIGHT MICROSWITCH INTERMITTENT.  PART TC:  5,463.						1	L	7	2 	3O				A29CE
1998111300285	19981113	00285	SO  	1998	11	13	AU981221         	2	19980922	G	8530	639272	CYLINDER        			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520BA     	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			503  				232639			(AUS) ENGINE CYLINDER CRACKED FROM EXHAUST VALVE PORT TO BOTH SPARK PLUG HOLES.  CYLINDER WAS A CHROME TYPE.						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA
1998111300286	19981113	00286	NM  	1998	11	13	AU981222         	1	19980831	G	5754		SLAT            			BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					LE FLAP	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 AND NR 3 LEADING EDGE SLAT TRAILING EDGES DELAMINATING.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998111300287	19981113	00287		1998	11	13	AU981223         	4	19980817	G	2565	60070102	SLIDE           	AIRCRUISERS 	D31865104   	AIRBUS	320   	A320212     		EU  										RT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			9072 		449006011					(AUS) RIGHT OFF-WING ESCAPE SLIDE LEAKING.  DURING INVESTIGATION OF THE LEAK, A PART OF THE SEAM APPROXIMATELY 152.4 MM 	(6 INCHES) IN LENGTH OPENED UP.  PART TC:  24,484.					2	L	7	2 	4F			RT	A28NM
1998111300288	19981113	00288		1998	11	13	AU981224         	4	19980817	G	2565	60070101	SLIDE           			AIRBUS	320   	A320212     		EU  										LT WING	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			9491 		C0081					(AUS) LEFT OFF-WING SLIDE RAMP LEAKING.  DURING INSPECTION ONE SEAM ON THE UPPER INBOARD RAIL TUBE OPENED UP FOR APPROXI	MATELY 406.4 MM (16 INCHES).  PART TC:  25,709.					2	L	7	2 	4F			RT	A28NM
1998111300289	19981113	00289	EU  	1998	11	13	AU981225         	1	19980518	G	2410	712196	GEAR            		728471B     	BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					GENERATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					0592					(AUS) NR 1 GENERATOR CONSTANT SPEED DRIVE (CSD) CLUSTER GEAR FAILED.  THE GENERATOR WAS THEN DRIVEN DIRECTLY FROM THE AC	CESSORY GEARBOX PRODUCING AN OVER-FREQUENCY OUTPUT.  A FAULTY OVER-FREQUENCY CARD IN THE GENERATOR CONTROL UNIT (GCU) CA	USED THE GENERATOR TO REMAIN ON-LINE CAUSING MAJOR COMPONENT FAILURES DUE TO THE OVER-FREQUENCY CONDITION.				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998111300290	19981113	00290		1998	11	13	AU981226         	1	19980922	G	7312	3036064	FUEL HEATER     								PWA   	PWA120	PW125B      		NE  					RT ENGINE	LEAKING         	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 			3692 		277		124027			(AUS) RIGHT ENGINE FUEL/OIL HEATER LEAKING INTERNALLY.  PART TC:  15,602.											4	T			E20NE
1998111300291	19981113	00291	NE  	1998	11	13	AU981227         	2	19980919	G	7200		ENGINE          								LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 NACELLE	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 							LFO5586A			(AUS) NR 4 ENGINE FAILED.   AT POWER APPLICATION FOR TAKEOFF, THE ENGINE EMITTED A LOUD BANG AND STARTED TO RUN DOWN.  T	GT INCREASED TO APPROXIMATELY 1,150 DEGREES.										4	F			E6NE
1998111800004	19981118	00004	NE  	1998	11	18	AU981229         	2	19980916	G	7261		ENGINE          			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 1 NACELLE	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							LFO5092			(AUS) NR 1 ENGINE OIL LOSS.  SUBMITTER STATED LIMITED INFORMATION PROVIDED.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998111300292	19981113	00292	SW  	1998	11	13	AU981230         	1	19980920	G	6520	212040004009	GEARBOX         		212040004009	BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					TAIL ROTOR	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AHT026		162519262180			(AUS) TAIL ROTOR GEARBOX OIL DIRTY.  OIL CHANGED BUT AGAIN BECAME DIRTY.  GEARBOX CHANGED.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998111300293	19981113	00293	CE  	1998	11	13	AU981231         	1	19980924	G	3610	130936P4MC2050	BLEED AIR DUCT  			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT WING	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			TO	TAKEOFF        	1			AU	S 										(AUS) BLEED AIR DUCT LOCATED IN LEFT WING LEADING EDGE FAILED AT JOIN.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998111300294	19981113	00294	CE  	1998	11	13	AU981232         	1	19980728	G	2436	IOI3642705	REGULATOR       	LEARSIEGLER 	51530007B   	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					DC SYSTEM	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 			9    		12154A					(AUS) LKH VOLTAGE REGULATOR FAULTY.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998111300295	19981113	00295	CE  	1998	11	13	AU981233         	1	19980727	G	2436	IOI3642705	REGULATOR       	LEARSIEGLER 	51530007B   	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					DC SYSTEM	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			AU	S 			2489 		12470A					(AUS) LEFT VOLTAGE REGULATOR FAILED.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998111300296	19981113	00296	SW  	1998	11	13	AU981234         	1	19980928	G	5720		WEB             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING CENTER SPAR WEB CRACKED.  PART TC:  26,549.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998111300297	19981113	00297	SO  	1998	11	13	AU981235         	1	19980930	G	2820	4123006	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	LT WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL HOSE LOCATED IN THE AREA OF THE LEFT WING ROOT LEAKING THROUGH THE OUTER WIRE BRAIDING.  HOSE IS AN AEROQUIP 	601 TYPE HOSE.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998111300298	19981113	00298	SW  	1998	11	13	AU981236         	1	19980929	G	2910	2781006635	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SYSTEM HYDRAULIC PIPE CHAFING ON MARMON CLAMP.  PIPE IS LOCATED FORWARD OF THE MAIN SPAR INBOARD OF THE WING/	FUSELAGE JOIN ADJACENT TO AIR CONDITIONING DUCTS.  PART TC:  8,860.					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998111300299	19981113	00299	CE  	1998	11	13	AU981237         	1	19980921	G	7120	57510061	TRUSS           			CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE3318     	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE MOUNT DIAGONAL TUBE CRACKED AT LEFT UPPER ATTACHMENT POINT.  CRACK CONFIRMED USING DYE PENETRANT AND MAGNET	IC PARTICLE INSPECTION.  CRACK LENGTH 9.525 MM (0.375 INCHES).					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE	6	C	P15EA
1998111300300	19981113	00300	SW  	1998	11	13	AU981238         	1	19980923	G	2910	2781006627	PIPE            			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SYSTEM HYDRAULIC PIPE WORN THROUGH AND LEAKING DUE TO RUBBING ON AN AIR CONDITIONING DUCT MARMON CLAMP.  PIPE	 IS LOCATED IN THE WING ROOT AREA.  PART TC:  10,846					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998111300301	19981113	00301	EU  	1998	11	13	AU981239         	1	19980903	G	5542		SKIN            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					RUDDER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TRAILING EDGE DELAMINATED. THE DELAMINATION STARTED APPROXIMATELY 145 MM (5.7 INCHES) UP FROM THE BOTTOM AN	D EXTENDED UP FOR A FURTHER 710 MM (27.9 INCHES). THE WIDTH OF THE DELAMINATION WAS APPROXIMATELY 135 MM (5.3 INCHES).					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998111300302	19981113	00302	SO  	1998	11	13	AU981240         	1	19980917	G	2752	3203001007	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP	FAULTY          	W				K				NONE                    				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 					0919					(AUS) RIGHT OUTBOARD FLAP ACTUATOR FAULTY.  INVESTIGATION FOUND A BREAKDOWN IN INSULATION RESISTANCE.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998111300303	19981113	00303	WP  	1998	11	13	AU981241         	1	19980927	G	6210	369A10045	PIN             			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR BLADE RETAINING PIN BROKEN.  PART TC:  4,180.						1	G	7	1 	3U	3	U		H3WE    	E4CE
1998111300304	19981113	00304	CE  	1998	11	13	AU981242         	1	19980925	G	3230	5741110204	PIN             			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3AF34C	3AF34C74    	GL  	RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR PIN CRACKED.						1	L	7	2 	3O				A25CE   		5	C	P22EA
1998111300305	19981113	00305	NM  	1998	11	13	AU981243         	1	19980918	G	5210	65458001215	SKIN            			BOEING	737   	737476      		NM  										PASSENGER DOOR	DAMAGED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR 1L SKIN PANEL HOLED DUE TO INTERFERENCE WITH THE FUSELAGE TORQUE TUBE CENTER ASSIST SPRING BOLT.  SIZE OF HOL	E 6.35 MM BY 12.7 MM (0.25 INCH BY 0.5 INCH) .  CENTER ASSIST SPRING BOLT HAD BEEN INCORRECTLY INSTALLED.					2	L	7	2 	4F			RT	A16WE
1998111300306	19981113	00306	NE  	1998	11	13	AU981244         	1	19980924	G	3246	5007681	WHEEL           		5007554     	SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			404  		JUN920609					(AUS) RIGHT MAIN WHEEL FLANGE SEPARATED FROM THE HUB.  SIZE OF SEPARATED FLANGE APPROXIMATELY 165.1 MM BY 38.1 MM (6.5 I	NCHES BY 1.5 INCH).  PART TC:  2,287.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
1998111300307	19981113	00307	SO  	1998	11	13	AU981245         	1	19980930	G	3260	67411002	SWITCH          			PIPER 	PA28  	PA28RT201   	7102818	SO  	LYC   	O360  	IO360C1C6   	41514	EA  	MCAULY	2D34C	2D34C215    	GL  	LT MLG	INOPERATIVE     	W				K				NONE                    				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOWNLOCK MICROSWITCH INOPERATIVE.  PART TC:  5,864.						1	L	7	1 	3O	3	O		2A13    	1E10	5	C	P7EA
1998111300308	19981113	00308	SW  	1998	11	13	AU981246         	1	19980924	G	5531	44222	RIB             			GULSTM	112   	112         	0144701	SW  	LYC   	O360  	IO360C1D6   	41514	EA  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER RIB CRACKED IN FOUR PLACES.  ONE OF THE CRACKS WAS IN A PREVIOUS REPAIR.  PART TC:  2,294.						1	L	7	1 	3O	3	O		A12SO   	1E10
1998111300309	19981113	00309	SW  	1998	11	13	AU981247         	1	19980924	G	5541	443191	RIB             			GULSTM	112   	112         	0144701	SW  	LYC   	O360  	IO360C1D6   	41514	EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER TOP RIB CRACKED IN TWO PLACES EITHER SIDE OF THE BALANCE WEIGHT ATTACHMENT BOLT.  PART TC:  2,294.						1	L	7	1 	3O	3	O		A12SO   	1E10
1998111300310	19981113	00310	CE  	1998	11	13	AU981248         	1	19980610	G	2810	6012	INSERT          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF34C	3AF34C502   	GL  	FUEL CELL	DISINTEGRATED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANK FOAM INSERT MATERIAL DETERIORATED AND BLOCKING FUEL FILTER AND FUEL DRAINS.  INSERT IS POST-MODIFICATION	 SB 2109 (AD/BEECH55/68).					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998111300311	19981113	00311	CE  	1998	11	13	AU981249         	1	19981001	G	2750	S16612	SWITCH          			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	TE FLAP	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP POSITION SWITCH FAULTY.  SWITCH WOULD NOT RETURN TO THE NEUTRAL POSITION.  PART TC:  6,825.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998111300312	19981113	00312	EU  	1998	11	13	AU981250         	1	19980714	G	5730		FASTENER        			AIRBUS	320   	A320212     		EU  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER WING SKIN CONTAINED TWO CRACKED FASTENER HEADS IN THE LEFT HAND WING GEAR SUPPORT AREA.  SUSPECT CAUSED BY O	VERTORQUING OF THE FASTENER HEADS DURING MANUFACTURE.					2	L	7	2 	4F			RT	A28NM
1998111300313	19981113	00313	NM  	1998	11	13	AU981251         	1	19980211	G	2612	894481	FIRE DETECTOR   			BOEING	737   	73733A      	1384673	NM  										APU BAY	MALFUNCTIONED   	W				K				NONE                    				N			FALSE WARNING             			CL	CLIMB          	1			AU	S 										(AUS) APU FIRE DETECTOR LOW INSULATION RESISTANCE.						2	L	7	2 	4F			RT	A16WE
1998111300314	19981113	00314	NM  	1998	11	13	AU981252         	1	19980112	G	2460	6130200502	HARNESS         			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					DC SYSTEM	DAMAGED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			AU	S 										(AUS) GENERATOR FEEDER CABLE W200 AND WIRING LOOM W1142 BURNT DUE TO ARCING AT THE PLUG AND SOCKET.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
1998111300315	19981113	00315	NM  	1998	11	13	AU981253         	1	19980112	G	2460	6131142501	HARNESS         			BOEING	737   	73733A      	1384673	NM  	GE    	CFM56 	CFM563B1    	13802	NE  					DC SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GENERATOR FEEDER CABLE W200 AND PYLON WIRING LOOM W1142 DAMAGED DUE TO ARCING OF THE CONNECTOR.						2	L	7	2 	4F	4	F	RT	A16WE   	E2GL
1998111300316	19981113	00316	EU  	1998	11	13	AU981254         	1	19980518	G	2410	TE0845	GEAR            		700122400420	BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR1 GENERATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 					TE0845					(AUS) NR 1 CONSTANT SPEED DRIVE CLUSTER GEAR FAILED.  NR 1 GENERATOR WAS THEN DRIVEN DIRECTLY FROM THE ACCESSORY GEARBOX	 PRODUCING AN OVER-FREQUENCY CONDITION.  THIS CONDITION WOULD NORMALLY BE SENSED BY THE GCU P/N 700-1-22400-420, BUT DUE	 TO A FAULT OVER-FREQUENCY CARD IN THE GCU, MAJOR COMPONENT FAILURES OCCURRED DUE TO THE OVER-FREQUENCY.  PART TC:  15,8	42.			2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998111300317	19981113	00317	EU  	1998	11	13	AU981255         	1	19980608	G	2130	2380515509	LINE            			AIRBUS	320   	A320212     		EU  										CABIN PRESSURE	FRACTURED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) BLEED SENSE LINE LOCATED BETWEEN THE HIGH PRESSURE VALVE AND THE PRESSURE REGULATING VALVE HAD FRACTURED AT THE FI	TTING ON THE DUCT ADJACENT TO THE HP BLEED VALVE.					2	L	7	2 	4F			RT	A28NM
1998111300318	19981113	00318	NM  	1998	11	13	AU981256         	1	19980712	G	2782	69734961	ACTUATOR        			BOEING	737   	737377      		NM  										LE FLAP	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 			4122 		4925					(AUS) RIGHT KRUEGER FLAP ACTUATOR LEAKING DUE TO EXCESS SEALANT ON THE SEAL PLATE BETWEEN THE ACTUATOR VALVE AND THE BLO	CKING VALVE.  LOSS OF HYDRAULIC FLUID.  PART TC:  23,138.					2	L	7	2 	4F			RT	A16WE
1998111300319	19981113	00319	NM  	1998	11	13	AU981257         	1	19980901	G	2620	10619093	NOZZLE          			BOEING	747   	747438      		NM  										EXTINGUISHER	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TOILET WASTE BIN FIRE EXTINGUISHER NOZZLES BENT AND NOT PROTRUDING INTO THE WASTE BIN AREA.						2	L	7	4 	4F			RT	A20WE
1998111800005	19981118	00005	NM  	1998	11	18	AU981258         	1	19980922	G	5330		SKIN            			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL WELL CUT-OUT CRACKED IN THE LOWER FORWARD CORNERS.						2	L	7	4 	4F				A20WE
1998111800006	19981118	00006	NM  	1998	11	18	AU981259         	1	19980922	G	5330		SKIN            			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL WELL CUT-OUT CRACKED IN THE LOWER FORWARD CORNERS.						2	L	7	4 	4F				A20WE
1998111800007	19981118	00007	NM  	1998	11	18	AU981260         	1	19980922	G	5330		SKIN            			BOEING	747   	747238B     	1384828	NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR WHEEL WELL CUT-OUT CRACKED IN THE FORWARD LOWER CORNERS.						2	L	7	4 	4F				A20WE
1998111300320	19981113	00320	NE  	1998	11	13	AU981261         	2	19980903	G	7250	9234M90G17	NOZZLE          								GE    	CF6   	CF680A      	30025	NE  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8082 				580242			(AUS) ENGINE HIGH PRESSURE TURBINE STAGE TWO NOZZLE SEGMENTS (2OFF) SEVERELY CRACKED.											4	F			E13NE
1998111300321	19981113	00321	CE  	1998	11	13	AU981262         	1	19981001	G	5711	572216531	CAP             			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR SPAR CAP CONTAINED DELAMINATION IN THE AREA OF THE RIGHT WHEEL WELL.  MINOR CORROSION OF THE SPAR CAP LOCATED	 IN THE LEFT WHEEL WELL.  PART TC:  11,423.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300322	19981113	00322	EA  	1998	11	13	AU981263         	2	19981002	G	8530	65756	CYLINDER        		O4351       	STNSON	L5    	L5B         	8630204	NE  	LYC   	O435  	O4351       	41516	EA  					ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1    				L0033868			(AUS) NR 1 CYLINDER LEAKING AT HEAD TO BARREL JOINT.  CYLINDER HAD BEEN RECENTLY OVERHAULED, BUT COULD HAVE BEEN MANUFAC	TURED AS LONG AGO AS 1940.					1	H	7	1 	3O	3	O		A764    	E228
1998111300323	19981113	00323	CE  	1998	11	13	AU981264         	1	19980924	G	3260	JE1	SWITCH          		JE1         	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG	BROKEN          	W				K				NONE                    				N			FALSE WARNING             			LD	LANDING        	1			AU	S 										(AUS) MICROSWITCH LEAF SPRING BROKEN.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998111300324	19981113	00324		1998	11	13	AU981265         	4	19980409	G	2350	AA1550411005	AUDIO UNIT      			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					CABIN	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					AA1550411005					(AUS) CENTRAL AUDIO UNIT FAULTY.  WORKSHOP INVESTIGATION FOUND LOSS OF POWER SUPPLY B CAPACITOR C77 ON THE STATION SELEC	TOR BOARD.  THE CAPACITOR THEN LEAKED ELECTROLYTE ONTO EDGE CONNECTOR SK6 CAUSING CORROSION.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998111300325	19981113	00325	EA  	1998	11	13	AU981266         	2	19980930	G	8520	L1061048	CRANKSHAFT      								LYC   	O540  	IO540E1B5   	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L1061048		L1061048			(AUS) ENGINE CRANKSHAFT CRACKED.  CRANKCASE SADDLES FRETTED.  CAMSHAFT LOBE DAMAGED.											3	O			1E4
1998111300326	19981113	00326	SO  	1998	11	13	AU981267         	2	19981002	G	8520		CRANKCASE       								CONT  	O520  	IO520F      	17032	SO  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE CRANKCASE BEARING MOVEMENT.  CAMSHAFT LOBES DAMAGED.  TWO CONNECTING RODS CRACKED.											3	O			E5CE
1998111300327	19981113	00327	CE  	1998	11	13	AU981268         	1	19980923	G	2913	98807001	PRESS SWITCH    		98812001    	CESSNA	210   	210L        	2073448	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			AU	S 										(AUS) LANDING GEAR POWERPACK PRESSURE SWITCH OPEN CIRCUITED.  PISTON P/N H2309 STUCK.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P3EA9
1998111300328	19981113	00328	EA  	1998	11	13	AU981269         	1	19980930	G	2750	C6CF11221	CONTROL CABLE   			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	TE FLAP	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP FOLLOW-UP VALVE OPERATING CABLE STRANDS FRAYED AND BROKEN.  PART TC:  7447.						1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
1998111300329	19981113	00329	SO  	1998	11	13	AU981270         	1	19981007	G	7922	53E22144	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							L118668A			(AUS) RIGHT ENGINE OIL TEMPERATURE REGULATOR VALVE (VERNATHERM) FAULTY.  PART TC:  1,198.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998111300330	19981113	00330	CE  	1998	11	13	AU981271         	1	19981006	G	5711	95110013607	CAP             			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	LT WING SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SPAR CAP CONTAINED EXFOLIATION CORROSION LOCATED ADJACENT TO PITOT HEAD AND EXTENDING OUTBOARD THR	OUGH THE LEADING EDGE RIBS.  FOUND DURING INSPECTION IAW AD/BEECH55/29 AMDT 1.  PART TC:  29,054.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA
1998111800008	19981118	00008	CE  	1998	11	18	AU981272         	1	19980803	G	5320	05121571	CHANNEL         			CESSNA	172   	172N        	2072434	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR POST CHANNEL CRACKED.  PART TC:  6,887.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998111800009	19981118	00009	CE  	1998	11	18	AU981273         	1	19980803	G	5320	05121572	CHANNEL         			CESSNA	172   	172N        	2072434	CE  						MCAULY	1C160	1C160DTM    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR POST CHANNEL CRACKED.  PART TC:  6,887.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998111300331	19981113	00331	EU  	1998	11	13	AU981274         	1	19980925	G	5730		SKIN            			AVIONS	R2160 	R2160       	0960101	EU  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1331039A	A56962		(AUS) LEFT WING UPPER LEADING EDGE SKIN CRACKED IN AREA OF RIVET LINE ON THE MAIN SPAR.  CRACK APPROXIMATELY 52.8 MM (2 	INCHES) IN LENGTH LOCATED 209.55 MM (8.25 INCHES) OUTBOARD OF THE WING ROOT.  CRACK APPROXIMATELY 19.05 MM (0.75 INCHES)	 LOCATED 514.35 MM (20.25 INCHES) OUTBOARD OF THE WING ROOT.  PART TC:  5,350.				1	L	7	1 	3O	3	O	RT	A48EU   	E274	5	N	P88614
1998111300332	19981113	00332	SO  	1998	11	13	AU981275         	1	19980915	G	8120	AO91709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	FAILED          	W				K				NONE                    				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			AU	S 			296  		L218868A		L218868A			(AUS) RIGHT ENGINE TURBOCHARGER COMPRESSOR/TURBINE SHAFT FAILED ALLOWING THE SHAFT TO RUN ECCENTRIC.  THE COMPRESSOR BLA	DES THEN RUBBED ON THE HOUSING ERODING THE BLADES WHICH WERE THEN INJESTED INTO THE ENGINE THROUGH THE INDUCTION SYSTEM.	  EVENTUALLY ONE SECTION OF THE COMPRESSOR BLADE SHEARED OFF AND DISINTEGRATED BEFORE ENTERING THE ENGINE.  LOSS OF APPR	OXIMATELY 1.5 LITRES OF OIL OCCURRED.  THE ENGINE OIL FILTER WAS REMOVED AND WAS FOUND TO CONTAIN A LARGE AMOUNT OF MAIN	LY NON-MAGNETIC METAL.  STRIP INSPECTION OF THE ENGINE FOUND NO COMPONENT FAILURE, BUT FOUND SEVERE METAL CONTAMINATION 	OF THE BEARINGS, SUMP AND OIL PRESSURE RELIEF VALVE.	1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998111300333	19981113	00333		1998	11	13	AU981276         	4	19981007	G	6122	B20258	FLYWEIGHT       		DCF5290D7T3 															GOVERNOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					790902					(AUS) PROPELLER GOVERNOR FLYWEIGHT DISC CRACKED.
1998111300334	19981113	00334	CE  	1998	11	13	AU981277         	1	19980910	G	5312		BULKHEAD        			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BULKHEAD CRACKED.						1	H	7	1 	3O	3	O	NT	TA13    	E273	5	C	P3EA
1998111300335	19981113	00335	SO  	1998	11	13	AU981278         	1	19980924	G	3230	756550	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN LANDING GEAR PRIORITY VALVE SUSPECT FAULTY.  PART TC:  6,122.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998111300336	19981113	00336	EU  	1998	11	13	AU981279         	1	19981008	G	2434		WIRE            			BAG   	BAE146	BAE146300A  	1500267	EU  										NR 1 GENERATOR	WORN            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 GENERATOR BLUE PHASE WIRE CHAFED APPROXIMATELY 300 MM (11.8 INCHES) FROM THE GENERATOR.						2	H	7	4 	4F			RT	A49EU
1998111300337	19981113	00337	SW  	1998	11	13	AU981280         	1	19980911	G	3230		DOWNLOCK        			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK CONTAMINATED WITH GRIT AND SAND.  AIRCRAFT HAD BEEN OPERATING ON UNSEALED RUNWAYS DURIN	G WET WEATHER.  PART TC:  13,799.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998111300338	19981113	00338	NM  	1998	11	13	AU981281         	1	19980928	G	2530	8101210000B	FAN             			BOEING	737   	737376      		NM  										GALLEY OVEN	JAMMED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					86060894					(AUS) OVEN FAN JAMMED BY MEAL TRAY CAUSING DAMAGE TO THE FAN MOTOR.						2	L	7	2 	4F			RT	A16WE
1998111300339	19981113	00339		1998	11	13	AU981282         	4	19981002	G	3457		GPS             	HONEYWELL   	SG811       	DHAV  	DHC8  	DHC8201     	2809001	NM  										COCKPIT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					REFEROVERLEA					(AUS) GPS INSTALLATION DOES NOT COMPLY WITH AD/RAD/61.						2	H	7	2 	4T			RT	A13NM
1998111300340	19981113	00340		1998	11	13	AU981283         	4	19981002	G	3457		GPS             	HONEYWELL   	SG811       	DHAV  	DHC8  	DHC8202     	2809007	NM  										COCKPIT	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) GPS INSTALLATION DOES NOT COMPLY WITH AD/RAD/61.						2	H	7	2 	4T			RT	A13NM
1998111300341	19981113	00341	NE  	1998	11	13	AU981284         	2	19980930	G	7200		ENGINE          								GE    	CF6   	CF680A      	30025	NE  					LT NACELLE	FOD             	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			AU	S 							580191			(AUS) LEFT ENGINE VIBRATION.  N2 VIBRATION INDICATED 5.1 UNITS AT 40 PERCENT N1.  INVESTIGATION FOUND THAT THE VIBRATION	 WAS DUE TO BIRD STRIKE DAMAGE.										4	F			E13NE
1998111300342	19981113	00342	CE  	1998	11	13	AU981285         	1	19981008	G	2436		REGULATOR       			CESSNA	150   	A150M       	2071831	CE  	LYC   	O320  	O320E2A     	41508	EA  	MCAULY	1A103	1A103TCM    	GL  	DC SYSTEM	CORRODED        	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) VOLTAGE REGULATOR TERMINALS SEVERELY CORRODED.  SWITCHED WIRE ALSO CORRODED AND BROKEN AT SPADE TERMINAL.						1	H	7	1 	3O	3	O		3A19    	E274	5	N	P50GL
1998111300343	19981113	00343	EU  	1998	11	13	AU981286         	1	19980903	G	3213	201160702	BOLT            			AIRBUS	320   	A320212     		EU  										LT MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR FORWARD PINTLE PIN LOCK BOLT ROTATING.  EVIDENCE OF LOADING ON THE CHROMED BEARING SURFACES	.					2	L	7	2 	4F			RT	A28NM
1998111300344	19981113	00344	NM  	1998	11	13	AU981287         	1	19980709	G	5314		WEB             			BOEING	737   	737377      		NM  										BS 272	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT KEEL BEAM WEBS CORRODED IN THE AREA JUST FORWARD OF STN 727A.  FURTHER INVESTIGATION FOUND THE CORR	OSION RAN UNDER THE SEALANT BETWEEN THE KEEL BEAM LOWER CHORDS AND THE FUSELAGE SKIN.  FOUND DURING INSPECTION IAW ER B7	3-53-20-5.				2	L	7	2 	4F			RT	A16WE
1998111300345	19981113	00345	EU  	1998	11	13	AU981288         	1	19980709	G	5330		SKIN            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BS 19	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) BELLY SKIN CRACKED AND CORRODED IN THE AREA AT THE FORWARD END OF THE FRONT CARGO COMPARTMENT AT FRAME 19 BETWEEN 	`Z' SECTION STRINGERS 34L AND 34R.  SUBMITTER SUSPECTED CAUSE AS THE RESULT OF A SPILL.  AREA OF CORROSION APPROXIMATELY	 40 MM BY 50 MM (1.57 INCHES BY 1.96 INCHES).				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998111300346	19981113	00346	EU  	1998	11	13	AU981289         	1	19980907	G	2520		SEAT BELT       			AIRBUS	320   	A320212     		EU  										CABIN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NUMEROUS SEAT BELTS AND HARNESSES CONTAINED ILLEGIBLE ID MARKINGS.  FOUND DURING INSPECTION IAW AD/RES/029 (ER Z21	-25-00-10J).					2	L	7	2 	4F			RT	A28NM
1998111300347	19981113	00347	EU  	1998	11	13	AU981290         	1	19980831	G	7620	B737610027	CABLE           		69733941    	BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					WS 219	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FUEL CUT-OFF CABLE WORN AND FRAYED IN AREA OF WING LEADING EDGE AT STN 219 WHERE THE CABLE PASSES THOUGH THE 	SEAL.					2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
1998111300348	19981113	00348	NM  	1998	11	13	AU981291         	1	19980831	G	7603	B7376100215	CABLE           		697345218   	BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					POWER LEVER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT THRUST CABLE WORN AND FRAYED IN AREA OF LEADING EDGE STN 219 WHERE THE CABLE PASSES THROUGH THE SEAL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
1998111300349	19981113	00349	EU  	1998	11	13	AU981292         	1	19980908	G	3213	201056844	BOLT            			AIRBUS	320   	A320212     		EU  										RT MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR FORWARD PINTLE PIN LOCK BOLT SHOWED EVIDENCE OF ROTATION AND CHROMED SURFACE LOADING.  FOU	ND DURING INSPECTION IAW ER A32-32-10-53.					2	L	7	2 	4F			RT	A28NM
1998111300350	19981113	00350	EA  	1998	11	13	AU981293         	2	19981005	G	8500		ENGINE          								LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	ENGINE BAY	FAILED          	W				K				NONE                    				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			AU	S 							L1375540			(AUS) ENGINE FAILED.  INVESTIGATION FOUND OIL FILTER CONTAMINATED WITH METAL PARTICLES.											3	O			E295	5	N	P874
1998111300351	19981113	00351	CE  	1998	11	13	AU981294         	1	19980917	G	2731	0860207144	CONTROL CABLE   			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ELEVATOR	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 										(AUS) ELEVATOR TRIM TAB CONTROL CABLE BROKEN AT THE FORWARD PULLEY BELOW THE TRIM WHEEL.  PART TC:  6,952.						1	L	7	2 	3O	3	O	 	3A10    	E5CE	5	C	P47GL
1998111300352	19981113	00352	SO  	1998	11	13	AU981295         	1	19980907	G	3220	31284	NLG             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE2Y	HCE2YK2     	GL  	NOSE	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			TO	TAKEOFF        	1			AU	S 					31284					(AUS) NOSE LANDING GEAR FAILED TO OPERATE CORRECTLY DUE TO LACK OF LUBRICATION.  INVESTIGATION FOUND THAT THE AIRCRAFT H	AD FLOWN THROUGH HEAVY RAIN WITH THE LANDING GEAR DOWN FOR APPROXIMATELY 20 MINUTES ON THE PREVIOUS FLIGHT THREE DAYS EA	RLIER.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P9EA
1998111300353	19981113	00353	EA  	1998	11	13	AU981296         	2	19980917	G	8520		CRANKSHAFT      			PIPER 	PA18  	PA18150     	7101828	SO  	LYC   	O320  	O320A2B     	41508	EA  	SNSNCH	74D	74DM        	EA  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L4889727A			(AUS) CRANKSHAFT CONTAINED MINOR CORROSION PITTING.  FOUND DURING INSPECTION IAW AD/LYC/102 AMDT 2.						1	H	7	1 	3O	3	O		1A2     	E274	5	N	P88614
1998111300354	19981113	00354	SO  	1998	11	13	AU981297         	2	19981012	G	7414	IO51676	CAPACITOR       	BENDIX      	IO790206    						CONT  	O360  	IO360HB     	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	MAGNETO	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					VARIOUS		VARIOUS	VARIOUS		(AUS) MAGNETO CAPACITORS FAULTY.  THE EXTERNAL ELECTRICAL LEAD BREAKS AT THE SOLDER JOINT.  SUBMITTER STATED THIS IS A F	LEET WIDE PROBLEM.										3	O			E1CE	5	C	P920
1998111300355	19981113	00355	EU  	1998	11	13	AU981299         	1	19980601	G	3234	HTE210014	ACTUATOR        			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					187GB251H					(AUS) LANDING GEAR SELECTOR VALVE ACTUATOR SUSPECT FAULTY.  WORKSHOP INVESTIGATION FOUND THE ACTUATOR TORQUE LIMITER SLI	PPING IN THE COUNTER CLOCKWISE DIRECTION (THIS WOULD NOT PRODUCE THE FAULT FOUND).  PART TC:  3,545.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998111300356	19981113	00356	NM  	1998	11	13	AU981300         	1	19980528	G	7722	CA17400	HARNESS         			BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563B2    	13802	EU  					NR 2 ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			2653 		18909					(AUS) NR 2 ENGINE EGT WIRING HARNESS FAULTY.  HARNESS FAILED THE `WET INSULATION' TEST IN THE WORKSHOP AFTER REMOVAL.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
1998111300357	19981113	00357	NM  	1998	11	13	AU981301         	1	19980915	G	5246	TPE47	SEAL            		TPE52       	BOEING	737   	737377      		NM  										WASTE DOOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLEET INSPECTION FOUND NUMEROUS TOILET WASTE BIN ENCLOSURE DOOR SEALS WORN AND/OR DAMAGED.						2	L	7	2 	4F			RT	A16WE
1998111300358	19981113	00358	NM  	1998	11	13	AU981302         	1	19980929	G	2913	6506605	PUMP            			BOEING	747   	747438      		NM  										HYDRAULIC SYS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 					168085					(AUS) NR 4 HYDRAULIC PUMP CRACKED AND LEAKING HYDRAULIC FLUID.  HYDRAULIC SYSTEM CONTAMINATED.						2	L	7	4 	4F			RT	A20WE
1998111300359	19981113	00359	NM  	1998	11	13	AU981303         	1	19981004	G	5311	A0202	FRAME           			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			438  							(AUS) FUSELAGE UPPER FRAME TUBE LOCATED UNDER THE LEFT REAR MAIN GEARBOX MOUNT PAD BROKEN.  PART TC:  2,430.						1	G	7	1 	3O	3	O		H10WE   	E274
1998111300360	19981113	00360	NE  	1998	11	13	AU981304         	2	19981008	G	7230	60221	COMPRESSOR      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					NR 2 ENGINE	STALLED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					60221		60221			(AUS) NR 2 ENGINE COMPRESSOR STALLED.  THE ENGINE WAS REDUCED TO IDLE AND DURING APPROACH, THE ENGINE CHIP LIGHT ILLUMIN	ATED.  INSPECTION FOUND METAL CONTAMINATION ON BOTH FORWARD AND AFT CHIP DETECTORS.  COMPRESSOR RUB WAS HEARD WHEN THE E	NGINE WAS ROTATED.				1	G	7	1 	4U	4	U		H4SW    	E22EA
1998111300361	19981113	00361	SO  	1998	11	13	AU981305         	1	19980822	G	3221		TRUNNION        			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NLG TRUNNION TO DRAG BRACE ATTACHMENT FAILED ALLOWING THE NLG TO REST AGAINST THE DRAG BRACE IN A PARTIALLY EXTEND	ED POSITION.  THE NLG FAILED TO FULLY EXTEND AND THE AIRCRAFT DEPARTED THE RUNWAY DURING LANDING CAUSING THE NLG TO BE T	ORN OFF.				1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1998111300362	19981113	00362	EU  	1998	11	13	AU981306         	2	19981001	G	7230		COMPRESSOR      			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 2 ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							9584			(AUS) NR 2 ENGINE N2 COMPRESSOR REAR STAGE COMPRESSOR BLADES SEVERELY DAMAGED.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998111300363	19981113	00363	CE  	1998	11	13	AU981307         	1	19980910	G	3411		HOSE            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	PITOT	SEPARATED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) ALTIMETER STATIC HOSE DISLODGED AND CRACKED.  STATIC HOSE BETWEEN THE ALTIMETER AND AIRSPEED INDICATOR SEPARATED A	T A UNION LOCATED BEHIND THE DIRECTIONAL GYRO CASE.					1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA
1998111300364	19981113	00364		1998	11	13	AU981308         	4	19981013	G	2312		TRANSCEIVER     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					COCKPIT VHF	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NIL RECEIVE OR TRANSMIT ON BOTH VHF RADIOS.  GROUND INVESTIGATION AND TESTING COULD FIND NO FAULT.						1	G	7	1 	3U	3	U		H9EU    	E19EU
1998111300365	19981113	00365	CE  	1998	11	13	AU981309         	1	19981009	G	2750	ARBL3E	ROD             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAP	BROKE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FLAP INBOARD ACTUATING ROD FORWARD ROD END BROKEN THROUGH THREADED SECTION IN AREA OF LOCKNUT.  SUBMITTER SU	SPECTED CAUSED BY OVERTORQUE OF THE LOCKNUT AND/OR FLAPS SLIGHTLY OUT OF RIG.					1	L	7	2 	4F	4	F		A22CE   	E1NE
1998111300366	19981113	00366	NE  	1998	11	13	AU981310         	2	19981010	G	7230		COMPRESSOR      								GE    	CF6   	CF680A      	30025	NE  					LT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							580391			(AUS) LEFT ENGINE COMPRESSOR STAGE 10 TO STAGE 12 DAMAGED.											4	F			E13NE
1998111300367	19981113	00367	SO  	1998	11	13	AU981311         	2	19980821	G	7314	6491251	PUMP            		6191251     	PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520B    	17040	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					C118832A		528021	AM2542		(AUS) ENGINE FUEL PUMP LEAKING FROM AREA OF THE MIXTURE SHAFT.  PART TC:  787.						1	L	7	1 	3O	3	O	RT	A25SO   	E8CE	5	C	P920
1998111300368	19981113	00368	NE  	1998	11	13	AU981313         	2	19981007	G	7320		PIPE            								PWA   	PWA120	PW125B      		NE  					LT ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							124086			(AUS) LEFT ENGINE PY LINE LOCATED BETWEEN THE FUEL CONTROL UNIT AND THE OVERSPEED GOVERNOR HAD A LOOSE CONNECTION.											4	T			E20NE
1998111300369	19981113	00369	CE  	1998	11	13	AU981314         	1	19981013	G	3230	358150772LH	BRACKET         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	LT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							287053R			(AUS) LEFT LANDING GEAR UPLOCK BRACKET SEVERELY CORRODED.						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA
1998111300370	19981113	00370	CE  	1998	11	13	AU981315         	1	19981013	G	3230	358150773RH	BRACKET         			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	RT MLG	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							287053R			(AUS) RIGHT LANDING GEAR UPLOCK BRACKET SEVERELY CORRODED.						1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA
1998111300371	19981113	00371	EU  	1998	11	13	AU981316         	1	19981008	G	2420		WIRE            			BAG   	BAE146	BAE146300A  	1500267	EU  										NR 1 GENERATOR	CHAFED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 GENERATOR BLUE PHASE WIRE CHAFED.						2	H	7	4 	4F			RT	A49EU
1998111300372	19981113	00372	CE  	1998	11	13	AU981317         	1	19980930	G	2750	51220465	BRACKET         			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING FLAP BELLCRANK UPPER AND LOWER BRACKETS CORRODED AND DAMAGED.  SUSPECT THE LOWER BRACKET HAD FAILED ALLO	WING THE FLAP ACTUATING BELLCRANK TO BE TORN OUT OF THE LOWER BRACKET AND DAMAGING THE UPPER BRACKET.					1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998111300373	19981113	00373	CE  	1998	11	13	AU981318         	1	19981008	G	5730	042240127	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED FROM RIVETS ATTACHING SKIN TO THE WING RIBS AT STN 102.0.  MAXIMUM CRACK LENGTH 3 MM 	(0.118 INCH).  PART TC:  14,730.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998111300374	19981113	00374	CE  	1998	11	13	AU981319         	1	19981008	G	5730	042240136	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 84	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING UPPER SKIN CRACKED FROM RIVETS ATTACHING THE SKIN TO THE WING RIBS.  ONE CRACK LOCATED AT STN 102.0 AND	 ONE CRACK LOCATED AT STN 84.0.  MAXIMUM LENGTH OF CRACKS 3 MM (0.118 INCH).  PART TC: 14,730.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998111300375	19981113	00375	CE  	1998	11	13	AU981320         	1	19981009	G	5730	042240127	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	2A34C	D2A34C98    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED FROM RIVETS ATTACHING THE SKIN TO THE WING RIBS.  SKIN CONTAINED THREE CRACKS LOCATED	 AT STN 102.0 AND ONE CRACK LOCATED AT STN 84.0.  PART TC:  6,516.					1	H	7	1 	3O				3A19    		5	C	P3EA
1998111300376	19981113	00376	CE  	1998	11	13	AU981321         	1	19981009	G	5730	042240136	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	2A34C	D2A34C98    	GL  	WS 84	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT UPPER WING SKIN CRACKED FROM RIVETS ATTACHING THE SKIN TO THE WING RIBS. SKIN CONTAINED TWO CRACKS LOCATED A	T STN 84.0. MAXIMUM CRACK LENGTH 4 MM (0.157 INCH).  PART TC:  6,516.					1	H	7	1 	3O				3A19    		5	C	P3EA
1998111300377	19981113	00377	CE  	1998	11	13	AU981322         	1	19981005	G	7603	63255512	LEVER           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ2Y	BHCJ2YF2    	GL  	COCKPIT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							299071			(AUS) ENGINE THROTTLE ARM WORN.  STEEL BUSHING PRESSED INTO THE BRONZE THROTTLE ARM WORE THROUGH THE ARM ALLOWING THE TH	ROTTLE TO BECOME DISCONNECTED.  PART TC:  111.					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P37EA
1998111300378	19981113	00378	SO  	1998	11	13	AU981323         	1	19981007	G	7922	53E22144	VALVE           			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	RT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT ENGINE OIL TEMPERATURE VALVE (VERNATHERM) INOPERATIVE.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998111300379	19981113	00379	EU  	1998	11	13	AU981324         	1	19981008	G	2730		HORN            			SCTAIV	PIONER	PIONEERSER3 		EU  										ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR HORN DAMAGED.  CENTER MEMBER UP STOP DAMAGED.						2	H	7	2 	3R				7A7
1998111300380	19981113	00380	EU  	1998	11	13	AU981325         	1	19980122	G	3411		HOSE            			SCTAIV	PIONER	PIONEERSER3 		EU  										PITOT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ALL PITOT/STATIC HOSES CONNECTING THE AIRCRAFT SYSTEM TO THE INSTRUMENTS BEHIND THE INSTRUMENT PANEL ARE MANUFACTU	RED FROM COMMERCIAL CLEAR PLASTIC HOSE AND IN SOME CASES WERE CRIMPED.  VACUUM HOSES ALSO MANUFACTURED FROM THE SAME MAT	ERIAL.  UNAPPROVED PART.				2	H	7	2 	3R				7A7
1998111300381	19981113	00381	EU  	1998	11	13	AU981326         	1	19981008	G	2810	SAB3562131186121	FUEL CELL       			SCTAIV	PIONER	PIONEERSER3 		EU  										FUSELAGE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL TANKS LEAKING.  SUBMITTER STATED ALL TANKS WERE DETERIORATED AND/OR DAMAGED.						2	H	7	2 	3R				7A7
1998111300382	19981113	00382	EU  	1998	11	13	AU981327         	1	19981008	G	2710	SAB34599	ROD             			SCTAIV	PIONER	PIONEERSER3 		EU  										AILERON	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT AILERON PUSH/PULL ROD FROM THE OUTBOARD WING BELLCRANK TO THE AILERON SEVERELY CORRODED AND STRESS CRACKED.						2	H	7	2 	3R				7A7
1998111300383	19981113	00383	EU  	1998	11	13	AU981329         	1	19981008	G	2620		FIRE LOOP       			SCTAIV	PIONER	PIONEERSER3 		EU  										ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE FIRE BOTTLE WIRING SYSTEM FAULTY AND WIRES INCORRECTLY CONNECTED.  BOTTLES WOULD NOT FIRE.						2	H	7	2 	3R				7A7
1998111300384	19981113	00384	EU  	1998	11	13	AU981330         	1	19981008	G	2700		CONTROL CABLE   			SCTAIV	PIONER	PIONEERSER3 	       	EU  										FLIGHT CONTROL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NUMEROUS CONTROL CABLES FRAYED WITH BROKEN WIRES AND STRANDS.						2	H	7	2 	3R			 	7A7
1998111300385	19981113	00385	NE  	1998	11	13	AU981331         	1	19981016	G	5711		CAP             			CONAER	LA4   	LA4250      	5110320	NE  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE3Y	HCE3YR1     	GL  	WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING LOWER SPAR CAP CRACKED VERTICALLY THROUGH THE ANGLE TO THE SECOND OUTBOARD MOUNT BOLT HOLE.  PART TC:  970.						1	H	7	1 	3O	3	O		1A13    	1E4	5	C	P33EA
1998111300386	19981113	00386	EU  	1998	11	13	AU981332         	1	19981008	G	2750		ROD             			SCTAIV	PIONER	PIONEERSER3 		EU  										TE FLAP	JAMMED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP SYSTEM JAMMING.  INVESTIGATION FOUND FLAP ROD TO SPOOL ADJUSTMENT SHIMS INCORRECTLY FITTED.						2	H	7	2 	3R				7A7
1998111300387	19981113	00387	EU  	1998	11	13	AU981333         	1	19981008	G	2780	SAB348183	PULLEY          			SCTAIV	PIONER	PIONEERSER3 		EU  										LE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WING SLAT PULLEYS LOCATED AT THE REAR OF THE WING WERE SEVERELY CORRODED.  PULLEYS ARE MANUFACTURED FROM ALUMINIUM	 ALLOY.					2	H	7	2 	3R				7A7
1998111300388	19981113	00388	EU  	1998	11	13	AU981334         	1	19981008	G	5740	SAB320326	BOLT            			SCTAIV	PIONER	PIONEERSER3 		EU  										ATTACH FITTING	FAILED          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) STABILIZING STRUT TO LIFT STRUT ATTACHMENT BOLTS OVERTORQUED AND BOLTS STRETCHED.						2	H	7	2 	3R				7A7
1998111300389	19981113	00389	EU  	1998	11	13	AU981335         	1	19981008	G	5740		LIFT STRUT      			SCTAIV	PIONER	PIONEERSER3 		EU  										ATTACH FITTING	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LIFT STRUT ATTACHMENT TO STABILIZER STRUT TEFLON STRIPS HAD THE TEFLON COATING WORN AWAY.  THE TEFLON WASHERS	 HAD BEEN SUBSTITUTED WITH ENGINE LOCK TABS.  UNAPPROVED PART.					2	H	7	2 	3R				7A7
1998111300390	19981113	00390	NM  	1998	11	13	AU981336         	1	19980803	G	2782	69734855	ROD             		654476010   	BOEING	737   	737377      		NM  										LE FLAP	FRACTURED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					031					(AUS) NR 1 LEADING EDGE SLAT ACTUATOR EYE END FRACTURED.  DAMAGE CAUSED TO NR 1 SLAT.  INVESTIGATION FOUND THAT THE FAIL	URE WAS INITIATED BY STRESS CORROSION CRACKING AT AN AREA OF FRETTING AND CORROSION ON BORE SURFACE.  PART TC:  28,098.					2	L	7	2 	4F			RT	A16WE
1998111300391	19981113	00391	EU  	1998	11	13	AU981337         	1	19981008	G	5740	SAB34013562A	BUSHING         			SCTAIV	PIONER	PIONEERSER3 		EU  										ATTACH FITTING	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT STRUT ATTACHMENT BUSHES SEVERELY DAMAGED.						2	H	7	2 	3R				7A7
1998111300392	19981113	00392	NE  	1998	11	13	AU981338         	2	19980824	G	7250	3360037030	BLADE           								CFMINT	CFM56 	CFM565A1    		NE  					TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							73186			(AUS) LEFT ENGINE 3RD STAGE LOW PRESSURE TURBINE BLADE SEPARATED.  4TH STAGE LPT BLADES DENTED ON THE TRAILING EDGES.  P	ART TC:  6,640.										4	F			E29NE
1998111300393	19981113	00393	CE  	1998	11	13	AU981339         	1	19981004	G	2720	571509616	CONTROL CABLE   			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	RUDDER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT FORWARD RUDDER CABLE FAILED AT THE FORWARD PULLEY.  PART TC:  61.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300394	19981113	00394	EA  	1998	11	13	AU981340         	2	19980924	G	8530	L154368A	VALVE GUIDE     			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L154368A			(AUS) ENGINE CYLINDER EXHAUST VALVE GUIDES TIGHT CAUSING VALVES TO STICK.  CYLINDERS ARE NEW ITEMS FITTED APPROXIMATELY 	184 HOURS PREVIOUSLY.  PART TC:  184.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998111300395	19981113	00395	SO  	1998	11	13	AU981341         	1	19980918	G	5753	623280001	RIB             			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  	SNSNCH	74D	74DM        	EA  	TE FLAP	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP RIB CORRODED IN AREA OF ATTACHMENT TO STEEL FLAP HINGE BRACKET.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
1998111300396	19981113	00396	SO  	1998	11	13	AU981342         	1	19981008	G	2913	OLI0094	PLATE           		1213HDG310A 	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	HYDRAULIC SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					OLI0094					(AUS) RIGHT HYDRAULIC PUMP SANDWICH PLATE CRACKED ON SUCTION SIDE.  AIR ENTERED HYDRAULIC SYSTEM.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1998111300397	19981113	00397	EU  	1998	11	13	AU981343         	1	19981012	G	6210	365A11002002	BLADE           	AEROSP      	365A11002002	AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					MAIN ROTOR	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2894 		515					(AUS) MAIN ROTOR BLADE DELAMINATED.  PART TC:  6,347.						1	G	7	2 	3U	3	U		H10EU   	E19EU
1998111300398	19981113	00398	NE  	1998	11	13	AU981344         	2	19980930	G	7532	310082903	DIAPHRAGM       		310082903   	CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					310334701		PCE17463			(AUS) ENGINE BLEED VALVE DIAPHRAGM SPLIT.  PART TC:  1,622.						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA
1998111300399	19981113	00399	CE  	1998	11	13	AU981345         	1	19981016	G	5751	65240005	BRACKET         		65240005    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AILERON	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					A001132					(AUS) LEFT AILERON HINGE BRACKET INCORRECTLY RE-FITTED FOLLOWING REPAIR.  PART TC:  9,382.						1	L	7	2 	4F	4	F		A22CE   	E1NE
1998111300400	19981113	00400	CE  	1998	11	13	AU981346         	1	19981016	G	5751	65240102	BRACKET         		65240102    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					AILERON	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 					A00929					(AUS) RIGHT AILERON HINGE BRACKET INCORRECTLY RE-FITTED FOLLOWING REPAIR.  PART TC:  9,832.						1	L	7	2 	4F	4	F		A22CE   	E1NE
1998111300401	19981113	00401	EU  	1998	11	13	AU981347         	1	19980714	G	3250	TS1160672	SWITCH          			AIRBUS	320   	A320212     		EU  										NLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					445505007					(AUS) NOSE WHEEL STEERING PEDAL DISCONNECT SWITCH FAULTY.  PART TC:  28,142.						2	L	7	2 	4F			RT	A28NM
1998111300402	19981113	00402	NE  	1998	11	13	AU981348         	2	19980910	G	7230	9339M40G03	SEAL            		9339M40G03  						CFMINT	CFM56 	CFM565A1    		NE  					LT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			18107				731170			(AUS) LEFT ENGINE NR 3 BEARING FORWARD STATIONARY AIR/OIL SEAL DAMAGED.  PART TC:  23,698.											4	F			E29NE
1998111300403	19981113	00403	NM  	1998	11	13	AU981349         	1	19980813	G	5210		BOLT            			BOEING	737   	737377      		NM  										PASSENGER DOOR	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD DOOR L1 STOP BOLTS SLIGHTLY OUT OF ADJUSTMENT.						2	L	7	2 	4F			RT	A16WE
1998111300404	19981113	00404	NM  	1998	11	13	AU981350         	1	19981006	G	3320		LIGHT           			BOEING	767   	767338      		NM  	GE    	CF6   	CF680C2B2   	30025	NE  					SEAT 5	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN LIGHTING FAULTY.  SIDEWALL FLUORESCENT TUBE LOCATED AT SEAT 5JK FAULTY CAUSING FAILURE OF UPPER EICAS DISPLA	Y AND THE FIRST OFFICER'S CLOCK.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998111300405	19981113	00405	NM  	1998	11	13	AU981351         	1	19981013	G	2910	82950010275	PIPE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					HYDRAULIC SYS	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT INBOARD ROLL SPOILER HYDRAULIC GROUND PRESSURE UP LINE LEAKING.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998111300406	19981113	00406	EA  	1998	11	13	AU981353         	2	19981019	G	7322	3242830	SHAFT           	GARRTT      	FCU         	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	THROTTLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3037 		A89271		56681	BU11566		(AUS) ENGINE FUEL CONTROL UNIT THROTTLE SHAFT BROKEN AT THE CAM.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
1998111300407	19981113	00407	CE  	1998	11	13	AU981354         	1	19981016	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT NOSE LANDING GEAR TRUNNION CRACKED.  CRACK LENGTH APPROXIMATELY 12 MM (0.472 INCH).  PART TC:  8,911.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300408	19981113	00408	CE  	1998	11	13	AU981355         	1	19981019	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT NOSE LANDING GEAR TRUNNIONS CRACKED.  CRACK LENGTHS 15 MM (0.59 INCH) LT AND 6MM (0.236 INCH) RT. P	ART TC:  8,694.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300409	19981113	00409	NE  	1998	11	13	AU981356         	1	19981015	G	6720	300SSDRML2410	SHAFT           			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR PITCH CHANGE SHAFT BINDING ON LINER DUE TO CORROSION.						1	G	7	2 	3U	3	U		H1NE    	E19EU
1998111300410	19981113	00410	CE  	1998	11	13	AU981357         	1	19981019	G	3233	11581002911	NUT             		LGACTUATOR  	BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3982 		2759					(AUS) LEFT MAIN LANDING GEAR ACTUATOR NUT CRACKED CIRCUMFERENTIALLY FOR APPROXIMATELY 25 PERCENT OF THE CIRCUMFERENCE 31	.75 MM (1.25 INCH FROM THE TOP OF THE NUT.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998111300411	19981113	00411	SO  	1998	11	13	AU981358         	2	19981019	G	8520	643627	CRANKSHAFT      			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	LTSIO360E   	17025	SO  	HARTZL	HCC2Y	BHCC2YF2    	GL  	ENGINE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 			109  				306429			(AUS) RIGHT ROTATION CRANKSHAFT INSTALLED IN LT ROTATION ENGINE.  NO TIMING MARKS ON CRANKSHAFT FLANGE.  UNAPPROVED PART	.					1	L	7	2 	3O	3	O		A7SO    	E9CE	5	C	P920
1998111300412	19981113	00412	EA  	1998	11	13	AU981359         	2	19980328	G	8530	72242	LUG             			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	ENGINE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			200  				L503461A			(AUS) ROCKER SHAFT RETAINING LUG BROKE OFF THE ROCKER HAT ALLOWING THE INLET VALVE ROCKER SHAFT TO MIGRATE AND THE ROCKE	R TO DISLODGE.  THE LUG IS NORMALLY SILVER SOLDERED TO THE ROCKER HAT. SUBMITTER SUSPECTED CAUSE AS POORLY SOLDERED JOIN	T.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P920
1998111300413	19981113	00413	CE  	1998	11	13	AU981360         	1	19981019	G	2400		ELECTRICAL      			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	BATTERY BAY	FIRE            	W				K				NONE                    				A			FLAME/FIRE                			TO	TAKEOFF        	1			AU	S 							L2760336A	861902		(AUS) ELECTRICAL FIRE IN REAR RADIO AND BATTERY COMPARTMENT.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
1998111300414	19981113	00414	SO  	1998	11	13	AU981361         	1	19981015	G	2820	41650000	PIPE            			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	WS 49-67	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGID FUEL PIPE LOCATED BETWEEN WS 49.0 TO WS 67.5 CHAFED BY THE ENGINE CONTROL CABLES.  PIPE WAS WORN HALF WAY TH	ROUGH AND IS THE MAIN AND ONLY FUEL SUPPLY TO THE ENGINE.  PART TC:  11,414.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998111300415	19981113	00415	SO  	1998	11	13	AU981362         	1	19981012	G	5520	40060000	CHANNEL         		ELEVATOR    	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR CHANNEL STRUCTURE CRACKED APPROXIMATELY 15 MM (0.59 INCH) ALONG THE CORNER RADIUS AT THE NUT PLATE LOCATI	ON.  PART TC:  11,414.					1	L	7	2 	3O				A20SO   		5	C	P33EA
1998111300416	19981113	00416	NM  	1998	11	13	AU981363         	1	19981015	G	2612		FIRE DETECTOR   			BOEING	737   	737476      		NM  										NR 2 ENGINE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE FIRE DETECTOR OPERATION.   INVESTIGATION FOUND A PIECE OF RAG LOCATED INSIDE THE THRUST REVERSER COWL 	CONTACTING THE FIRE DETECTOR.  FOD.					2	L	7	2 	4F			RT	A16WE
1998111300417	19981113	00417	CE  	1998	11	13	AU981365         	1	19981020	G	3222	57411405	FORK            			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT LANDING GEAR FORK/AXLE ASSEMBLY CRACKED ON THE FORK LOWER SURFACE.  CRACK LENGTH APPROXIMATELY 6 MM (0.236 IN	CH).  PART TC:  11,423.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300418	19981113	00418	NE  	1998	11	13	AU981366         	1	19981015	G	6720	300SSDRML2410	LINER           			SKRSKY	S76   	S76A        	8143006	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					TAIL ROTOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) TAIL ROTOR PITCH CHANGE SHAFT LINER CORRODED CAUSING BINDING OF THE PITCH CHANGE SHAFT.						1	G	7	2 	3U	3	U		H1NE    	E19EU
1998111300419	19981113	00419	CE  	1998	11	13	AU981368         	1	19981015	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT NOSE LANDING GEAR TRUNNIONS CRACKED.  CRACK LENGTHS APPROXIMATELY 14 MM (0.55 INCH) LT AND 20 MM (0	.787 INCH) RT.  PART TC:  11,300.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300420	19981113	00420	CE  	1998	11	13	AU981369         	1	19980805	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT NOSE LANDING GEAR TRUNNION FITTING CRACKED.  CRACK LENGTH APPROXIMATELY 17 MM (0.669 INCH).  PART TC:  12,197	.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998111300421	19981113	00421	NM  	1998	11	13	AU981370         	1	19980821	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD LEFT SIDE CHORD LOCATED AT WL 207 CRACKED AT FLOOR LEVEL.  CRACK LENGTH 12.7 MM (0.5 INC	H).  FOUND DURING EDDY CURRENT INSPECTION IAW ER B73-53-10-39D.					2	L	7	2 	4F			RT	A16WE
1998111300422	19981113	00422	NM  	1998	11	13	AU981371         	1	19981014	G	7603	87600575001	CABLE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					POWER LEVER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT (NR 2) ENGINE CONTROL CABLE TO THE POWER LEVER TOO LONG.  CABLE HAD BOTTOMED OUT WITH NIL ADJUSTMENT AVAILAB	LE AND WAS WELL BELOW THE REQUIRED TENSION.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998111300423	19981113	00423		1998	11	13	AU981372         	4	19981021	G	2312	B692242	CONTROL BOX     			BAG   	JETSTM	JETSTM3107  	1500215	EU  						ROTOL	R333	R333482F12  	GL  	COCKPIT	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					00004					(AUS) FIRST OFFICER'S RADIO STATION BOX FAULTY.						2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL
1998111300424	19981113	00424	CE  	1998	11	13	AU981373         	1	19981015	G	3260		SWITCH          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	NLG	OUT OF ADJUST   	W				K				NONE                    				O	N		OTHER                     	FALSE WARNING             		LD	LANDING        	1			AU	S 										(AUS) NOSE LANDING GEAR MICROSWITCH OUT OF ADJUSTMENT.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998111300425	19981113	00425	SO  	1998	11	13	AU981374         	2	19981019	G	8500		ENGINE          			BEECH 	36    	A36         	1151604	CE  	CONT  	O520  	IO520B      	17032	SO  	MCAULY	3A32C	3A32C76     	GL  	ENGINE BAY	ROUGH           	W				K				NONE                    				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			AU	S 							281572R			(AUS) ENGINE RUNNING ROUGH AND STOPPED WHEN THE THROTTLE WAS RETARDED FOLLOWING LANDING.   INVESTIGATION COULD FIND NO F	AULT.  SUBMITTER SUSPECTED FUEL CONTAMINATION OR FUEL VAPOR LOCK.					1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA
1998111300426	19981113	00426	NM  	1998	11	13	AU981375         	1	19981019	G	3260		INDICATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR INDICATIONS FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998111300427	19981113	00427	CE  	1998	11	13	AU981376         	1	19981019	G	7721		PROBE           			CESSNA	182   	182P        	2075816	CE  	CONT  	O470  	O470S       	17026	SO  					CYLINDER HEAD	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) INCORRECT CYLINDER HEAD TEMPERATURE SYSTEM FITTED.  UNAPPROVED PART.						1	H	7	1 	3O	3	O	NT	TA13    	E273
1998111300428	19981113	00428	CE  	1998	11	13	AU981377         	1	19981023	G	5730	042240127	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 102	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING UPPER SKIN CRACKED FROM RIVETS ATTACHING RIBS TO THE SKIN AT THE FOLLOWING LOCATIONS:  1.  STN 84.0 - ON	E CRACK.  2.  STN 102.0 - ONE CRACK.  MAXIMUM CRACK LENGTH 3 MM (0.118 INCH).  PART TC:  13,936.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998111300429	19981113	00429	CE  	1998	11	13	AU981378         	1	19981023	G	5730	042240136	SKIN            			CESSNA	150   	A152        	2071836	CE  						MCAULY	1A103	1A103TCM    	GL  	WS 84	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING UPPER SKIN CRACKED FROM RIVETS ATTACHING RIBS TO THE SKIN AT THE FOLLOWING LOCATIONS:  1.  STN 84.0 - O	N CRACK 2.  STN 102.0 - TWO CRACKS.  MAXIMUM CRACK LENGTH 3 MM (0.118 INCH).  PART TC:  13,936.					1	H	7	1 	3O				3A19    		5	N	P50GL
1998111300430	19981113	00430	EU  	1998	11	13	AU981379         	1	19981019	G	3222	1155204	FORK            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	NLG	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FIBERGLASS FORK DELAMINATED.  SUBMITTER SUSPECTED CAUSE AS HEAVY LANDINGS.  PART TC:  13,936.						1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045
1998111300431	19981113	00431	EU  	1998	11	13	AU981380         	1	19980806	G	5311		FRAME           			AIRBUS	320   	A320212     		EU  										BS 38-41	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTER FUSELAGE FRAME FLANGES LOCATED BETWEEN STRINGERS 23 AND 24 CRACKED IN THE FOLLOWING AREAS:   1.  FRAME 38 - 	FORWARD FACE INBOARD HOLE.  2.  FRAME 41 - INBOARD UPPER HOLE FOUND DURING EDDY CURRENT INSPECTION.					2	L	7	2 	4F			RT	A28NM
1998111300432	19981113	00432	EU  	1998	11	13	AU981381         	1	19981016	G	2910	AE7064584	HOSE            			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R320	R3204123F1  	NE  	HYDRAULIC SYS	BURST           	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR DOWNLOCK ACTUATOR HYDRAULIC PRESSURE HOSE RUPTURED.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P5NE
1998111300433	19981113	00433	EU  	1998	11	13	AU981382         	2	19981024	G	7322	848237	VALVE           		6432391     						ROTAX 	912   	ROTAX912    	55555	EU  					CARBURETOR	SEIZED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) CARBURETOR THROTTLE VALVE SEIZED, IN GRADUATED SLEEVE P/N 847,740, DUE TO CORROSION.  THROTTLE CABLE FAILED.											3	I			EXPE3I
1998111300434	19981113	00434	SO  	1998	11	13	AU981383         	2	19981002	G	8520	642135	CRANKCASE       			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			711  				227818R			(AUS) CRANKCASE CRACKED FROM NR 5 CYLINDER LOWER FRONT STUD.						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL
1998111300435	19981113	00435	SO  	1998	11	13	AU981384         	2	19981004	G	8530		TAPPET          		CYLINDER    	CESSNA	182   	182J        	2072722	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ENGINE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							275714R			(AUS) ENGINE TAPPETS FITTED IN THE INCORRECT LOCATIONS.  SUBMITTER SUSPECTED ALSO UNAPPROVED PARTS.  PART TC:  740.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998111300436	19981113	00436	SO  	1998	11	13	AU981385         	2	19981002	G	8530	227818R	EXHAUST VALVE   			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			289  				227818R			(AUS) RIGHT ENGINE CYLINDERS (FIVE NEW - ONE USED) HAD THE INLET AND EXHAUST VALVES WORN BEYOND LIMITS.  ALL EXHAUST VAL	VE GUIDES UNSERVICEABLE.  PART TC:  289.					1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL
1998111300437	19981113	00437	CE  	1998	11	13	AU981386         	1	19981009	G	2750	ARBL3E	ROD             			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					TE FLAP	BROKE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FLAP INBOARD ACTUATING ROD FORWARD ROD END BROKEN THROUGH THE THREADED SECTION IN THE AREA OF THE LOCKNUT. S	UBMITTER SUSPECTED CAUSE AS OVERTORQUING OF THE LOCK NUT WITH THE FLAPS BEING OUT OF ADJUSTMENT AS A CONTRIBUTING FACTOR	.				1	L	7	2 	4F	4	F		A22CE   	E1NE
1998111300438	19981113	00438	NE  	1998	11	13	AU981387         	2	19981021	G	7261		OIL             								LYC   	ALF502	ALF502R5    	41580	NE  					NR 3 ENGINE	LOW PRESSURE    	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							LF05155			(AUS) NR 3 ENGINE LOST OIL PRESSURE.  OIL QUANTITY AND TEMPERATURE INDICATIONS NORMAL.											4	F			E6NE
1998111300439	19981113	00439	NE  	1998	11	13	AU981388         	2	19981021	G	7200		ENGINE          								LYC   	ALF502	ALF502R5    	41580	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							LF05474A			(AUS) NR 2 ENGINE LOW POWER.											4	F			E6NE
1998111300440	19981113	00440	NM  	1998	11	13	AU981389         	1	19980910	G	3230	BACB10BW33	BEARING         			BOEING	737   	737376      		NM  										NLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR MANUAL RELEASE MECHANISM BEARINGS (2OFF) SEIZED PREVENTING EMERGENCY EXTENSION.  SUBMITTER SUSPE	CTED CAUSE AS HIGH PRESSURE CLEANING OF THE NOSE WHEEL AREA FLUSHING THE GREASE FROM THE BEARINGS.					2	L	7	2 	4F			RT	A16WE
1998111300441	19981113	00441		1998	11	13	AU981390         	1	19981002	G	3610	1379287L403	LINE            								GARRTT	TPE331	TPE33110UA  	01514	WP  	ROTOL	R333	R333482F12  	GL  	BLEED AIR	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							P63115			(AUS) CABIN BLEED HOSE BROKEN AT FLANGE.  HOSE IS A PRE-MOD ITEM.											4	T			E4WE	6	C	P61GL
1998111300442	19981113	00442	EA  	1998	11	13	AU981391         	2	19980330	G	7414	4250	MAGNETO         	SLICK       	4250        	GULSTM	GA7   	GA7         	3960401	SO  	LYC   	O320  	O320D1D     	41508	EA  					ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					2030040		L891939A			(AUS) RIGHT MAGNETO ROTOR AND BEARINGS LOOSE IN THE HOUSING ALLOWING THE ROTOR TO CONTACT THE HOUSING.  PART TC:  1,736.						1	L	7	2 	3O	3	O		A17SO   	E274
1998111300443	19981113	00443	EU  	1998	11	13	AU981392         	1	19981014	G	3233	5230606040146	HOSE            			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R320	R3204123F1  	NE  	RT MLG	BURST           	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR ACTUATOR HYDRAULIC HOSE BURST.  HOSE WAS MANUFACTURED 7/82 AND IS SUSPECTED TO BE AN ORIGI	NAL FIT ITEM.  WHEN EXAMINED BY THE MANUFACTURER, THE HOSE SHOWED NO VISIBLE EXTERNAL SIGNS OF DEGRADATION.  PART TC:  2	2,053.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P5NE
1998111300444	19981113	00444	SW  	1998	11	13	AU981393         	1	19981022	G	3243	400021	BOLT            	CLEVELAND   	1086        	AIRTRC	AT802 	AT802       	0390305	SW  	PWA   	PT6   	PT6A65AG    	52043	NE  	HARTZL	HCB5M	HCB5MP3     	GL  	BRAKE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) BRAKE MASTER CYLINDER EYEBOLT FAILED AT THE LOWER END OF THE LOCKNUT CAUSING THE AIRCRAFT TO SWERVE OFF THE RUNWAY	.  PART TC:  800.					1	L	7	1 	3T	4	T	NC	A19SW   	E4EA	6	C	P44GL
1998111300445	19981113	00445	CE  	1998	11	13	AU981394         	1	19981023	G	2810		FUEL CELL       			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT WING	LEAKING         	W				K				NONE                    				K	B		FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  		NR	NOT REPORTED   	1			AU	S 										(AUS) INTERNAL WING FIRE IN LT WING LOCATED IN AREA OF THE BATTERY.  DAMAGE TO ELECTRICAL CABLES AND AILERON TRIM CABLES	 AND PULLEY.  SUBMITTER SUSPECTED CAUSE AS IGNITION OF FUEL VAPOR FROM LEAKING/DETERIORATED AUXILIARY FUEL TANKS IN THE 	WING BEING IGNITED BY THE HOT EXHAUST.				1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998111300446	19981113	00446	CE  	1998	11	13	AU981395         	1	19981021	G	3230	574122214	HOOK            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR UPLOCK HOOK CRACKED.						1	L	7	2 	3O				A25CE   		5	C	P45GL
1998111300447	19981113	00447	CE  	1998	11	13	AU981396         	1	19981022	G	2711	4513503225	ARM             			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON TRIM TAB ARM WORN.  INVESTIGATION FOUND THE ARM WAS MANUFACTURED FROM ALUMINIUM INSTEAD OF STEEL AND A BUS	HING HAD BEEN FITTED TO REMOVE PREVIOUS WEAR.  UNAPPROVED PART.					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1998111300448	19981113	00448	SO  	1998	11	13	AU981397         	1	19981016	G	5531		SPAR            			PIPER 	PA36  	PA36375     	7103620	SO  	LYC   	O720  	IO720D1C    	41546	EA  					VERTICAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FIN STRUCTURE EXTENSIVELY CORRODED.  FORWARD ATTACHMENT POINT, REAR SPAR AND LOWER RIB AS WELL AS THE INNER SKIN A	ND UPPER FIN STRUCTURE CORRODED.					1	L	7	1 	3O	3	O		A10SO   	1E15
1998121800127	19981218	00127	CE  	1998	12	18	AU981398         	1	19980806	G	2913	105932B	POWER PACK      			BEECH 	23    	C24R        	1151254	CE  	LYC   	O360  	IO360A1B6   	41514	EA  					HYDRAULIC SYS	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) HYDRAULIC POWER PACK FAILURE.  LIMITED INFORMATION PROVIDED.						1	L	7	1 	3O	3	O		A1CE    	1E10
1998121800128	19981218	00128	SW  	1998	12	18	AU981399         	1	19980810	G	5330	2822	SKIN            			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2822					(AUS) RIGHT FUSELAGE CRACKED FROM THE FORWARD FACE OF THE HEATER DUCT HOLE THROUGH THE INNER INSPECTION HOLE AND UP THE 	AFT FACE OF THE CLOSURE PANEL.  CRACKING WAS HIDDEN BENEATH SOUND PROOFING.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800129	19981218	00129	SO  	1998	12	18	AU981400         	1	19981019	G	2913	3117	O RING          	PRESTOLITE  		PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  	HARTZL	HCC2Y	HCC2YR2     	GL  	HYDRAULIC PUMP	FAILED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					3117					(AUS) HYDRAULIC PUMP BODY TO ELECTRIC MOTOR `O' RING SEAL DETERIORATED ALLOWING OIL CONTAMINATION OF THE ELECTRIC MOTOR.						1	L	7	2 	3O	3	O		A19S0   	E286	5	C	P920
1998121800130	19981218	00130	EU  	1998	12	18	AU981401         	1	19981012	G	2611	72111211000	SMOKE DETECTOR  			SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  	ROTOL	R354	R3544123F13 	NE  	CARGO BAY	MALFUNCTIONED   	W				F				ACTIVATE FIRE EXT.      				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) CARGO BAY SMOKE DETECTOR FAULTY.  FALSE INDICATION RESULTED IN FIRING OF THE CARGO BAY FIRE BOTTLE.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6	6	C	P61GL
1998121800131	19981218	00131	NE  	1998	12	18	AU981402         	2	19981012	G	7200		ENGINE          			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					NR 4	OVERHEATED      	W				K				NONE                    				M			OVER TEMP                 			TO	TAKEOFF        	1			AU	S 										(AUS) NR 4 ENGINE EXPERIENCED HIGH EGT DURING TAKEOFF.  LIMITED INFORMATION PROVIDED.						2	L	7	4 	4F	4	F		A20WE   	E12EU
1998121800132	19981218	00132	NM  	1998	12	18	AU981403         	1	19981008	G	2430		GENERATOR       			BOEING	757   	757200      	1384950	NM  										DC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT GENERATOR SYSTEM FAILED.  LIMITED INFORMATION PROVIDED.						2	L	7	2 	4F			RT	A2NM
1999012100001	19990121	00001	EA  	1999	1	21	AU981404         	2	19981028	G	8530	LW14995	SPRING          			SOCATA	TB10  	TB10TOBAGO  	8680696	EU  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3370936A			(AUS) NR 2 CYLINDER INLET VALVE PUSH ROD TUBE COVER RETAINING SPRING BROKEN.    PART TC:  1,711.						1	L	7	1 	3O	3	O	NT	A51EU   	E286	5	C	P920
1998121800133	19981218	00133	EA  	1998	12	18	AU981405         	2	19981023	G	8550	DKLM22X1590GRDKJ	LINE            								LYC   	O360  	O360A1F6    	41514	EA  					ENGINE OIL	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) ENGINE OIL HOSE FLATTENED WHEN BENT (NOT EXCESSIVELY) AND WHEN STRAIGHTENED OUT AGAIN THE FLATTENED AREA REMAINED.	  HOSE APPEARS TO BE CORE WITH A SINGLE LAYER OF STAINLESS STEEL BRAIDING.										3	O			E286
1998121800134	19981218	00134	SW  	1998	12	18	AU981406         	1	19981023	G	6230	204011402	SWASHPLATE      		204011400025	BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			4809 		GD10356					(AUS) MAIN ROTOR SWASHPLATE INNER LUG CRACKED THROUGH BUSHING HOLE.    PART TC:  5,061.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998121800135	19981218	00135	EA  	1998	12	18	AU981407         	2	19981026	G	8520	LW12164	CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2496 		L225968A		L225968A			(AUS) CRANKSHAFT COUNTERWEIGHT BUSHING P/N 73810 BROKE UP ALLOWING BUSH TO SPIN IN THE BORE AND DAMAGE THE CRANKSHAFT.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998121800136	19981218	00136	SW  	1998	12	18	AU981408         	1	19981026	G	6520	ADKP00672	SUPPORT         		20603300411A	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					T/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					ADKP00672					(AUS) TAIL ROTOR GEARBOX SUPPORT CRACKED ON LT SIDE.  CRACK STARTS AT A COUNTERSUNK RIVET AND RUNS THROUGH TO THE UPPER 	SKIN EDGE.  SUBMITTER SUSPECTS CAUSED BY INCORRECT SHIMMING BETWEEN THE SKIN AND THE BELLCRANK LONGERON.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998121800137	19981218	00137		1998	12	18	AU981409         	4	19981015	G	2565		ACTUATOR        			BOEING	767   	767338      		NM  	GE    	CF6   	CF680C      		GL  					ESCAPE SLIDE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OFF-WING ESCAPE SLIDE COMPARTMENT DOOR UNLATCHING ACTUATOR FAILED TO UNLATCH THE DOOR SUFFICIENTLY FOR DOOR DEPLOY	MENT ACTUATORS TO OPERATE.					2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
1998121800138	19981218	00138		1998	12	18	AU981410         	4	19981008	G	2565	7A144710	SLIDE           			BOEING	747   	747238B     	1384828	NM  										PASSENGER DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DOOR 1 RT SIDE ESCAPE SLIDE FAILED TO INFLATE CORRECTLY AND APPEARED TO CONTACT THE LOWER DOOR BUSTLE/HINGE CAUSIN	G THE SLIDE TO TEAR.					2	L	7	4 	4F				A20WE
1998121800139	19981218	00139	NM  	1998	12	18	AU981411         	1	19981022	G	3244		TIRE            			BOEING	767   	767338      		NM  	GE    	CF6   	CF680C      		GL  					MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR WHEEL 2F TIRE TREAD SEPARATED.						2	L	7	2 	4F	4	F	RT	A1NM    	E23EA
1998121800140	19981218	00140		1998	12	18	AU981412         	4	19981012	G	6113	611M20301	BACKPLATE       													MCAULY	1A135	1A135BRM    	GL  	SPINNER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								OH036		(AUS) PROPELLER SPINNER FRONT ATTACHMENT PLATE CRACKED AROUND THE EDGES OF THE MOUNT BOLT WASHERS.    PART TC:  118.																5	N	P842
1998121800141	19981218	00141	WP  	1998	12	18	AU981413         	1	19981028	G	6320	A0061	SUMP            	ROBSIN      	A0061       	ROBSIN	R22   	R22ALPHA    	7640104	WP  	LYC   	O320  	O320B2C     	41508	EA  					M/R GEARBOX	CLOGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			138  		1817					(AUS) RECENTLY OVERHAULED MAIN TRANSMISSION CONTINUALLY RUNNING HOT.  INVESTIGATION FOUND THAT THE SUMP WAS SLUDGED.						1	G	7	1 	3O	3	O		H10WE   	E274
1998121800142	19981218	00142	EA  	1998	12	18	AU981414         	2	19981028	G	8530	LW117751	PLUG            								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3407136A			(AUS) NR 1 CYLINDER PISTON PIN PLUG WORN EXCESSIVELY.    PART TC:  1,773.											3	O			E286	5	C	P27EA
1998121800143	19981218	00143	EA  	1998	12	18	AU981415         	2	19981015	G	8530	LW11775	PLUG            								LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L3422636A			(AUS) PISTON PIN PLUG WORN.    PART TC:  471.											3	O			E286	5	C	P27EA
1998121800144	19981218	00144	NM  	1998	12	18	AU981416         	1	19980710	G	3040		WARNING LIGHT   			BOEING	737   	737377      		NM  										COCKPIT	ILLUMINATED     	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) LT SIDE WINDOW OVERHEAT LIGHT ILLUMINATED AND STAYED ON FOR APPROXIMATELY 1.5 HOURS.  EXTENSIVE INVESTIGATION OF T	HE ELECTRICAL SYSTEM COULD FIND NO FAULTS.					2	L	7	2 	4F			RT	A16WE
1998121800145	19981218	00145	SW  	1998	12	18	AU981417         	1	19981030	G	6720	206010743013	TUBE            			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					PITCH CONTROL	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							800659			(AUS) TAIL ROTOR PITCH CONTROL TUBE FITTED TO THE AIRCRAFT WAS A DIFFERENT PART NUMBER TO THE ONE IN THE MAINTENANCE DOC	UMENTATION.    PART TC:  13,461.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800146	19981218	00146	EU  	1998	12	18	AU981418         	1	19981030	G	2821		RETAINER        		1433002     	BNORM 	BN2   	BN2A20      	1520220	EU  	LYC   	O540  	IO540K1B5   	41532	EA  	HARTZL	HCC2Y	HCC2YK2     	GL  	FUEL FILTER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT ENGINE FUEL FILTER BOWL RETAINER BROKEN.						1	H	7	2 	3O	3	O		A17EU   	1E4	5	C	P920
1998121800147	19981218	00147	CE  	1998	12	18	AU981419         	1	19981023	G	3244	600X6	TIRE            			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	RT MLG	DEFLATED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							294527R			(AUS) RIGHT TIRE DEFLATED DURING LANDING.  NIL DAMAGE FOUND TO THE TIRE.  SUBMITTER SUSPECTED VALVE MAY HAVE BEEN DETACH	ED BY A STONE. THE LANDING STRIP WAS VERY ROUGH AND STONY.					1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL
1998121800148	19981218	00148	CE  	1998	12	18	AU981420         	1	19981029	G	2436	C6110050103	REGULATOR       			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	DC SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							294527R			(AUS) VOLTAGE REGULATOR SUSPECT FAULTY.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL
1998121800149	19981218	00149	SO  	1998	12	18	AU981421         	1	19981031	G	2844	55000064	LINE            			GULSTM	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320E2G     	41508	EA  					PRESS INDICATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ALUMINIUM FUEL PRESSURE LINE FROM FIREWALL REAR FITTING TO FUEL PRESSURE GAUGE CORRODED THROUGH FROM CONTACT WITH 	THE STEEL WIRE OF THE DE-MISTER SCAT HOSE.  FUEL LEAKAGE.					1	L	7	1 	3O	3	O		A16EA   	E274
1998121800150	19981218	00150	SO  	1998	12	18	AU981422         	1	19981031	G	3040	54060014	DUCT            			GULSTM	AA5   	AA5         	0631410	SO  	LYC   	O320  	O320E2G     	41508	EA  					WINDSHIELD	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DE-MISTER SCAT HOSE RUBBING ON FUEL PRESSURE PIPE.  REF:  OPERATOR CONTROL NR AU981421 FOR ADDITIONAL INFORMATION.						1	L	7	1 	3O	3	O		A16EA   	E274
1998121800151	19981218	00151	CE  	1998	12	18	AU981423         	1	19981027	G	7721	13723	SENSOR          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	CYLINDER HEAD	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					294803R		294803R			(AUS) ENGINE CYLINDER HEAD TEMPERATURE PROBE BROKEN OFF SENDING UNIT.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P47GL
1998121800152	19981218	00152	WP  	1998	12	18	AU981425         	1	19981025	G	3234	4209829	VALVE           			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			122  		5A5B306					(AUS) LANDING GEAR SELECTOR VALVE FAULTY.  INVESTIGATION FOUND THAT THE PRESSURE TRANSFER BOBBINS WERE TIGHT IN THE BORE	S CAUSING LOSS OF FACE CONTACT WITH THE ROTOR.					2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603
1998121800153	19981218	00153	SO  	1998	12	18	AU981426         	2	19981008	G	8520	653877	LIFTER          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							2948154			(AUS) HYDRAULIC EXHAUST VALVE LIFTER DAMAGED WITH SURFACE HARDENING CHIPPING AWAY.    PART TC:  670.						1	H	7	1 	3O	3	O		3A21    	E5CE	5	C	P21EA
1998121800154	19981218	00154	SO  	1998	12	18	AU981427         	2	19980911	G	7414	IO357586	GEAR            	BENDIX      	6RN201      	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MAGNETO	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1761 		E179508ER					(AUS) MAGNETO DISTRIBUTOR GEAR DAMAGED.  EIGHT CONSECUTIVE TEETH STRIPPED.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1998121800155	19981218	00155	NM  	1998	12	18	AU981428         	1	19981024	G	3610	656620111	DUCT            			BOEING	737   	737376      		NM  										APU BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) APU BLEED AIR DUCT CRACKED CAUSING BLEED AIR TO ACTIVATE APU FIRE WARNING SYSTEM.						2	L	7	2 	4F			RT	A16WE
1998121800156	19981218	00156	NM  	1998	12	18	AU981429         	1	19981031	G	2780	251N50999	TORQUE TUBE     			BOEING	757   	757200      	1384950	NM  										LE FLAP	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT LEADING EDGE SLAT TORQUE TUBE LOCATED BETWEEN NR 4 AND NR 5 SLATS DAMAGED DUE TO ABRASION WITH THE PRE-COOLER	 TEMPERATURE BULB P/N 56133A WIRING.					2	L	7	2 	4F			RT	A2NM
1998121800157	19981218	00157	EU  	1998	12	18	AU981430         	1	19981102	G	3222	1155204	FORK            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O235  	O235H2C     	41505	EA  	SNSNCH	72C	72CK        	EA  	NLG	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR FORK DELAMINATED.  FORK IS CONSTRUCTED OF FIBERGLASS MATERIAL.  PART TC:  1,019.						1	L	7	1 	3O	3	O	NT	A57EU   	E223	5	N	P9045
1998121800158	19981218	00158	GL  	1998	12	18	AU981431         	3	19980820	G	6114	D4804C401	HUB             			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	D3A34	D3A34C401   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					950605			950605		(AUS) PROPELLER HUB SEVERELY CORRODED.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
1998121800159	19981218	00159	SW  	1998	12	18	AU981432         	1	19980824	G	6230	206040036103	BEARING         			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					M/R MAST	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					BP0000070					(AUS) MAIN ROTOR MAST UPPER BEARING FAULTY.  INVESTIGATION FOUND ONE BALL TO HAVE SEVERE PITTING/BRINELLING WITH THE OUT	ER RACE SHOWING SIGNS OF FAILURE.    PART TC:  1,224.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800160	19981218	00160	NE  	1998	12	18	AU981433         	2	19981019	G	7323	661002010A	GOVERNOR        								PWA   	PWA120	PW125B      		NE  					LT ENGINE	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							124028			(AUS) LEFT ENGINE OVERSPEED GOVERNOR FAULTY.											4	T			E20NE
1998121800161	19981218	00161	SW  	1998	12	18	AU981434         	1	19981016	G	5730	DC874B	SKIN            	SWRNGN      		FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	WS 202/217	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					DC874B					(AUS) RIGHT WING LEADING EDGE DAMAGED BETWEEN STA 202.250 AND STA 217.500 BY A BIRDSTRIKE. SOME RIPPLING OF THE UPPER AN	D LOWER SKINS TO THE REAR OF THE FRONT SPAR EVIDENT.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998121800162	19981218	00162	NM  	1998	12	18	AU981435         	1	19981028	G	5751	85740152005	AILERON         			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					LEFT	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AILERON TIP DAMAGED IN A GROUND ACCIDENT.    PART TC:  24,413.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121800163	19981218	00163	EU  	1998	12	18	AU981436         	1	19981020	G	3411		LINE            			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					PITOT SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) PITOT SYSTEM LEAKING FROM SPEED COMM AND AIR SPEED TRANSDUCER.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998121800164	19981218	00164	CE  	1998	12	18	AU981437         	1	19980920	G	3246	D30259	WHEEL           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) WHEEL HUB CRACKED INTERNALLY BETWEEN SCREW HOLES. CRACKING IS NOT VISIBLE UNLESS THE WHEEL IS DISMANTLED.    PART 	TC:  4,960.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA
1998121800165	19981218	00165	CE  	1998	12	18	AU981438         	1	19981026	G	3340	6119805	STROBE          	GRIMES      	3011725REVD 	CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	FUSELAGE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					2209					(AUS) STROBE LIGHT CIRCUIT BOARD BURNT.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998121800166	19981218	00166	CE  	1998	12	18	AU981439         	1	19981029	G	5540	101630000613	STRUCTURE       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	RUDDER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER DAMAGED BY COLLISION WITH ANOTHER AIRCRAFT.    PART TC:  14,326.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1998121800167	19981218	00167	NM  	1998	12	18	AU981440         	1	19980922	G	5312		BULKHEAD        			BOEING	737   	737377      		NM  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD PRESSURE BULKHEAD FORWARD FACE LOCATED AT STA 178 CRACKED IN THE FOLLOWING AREAS:  1. FORWARD PRESSURE BUL	KHEAD WEBS CRACKED IN FOUR PLACES IN THE AREA BELOW THE RADAR ANTENNA MOUNT POINTS.  2.  VERTICAL CHORD RADIUS ON THE RE	AR FACE OF THE BULKHEAD LOCATED  AT LBL 5.7 LEVEL WITH THE HORIZONTAL STIFFENER AT WL 184 - CRACK LENGTH 20 MM (0.787 IN	CH).  3.  LT AND RT SIDE CHORDS AT COCKPIT FLOOR LEVEL WL 207 - LT CRACK LENGTH 20 MM (0.787 INCH) - RT CRACK LENGTH 8 M	M (0.314 INCH) FOUND DURING INSPECTION IAW ER B73-53-10-39D.		2	L	7	2 	4F			RT	A16WE
1998121800168	19981218	00168	WP  	1998	12	18	AU981441         	2	19981029	G	7200	TPE33112UHR701G	ENGINE          			FRCHLD	SA227 	SA227DC     	3377521	SW  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	LEFT	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 							P70207			(AUS) LEFT ENGINE EGT, TORQUE AND WF FLUCTUATIONS.  ENGINE SHUT DOWN.  EXTENSIVE INVESTIGATION AND GROUND RUNS COULD FIN	D NO FAULTS WITH THE ENGINE.  AIRCRAFT HAS RETURNED TO SERVICE WITH NO FURTHER PROBLEMS.    PART TC:  4,812.					2	L	7	2 	4T	4	T	RT	A18SW   	E4WE	6	C	3PNE
1998121800169	19981218	00169	CE  	1998	12	18	AU981442         	1	19981104	G	3213	51411036	STRUT           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR STRUT CRACKED IN AREA OF TORQUE LINK ATTACHMENT.  CRACK CONFIRMED USING DYE PENETRANT INSP	ECTION.  PART TC:  10,036.					1	L	7	2 	3O	3	O		A7CE    	E8CE
1998121800170	19981218	00170	CE  	1998	12	18	AU981443         	1	19981104	G	3213	51411035	STRUT           			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR STRUT CRACKED IN AREA OF TORQUE LINK ATTACHMENT.  CRACK CONFIRMED USING DYE PENETRANT INSPE	CTION.  PART TC:  10,036.					1	L	7	2 	3O	3	O		A7CE    	E8CE
1998121800171	19981218	00171	EU  	1998	12	18	AU981445         	1	19981106	G	5312		BULKHEAD        			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STRUCTURE CRACKED ON LT AND RT SIDES IN AREA ADJACENT TO THE FORWARD UPPER TAILPLANE ATTACHMENT AREA WHER	E THE FUSELAGE SHELL JOINS THE BULKHEAD.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800172	19981218	00172	EU  	1998	12	18	AU981446         	1	19981109	G	5321	115C2255	FLOOR PANEL     			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) COCKPIT LT FLOOR PANEL CRACKED IN AREA ADJACENT TO THE RT RUDDER PEDAL.    PART TC:  1,420.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800173	19981218	00173	EU  	1998	12	18	AU981447         	1	19981026	G	5321	115C2255	FLOOR PANEL     			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT COCKPIT FLOOR ASSEMBLY CRACKED.    PART TC:  1,300.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800174	19981218	00174	EU  	1998	12	18	AU981448         	1	19981026	G	5321	115C2256	FLOOR PANEL     			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT COCKPIT FLOOR PANEL CRACKED.    PART TC:  1,300.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800175	19981218	00175	NE  	1998	12	18	AU981449         	2	19981103	G	7321		INDICATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					COCKPIT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							120729			(AUS) ENGINE EXPERIENCED A TORQUE SWING OF PLUS OR MINUS 4 PERCENT.  INVESTIGATION WAS UNABLE TO RE-PRODUCE THE FAULT. E	CU, TSCU, AND TORQUE PROBE CONNECTORS CLEANED AS A PRECAUTION.  NO FURTHER OCCURRENCES.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121800176	19981218	00176	SO  	1998	12	18	AU981450         	1	19981109	G	3260	MS272401	SWITCH          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR UPLOCK MICROSWITCH FAULTY.						1	L	7	2 	4T	4	T		A21SO   	E4EA	6	C	P15EA
1998121800177	19981218	00177	CE  	1998	12	18	AU981451         	1	19981109	G	3240	26410276	LINE            			CESSNA	208   	208B        	2073701	CE  										BRAKE SYSTEM	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT BRAKE HOSE FAILED AT END FITTING ON BRAKE ASSEMBLY.  HOSE CAME OUT OF END FITTING DUE TO FAULTY MANUFACTURE.						1	H	7	1 	3T				A37CE
1998121800178	19981218	00178	NM  	1998	12	18	AU981452         	1	19981030	G	5280	65C332197SP	DOOR            			BOEING	737   	737476      		NM  										MLG	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR CENTER DOOR AND FITTINGS DAMAGED.						2	L	7	2 	4F			RT	A16WE
1998121800179	19981218	00179	NE  	1998	12	18	AU981453         	2	19980903	G	7250		NOZZLE          								GE    	CF6   	CF680A      	30025	NE  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8082 				580242			(AUS) HIGH PRESSURE TURBINE STAGE TWO NOZZLE SEGMENTS (3 OFF) CRACKED.											4	F			E13NE
1998121800180	19981218	00180	NM  	1998	12	18	AU981454         	1	19980827	G	5311		FRAME           			BOEING	747   	747312      	1384932	NM  										BS 1265	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT SIDE FUSELAGE FRAME WEB LOCATED AT STA 1265 CRACKED.  FOUND DURING INSPECTION IAW SB 747-53A2416.						2	L	7	4 	4F			RT	A20WE
1998121800181	19981218	00181	SW  	1998	12	18	AU981455         	1	19981030	G	2910	27B10322682	LINE            			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	FAILED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) STAINLESS STEEL HYDRAULIC PIPE LOCATED IN THE LEFT ENGINE NACELLE AREA FAILED.  PIPE WAS FITTED IN JULY 1998.    P	ART TC:  484.					2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998121800182	19981218	00182	EU  	1998	12	18	AU981456         	1	19981023	G	5321	115C2255	PANEL           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FLOOR PANEL ASSEMBLY CRACKED.    PART TC:  1,498.						1	L	7	1 	3O	3	O	NT	A57EU   	E286
1998121800183	19981218	00183	EU  	1998	12	18	AU981457         	1	19981023	G	5321	115C2256	PANEL           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT COCKPIT FLOOR PANEL ASSEMBLY CRACKED.    PART TC:  1,498.						1	L	7	1 	3O	3	O	NT	A57EU   	E286
1998121800184	19981218	00184	SO  	1998	12	18	AU981458         	1	19981106	G	5753		SHOE            			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP DISAGREEMENT.  INVESTIGATION FOUND A FLAP BONDING SHOE DISPLACED AND LOADING THE LT OUTBOARD FLAP TRACK.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998121800185	19981218	00185	SW  	1998	12	18	AU981459         	1	19981105	G	2720	2672008029	PUSHROD         			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	RUDDER PEDDLE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PILOT AND COPILOT RUDDER PEDAL PUSH RODS INCORRECTLY INSTALLED.  THE PUSH RODS WERE INSTALLED ON TOP OF THE BELLCR	ANKS ALLOWING THE PUSH ROD LOCK WIRE TO CONTACT AND SCORE THE CROSSOVER ROD.  A FLEET INVESTIGATION FOUND THE PUSH RODS 	ON VH-WBQ TO ALSO BE INCORRECTLY INSTALLED.				2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998121800186	19981218	00186	SO  	1998	12	18	AU981460         	1	19980915	G	8120	AO91709001	TURBOCHARGER    			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	FAILED          	W				K				NONE                    				E			VIBRATION/BUFFET          			CL	CLIMB          	1			AU	S 			296  		L218868A		L218868A			(AUS) ENGINE TURBOCHARGER FAILED.  SEVERE METAL CONTAMINATION OF THE ENGINE BEARINGS AND OIL SYSTEM.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998121800187	19981218	00187	EU  	1998	12	18	AU981461         	1	19981107	G	3260	801801	SENSOR          			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT MLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) EFT MAIN LANDING GEAR UPLOCK PROXIMITY SENSOR FAULTY.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998121800188	19981218	00188	SO  	1998	12	18	AU981462         	2	19981109	G	7414	IO382585	MAGNETO         			CESSNA	404   	404CESSNA   	2075901	CE  	CONT  	O520  	GTSIO520M   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	RT ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					C189316FR		606777N			(AUS) RIGHT ENGINE RT MAGNETO CONTACT POINTS FAILED.						1	L	7	2 	3O	3	O		A25CE   	E7CE	5	C	P45GL
1998121800189	19981218	00189	EA  	1998	12	18	AU981463         	2	19980905	G	8520	LW1934185	CAMSHAFT        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			968  		L203568A		L203568A			(AUS) NR 5 CYLINDER EXHAUST CAM LOBE WAS WORN BEYOND MANUFACTURER'S SPECIFICATIONS.  THE LOBE WAS EXCESSIVELY WORN FROM 	WHAT APPEARS TO BE METAL FATIGUE. FAULT FOUND DURING SCHEDULED 1000 HOUR INSPECTION. THE ENGINE WAS FACTORY OVERHAULED O	N THE 15NOV96.				1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998121800190	19981218	00190	EU  	1998	12	18	AU981464         	1	19981111	G	3244	9006	PATCH           			STBROS	SD3   	SD360       	8100606	EU  	PWA   	PT6   	PT6A67R     	52043	NE  	HARTZL	HCA6A	HCA6A3      	NE  	TIRE	SEPARATED       	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					NQ041					(AUS) NOSE WHEEL TIRE BALANCE PATCH SEPARATED FROM THE INSIDE OF THE TIRE.						2	H	7	2 	4T	4	T		A41EU   	E26NE	6	C	P14NE
1998121800191	19981218	00191		1998	12	18	AU981466         	4	19981108	G	2312	PT200	SWITCH          	KING        	KMA2004     	DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  	HAMSTD	23E	23E50       	NE  	VHF COMM	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					22387					(AUS) AUDIO SELECTOR PANEL SUSPECT FAULTY.  PANEL REMOVED AND TESTED WITH NO FAULT FOUND.  FURTHER INVESTIGATION FOUND A	 FAULTY PRESS-TO-TRANSMIT (PTT) SWITCH.					2	L	7	2 	4R	4	R		A669    	5E4	6	C	P603
1998121800192	19981218	00192	NM  	1998	12	18	AU981467         	1	19980731	G	5313		STRINGER        			BOEING	737   	737377      		NM  										BS 277	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE STRUCTURE CONTAINED FIVE CRACKS IN AN AREA LOCATED FORWARD OF THE FORWARD SERVICE DOOR IN THE FOLLOWING L	OCATIONS:  ONE CRACK IN STRINGER 14R AT THE FORWARD END OF THE WEB IMMEDIATELY AFT OF THE FRAME AT STA 2772.  ONE CRACK 	IN STRINGER 15R TO FRAME AT STA 277 STRINGER TIE P/N 69-37411-2 3.  THREE STIFFENER ANGLES ATTACHING WEBS TO FRAME AT ST	A 294.5 CRACKED AT AFT END JOGGLE TO FRAME CRACK LENGTHS 6.35 MM (0.25 INCH) TO 76.2MM (3 INCH).			2	L	7	2 	4F			RT	A16WE
1998121800193	19981218	00193	NM  	1998	12	18	AU981469         	1	19981112	G	3297		WIRE            		864202      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					NLG	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR PROXIMITY SWITCH CANNON PLUG WIRING FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121800194	19981218	00194	SO  	1998	12	18	AU981470         	1	19981014	G	3710	2H2211	REGULATOR       			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  	HARTZL	HCE3Y	HCE3YR2     	GL  	VACUUM SYS	INCORRECT PART  	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					317405201					(AUS) VACUUM PUMP REGULATORS WERE THE INCORRECT PART FOR THE MODEL OF VACUUM PUMP FITTED.  REGULATORS P/N 2H22-11 WERE F	ITTED INSTEAD OF THE CORRECT P/N 2H30-1 TYPE USED WITH P/N 215CC AND P/N 216CW PUMPS.					1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1998121800195	19981218	00195	NE  	1998	12	18	AU981471         	2	19981109	G	7210	311292301	GEAR            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	GEARBOX	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PCE945321		PCE95432			(AUS) PROPELLER REDUCTION GEARBOX GEAR CORRODED.    PART TC:  1,710.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE
1998121800196	19981218	00196	NM  	1998	12	18	AU981472         	1	19981008	G	2761	654494710	HOUSING         			BOEING	737   	737377      		NM  										SPOILER ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4375					(AUS) RIGHT INBOARD SPOILER OUTBOARD ACTUATOR HOUSING PIVOT LUG BROKEN.  SUBMITTER SUSPECTS CAUSED BY FATIGUE CRACKING O	RIGINATING FROM CORROSION PITTING OF THE HOUSING PIVOT BEARING BORE.    PART TC:  33,875.					2	L	7	2 	4F			RT	A16WE
1998121800197	19981218	00197	NM  	1998	12	18	AU981473         	1	19981019	G	2761	654494710	HOUSING         			BOEING	737   	737377      		NM  										SPOILER ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4323					(AUS) LEFT INBOARD GROUND SPOILER OUTBOARD ACTUATOR HOUSING PIVOT LUG BROKEN.  SUBMITTER SUSPECTS CAUSED BY FATIGUE CRAC	KING ORIGINATING FROM CORROSION PITTING IN THE HOUSING PIVOT BEARING BORE.    PART TC:  34,043.					2	L	7	2 	4F			RT	A16WE
1998121800198	19981218	00198	NM  	1998	12	18	AU981474         	1	19981101	G	2761	654494710	HOUSING         			BOEING	737   	737377      		NM  										SPOILER ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4552					(AUS) NR 5 RT INBOARD GROUND SPOILER OUTBOARD ACTUATOR HOUSING PIVOT LUG BROKEN.  CAUSED BY TWO FATIGUE CRACKS ORIGINATI	NG FROM CORROSION PITTING IN THE HOUSING PIVOT BEARING BORE.    PART TC:  34,921.					2	L	7	2 	4F			RT	A16WE
1998121800199	19981218	00199	NM  	1998	12	18	AU981475         	1	19980902	G	5311		FRAME           			BOEING	747   	747312      	1384932	NM  										BS 1265	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME WEB LOCATED AT BS 1265 LT AND RT SIDES CRACKED IN THE FOLLOWING AREAS:  1.  LT SIDE AT 12 O'CLOCK P	OSITION.   2.  RT SIDE AT 3 O'CLOCK POSITION.  FOUND DURING INSPECTION IAW SB 747-53A2416.					2	L	7	4 	4F			RT	A20WE
1998121800200	19981218	00200	NM  	1998	12	18	AU981476         	1	19981009	G	2910	272T4300123	LINE            			BOEING	767   	767277      		NM  	GE    	CF6   	CF680A      	30025	NE  					HYDRAULIC SYS	DAMAGED         	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR `DOWN' TITANIUM HYDRAULIC PIPE LOCATED AT FS 625 BETWEEN THE FORWARD CARGO HOLD LEFT SIDEWALL AN	D THE FUSELAGE SKIN DENTED AND CRACKED.  LEAKING HYDRAULIC FLUID MIST IN CABIN.  PIPE HAD BEEN DAMAGED DUE TO PREVIOUS M	AINTENANCE.    PART TC:  41.928.				2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998121800201	19981218	00201	NM  	1998	12	18	AU981477         	1	19980829	G	2761	654494710	HOUSING         			BOEING	737   	737377      		NM  										SPOILER ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					4532					(AUS) LT INBOARD GROUND SPOILER ACTUATOR HOUSING PIVOT LUG BROKEN.  CRACK WAS CAUSED BY FATIGUE ORIGINATING FROM CORROSI	ON PITTING IN THE PIVOT LUG BEARING BORE.  PART TC:  34,028.					2	L	7	2 	4F			RT	A16WE
1998121800202	19981218	00202	NM  	1998	12	18	AU981478         	1	19981109	G	4920	GTCP331200A	APU             	GARRTT      	GTCP331200A 	BOEING	767   	767204      		NM  	GE    	CF6   	CF680A      	30025	NE  					APU BAY	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 							319			(AUS) APU FAILED.  REAR BEARING HOUSING AND OIL SCAVENGE PUMP FOUND ON THE RAMP.    PART TC:  27,149.						2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998121800203	19981218	00203	SO  	1998	12	18	AU981479         	2	19981006	G	8530	SA530830	PIN             	SUPAIRPART  		CESSNA	150   	A150L       	2071828	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							254167			(AUS) NR 2 CYLINDER PISTON PIN END PLUG WORN AND DAMAGED.  METAL CONTAMINATION OF ENGINE OIL SYSTEM.    PART TC:  654.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998121800204	19981218	00204	NM  	1998	12	18	AU981480         	1	19981112	G	3350		SIGN            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					ROW 4	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY EXIT LOCATED AT ROW 4 LT WAS INCORRECTLY INSTALLED PREVENTING PRESSURIZATION.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121800205	19981218	00205	EU  	1998	12	18	AU981481         	1	19980821	G	2130		VALVE           			AIRBUS	320   	A320212     		EU  										CABIN	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN OUTFLOW VALVE SUSPECT FAULTY.						2	L	7	2 	4F			RT	A28NM
1998121800206	19981218	00206	NM  	1998	12	18	AU981482         	1	19981008	G	3242	161T10191	PIN             			BOEING	767   	767324      		NM  	GE    	CF6   	CF680C2B7   		NE  					BRAKE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 6 BRAKE HOUSING ANTI-ROTATION PIN HAD A SMALL AREA OF CHROME PLATING MISSING.  AREA OF PLATING MISSING WAS APPR	OXIMATELY 12.7  MM BY 12.7 MM (0.5 INCH BY 0.5 INCH).					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998121800207	19981218	00207	CE  	1998	12	18	AU981483         	1	19981007	G	5220		DOOR            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	EMERGENCY EXIT	STICKING        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) EMERGENCY EXIT DOOR WAS UNABLE TO BE OPENED DUE TO IT BEING GLUED IN AND SEALED WITH PLASTIC FILLER.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1998121800208	19981218	00208	SW  	1998	12	18	AU981485         	1	19981112	G	2701	MS2764216	BEARING         			FRCHLD	SA227 	SA227DC     	3377521	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	COCKPIT	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AILERON CONTROL SYSTEM BEARING LOCATED IN THE PILOT'S CONTROL WHEEL STIFF AND BINDING.						2	L	7	2 	4T			RT	A18SW   		6	C	3PNE
1998121800209	19981218	00209	EU  	1998	12	18	AU981486         	1	19981116	G	2611	72111211000	SMOKE DETECTOR  			SAAB  	SF340 	340B        	7860101	EU  	GE    	CT7TP 	CT79B       	30030	NE  	ROTOL	R375	R3754123F21 	NE  	CARGO BAY	FAULTY          	W				K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) CARGO BAY SMOKE DETECTOR FAULTY.  FALSE FIRE WARNING.						2	L	7	2 	4T	4	T	RT	A52EU   	E8NE	6	C	P17NE
1998121800210	19981218	00210	CE  	1998	12	18	AU981487         	1	19981025	G	5343		BLOCK           			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR OUTBOARD BLOCK CRACKED IN LOWER RIGHT CORNER.						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998121800211	19981218	00211	CE  	1998	12	18	AU981488         	1	19981025	G	5320		POST            			CESSNA	182   	182K        	2072724	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT AND RIGHT SIDE DOOR POSTS CRACKED IN CORNER.  CRACK LENGTH 6.35 MM (0.25 INCH).						1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998121800212	19981218	00212		1998	12	18	AU981489         	4	19980731	G	2370	51352	CVR             			BOEING	767   	767324      		NM  	GE    	CF6   	CF680C2B7   		NE  					COCKPIT	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					51352					(AUS) COCKPIT VOICE RECORDER INOPERATIVE.  WORKSHOP INSPECTION FOUND THE FOLLOWING DEFECTS:  1.  TAPE STALLED AT CAPSTAN	.  2.  TAPE WORN.  3. TAPE GUIDE ROLLER WORN AND BEARINGS CONTAMINATED.  4.  DRIVE BELT SLIPPING.  5.  DESK ASSEMBLY CON	TAMINATED.   6.  EXCESSIVE CAPSTAN END PLAY.  7.  EXCESSIVE WEAR AND OXIDE BUILD-UP ON CAPSTAN SHAFT.  8.  FLYWHEEL CONT	ACTING BELT COVER.    PART TC:  22,421.			2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1998121800213	19981218	00213	NM  	1998	12	18	AU981490         	1	19981028	G	2435	23088002A	START/GEN       	LUCAS       	23088002A   	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					DC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			442  		214					(AUS) STARTER/GENERATOR WENT OFF-LINE AND COULD NOT BE RESET.  SUSPECT BRUSH END BEARING FAILED ALLOWING THE ROTOR TO CO	ME IN CONTACT WITH THE STATOR.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121800214	19981218	00214	NE  	1998	12	18	AU981491         	2	19981115	G	7313		O RING          			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					NR 4 ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 							LFO5290			(AUS) NR 4 ENGINE NR 7 FUEL NOZZLE LEAKING FUEL.  SUSPECT DUE TO FAILURE OF THE NOZZLE `O' RING SEAL.  SOME HEAT DAMAGE 	TO THE RT OVERSPEED PICKUP LEAD.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998121800215	19981218	00215	CE  	1998	12	18	AU981492         	1	19981114	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR TRUNNION CRACKED IN RT RADIUS.  CRACK LENGTH 8 MM (0.314 INCH).    PART TC:  15,417.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1998121800216	19981218	00216	EU  	1998	12	18	AU981493         	1	19981116	G	3610	4353C000	PRECOOLER       			BAG   	BAE146	BAE146300A  	1500267	EU  										PNEUMATIC SYS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 3 ENGINE AIR PRE-COOLER OUTER CASING CRACKED ON SEAM WELD.  CRACK LENGTH 9.525 MM (0.375 INCH).						2	H	7	4 	4F			RT	A49EU
1998121800217	19981218	00217	SO  	1998	12	18	AU981494         	1	19981111	G	3250	11595CL3062415	PIN             			GULSTM	G1159 	GIV         	3980115	SO  	RROYCE	TAY   	TAY6118     		EU  					STEERING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING GEAR STEERING SYSTEM TORQUE LINK ATTACHMENT PIN CORRODED.    PART TC:  4,550.						2	L	7	2 	4F	4	F	RT	A12EA   	E25NE
1998121800218	19981218	00218	EU  	1998	12	18	AU981495         	1	19981103	G	5712		RIB             			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING RIB CRACKED ADJACENT TO THE MLG ATTACHMENT BRACKET.  SUSPECT CAUSED BY HEAVY LANDING.    PART TC:  1,598	.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800219	19981218	00219	EU  	1998	12	18	AU981496         	1	19981026	G	5321	115C2255	PANEL           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT FLOOR ASSEMBLY CRACKED IN AREA ADJACENT TO PILOT'S RT PEDAL.    PART TC:  1,297.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800220	19981218	00220	EU  	1998	12	18	AU981497         	1	19981026	G	5321	115C2256	PANEL           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	CABIN FLOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT FLOOR ASSEMBLY CRACKED IN AREA ADJACENT TO COPILOT'S LEFT PEDAL.    PART TC:  1,297.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800221	19981218	00221	NE  	1998	12	18	AU981498         	2	19981109	G	7250	PCE94532	SEAL            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A42      	52043	NE  	MCAULY	4HFR34	4HFR34C754  	NE  	TURBINE SECTION	FAILED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 					PCE94532		PCE94532			(AUS) LOSS OF TORQUE AND ENGINE OIL PRESSURE.  SUSPECT CAUSED BY FAILURE OF NR 3 OR NR 4 BEARING OIL SEAL DUE TO CORROSI	ON OF THE HOUSING.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE
1998121800222	19981218	00222	CE  	1998	12	18	AU981499         	1	19981118	G	5330	12124006	SKIN            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT FUSELAGE SKIN CORRODED IN AREA OF LAP JOINT BETWEEN SKIN AND FRAME P/N 1212415-11.    PART TC:  6,471.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA
1998121800223	19981218	00223	NM  	1998	12	18	AU981500         	1	19980813	G	7922	45E041	VALVE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					OIL COOLER	FAULTY          	W				K				NONE                    				E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			AU	S 					6891106					(AUS) RIGHT ENGINE OIL COOLER VALVE ASSEMBLY FAULTY.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121800224	19981218	00224	EU  	1998	12	18	AU981501         	1	19981028	G	5712	NOPNOLISTED	RIB             			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT WING RIB CRACKED ADJACENT TO THE MLG ATTACHMENT BRACKET ON THE REAR END.  SUSPECT CAUSED BY HEAVY LANDING.  P	ART TC:  1,297.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800225	19981218	00225	EU  	1998	12	18	AU981502         	1	19981110	G	5312		FRAME           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME (BULKHEAD) ADJACENT TO THE HORIZONTAL STABILIZER FORWARD ATTACHMENT POINT CRACKED AT FRAME TO FUSEL	AGE SHELL JOINT.    PART TC:  129.					1	L	7	1 	3O	3	O	NT	A57EU   	E286
1998121800226	19981218	00226	NM  	1998	12	18	AU981503         	1	19981106	G	5230	6546921528	SKIN            			BOEING	737   	737376      		NM  										CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD CARGO DOOR CRACKED IN THREE PLACES ADJACENT TO THE AFT LOWER STOP FITTING.						2	L	7	2 	4F			RT	A16WE
1998121800227	19981218	00227	CE  	1998	12	18	AU981504         	1	19981118	G	5311	121241511	FRAME           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE FRAME CORRODED BETWEEN SKIN AND FRAME.    PART TC:  6,471.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA
1998121800228	19981218	00228	CE  	1998	12	18	AU981505         	1	19981118	G	5330	121165016	SKIN            			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE TOP SKIN CORRODED BETWEEN SKIN AND DOUBLER ANGLES AT LAP JOINT.    PART TC:  6,471.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P21EA
1998121800229	19981218	00229	EU  	1998	12	18	AU981506         	1	19981110	G	2822	476088	PUMP            			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FUEL BOOST	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRICAL FUEL PUMP FAULTY.    PART TC:1,449.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800230	19981218	00230	NE  	1998	12	18	AU981507         	1	19981112	G	2913	7665109002060	LINE            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					HYDRAULIC SYS	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 1 HYDRAULIC PUMP CASE DRAIN PIPE CHAFED BY HYDRAULIC PUMP COVER P/N 76302-07010-101.  LOSS OF HYDRAULIC FLUID. 	   PART TC:  4,567.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
1998121800231	19981218	00231	EU  	1998	12	18	AU981508         	3	19981117	G	6111	2202	SLEEVE          													CNPSL	AW2	AW2*        	EU  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								W488038W2990		(AUS) PROPELLER ROTATIONAL SLEEVES CRACKED IN BALL GROOVES.																6	C	P9EU
1998121800232	19981218	00232	NE  	1998	12	18	AU981509         	2	19981116	G	7200		ENGINE          								LYC   	ALF502	ALF502R5    	41580	NE  					NR 4	FAILED          	W				O				OTHER                   				X			ENGINE FLAMEOUT           			NR	NOT REPORTED   	1			AU	S 							LFO5151			(AUS) NR 4 ENGINE N2 FLAMED OUT.  N2 SEIZED FOR APPROXIMATELY 10 MINUTES AND THEN FREED UP AND WINDMILLED.  ENGINE REMOV	ED.										4	F			E6NE
1998121800233	19981218	00233	EA  	1998	12	18	AU981510         	2	19980930	G	8530	68326	SPRING          			BELL  	47    	47G3B       	1181026	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					L108752		L108752			(AUS) NR 1 CYLINDER INLET VALVE OUTER VALVE SPRING BROKEN.						1	G	7	1 	3O	3	O		2H3     	1E13
1998121800234	19981218	00234	NM  	1998	12	18	AU981512         	1	19980911	G	5210		LEVER           			BOEING	747   	747338      		NM  										PASSENGER DOOR	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 MAIN ENTRY DOOR TOGGLE LEVER AND STOP OUT OF ADJUSTMENT.						2	L	7	2 	4F			RT	A20WE
1998121800235	19981218	00235		1998	12	18	AU981513         	1	19981017	G	7810	12633	TAILPIPE        								RROYCE	RB211 	RB211524D419	54555	NE  					NR 3 ENGINE	FIRE            	W				K				NONE                    				O	E	A	OTHER                     	VIBRATION/BUFFET          	FLAME/FIRE                	IN	INSP/MAINT     	1			AU	S 					12633					(AUS) NR 3 ENGINE TAILPIPE FIRE.											4	F			E12EU
1998121800236	19981218	00236	NE  	1998	12	18	AU981514         	2	19981101	G	7322	FFR105MK2S	REGULATOR       								RROYCE	RB211 	RB211524D419	54555	NE  					FUEL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 4 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY.											4	F			E12EU
1998121800237	19981218	00237	NE  	1998	12	18	AU981515         	2	19981107	G	7322	FFR105MK2S	REGULATOR       			BOEING	747   	747238B     	1384828	NM  	RROYCE	RB211 	RB211524D419	54555	NE  					FUEL SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 ENGINE FUEL FLOW REGULATOR (FFR) FAULTY.						2	L	7	4 	4F	4	F		A20WE   	E12EU
1998121800238	19981218	00238	NE  	1998	12	18	AU981516         	3	19981113	G	6111	RFC11N1R6A	BLADE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	PROPELLER	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			18074		1876					(AUS) NR 1 PROPELLER NR 1 BLADE NICKEL SHEATH SEPARATED.  SHEATH CONTACTED THE RUNWAY AND THEN BOUNCED INTO NR 2 PROPELL	ER CAUSING DAMAGE TO NR 1 AND NR 2 BLADES ON THAT PROPELLER.    PART TC:  17,177.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998121800239	19981218	00239	SO  	1998	12	18	AU981517         	1	19981114	G	2750	3075001017	CONTROL UNIT    			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FLAP CONTROL UNIT FAULTY.    PART TC:  2,510.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1998121800240	19981218	00240	EU  	1998	12	18	AU981518         	1	19981119	G	5312		BULKHEAD        			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) REAR BULKHEAD/FUSELAGE SHELL JOINT CRACKED.    PART TC:  1,498.						1	L	7	1 	3O	3	O	NT	A57EU   	E286
1998121800241	19981218	00241	SO  	1998	12	18	AU981519         	2	19980904	G	8530	653446P010	CYLINDER        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					564437		564437			(AUS) NR 4 CYLINDER HEAD CRACKED.  CRACK LENGTH APPROXIMATELY 25.4 MM (1 INCH).    PART TC:  1,865.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P22EA
1998121800242	19981218	00242		1998	12	18	AU981520         	4	19981110	G	2216	06500561	SERVO           	KING        	K5271       	BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	AUTOPILOT	STICKING        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					1164					(AUS) AUTOPILOT SERVO STICKING.  UNCOMMANDED ELEVATOR PITCH DOWN RESULTED IN SEVERE DAMAGE TO THE NLG WHEN THE AIRCRAFT 	IMPACTED THE GROUND DURING LANDING.					1	L	7	2 	3T	4	T		3A20    	E4EA	6	C	P15EA
1998121800243	19981218	00243	NM  	1998	12	18	AU981521         	1	19981113	G	2810		FUEL CELL       			BOEING	737   	737476      		NM  										WING	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL LEAKING FROM FORWARD SPAR IN AREA OF NR 2 ENGINE FIRE SHUTOFF VALVE.  FUEL FLOWING ALONG LEADING EDGE AND OUT	 OF PANEL P/N 6407ON TO NR 2 ENGINE EXHAUST.					2	L	7	2 	4F			RT	A16WE
1998121800244	19981218	00244	NM  	1998	12	18	AU981522         	1	19981111	G	4920	737M49503011	APU             			BOEING	737   	737376      		NM  										APU BAY	FAILED          	W				K	F			NONE                    	ACTIVATE FIRE EXT.      			J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) APU VIBRATION AND AUTO SHUTDOWN FOLLOWED BY FIRE WARNING LIGHT.  APU FIRE BOTTLE DISCHARGED.						2	L	7	2 	4F			RT	A16WE
1998121800245	19981218	00245	NE  	1998	12	18	AU981523         	2	19981113	G	7532	310543601	VALVE           			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					COMPRESSOR	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					PCE0570		PCE0570			(AUS) COMPRESSOR BLEED VALVE DIAPHRAGM RUPTURED.    PART TC:  420.						1	H	7	1 	3T	3	T		A37CE   	E4EA
1998121800246	19981218	00246	SW  	1998	12	18	AU981524         	1	19981103	G	6322	476205302	SHAFT           			BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  					M/R GEARBOX	WORN            	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 										(AUS) MAIN TRANSMISSION FAN PULLEY ASSEMBLY GEARSHAFT SPLINES WORN.  SEE OPERATOR CONTROL NR AU981525 FOR ADDITIONAL INF	ORMATION.					1	G	7	1 	3O	3	O		2H3     	E279
1998121800247	19981218	00247	SW  	1998	12	18	AU981525         	1	19981103	G	6320	476205723	DRIVE           			BELL  	47    	47G5A       	1181034	SW  	LYC   	O435  	VO435B1A    	41516	EA  					M/R GEARBOX	STRIPPED        	W				K				NONE                    				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) MAIN TRANSMISSION FAN PULLEY DRIVE STRIPPED.  SUSPECT INCORRECTLY TORQUED AT LAST MAINTENANCE CHECK.						1	G	7	1 	3O	3	O		2H3     	E279
1998121800248	19981218	00248	SW  	1998	12	18	AU981526         	1	19981026	G	2550	SP4208UK	HOOK            			BELL  	47    	47G3B1      	1181028	SW  	LYC   	O435  	TVO435B1A   	41516	EA  					CARGO BAY	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					CAL689		L90152			(AUS) CARGO HOOK ELECTRIC RELEASE INTERMITTENT IN OPERATION.  DURING AN EMERGENCY LOAD RELEASE THE HOOK DID NOT OPEN AND	 THE AIRCRAFT CRASHED INTO THE GROUND.  AIRCRAFT WAS OPERATING IN A SWAMP AND IT IS SUSPECTED THAT WATER OR FOREIGN MATE	RIAL CAUSED THE HOOK RELEASE PROBLEM.				1	G	7	1 	3O	3	O		2H3     	1E13
1998121800249	19981218	00249	SO  	1998	12	18	AU981527         	2	19981118	G	8530		PEDESTAL        			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1600 				12389A	F4753		(AUS) NR 1 CYLINDER ROCKER PEDESTAL BROKEN.						1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998121800250	19981218	00250	CE  	1998	12	18	AU981528         	1	19981115	G	2434	991059111	ALTERNATOR      			CESSNA	172   	172R        	2072401	CE  										DC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A128136					(AUS) ALTERNATOR INTERNAL FAILURE.  CIRCUIT BREAKER TRIPPED.  BATTERY DRAINED.						1	H	7	1 	3O			NT	3A12
1998121800251	19981218	00251	EU  	1998	12	18	AU981529         	1	19981111	G	5320	A78708005	ANGLE           		A78711009   	FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					FUSELAGE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOOR FORWARD MICROSWITCH ATTACHMENT ANGLE BROKEN.    PART TC:  35,926.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998121800252	19981218	00252	EU  	1998	12	18	AU981530         	2	19981024	G	7322	848237	LEVER           		6432391     						ROTAX 	912   	ROTAX912    	55555	EU  					FUEL CONTROL	CORRODED        	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) THROTTLE VALVE LEVER AND GRADUATED SLEEVE P/N 847740 SEIZED TOGETHER DUE TO CORROSION.  THROTTLE CABLE FAILED.											3	I			EXPE3I
1998121800253	19981218	00253	NE  	1998	12	18	AU981531         	2	19981112	G	7200	LTS101750B1	ENGINE          			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 2	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					LE45612		LE45612			(AUS) NR 2 ENGINE SPOOLED DOWN TO FLIGHT IDLE.  INSPECTION AND GROUND RUN COULD FIND NO FAULTS.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998121800254	19981218	00254	NE  	1998	12	18	AU981532         	2	19980911	G	7260	430126801	BEARING         			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					NR 1 ENGINE G/B	BRINELLED       	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					W90L025		LE45885E			(AUS) NR 1 ENGINE ACCESSORY GEARBOX NR 19 BEARING BRINELLED.  METAL CONTAMINATION OF ENGINE OIL SYSTEM.  INVESTIGATION A	LSO FOUND THE GAS PRODUCER SHROUD WORN FOR APPROXIMATELY 180 DEGREES OF THE CIRCUMFERENCE BY THE GAS PRODUCER WHEEL. PAR	T TC:  566.				1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998121800255	19981218	00255	NM  	1998	12	18	AU981533         	1	19980911	G	5311		FRAME           			BOEING	747   	747312      	1384932	NM  										BS 2598	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT SIDE INNER CHORD LOCATED AT BULKHEAD STA 2598 CONTAINED TWO CRACKS IN THE FOLLOWING LOCATIONS:  1.  CRACK RUN	NING FROM EDGE OF FASTENER - CRACK LENGTH 6.35 MM (0.25 INCH).   2.  CRACK RUNNING FROM THE EDGE THROUGH THE INBOARD FAS	TENER HOLE AND STOPPING AT THE EDGE OF THE RADIUS - CRACK LENGTH 46.482 MM  (1.83 INCH) FOUND DURING INSPECTION IAW ER B	747-53-10-25 (BSB53A2423).			2	L	7	4 	4F			RT	A20WE
1998121800256	19981218	00256		1998	12	18	AU981534         	4	19981014	G	2565	31180101	DOOR            			AIRBUS	320   	A320212     		EU  										ESCAPE SLIDE	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A5132					(AUS) RIGHT OVERWING ESCAPE SLIDE ENCLOSURE DOOR DELAMINATED AT THE AFT LOWER CORNER.  AREA OF DELAMINATION 2258.06 SQMM	 (3.5SQ INCH).  FOUND DURING INSPECTION IAW AD/A320/061.					2	L	7	2 	4F			RT	A28NM
1998121800257	19981218	00257	NM  	1998	12	18	AU981535         	1	19980824	G	5730		SKIN            			BOEING	737   	737377      		NM  										WING	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LOWER WING SKIN CRACKED AND CORRODED IN THE AREA OF THE REAR SPAR ATTACHMENT POINT FOR THE NR 1 TRAILING EDGE FLAP	 TRACK.					2	L	7	2 	4F			RT	A16WE
1998121800258	19981218	00258	NE  	1998	12	18	AU981536         	2	19981104	G	7250		GUIDE VANES     								LYC   	ALF502	ALF502R5    	41580	NE  					TURBINE SECTION	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							LF05194			(AUS) NR 4 ENGINE FIRST STAGE HIGH PRESSURE NOZZLE GUIDE VANES DAMAGED AT APPROXIMATELY THE 8 O'CLOCK POSITION.  PIECES 	MISSING FROM THE INNER SHROUD.  COMBUSTOR BURNED WITH PIECES MISSING NEAR FUEL NOZZLES FROM THE 7 O'CLOCK TO 4 O'CLOCK P	OSITIONS.									4	F			E6NE
1998121800259	19981218	00259	SW  	1998	12	18	AU981537         	1	19980925	G	2810	206061661103	FUEL CELL       			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL STORAGE	CONTAMINATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUEL CELL CONTAMINATED BY DEBRIS AND FUNGAL GROWTH.  BOTH FUEL BOOST PUMPS ALSO COVERED WITH FUNGUS.    PART TC: 1	,246.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800260	19981218	00260	SW  	1998	12	18	AU981538         	1	19981104	G	2913	8505101	RING            		206076022101	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					HYDRAULIC PUMP	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					BD00723					(AUS) HYDRAULIC PUMP ATTACHMENT COUPLING P/N  850509-1 SEPARATED FROM THE HYDRAULIC PUMP.  INVESTIGATION FOUND THE PUMP 	DRIVE SPLINE RETAINING RING WAS MISSING.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800261	19981218	00261	SW  	1998	12	18	AU981539         	1	19981104	G	6310	206040118001	COUPLING        		206040015103	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					A1067					(AUS) ENGINE TO MAIN TRANSMISSION DRIVESHAFT AFT OUTER COUPLING TO FREEWHEEL ASSEMBLY FLANGE INCORRECTLY ASSEMBLED.  TWO	 WASHERS WERE INSTALLED UNDER EACH OF THE FOUR ATTACHMENT BOLT HEADS.  WASHERS SHOULD ONLY BE INSTALLED UNDER EACH NUT. 	 THE BOLTS WERE NOT FULLY SEATED AGAINST THE COUPLING AND INADEQUATELY TORQUED.				1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800262	19981218	00262	SW  	1998	12	18	AU981540         	1	19981117	G	5711		WEB             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  	HARTZL	HCB3T	HCB3TN5     	GL  	WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CENTER SPAR WEB CRACKED.  FOUND DURING INSPECTION IAW SA226/ST-UN-M002.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P15EA
1998121800263	19981218	00263	GL  	1998	12	18	AU981541         	2	19981115	G	7261	23001819	NOZZLE          	ALLSN       		BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	CARBONED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					CAT25245		CAE270453			(AUS) NR 6 AND NR 7 BEARING OIL PRESSURE NOZZLE EXTENSIVELY CARBONED UP BETWEEN THE NOZZLE AND THE SCAVENGE OIL STRUT IN	 THE POWER TURBINE SUPPORT.  OIL PRESSURE NOZZLE PARTIALLY CLOGGED.  EXTERNAL SUMP ALSO CONTAINED EXCESSIVE AMOUNTS OF C	ARBON DEPOSITS.  SUSPECT NOZZLE HAD NOT BEEN REMOVED FOR SOME TIME.				1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800264	19981218	00264	SW  	1998	12	18	AU981542         	1	19981104	G	6220	M52469455	SCREW           		206011116001	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN ROTOR HUB FLAP RESTRAINT ASSEMBLY SCREWS WERE THE INCORRECT PART NUMBER FOR THE INSTALLATION.  CORRECT P/N M5	24694-555.  MAST NUT FOUND BELOW MINIMUM TORQUE VALUE.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800265	19981218	00265	EU  	1998	12	18	AU981543         	1	19981123	G	5311	115C2130	FRAME           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT FUSELAGE FRAME CRACKED ADJACENT TO HORIZONTAL STABILIZER AFT ATTACHMENT BOLT.  SUSPECT EXCESSIVE TORQUE ON BOL	T.					1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1998121800266	19981218	00266	EU  	1998	12	18	AU981545         	1	19980312	G	3241	NP049	CONTROL UNIT    			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					ANTI-SKID SYS	FAULTY          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					NP049					(AUS) ANTI-SKID UNIT FAULTY DUE TO FAILURE OF THE SUPPRESSION NETWORK POWER SUPPLY.  PART TC:  11,112.						2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998121800267	19981218	00267	WP  	1998	12	18	AU981546         	1	19981117	G	3260	H146	SWITCH          			DOUG  	DC9   	DC933F      	302207A	WP  	PWA   	JT8   	JT8D9A      	52048	NE  					LT MLG	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOOR MICROSWITCH OUT OF ADJUSTMENT.						2	L	7	2 	4F	4	F		A6WE    	E2EA
1998121800268	19981218	00268	CE  	1998	12	18	AU981547         	1	19980710	G	3230		SIDE BRACE      			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	RT MLG	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR SIDE BRACE FAULTY.  LANDING GEAR COMPONENTS STIFF IN OPERATION.  MAIN LANDING GEAR COLLAPS	ED DURING LANDING.					1	L	7	2 	3O	3	O		3A25    	E8CE	5	C	P22EA
1998121800269	19981218	00269	EU  	1998	12	18	AU981548         	1	19981112	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										PASSENGER DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) R2 CABIN DOOR UPPER CONNECTION LINK BUSHING MIGRATED.  FOUND DURING INSPECTION IAW ER A32-52-20-7C.						2	L	7	2 	4F			RT	A28NM
1998121800270	19981218	00270	GL  	1998	12	18	AU981549         	3	19981105	G	6111	PEA12D19B	BLADE           			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	PROPELLER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1043 		237119			237119		(AUS) PROPELLER BLADE TRAILING EDGE DELAMINATED IN AN AREA BETWEEN 400 MM (15.74 INCH) TO 800 MM (31.49 INCH) FROM THE B	LADE TIP.  THE DELAMINATION CONTINUED INTO THE BLADE FOR APPROXIMATELY 100 MM (3.937 IN).					2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
1998121800271	19981218	00271	EU  	1998	12	18	AU981550         	1	19981108	G	2913	56692	SEAL            	ABEX        		FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					LT ENGINE	WORN            	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			AU	S 			4347 		AH35166ABC					(AUS) LEFT ENGINE DRIVEN HYDRAULIC PUMP SHAFT SEAL FAILED.  LOSS OF HYDRAULIC FLUID.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1998121800272	19981218	00272	CE  	1998	12	18	AU981551         	1	19981112	G	2731	50524495	CONTROL CABLE   			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	ELEVATOR TAB	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TRIM CABLE BROKEN AT TRIM DRUM.						1	L	7	2 	3T	3	T	 	3A20    	E4EA	6	C	P15EA
1998121800273	19981218	00273	EU  	1998	12	18	AU981552         	1	19981108	G	2913	66479	SEAL            	ABEX        		FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					LT ENGINE	WORN            	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			4347 		AH35166ABC					(AUS) LEFT ENGINE DRIVEN HYDRAULIC PUMP SHAFT SEAL LEAKING.  LOSS OF HYDRAULIC FLUID.  SEE ALSO OPERATOR CONTROL NR AU98	1550.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1999011500271	19990115	00271	CE  	1999	1	15	AU981553         	1	19981120	G	3244	5005	TREAD           			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	NLG TIRE	SEPARATED       	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			AU	S 										(AUS) NOSE LANDING GEAR TIRE TREAD SEPARATED.  TIRE REMAINED INFLATED.						1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA
1999011500272	19990115	00272	EA  	1999	1	15	AU981554         	2	19981124	G	7414	67542	BEARING         			PIPER 	PA25  	PA25235     	7102504	SO  	LYC   	O540  	O540A1D5    	41532	EA  	MCAULY	1A200	1A200FA     	GL  	LT MAGNETO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1743640A	PD010		(AUS) LEFT MAGNETO BEARING FAILED.  METAL CONTAMINATION OF ENGINE OIL SYSTEM.						1	L	7	1 	3O	3	O		2A10    	E295	5	N	P874
1999011500273	19990115	00273	EU  	1999	1	15	AU981555         	1	19980901	G	7500	1379287L405	LINE            			BAG   	JETSTM	JETSTM3201  	1500217	EU  	GARRTT	TPE331	TPE33112UA  	01514	WP  	MCAULY	4HFR34	4HFR34C653  	NE  	RT ENGINE	BROKEN          	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 										(AUS) RIGHT ENGINE P3 BLEED AIR PIPE BROKEN AT ENGINE ATTACHMENT.						2	L	7	2 	4T	4	T	RT	A56EU   	E4WE	6	C	3PNE
1999011500274	19990115	00274	EU  	1999	1	15	AU981556         	1	19981124	G	6720	C4105B1	SERVO           		C4105B1     	AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					TAIL ROTOR	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 			66   		833					(AUS) TAIL ROTOR SERVO, INTERNAL FAULT.						1	G	7	2 	3U	3	U		H10EU   	E19EU
1999011500275	19990115	00275	SO  	1999	1	15	AU981557         	2	19981121	G	8500		ENGINE          			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE BAY	MAKING METAL    	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 							565625			(AUS) ENGINE FILTERS CONTAINED A LARGE AMOUNT OF METAL CONTAMINATION.  LIMITED INFORMATION PROVIDED.						1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1999011500276	19990115	00276	SO  	1999	1	15	AU981558         	1	19981124	G	5312	6695500	BULKHEAD        			PIPER 	PA28  	PA28161     	7102803	SO  										VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FORWARD FIN ATTACHMENT FITTING DOUBLER CRACKED.  FOLLOWING REMOVAL OF THE DOUBLER, THE BULKHEAD P/N 62444-05 AT FS	 228-30 WAS ALSO FOUND TO BE CRACKED.					1	L	7	1 	3O				2A13
1999011500277	19990115	00277	EU  	1999	1	15	AU981559         	1	19981108	G	5330		SKIN            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					BS 29	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE SKIN CRACKED.  CRACK PASSED THROUGH A RIVET HOLE AT FRAME 29 APPROXIMATELY 50.8 MM (2 INCHES) ABOVE STRIN	GER 13 LT.  FOUND DURING INSPECTION IAW BRITISH AEROSPACE SB 53-144 (AD/BAE146/70).					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1999011500278	19990115	00278		1999	1	15	AU981560         	4	19980918	G	3441	201501	IRS             			BOEING	737   	737376      		NM  										NR 2	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					201501					(AUS) NR 2 INERTIAL REFERENCE UNIT (IRU) FAULTY.						2	L	7	2 	4F			RT	A16WE
1999011500279	19990115	00279	EU  	1999	1	15	AU981561         	1	19981118	G	3213	201160702	BOLT            			AIRBUS	320   	A320212     		EU  										RT MLG	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT MAIN LANDING GEAR PINTLE PIN LOCKBOLT SHOWED EVIDENCE OF ROTATION.						2	L	7	2 	4F			RT	A28NM
1999011500280	19990115	00280	EU  	1999	1	15	AU981562         	1	19981122	G	3231	HC321H0026002	LINK            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR RT AND LT FORWARD HINGE LINKS CORRODED BEYOND LIMITS.  LINKS P/N HC321H0026-002, P/N HC321B	0045-002 AND P/N  HC321B0043-001.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1999011500281	19990115	00281	EU  	1999	1	15	AU981563         	1	19981122	G	3231	HC321H0026002	LINK            			BAG   	BAE146	BAE146100A  	1500260	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR RT AND LT FORWARD HINGE LINKS CORRODED BEYOND LIMITS.  LINKS P/N HC321H0026-002, P/N HC321B	0045-002, AND P/N HC321B0043-001.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1999011500282	19990115	00282	EU  	1999	1	15	AU981564         	1	19981122	G	3231	HC321H0026002	LINK            			BAG   	BAE146	BAE146200A  	1500266	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					MLG DOOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR DOOR RT AND LT FORWARD HINGE LINKS CORRODED BEYOND LIMITS.  LINKS P/N HC321H0026-002, P/N HC321B	0045-002, AND P/N HC321B0043-001.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1999011500283	19990115	00283	EU  	1999	1	15	AU981565         	1	19981127	G	5320		RIB             			REIMS 	406   	F406        		EU  	PWA   	PT6   	PT6A112     	52043	NE  	MCAULY	3G34C7	3GFR34C701  	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CANTED RIB CRACKED.  FOUND DURING INSPECTION IAW SB CAB98-16.						1	L	7	2 	3T	3	T	RT	A54EU   	E4EA	5	C	P60GL
1999011500284	19990115	00284	NM  	1999	1	15	AU981566         	1	19981126	G	2750	69736061	BOLT            			BOEING	737   	737476      		NM  										TE FLAP	SHEARED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			20775		20881A					(AUS) FLAP TRANSMISSION UNIVERSAL BOLT SHEARED.						2	L	7	2 	4F			RT	A16WE
1999011500285	19990115	00285	EU  	1999	1	15	AU981567         	2	19981126	G	7321	8063210	FCU             	WOODWARD    	8063210     						CFMINT	CFM56 	CFM563C     	13802	EU  					NR 2 ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			14929		WYG64296		857664			(AUS) NR 2 ENGINE FUEL CONTROL UNIT FAULTY.											4	F			E21EU
1999011500286	19990115	00286	NE  	1999	1	15	AU981568         	2	19981124	G	7530	3036783	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					BLEED AIR SYSTEM	CRACKED         	W				K				NONE                    				R	J	E	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	VIBRATION/BUFFET          	CR	CRUISE         	1			AU	S 			229  				120009			(AUS) COMPRESSOR AIR DIFFUSER LINE CRACKED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999011500287	19990115	00287	SO  	1999	1	15	AU981569         	2	19981114	G	8520	653877KSEXH	TAPPET          			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  	MCAULY	2AF34C	2AF34C55    	GL  	LT ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			197  				297682R			(AUS) LT ENGINE NR 6 CYLINDER EXHAUST VALVE HYDRAULIC LIFTER CHIPPED AND PITTED.  CORRESPONDING CAM LOBE ALSO BADLY WORN	.  PART TC:  97.					1	L	7	2 	3O	3	O	RT	3A16    	3E1	5	C	P5EA
1999011500288	19990115	00288	SO  	1999	1	15	AU981570         	1	19981126	G	2420	51539014A	GCU             			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					AC REGULATOR	MALFUNCTIONED   	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			10453		5679					(AUS) GENERATOR CONTROL UNIT (GCU) FAULTY.  PART TC:  11,118.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1999011500289	19990115	00289	CE  	1999	1	15	AU981571         	1	19981130	G	5712	052311011LH	RIB             		A152        	CESSNA	150   	A152        	2071836	CE  						MCAULY	2A34C	D2A34C98    	GL  	LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LT WING NOSE RIBS LOCATED AT WS 84.00 CRACKED.						1	H	7	1 	3O				3A19    		5	C	P3EA
1999011500290	19990115	00290	CE  	1999	1	15	AU981572         	1	19981130	G	5712	052311010RH	RIB             		A152        	CESSNA	150   	A152        	2071836	CE  						MCAULY	2A34C	D2A34C98    	GL  	RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING NOSE RIB LOCATED AT WS 84.00 CRACKED.						1	H	7	1 	3O				3A19    		5	C	P3EA
1999011500291	19990115	00291	CE  	1999	1	15	AU981573         	1	19981130	G	2460	ATC30	FUSE            	LAMAR       	MCO12       	CESSNA	172   	172R        	2072401	CE  										DC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELECTRICAL SYSTEM FUSE F2 SEPARATED AT THE BASE OF THE ASSEMBLY.  FUSE HAD ARCED AND DISCONNECTED THE NR 2 BUS.						1	H	7	1 	3O			NT	3A12
1999011500292	19990115	00292	EU  	1999	1	15	AU981574         	1	19981124	G	5312	115C2128	BULKHEAD        			GROB  	G115  	G115C       	1660303	EU  	LYC   	O360  	O360A1F6    	41514	EA  	HARTZL	HCF2Y	HCF2YR1     	GL  	FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE REAR BULKHEAD FRAME CRACKED AT JOINT.  FOUND DURING INSPECTION IAW AD/GROBG115/13.						1	L	7	1 	3O	3	O	NT	A57EU   	E286	5	C	P27EA
1999011500293	19990115	00293	SO  	1999	1	15	AU981575         	1	19981113	G	2434	8051884	BRUSH           	PRESTOLITE  		PIPER 	PA32  	PA32301     	7103207	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	DC GENERATOR	FAILED          	W				K				NONE                    				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			AU	S 			115  		8051884					(AUS) ALTERNATOR BRUSH (1OFF) IN BRUSH CARRIER ASSEMBLY FAILED TO CONTACT SLIP RING.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1999011500294	19990115	00294	SO  	1999	1	15	AU981576         	1	19980914	G	2436	688093	REGULATOR       			PIPER 	PA32  	PA32R301    	7103218	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	DC SYSTEM	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AUTOMOTIVE TYPE VOLTAGE REGULATOR (BOSCH) FITTED INSTEAD OF THE CORRECT UNIT.  INSPECTION ALSO FOUND THAT THE OVER	VOLTAGE CONTROL UNIT HAD BEEN REMOVED AND THE REGULATOR HAD BEEN INCORRECTLY WIRED.					1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1999011500295	19990115	00295	EU  	1999	1	15	AU981577         	1	19981028	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										PASSENGER DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR CONNECTION LINK BUSHINGS MIGRATED AT THE FOLLOWING POSITIONS:  1.  LT FORWARD DOOR UPPER BUSHING.  2. L	T AFT DOOR UPPER AND LOWER BUSHINGS.  3.  RT FORWARD DOOR UPPER BUSHINGS.  4.  RT AFT DOOR LOWER BUSHING FOUND DURING IN	SPECTION IAW ER A32-52-10-7C.				2	L	7	2 	4F			RT	A28NM
1999011500296	19990115	00296	EU  	1999	1	15	AU981578         	1	19980817	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										PASSENGER DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR CONNECTION LINK BUSHINGS MIGRATED FROM THE FOLLOWING POSITIONS:  1.  LT FORWARD CABIN DOOR LOWER LINK B	USHING.  2.  LT AFT CABIN DOOR UPPER AND LOWER LINK BUSHINGS FOUND DURING INSPECTION IAW ER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1999011500297	19990115	00297		1999	1	15	AU981579         	1	19980806	G	7603	2818	CLAMP           								ROTAX 	912   	ROTAX912    	55555	EU  					POWER LEVER	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) THROTTLE HANDLE SEPARATED FROM DASHBOARD DUE TO SPLITTER CLAMP COMING LOOSE WHEN THE SCREW FELL OUT.											3	I			EXPE3I
1999011500298	19990115	00298	CE  	1999	1	15	AU981580         	1	19981127	G	7602		SPRING          			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  	HARTZL	HCJ2Y	BHCJ2YF2    	GL  	MIXTURE CONTROL	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 							299016R			(AUS) MIXTURE CONTROL LINKAGE ANTI-RATTLE SPRING MISSING.  MIXTURE LEVER FITTED WITHOUT WAVE WASHERS.  NO WAVE WASHERS F	ITTED BETWEEN THE THROTTLE BODY AND COLLAR.  MANUFACTURING DEFECT.  INCORRECT ASSEMBLY.					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P37EA
1999021200587	19990212	00587	NE  	1999	2	12	AU981581         	3	19981125	G	6111	RFC11U1R6A	BLADE           			EMB   	120   	EMB120      	3260201	SO  						HAMSTD	14RF	14RF9       	NE  	PROPELLER	LIGHTNING STRIKE	W				K				NONE                    				C			F.O.D.                    			CR	CRUISE         	1			AU	S 										(AUS) RIGHT PROPELLER NR 2, NR 3, AND N4 4 BLADES DAMAGED BY LIGHTNING STRIKE.  PART TOTAL CYCLES 4,498.						2	L	7	2 	4T			RT	A31SO   		6	C	P11NE
1999011500299	19990115	00299	SO  	1999	1	15	AU981582         	1	19981130	G	2752	3203001007	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					TE FLAP	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			AU	S 					0890					(AUS) LEFT OUTBOARD FLAP ACTUATOR SUSPECT FAULTY.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1999011500300	19990115	00300	SO  	1999	1	15	AU981583         	1	19981124	G	2424	448258051002	RELAY           	LEARSIEGLER 		EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					AC REGULATOR	MALFUNCTIONED   	W				O				OTHER                   				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	NR	NOT REPORTED   	1			AU	S 					6703					(AUS) GENERATOR CONTROL UNIT AND GENERATOR FEEDER PROTECTION RELAY OVERHEATED.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1999011500301	19990115	00301	CE  	1999	1	15	AU981584         	1	19981117	G	2432	114361026605	CONNECTOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					BATTERY	CORRODED        	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			AU	S 			860  							(AUS) BATTERY POSITIVE CONNECTOR LEADS BURNED AND DETERIORATED.  SUSPECT CAUSED BY POOR CONNECTION INSIDE THE CONNECTOR 	CREATING A HIGH RESISTANCE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999011500302	19990115	00302	SO  	1999	1	15	AU981585         	1	19981130	G	3260	JE6	SWITCH          			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR MICROSWITCH ACTUATOR TAB BROKEN OFF.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1999011500303	19990115	00303	NM  	1999	1	15	AU981586         	1	19981123	G	3230	AM0019	POWER PACK      			BOEING	757   	757200      	1384950	NM  										MLG	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					AM0019					(AUS) ALTERNATE LANDING GEAR EXTENSION POWER PACK FAULTY.						2	L	7	2 	4F			RT	A2NM
1999011500304	19990115	00304	SO  	1999	1	15	AU981587         	1	19981109	G	3221	670543	TRUNNION        			PIPER 	PA32  	PA32R300    	7103213	SO  	LYC   	O540  	IO540K1G5   	41532	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					7214P					(AUS) NOSE LANDING GEAR TRUNNION CRACKED IN SEVERAL PLACES.						1	L	7	1 	3O	3	O		A3SO    	1E4	5	C	P920
1999011500305	19990115	00305	EU  	1999	1	15	AU981588         	1	19981203	G	5330	365A2300000101	SKIN            		365A23000001	AEROSP	SA365 	SA365C      	8680667	EU  	TMECA 	ARRIEL	ARRIEL1A    	60030	NE  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8790 		5028					(AUS) TAIL BOOM ASSEMBLY CRACKED IN AREA ADJACENT TO THE RIGHT HORIZONTAL STABILIZER ATTACHMENT POINT.						1	G	7	2 	3U	3	U		H10EU   	E19EU
1999011500306	19990115	00306	SO  	1999	1	15	AU981589         	1	19981126	G	2752	12023217001	ACTUATOR        			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  	HAMSTD	14RF	14RF9       	NE  	TE FLAP	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT OUTBOARD FLAP ACTUATOR HOUSING ELECTRICAL CONNECTOR CONTAMINATED BY FUEL.						2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1999011500307	19990115	00307	NM  	1999	1	15	AU981590         	1	19981126	G	3232		ROD             			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					NLG DOOR	OUT OF ADJUST   	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) NOSE LANDING GEAR DOOR ACTUATOR ROD OUT OF ADJUSTMENT.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999011500308	19990115	00308	NE  	1999	1	15	AU981591         	3	19981020	G	6111		BLADE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT PROPELLER	BIRD STRIKE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			AU	S 							114442	HJ545		(AUS) LEFT ENGINE SUFFERED A BIRD STRIKE (BROLGA) DURING TAXIING RESULTING IN A PROPELLER BLADE SEPARATING APPROXIMATELY	 25.4 MM TO 50.8 MM (1 INCH TO 2 INCHES) FROM THE BLADE ROOT.  THE RESULTING OUT OF BALANCE CAUSED ADDITIONAL DAMAGE TO 	THE FIREWALL AND THE INBOARD UPPER KEEL WEB.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
1999011500309	19990115	00309	CE  	1999	1	15	AU981592         	1	19981130	G	2450	2058602	CONNECTOR       			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	AC SYSTEM	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					NSN					(AUS) DIODE BOX CORRODED DUE TO WATER CONTAMINATION FROM WATER LEAKINGTHROUGH THE PILOTS DV WINDOW.  INVESTIGATION FOUND	 CORROSION ON THE BOARDS AND CONNECTORS WITH PINS 27, 28, AND 30 OF P141 COMPLETELY CORRODED AWAY.					1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1999011500310	19990115	00310	SO  	1999	1	15	AU981593         	1	19981125	G	3221	4027300	TRUNNION        		4027300     	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 								DJ9476A		(AUS) NOSE LANDING GEAR TRUNNION RIGHT TURN STOP AREA BENT AND CRACKED.  SUSPECT CAUSED BY EXCEEDING TOW LIMITS.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1999011500311	19990115	00311	CE  	1999	1	15	AU981594         	1	19981018	G	5531	07310292	SPAR            			CESSNA	180   	180K        	2072624	CE  						MCAULY	2A34C	C2A34C204   	GL  	VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL FIN REAR SPAR CRACKED UNDER DOUBLERS AS INDICATED IN CESSNA SE-80-85.						1	H	7	1 	3O				5A6     		5	C	P3EA
1999011500312	19990115	00312	CE  	1999	1	15	AU981595         	1	19981115	G	3260	1E13	SWITCH          			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	LT MLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR DOWN LIMIT MICROSWITCH FAILED.						1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1999011500313	19990115	00313	EA  	1999	1	15	AU981596         	2	19981116	G	8530	LW13445	PIN             								LYC   	O320  	O320E2D     	41508	EA  					ENGINE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) CYLINDER KITS (4OFF) USED TO SERVICE THE ENGINE HAD THE INCORRECT LIGHTWEIGHT PISTON PINS FITTED INSTEAD OF THE CO	RRECT HEAVYWEIGHT PINS.  THE INCORRECT PINS WERE MARKED LW13445 WHICH IS THE PART NUMBER FOR THE CORRECT HEAVYWEIGHT PIN	.									3	O			E274
1999011500314	19990115	00314	WP  	1999	1	15	AU981597         	1	19981127	G	6320	36902512711	GEAR            		369D25100901	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C30      	03013	GL  					M/R GEARBOX	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			981  		1621					(AUS) MAIN TRANSMISSION MAIN DRIVE GEAR TOOTH BROKEN OFF.						1	G	7	1 	3U	3	U		H3WE    	E1GL
1999011500315	19990115	00315	NE  	1999	1	15	AU981598         	2	19981117	G	7230		COMPRESSOR      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3A     	NE  	LT ENGINE	FOD             	W				O				OTHER                   				C	B	E	F.O.D.                    	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	NR	NOT REPORTED   	1			AU	S 							114270			(AUS) LEFT ENGINE GAS GENERATOR COMPRESSOR DAMAGED DUE TO FOD.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
1999011500316	19990115	00316	CE  	1999	1	15	AU981599         	1	19981119	G	5540	52330019	BRACKET         			CESSNA	441   	441         	2076020	CE  						HARTZL	HCB3T	HCB3TN5     	GL  	RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RUDDER UPPER AND LOWER HINGE BRACKETS WORN EXCESSIVELY.						1	L	7	2 	3T			RT	A28CE   		6	C	P15EA
1999011500317	19990115	00317	EU  	1999	1	15	AU981600         	1	19981023	G	5210		BUSHING         			AIRBUS	320   	A320212     		EU  										PASSENGER DOOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN DOOR CONNECTION LINK BUSHINGS MIGRATED FROM THE FOLLOWING POSITIONS:  1.  LT FORWARD DOOR UPPER AND LOWER BU	SHINGS.  2.  LT AFT DOOR LOWER BUSH.  3.  RT FORWARD DOOR LOWER BUSH FOUND DURING INSPECTION IAW ER A32-52-10-7C.					2	L	7	2 	4F			RT	A28NM
1999011500318	19990115	00318	EU  	1999	1	15	AU981601         	1	19980915	G	5311		FRAME           			AIRBUS	320   	A320212     		EU  										BS 40	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTER FUSELAGE FLANGE CAP LOCATED AT FRAME 40 LT SIDE CRACKED IN THE UPPERMOST FASTENER HOLE.  FOUND DURING EDDY C	URRENT INSPECTION.					2	L	7	2 	4F			RT	A28NM
1999011500319	19990115	00319	EU  	1999	1	15	AU981602         	2	19981126	G	7230		COMPRESSOR      			BOEING	737   	737377      		NM  	CFMINT	CFM56 	CFM563BFR   	13802	EU  					NR 1 ENGINE	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 							721507			(AUS) NR 1 ENGINE LEAKING OIL FROM THE LP COMPRESSOR.  OIL CONTAMINATION OF NR 1 AIR CONDITIONING SYSTEM.						2	L	7	2 	4F	4	F	RT	A16WE   	E21EU
1999011500320	19990115	00320	NE  	1999	1	15	AU981603         	2	19981130	G	7200		ENGINE          								LYC   	ALF502	ALF502R5    	41580	NE  					NR 1	VIBRATES        	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			AU	S 							LF05597A			(AUS) NR 1 ENGINE HAD A VIBRATION READING OF 1.6 TOGETHER WITH A LOUD GRINDING NOISE AND THROTTLE BUZZ.											4	F			E6NE
1999011500321	19990115	00321	EU  	1999	1	15	AU981604         	1	19981026	G	3260	SA7670006149	LINE            			BAG   	BAE146	BAE146300A  	1500267	EU  	LYC   	ALF502	ALF502R5    	41580	NE  					LT MLG	FAILED          	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 										(AUS) LEFT MAIN LANDING GEAR UPLOCK ACTUATOR HOSE ASSEMBLY RUPTURED.  HOSE LEAKING FROM END FITTING.  LOSS OF `GREEN' SY	STEM HYDRAULICS.					2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1999011500322	19990115	00322	NM  	1999	1	15	AU981605         	1	19981010	G	5753		NUT             			BOEING	767   	767324      		NM  										TE FLAP	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) OUTBOARD FLAP SUPPORT BEAM ATTACH BOLT NUTS (AFT TWO) ON THE RT OUTBOARD INBOARD BEAM FAILED TORQUE THRESHOLD TEST	.  ALL SIX BOLTS, NUTS AND WASHERS ATTACHING THE FLAP TO THE SUPPORT BEAM WERE REPLACED PER BOEING ALERT SB 767-27A0151 	AND AMM27-51-20.  FOUND IAW AD 105-B767-096 AND ER B76-27-50-27D.				2	L	7	2 	4F			RT	A1NM
1999011500323	19990115	00323	EU  	1999	1	15	AU981606         	1	19981115	G	3246	DAS2062271	BEARING         			BAG   	BAE146	BAE146200A  	1500266	EU  										NR 3 WHEEL	COLLAPSED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2069 		GV137					(AUS) ON REMOVAL OF NR 3 MAIN WHEEL BECAUSE OF TIRE WORN TO LIMITS, THE INBOARD WHEEL BEARING WAS FOUND COLLAPSED AND HA	D DAMAGED THE AXLE ASSEMBLY.  EXAMINATION OF THE BEARING INDICATED THAT POSSIBLE CAUSE OF THE BEARING BREAKUP WAS HEAT R	ELATED DUE TO EVIDENCE OF TEMPERATURE DISCOLORATION (I.E. BLUE).  PART TC:  19,624.				2	H	7	4 	4F			RT	A49EU
1999011500324	19990115	00324	SO  	1999	1	15	AU981607         	1	19981121	G	3233	OA29233	ACTUATOR        	OZONE       	OA29233     	PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2     	GL  	NLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 					5704			DJA4625		(AUS) NLG WOULD NOT FULLY RETRACT WHEN SELECTED UP.  INVESTIGATION FOUND THE ACTUATOR TO BE FAULTY.						1	L	7	2 	3O				A20SO   		5	C	P33EA
1999011500325	19990115	00325	CE  	1999	1	15	AU981608         	1	19981203	G	2823	583801093	VALVE           			BEECH 	58    	58          	1152740	CE  	CONT  	O520  	IO520C      	17032	SO  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 					725					(AUS) FUEL SELECTOR VALVE (NEW) LEAKING INTERNALLY.						1	L	7	2 	3O	3	O		3A16    	E5CE
1999011500326	19990115	00326	CE  	1999	1	15	AU981609         	1	19981127	G	3231	1315534M	ROD             		58          	BEECH 	58    	58          	1152740	CE  										RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING RETRACTION CHECKS IN PERIODIC INSPECTION, THE RT LANDING GEAR INBOARD DOOR'S INBOARD ROD END SNAPPED AT THE	 TOP OF THE THREADED SECTION.  INVESTIGATION FOUND THAT INCORRECT SPACERS WERE FITTED CAUSING EXCESSIVE SIDE LOADS.					1	L	7	2 	3O				3A16
1999011500327	19990115	00327	NM  	1999	1	15	AU981610         	1	19981031	G	5754		WEDGE           			BOEING	767   	767277      		NM  										LE FLAP	DISBONDED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEADING EDGE SLAT TRAILING EDGE WEDGES FOUND DISBONDED ON A TOTAL OF EIGHT SLATS:  SLAT 3 - P/N 114T4103-25P, 8 DI	SBONDED AREAS.  SLAT 4 - P/N 114T4104-21C, 1 DISBONDED AREA.  SLAT 5 - P/N 114T4105-37, 1 DISBONDED AREA.  SLAT 6 - P/N 	114T3100-1A, 2 DISBONDED AREAS.  SLAT 7 - P/N 114T3100-2C, 2 DISBONDED AREAS.  SLAT 9 - P/N 114T4104-22C, 1 DISBONDED AR	EA.   SLAT 11 - P/N 114T4102-26SP, 2 DISBONDED AREAS.  SLAT 12 - P/N 114T4101-44, 1 DISBONDED AREA.  FOUND IAW BOEING AL	ERT SB 767-57A0039.		2	L	7	2 	4F			RT	A1NM
1999011500328	19990115	00328	SW  	1999	1	15	AU981611         	1	19981202	G	3250	575003911	SHAFT           			GULSTM	500   	500B        	0141106	SW  										NLG STEERING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) PUSHING THE NOSE LEG FIRMLY IN A FORE AND AFT DIRECTION RESULTED IN A CREAKING SOUND AT THE TOP OF THE NOSE GEAR C	OMPARTMENT.  THE CROSS SHAFT AND DRAG LINK WERE REMOVED AND A VISIBLE 3.5 CM (1.38 INCH) CRACK WAS FOUND STARTING AT THE	 BOLT ATTACH HOLE FOR THE DRAG LINK AND RUNNING LONGITUDINALLY ALONG THE SHAFT.				1	H	7	2 	3O				6A1
1999011500329	19990115	00329	SO  	1999	1	15	AU981612         	1	19981005	G	7810		EXHAUST STACK   			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					RT ENGINE	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1305557			(AUS) PILOT REPORTED UNUSUAL NOISE COMING FROM THE RT ENGINE AND SUSPECTED A STICKY VALVE.  AFTER ENGINE RUNS, THE COWLS	 WERE REMOVED FROM THE RT ENGINE TO CARRY OUT A COMPRESSION CHECK.  IT WAS THEN NOTICED THAT THE NR 3 EXHAUST STACK WAS 	NOT FITTED TO THE NR 3 CYLINDER.  THE STACK WAS APPROX 3.81 CM (1.5 INCHES) BELOW ITS CORRECT POSITION.  SUSPECT THAT EI	THER THE EXHAUST STACK WAS NOT FITTED OR WAS FITTED INCORRECTLY.			1	L	7	2 	3O	3	O		A1EA    	1E12
1999011500330	19990115	00330	EU  	1999	1	15	AU981614         	1	19981206	G	3246	AM52688	WHEEL           			BAG   	JETSTM	JETSTM3201  	1500217	EU  										MLG	OUT OF BALANCE  	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			7    							(AUS) DURING TAKEOFF AND LANDING, SEVERE NOSE WHEEL VIBRATION WAS FELT.  AT TAXI, THE VIBRATION STOPPED.  BOTH WHEELS WE	RE INSPECTED AND WHEEL S/N QQ001 WAS FOUND OUT OF BALANCE BY 060 AND 030 GRAMS AT DIFFERENT 'CLOCK' POSITIONS.  FURTHER 	INVESTIGATION FOUND AN INTERNAL VULCANIZED BALANCE PATCH HAD COME LOOSE INSIDE TIRE AND ALSO THE WHEEL ASSEMBLY LEAD WEI	GHTS.  PART TC:  8,561.			2	L	7	2 	4T			RT	A56EU
1999011500331	19990115	00331	NE  	1999	1	15	AU981615         	2	19981201	G	7230	120588	IMPELLER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							120588			(AUS) DURING ENGINE COMPRESSOR INSPECTION, FOD DAMAGE WAS FOUND ON THE LP IMPELLER BLADES.  A BORESCOPE INSPECTION ON TH	E HP IMPELLER REVEALED DAMAGE THAT WAS OUTSIDE ACCEPTABLE LIMITS.  THE ORIGIN OF THE FOD WAS NOT IDENTIFIED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999011500332	19990115	00332	CE  	1999	1	15	AU981616         	1	19981209	G	3260	727755	CIRCUIT BREAKER 			CESSNA	441   	441         	2076020	CE  										MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR WOULD NOT RETRACT ON FIRST AND SECOND ATTEMPTS.  GEAR EXTENSION WAS SELECTED, BUT THE GEAR FAILED TO 	EXTEND.  A NUMBER OF ATTEMPTS WERE CARRIED OUT, UNTIL THE GEAR DID EXTEND.   ON INSPECTION, THE LANDING GEAR CIRCUIT BRE	AKER WAS FOUND TO BE DEFECTIVE.				1	L	7	2 	3T			RT	A28CE
1999011500333	19990115	00333	NM  	1999	1	15	AU981617         	1	19980824	G	5510		FITTING         			BOEING	737   	737377      		NM  										HORIZONTAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING 4C CHECK, TWO CRACKS WERE FOUND AT LT LOWER SUPPORT ANGLE WHERE HORIZONTAL STABILIZER JACK SCREW PRIMARY SU	PPORT BEAM ATTACHES TO STAR TRUSS.  IN ADDITION, FOUR ATTACH BOLTS WERE SHOWING SIGNS OF LOOSENESS.  CRACKS RAN UPWARD I	N RADIUS OF ANGLE, CRACK LENGTHS APPROXIMATELY 6.99 CM (2.75 INCHES) INBOARD AND 6.35 CM (2.5 INCHES) OUTBOARD.				2	L	7	2 	4F			RT	A16WE
1999011500334	19990115	00334	EU  	1999	1	15	AU981618         	1	19981207	G	5320		RIB             			REIMS 	406   	F406        		EU  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION, SEVERAL HAIR LINE CRACKS WERE DISCOVERED IN THE CANTED RIB UPPER CAP IN THE CENTER WING CARRY-T	HROUGH AREA.  THIS IS SECOND AIRCRAFT IN THE FLEET WITH CRACKS - REFER OPERATOR CONTROL NR AU981565.   FOUND IAW RHEIMS 	SB CAB98-16.				1	L	7	2 	3T			RT	A54EU
1999011500335	19990115	00335	SO  	1999	1	15	AU981619         	1	19981129	G	2720	12026726001	BELLCRANK       			EMB   	120   	EMB120      	3260201	SO  										RUDDER	SLIPPED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) AFTER ENGINE START-UP AND DURING FLIGHT, CONTROL FREEDOM CHECK PRESSURE WAS APPLIED TO THE RUDDER PEDALS WHICH COL	LAPSED OUT OF REACH OF PILOT'S FEET.  RUDDER PEDAL LINKAGE AND SPINDLE ASSEMBLY WERE INSPECTED, ADJUSTED, AND LUBRICATED	 IAW MAINTENANCE MANUAL, FORCE APPLIED TO PEDALS UNABLE TO RE-PRODUCE DEFECT, AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T			RT	A31SO
1999011500336	19990115	00336	WP  	1999	1	15	AU981620         	2	19981204	G	7200		ENGINE          								GARRTT	TPE331	TPE33110U   	01514	WP  					LT & RT	MALFUNCTIONED   	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			NR	NOT REPORTED   	1			AU	S 							P63098LH			(AUS) PILOT REPORTED POWER LOSS ON BOTH ENGINES WHEN BECOMING AIRBORNE.  ON RETURN, ENGINES GROUND RUN IAW MAINTENANCE M	ANUAL.  ENGINE PERFORMANCE WELL WITHIN BOOK FIGURES.  ENGINE INSPECTION CARRIED OUT FOR BLEED AIR LEAKS, WIRING HARNESS 	INSPECTED, ALL IN GOOD CONDITION.  FUEL FILTERS CHECKED CLEAN, ENGINE GROUND RUN AGAIN IAW MAINTENANCE MANUAL, AND COULD	 NOT FAULT ENGINE PERFORMANCE.								4	T			E4WE
1999011500337	19990115	00337	NM  	1999	1	15	AU981622         	1	19981014	G	2710	82700521001	CONTROL CABLE   			DHAV  	DHC8  	DHC8202     	2809007	NM  										AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS  RIGHT WING AILERON CONTROL CABLE WORN - FOUND DURING RE-TENSIONING.						2	H	7	2 	4T			RT	A13NM
1999011500338	19990115	00338	NM  	1999	1	15	AU981623         	1	19981014	G	2710	82700518001	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  										AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING AILERON CONTROL CABLE WORN - FOUND DURING RE-TENSIONING.						2	H	7	2 	4T			RT	A13NM
1999011500339	19990115	00339	NM  	1999	1	15	AU981624         	1	19981014	G	2710	82700522001	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  										AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING AILERON CONTROL CABLE P/N 82700517-001 WORN - FOUND DURING RE-TENSIONING.						2	H	7	2 	4T			RT	A13NM
1999011500340	19990115	00340	NM  	1999	1	15	AU981625         	1	19981014	G	2710	82700522001	CONTROL CABLE   			DHAV  	DHC8  	DHC8102     	2809003	NM  										AILERON	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) RIGHT WING AILERON CONTROL CABLE P/N  82700522-001 WORN - FOUND DURING RE-TENSIONING.						2	H	7	2 	4T			RT	A13NM
1999011500341	19990115	00341	NM  	1999	1	15	AU981626         	1	19981013	G	7602	87600515001	CABLE           			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					MIXTURE CONTROL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							12002B			(AUS) ENGINE CONTROL CABLE FOUND WITH LOW TENSION.  FURTHER INVESTIGATION FOUND THE CABLE TURN-BUCKLE TO BE LOCKWIRED AN	D BOTTOMED OUT - TENSION COULD NOT BE ADJUSTED.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999011500342	19990115	00342	CE  	1999	1	15	AU981627         	1	19981119	G	5753		TRACK           		172         	CESSNA	172   	172N        	2072434	CE  										TE FLAP	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) RIGHT FLAP TRACK MUSHROOMED AND TORE THE ROLLER SPACER, JAMMING THE ROLLER P/N 0523920 AND CAUSING THE FLAP TO JAM	.  THE FLAP MOTOR CONTINUED TO DRIVE UP AND TWISTED THE FLAP.					1	H	7	1 	3O			NT	3A12
1999011500343	19990115	00343	WP  	1999	1	15	AU981628         	1	19981209	G	3234	59164605509	VALVE           			DOUG  	DC9   	DC933F      	302207A	WP  										MLG	OUT OF RIG      	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) ON DESCENT, LANDING GEAR WAS SELECTED DOWN AND DOOR WARNING LIGHT INDICATED UNSAFE.  MANUAL EXTENSION CARRIED OUT 	PER EMERGENCY PROCEDURES AND AIRCRAFT MADE UNEVENTFUL LANDING.  INVESTIGATION FOUND THAT THE MLG CONTROL VALVE WAS NOT R	IGGED CORRECTLY.				2	L	7	2 	4F				A6WE
1999011500344	19990115	00344	EU  	1999	1	15	AU981629         	2	19981126	G	7321	WYG64296	FCU             	WOODWARD    	8063215     						CFMINT	CFM56 	CFM563C     	13802	EU  					FUEL SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			14929		WYG64296		857664			(AUS) DURING MAINTENANCE, THE NR 2 ENGINE POWER LEVER ANGLE WAS ADJUSTED AND AN EGR CARRIED OUT.  ENGINE STARTED AND ACH	IEVED IDLE.  WHEN PART POWER CHECK CARRIED OUT NIL, ENGINE RESPONSE WHEN THROTTLE MOVED FROM PART POWER TO IDLE POSITION	.  THE MAIN ENGINE CONTROL WAS DISASSEMBLED AND THE TORQUE MOTOR SERVO PISTON WAS FOUND TO BE STICKING.									4	F			E21EU
1999011500345	19990115	00345	NE  	1999	1	15	AU981630         	2	19981213	G	7532	97962641	VALVE           			EMB   	120   	EMB120      	3260201	SO  	PWA   	118   	PW118A      		NE  					BLEED AIR	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			AU	S 										(AUS) ON TAKEOFF WITH APU RUNNING AND ENGINE BLEEDS CLOSED, THE LT BLEED (ENGINE) CLOSED LIGHT WAS NOT ON.  DURING GROUN	D CHECKS, THE LT BLEED AIR SHUT/OFF VALVE WAS REPLACED DUE TO A SUSPECTED INTEGRAL FAULTY MICROSWITCH.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE
1999011500346	19990115	00346	CE  	1999	1	15	AU981631         	1	19981207	G	2842	C6680501108	TRANSMITTER     			CESSNA	208   	208B        	2073701	CE  										FUEL SYSTEM	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			950  							(AUS) FUEL GAUGES STARTED TO ONLY READ TO 550 POUNDS PER SIDE AND WOULD GO FULL SCALE ANY HIGHER.  CENTER OUTBOARD FUEL 	TRANSMITTERS REMOVED BOTH SIDES AND FOUND TO HAVE BROKEN WIRES IN UNIT AT EXACTLY THE SAME POSITIONS.					1	H	7	1 	3T				A37CE
1999011500347	19990115	00347	SO  	1999	1	15	AU981632         	1	19981208	G	5312	6695500	BULKHEAD        			PIPER 	PA28  	PA28181     	7102807	SO  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) VERTICAL STABILIZER FORWARD ATTACH FITTING WAS REMOVED DUE TO CORROSION AND IT WAS THEN DISCOVERED THAT THE DOUBLE	R AND BULKHEAD (P/N 62444-05) WERE FOUND TO BE CRACKED.					1	L	7	1 	3O				2A13
1999011500348	19990115	00348	CE  	1999	1	15	AU981633         	1	19981215	G	7922	53E22144	NUT             			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE OIL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L1470339A			(AUS) ENGINE THERMOSTATIC VALVE (VERNATHERM) WAS REMOVED TO DETERMINE PART NUMBER WAS COMPLIANT WITH AD/LYC/78A5.  IT WA	S FOUND THAT THE VALVE'S P/N 53E22144 WAS NOT APPLICABLE, BUT THE VALVE STILL FAILED THE INSPECTION CRITERIA - LOOSE RET	AINING NUT.  NOTE:  VALVE P/N 53E22144 IS NOT MENTIONED IN SB 318A AS A PROBLEM.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1999011500349	19990115	00349	GL  	1999	1	15	AU981634         	1	19981210	G	2720		STOP            			AMTR  	LNCAIR	320LANCAIR  	056129G	GL  										RUDDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THE RUDDER STOPS WORN ALLOWING OVER TRAVEL OF THE RUDDER.						1	L	7	1 	3O			RT	EXPA1L71
1999011500350	19990115	00350	EU  	1999	1	15	AU981635         	1	19981123	G	2710	NB45309	PUSHROD         			BNORM 	BN2   	BN2A8       	1520209	EU  										AILERON	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) PILOT REPORTED THAT FLIGHT CONTROLS SEEMED SLOPPY WHILE INSPECTING THEM PRIOR TO FLIGHT.  INSPECTION FOUND RIGHT A	ILERON PUSH-PULL ROD HAD BROKEN.					1	H	7	2 	3O				A17EU
1999011500351	19990115	00351	NM  	1999	1	15	AU981636         	1	19981128	G	2120		LOOM            			BOEING	747   	747438      		NM  										AIR DIST	MISINSTALLED    	W				O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			AU	S 										(AUS) DURING CLIMB CAUTION MESSAGE, 'EQUIPMENT COOLING'  ANNOUNCED.   GROUND INSPECTION FOUND DAMAGED AND BURNED EQUIPME	NT COOLING WIRING IN FORWARD CARGO AREA.  THE ADJACENT INSULATION BLANKET WAS FOUND TO HAVE BEEN BURNED BY THE SHORTING 	WIRING.  FURTHER INVESTIGATION REVEALED THE AFFECTED WIRING HAD BEEN ROUTED UNDER INSTEAD OF OVER THE INSULATION BLANKET	.  THE DAMAGE HAD BEEN CAUSED BY STEPPING ON THE BLANKET CRUSHING THE WIRING AGAINST THE METAL STRUCTURE.			2	L	7	4 	4F			RT	A20WE
1999011500352	19990115	00352	NM  	1999	1	15	AU981637         	1	19981207	G	5753	65B085641	FLAP            			BOEING	747   	747238B     	1384828	NM  										TE FLAP	MALFUNCTIONED   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			AU	S 										(AUS) ON LANDING, THE RT OUTBOARD TE FLAPS STOPPED AT 25 DEGREES.  FURTHER ATTEMPTS TO DRIVE FLAPS RESULTED IN STALLED D	RIVE ABILITY.  INVESTIGATION FOUND A SHEARED FITTING BETWEEN THE FLAP AND FLAP-DRIVE BALLSCREW.					2	L	7	4 	4F				A20WE
1999011500353	19990115	00353	NM  	1999	1	15	AU981638         	1	19981208	G	4920	P1302	APU             			BOEING	767   	767238      		NM  	PWA   	JT9   	JT9D7R4E    	52054	NE  					APU BAY	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 					P1302					(AUS) DURING ENGINE START, A SHUDDER WAS FELT THROUGHOUT THE AIRCRAFT.  THIS WAS ACCOMPANIED BY A LOUD NOISE.  INVESTIGA	TION FOUND THE APU HAD FAILED WITH MANY METAL PIECES BEING EJECTED FROM THE TAILPIPE ONTO THE GROUND.					2	L	7	2 	4F	4	F	RT	A1NM    	E3NE
1999011500354	19990115	00354	NM  	1999	1	15	AU981639         	1	19981205	G	3244	161U0011	TIRE            			BOEING	747   	747438      		NM  										RT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) AFTER LIFT-OFF, EICAS MESSAGE DISPLAYED 'LOW TIRE PRESSURE' AND THE CABIN CREW ALSO REPORTED A LOUD EXPLOSION AND 	OTHER NOISE.   LANDING GEAR SYNOPTIC CONFIRMED NR 11 RT MLG TIRE DEFLATED.					2	L	7	4 	4F			RT	A20WE
1999011500355	19990115	00355	NM  	1999	1	15	AU981640         	1	19981216	G	6720	3132	BEARING         		AO311       	ROBSIN	R22   	R22BETA     		NM  										TAIL ROTOR	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					3132					(AUS) PILOT REPORTED NOISE ON ROTOR RUN DOWN AND ALSO HAD EXPERIENCED AN UNEXPLAINED YAW DURING LAST FLIGHT.  INSPECTION	 OF THE TAIL ROTOR PITCH CONTROL FOUND THAT THE BALL BEARING WITHIN THE ASSEMBLY WAS AT THE POINT OF SEIZURE.   BEARING 	WAS MANUFACTURED BY MRC JAPAN P/N 105KSZZ H401.				1	G	7	1 	3O				H10WE
1999011500356	19990115	00356	NE  	1999	1	15	AU981641         	3	19981214	G	6111	880808	SHEATH          	HAMSTD      		DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  	HAMSTD	14SF	14SF7       	NE  	PROPELLER BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			8103 				120282	880808		(AUS) PROPELLER BLADE (P/N $FA13MIROA+) METAL SHEATH CRACKED ALONG THE LEADING EDGE OF THE BLADE APPROXIMATELY 31.75 MM 	(1.25 INCHES) IN LENGTH.  PART TC:  14,103.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
1999011500357	19990115	00357		1999	1	15	AU981642         	4	19981214	G	3422	D3137LB21C	INDICATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  										COCKPIT	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			AU	S 					9183					(AUS) CREW REPORTED AN ELECTRICAL SMELL IN THE COCKPIT, CO-INCIDENT WITH CAPTAIN'S RADIO MAGNETIC INDICATOR U/S FLAG AND	 ADF NR 2 NEEDLE FREEZING AND TRIPPING OF 26VAC ADF NR 2 CIRCUIT BREAKER.					2	H	7	2 	4T			RT	A13NM
1999011500358	19990115	00358	NM  	1999	1	15	AU981643         	1	19981011	G	3231	82910010175	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  										MLG DOOR	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING TURN-AROUND, HYDRAULIC FLUID WAS FOUND ON THE GROUND NEAR NOSE-WHEELS.  INSPECTION FOUND THAT THE NOSE GEAR	 DOOR (PRESSURE CLOSE) PIPE ASSEMBLY P/N 82910010-175 HAD A PIN HOLE.					2	H	7	2 	4T			RT	A13NM
1999011500359	19990115	00359	NE  	1999	1	15	AU981644         	1	19981211	G	3246	50076812	WHEEL           			SKRSKY	S76   	S76C        	8143008	NE  										LT MLG	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 			114  		JUN920645					(AUS) LEFT MAIN OUTBOARD WHEEL HALF FLANGE PIECE 17.15 CM BY 3.81 CM (6.75 INCHES BY 1.5 INCHES) BROKE OFF WHILE AIRCRAF	T ON TAXI TO TAKEOFF - TIRE PARTIALLY DEFLATED.  PART TC:  2,334.					1	G	7	2 	3U			NC	H1NE
1999011500360	19990115	00360	NE  	1999	1	15	AU981645         	1	19981211	G	6322	0401272820	DUCT            			SKRSKY	S76   	S76C        	8143008	NE  	TMECA 	ARRIEL	ARRIEL1S    	60030	NE  					NR 2 ENGINE	DELAMINATED     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) NR 2 ENGINE OIL TEMPERATURE REPORTED HIGH.  INVESTIGATION FOUND THE OIL COOLER BLOWER FLEX DUCT INNER LINING COMPL	ETELY DELAMINATED AND EFFECTIVELY BLOCKING AIR FLOW.					1	G	7	2 	3U	3	U	NC	H1NE    	E19EU
1999011500361	19990115	00361		1999	1	15	AU981646         	1	19981214	G	7921	45E041	VALVE           								PWA   	PW120 	PW123       		NE  					LT ENGINE	FAULTY          	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 										(AUS) DURING CLIMB, THE LT ENGINE OIL TEMPERATURE EXCEEDED THE 'RED' LINE.  GROUND INVESTIGATION FOUND THAT THE OIL COOL	ER'S TEMPERATURE CONTROL VALVE WAS FAULTY.										4	T			E20NE
1999021200026	19990212	00026		1999	2	12	AU981647         	1	19981216	G	7931	230386402	PROCESSOR       								LYC   	ALF502	ALF502R5    	41580	NE  					OIL PRESSURE	MALFUNCTIONED   	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			AU	S 										(AUS) DURING CRUISE, THE NR 3 ENGINE LOW OIL PRESSURE LIGHT ILLUMINATED - GAUGE WAS SHOWING NORMAL 90 PSI.  GROUND INVES	TIGATION FOUND THE DUAL LOW OIL PRESSURE PROCESSOR DEFECTIVE.										4	F			E6NE
1999021200027	19990212	00027	EA  	1999	2	12	AU981648         	1	19981203	G	2760	2335627	MANIFOLD        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  					DRAG CONTROL	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			AU	S 					053L					(AUS) AFTER STARTING ALL ENGINES, NR 2 HYDRAULIC SYSTEM PRESSURE FELL TO ZERO AND THE ANNUNCIATOR LIGHT ILLUMINATED.  IN	SPECTION REVEALED TOTAL LOSS OF FLUID FROM TWO 3.81 CM (1.5 INCHES) AXIAL CRACKS IN THE FLIGHT SPOILER MANIFOLD BODY CYL	INDER WALL.				2	H	7	4 	4T	4	T		A20EA   	E4EA
1999021200028	19990212	00028	SO  	1999	2	12	AU981649         	2	19981217	G	8550		LINE            			CESSNA	340   	340A        	2076405	CE  	CONT  	O520  	TSIO520N    	17040	SO  					ENGINE OIL	LEAKING         	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 							514242			(AUS) DURING FLIGHT, ENGINE WAS SHUT DOWN DUE TO LOSS OF ENGINE OIL PRESSURE.  INVESTIGATION FOUND AN OIL PIPE LEAKING A	S RESULT OF PIT HOLE CORROSION - PIPE RUBBING AGAINST THE SCAT HOSE APPEARS TO BE A POSSIBLE CAUSE.					1	L	7	2 	3O	3	O		3A25    	E8CE
1999021200029	19990212	00029	EU  	1999	2	12	AU981650         	1	19981216	G	5302	365A2300000103	SKIN            	AEROSP      	365A230000  	AEROSP	SA365 	SA365C      	8680667	EU  										TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			3729 		5093					(AUS) DURING A SCHEDULED INSPECTION, CRACKS WERE FOUND IN THE TAIL BOOM.  THE CRACKS WERE ISOLATED TO THE AREA ADJACENT 	TO THE LT AND RT HORIZONTAL STABILIZER ATTACHMENT POINTS.  PART TC:  3,729.					1	G	7	2 	3U				H10EU
1999021200030	19990212	00030	SW  	1999	2	12	AU981651         	1	19981112	G	2910	27810322682	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  					HYDRAULIC SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					AC600		P44320CP4433			(AUS) DURING CRUISE, THE LT 'RED' HYDRAULIC ANNUNCIATOR LIGHT ILLUMINATED AND HYDRAULIC PRESSURE DROPPED TO ZERO.  GROUN	D INVESTIGATION FOUND A HYDRAULIC PIPE HAD CHAFED AGAINST THE OIL TANK CAUSING A PIN HOLE LEAK.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999021200031	19990212	00031	WP  	1999	2	12	AU981652         	2	19981209	G	7250		NUT             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313U    	01514	WP  					TURBINE SECTION	FAILED          	W				O				OTHER                   				W			INADEQUATE Q C            			TO	TAKEOFF        	1			AU	S 			4944 							(AUS) ENGINE REAR TURBINE SHAFT NUT NOT REPLACED WITH NEW ITEM FOLLOWING MAINTENANCE.  CONSEQUENTLY, AFTER 290 HRS OF EN	GINE RUNNING, THE 'OLD' NUT FAILED AND BROKE INTO 4 PARTS CAUSING EXTENSIVE DAMAGE TO TURBINE WHEELS, IMPELLORS AND STAT	ORS.  PART TC:  15,395.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999021200032	19990212	00032	NM  	1999	2	12	AU981653         	1	19981212	G	5414		PANEL           			BOEING	737   	737376      		NM  										NR 1 PYLON	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING PRE-FLIGHT INSPECTION, TWO PANELS FOUND MISSING FROM NR 1 PYLON:  PANEL NR 5728L, PN 311A1065-77, AND PANEL	 NR 5729L, PN 311A1065-78.					2	L	7	2 	4F			RT	A16WE
1999021200033	19990212	00033	NM  	1999	2	12	AU981654         	1	19981128	G	2150	1828201	HEAT EXCHANGER  			BOEING	737   	737376      		NM  										CABIN COOLING	CONTAMINATED    	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			AU	S 					125702265684					(AUS) AIRCRAFT UNABLE TO PRESSURIZE AFTER TAKEOFF.  INVESTIGATION FOUND BOTH LEFT PACK HEAT EXCHANGERS WERE CONTAMINATED	 WITH A FIBREGLASS MATERIAL, SEVERELY RESTRICTING FLOW, ALSO, THE AUTOMATIC FLOW CONTROL VALVE WAS STICKING.					2	L	7	2 	4F			RT	A16WE
1999021200034	19990212	00034	SO  	1999	2	12	AU981655         	2	19981202	G	8500	528021	ENGINE          			PIPER 	PA46  	PA46310P    	7104605	SO  	CONT  	O520  	TSIO520B    	17040	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	ENGINE BAY	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			71   		528021		528021	AM2542		(AUS) DURING SCHEDULED ENGINE MAINTENANCE, THE FOLLOWING PROBLEMS WERE FOUND:  1.  ENGINE OIL FILTER INSPECTED AND FOUND	 (EXCESSIVE) HIGH LEVELS OF COPPER.  2.  TWO CYLINDERS REMOVED DUE TO LOW COMPRESSION.  3.  SUMP REMOVED - MINOR METAL P	ARTICLES FOUND.  4.  CON ROD REMOVED FROM LOW CYLINDER POSITION AND CON ROD BEARING  SURFACE HAVE METAL CONTAMINATION. 5	.  OIL ANALYSIS CARRIED OUT - HIGHER WEAR LEVELS FOUND.  PART TC:  2,386.			1	L	7	1 	3O	3	O	RT	A25SO   	E8CE	5	C	P920
1999021200035	19990212	00035	SO  	1999	2	12	AU981656         	2	19981102	G	8530	653426A7	CYLINDER        			CESSNA	175   	175A        	2072504	CE  	CONT  	O300  	GO300C      	17022	SO  					ENGINE	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							125330C			(AUS) DURING INSPECTION, NR 4 CYLINDER FOUND LEAKING AT HEAD/BARREL JOINT.  PART TC:  108.						1	H	7	1 	3O	3	O		3A17    	E298
1999021200036	19990212	00036	NM  	1999	2	12	AU981657         	1	19981227	G	7921	20008A	OIL COOLER      			ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			AU	S 			328  		L96266184		L1416239A			(AUS) DURING CRUISE, THE ENGINE LOW OIL PRESSURE LIGHT BEGAN TO FLICKER AND OIL PRESSURE DROPPED.  GROUND INSPECTION FOU	ND THAT THE ENGINE HAD ONLY 2.75 LITERS OF OIL LEFT.  FURTHER INVESTIGATION FOUND A SMALL HAIRLINE CRACK APPROXIMATELY 2	.54 CM (1.0 INCHES LONG IN ONE OF THE OIL COOLER PN 20008A (A649-2) FINS CLOSEST TO THE INLET AND OUTLET FITTINGS ON THE	 OUTBOARD SIDE.			1	G	7	1 	3O	3	O		H10WE   	E274
1999021200037	19990212	00037	SO  	1999	2	12	AU981658         	1	19981228	G	3260	M5272401	SWITCH          			EMB   	110   	EMB110P2    	3260124	SO  										MLG	MALFUNCITIONED  	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) WITH LANDING GEAR SELECTED DOWN, THE RIGHT SIDE HAD NO DOWNLOCK INDICATION.  FAULT TRACED TO FAULTY UPLOCK MICROSW	ITCH.  SUSPECT WATER INGRESS INTO THE MICROSWITCH.					1	L	7	2 	4T				A21SO
1999021200038	19990212	00038	SO  	1999	2	12	AU981659         	1	19981228	G	3260	MS272402	SWITCH          			EMB   	110   	EMB110P2    	3260124	SO  										MLG	MALFUNCTIONED   	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			AU	S 										(AUS) WITH LANDING GEAR SELECTED DOWN, THE RT SIDE HAD NO DOWNLOCK INDICATION.  FAULT TRACED TO FAULTY UPLOCK MICROSWITC	H - DOWNLOCK MICROSWITCH WAS ALSO REPLACED.  SUSPECT WATER INGRESS INTO THE MICROSWITCH.					1	L	7	2 	4T				A21SO
1999021200039	19990212	00039	SO  	1999	2	12	AU981660         	2	19981203	G	8530	SA52000A2	CYLINDER HEAD   			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					570635		570635			(AUS) DURING ENGINE INSPECTION, NRS 1 AND 2 CYLINDER HEADS WERE FOUND TO HAVE CRACKS WHICH STARTED AT THE TOP SPARK PLUG	 HOLE RUNNING BEHIND THE FUEL INJECTOR DOWNWARDS BETWEEN FIN NRS 17 AND 18 (COUNTED FROM THE BARREL JOINT).  THE VERTICA	L CRACK IN CYLINDER NR 1, TRANSFERRED ACROSS ONE FIN AND FINISHED AT APPROXIMATELY 30 MM (1.18 INCHES) ABOVE THE INLET F	LANGE.  PART TC:  1,322.			1	H	7	1 	3O	3	O		A4CE    	E5CE
1999021200040	19990212	00040	CE  	1999	2	12	AU981661         	1	19981215	G	5730		WING TIP        			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A20      	52043	EA  					LT WING	LIGHTNING STRIKE	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			AU	S 										(AUS) DURING CRUISE, LIGHTNING DISCHARGED ONTO THE LEFT HAND WING TIP.  INVESTIGATION FOUND DAMAGE WAS LIMITED TO THE OU	TBOARD WING TIP PLASTIC FAIRING AND MINOR TRAILING EDGE DAMAGE AT THE EXIT POINT LOCATED ON THE LEFT HAND WING TRAILING 	EDGE APPROXIMATELY 30.48 CM (12 INCHES) INBOARD FROM THE WING TIP.				1	L	7	2 	3T	3	T		3A20    	E4EA
1999021200041	19990212	00041	NM  	1999	2	12	AU981662         	1	19981216	G	5755	85770068003	BRACKET         			DHAV  	DHC8  	DHC8102     	2809003	NM  										SPOILER	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) WING GROUND SPOILER PANEL'S LT OUTBOARD ATTACHMENT BRACKET FOUND BROKEN AT ACTUATOR LINK ATTACHMENT.  SUSPECT A PO	SSIBLE CAUSE OF THE FAILURE WAS DUE TO INCORRECT RIGGING ASSEMBLY AT LAST FITMENT AS THE ACTUATOR ROD END REQUIRED ADJUS	TMENT TO RECONNECT THE LINK TO THE SPOILER.				2	H	7	2 	4T			RT	A13NM
1999021200042	19990212	00042	SO  	1999	2	12	AU981663         	1	19981223	G	3233		ACTUATOR        			PIPER 	PA46  	PA46310P    	7104605	SO  										MLG	LEAKING         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) AFTER TAKEOFF AND LANDING GEAR RETRACTED, THE HYDRAULIC PRESSURE CYCLED AND TRIPPED THE HYDRAULIC MOTOR CIRCUIT BR	EAKER.  THE LANDING GEAR THEN PARTIALLY EXTENDED BY ITSELF.  AN EMERGENCY EXTENSION DID NOT FULLY EXTEND THE NOSE GEAR. 	 BY STEEP TURNING AT LOW AIRSPEED, THE NLG EXTENDED, BUT NO GREEN LIGHT CAME ON. PROBLEM WAS TRACED TO A LEAKING SHAFT S	EAL IN THE LT MLG ACTUATOR.			1	L	7	1 	3O			RT	A25SO
1999021200043	19990212	00043	CE  	1999	2	12	AU981664         	1	19981215	G	5730		WING TIP        			CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	WING	DAMAGED         	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			AU	S 							286463	780945		(AUS) AFTER LANDING, THE AIRCRAFT DEPARTED RUNWAY AND RAN INTO SOFT SOIL SLIGHTLY DAMAGING BOTH DROP WING TIPS AND ONE P	ROPELLER BLADE.					1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
1999021200044	19990212	00044	NE  	1999	2	12	AU981665         	2	19981215	G	7230	3035569	IMPELLER        			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2305 		120831		120831			(AUS) NR 2 ENGINE LP IMPELLER DAMAGED BY FOD.  ALL SIXTEEN VANES WERE DAMAGED WITH 1.58 MM (.0625 INCH) TO 6.35 MM (.25 	INCH) CUTS AND DENTS ALONG THE LEADING EDGE.  PART TC:  2,305.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999021200045	19990212	00045	CE  	1999	2	12	AU981666         	1	19981207	G	3213	AN17520	BOLT            			CESSNA	402   	402C        	207590R	CE  										LT MLG	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT MLG CENTER TORQUE LINK BOLT DETACHED.						1	L	7	2 	3O				A7CE
1999021200046	19990212	00046	EA  	1999	2	12	AU981667         	1	19981220	G	5220		DOOR            			DHAV  	DHC6  	DHC6200     		EA  										EMERGENCY EXIT	UNLOCKED        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			AU	S 										(AUS) ON ROTATION, THE DOOR UNSAFE WARNING ANNUNICATOR ILLUMINATED.  DURING GROUND INVESTIGATION, THE RT EMERGENCY EXIT 	DOOR LATCHING MECHANISM WAS REMOVED AND INSPECTED - NO OBVIOUS DEFECTS WERE NOTED OTHER THAN THE MECHANISM REQUIRED TIGH	TENING AND THE DOOR HANDLE KEY SHAFT WAS REPLACED.				1	H	7	2 	3T				A9EA
1999021200047	19990212	00047	EA  	1999	2	12	AU981668         	2	19981223	G	8520		BEARING         			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	FAILED          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			AU	S 							L256661A			(AUS) DURING CLIMB, THE LT ENGINE MANIFOLD PRESSURE DECREASED FROM 39 INCHES TO 30 INCHES WITH A VISIBLE OIL AND SMOKE T	RAIL.  GROUND INVESTIGATION FOUND METAL CONTAMINATION IN THE LT ENGINE OIL FILTER AND FURTHER INVESTIGATION FOUND THAT T	HE NR 6 MAIN BEARING HAD FAILED.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1999021200048	19990212	00048		1999	2	12	AU981669         	2	19981218	G	7313		INJECTOR        																	FUEL SYSTEM	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) AT BENCH TEST, ENGINE INJECTION SYSTEM UNIT FOUND TO HAVE EXCESSIVE HYSTERESIS.  ALSO, UNABLE TO ALIGN DIAPHRAGM S	TACK TO CORRECT PROBLEM.
1999021200049	19990212	00049	CE  	1999	2	12	AU981671         	1	19981129	G	2731	12600743	ACTUATOR        			CESSNA	402   	402B        	207590P	CE  										ELEVATOR TAB	SEIZED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CL	CLIMB          	1			AU	S 			740  							(AUS) RIGHT ELEVATOR TRIM ACTUATOR SEIZED.						1	L	7	2 	3O				A7CE
1999021200050	19990212	00050	EA  	1999	2	12	AU981672         	2	19981231	G	7414	IO50746Y	GEAR            	BENDIX      	S4LN200     	ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					MAGNETO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			2028 		834201		L1679839A			(AUS) MAGNETO DISTRIBUTOR GEAR FINGER CENTERING HOLE ELONGATED CAUSING ENGINE TO RUN ROUGH.						1	G	7	1 	3O	3	O		H10WE   	E274
1999021200051	19990212	00051	EU  	1999	2	12	AU981673         	1	19981230	G	5753		RIVET           			BAG   	BAE146	BAE146200A  	1500266	EU  										TE FLAP	MISSING         	W				O				OTHER                   				F			FLT CONT AFFECTED         			LD	LANDING        	1			AU	S 										(AUS) DURING LANDING, VIBRATION WAS NOTICED WHEN FLAPS WERE EXTENDED.  GROUND INVESTIGATION REVEALED 38 RIVETS MISSING F	ROM UPPER TORSION BOX SKIN AT THE MID-POINT ALONG THE RT FLAP FORWARD EDGE.  SKIN EDGE LIFTED IN AIR FLOW AND INITIAL BO	RESCOPE INSPECTION REVEALED 3 CRACKED TORSION BOX RIB FLANGES.				2	H	7	4 	4F			RT	A49EU
1999021200052	19990212	00052	SO  	1999	2	12	AU981674         	1	19981224	G	3230		BOLT            			PIPER 	PA23  	PA23250     	7102308	SO  										NLG	OVERTORQUED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING A TEST FLIGHT FOLLOWING MAJOR MAINTENANCE, THE LANDING GEAR WAS SELECTED DOWN, RESULTING IN NO NLG INDICATI	ON.  ON LANDING, THE NOSE GEAR COLLAPSED.  GROUND INVESTIGATION FOUND THAT A DRAG LINK BOLT HAD BEEN OVER-TORQUED.					1	L	7	2 	3O				1A10
1999021200053	19990212	00053	NM  	1999	2	12	AU981675         	1	19981222	G	2910	65C268393202	LINE            			BOEING	737   	737476      		NM  										HYDRAULIC SYSTEM	FAILED          	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 										(AUS) DURING CLIMB, SYSTEM 'A' HYDRAULIC QUANTITY AND PRESSURE FELL TO ZERO.  INVESTIGATION FOUND A TUBE FROM SYSTEM 'A'	 MODULE TO POWER TRANSFER UNIT HAD FAILED.					2	L	7	2 	4F			RT	A16WE
1999021200054	19990212	00054	CE  	1999	2	12	AU981676         	1	19981124	G	3260	1CH16	SWITCH          			CESSNA	402   	402B        	207590P	CE  										MLG	MALFUCNITIONED  	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			AU	S 										(AUS) LANDING GEAR WOULD NOT RETRACT DUE TO A FAULTY 'SQUAT' MICROSWITCH.						1	L	7	2 	3O				A7CE
1999021200055	19990212	00055	EU  	1999	2	12	AU981677         	1	19981230	G	2910	A71940023	ELBOW           			FOKKER	F28   	F28MK4000   	4990810	EU  										HYDRAULIC SYSTEM	SHEARED         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			AU	S 					AH37361AB					(AUS) DURING CLIMB, PILOT NOTICED LOSS OF UTILITY SYSTEM HYDRAULIC PRESSURE AND CONTENTS.  GROUND INVESTIGATION FOUND TH	E RIGHT ANGLE PRESSURE LINE ELBOW ON SYSTEM '1' HYDRAULIC PUMP FITTED TO NR 1 ENGINE HAD COMPLETELY SHEARED OFF AT THE T	HREAD.  PART TC:  35,076.				2	L	7	2 	4F			RT	A20EU
1999021200056	19990212	00056	CE  	1999	2	12	AU981678         	1	19981224	G	2750		SWITCH          			CESSNA	206   	U206G       	2073356	CE  										TE FLAP	CORRODED        	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			AU	S 										(AUS) ON SELECTION, FLAPS FAILED TO EXTEND.  INVESTIGATION FOUND CORRODED TERMINALS ON THE SELECTOR SWITCH MICROSWITCHES	.					1	H	7	1 	3O				A4CE
1999021200057	19990212	00057	CE  	1999	2	12	AU981679         	1	19981222	G	2910		CONNECTOR       			CESSNA	206   	U206G       	2073356	CE  										HYDRAULIC SYSTEM	LOOSE           	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) MAIN LANDING GEAR 'UP' PRESSURE LINE CONNECTION TO SELECTOR FOUND NOT CORRECTLY TIGHTENED - RESULTING IN COMPLETE 	LOSS OF RESERVOIR OIL.					1	H	7	1 	3O				A4CE
1999021200058	19990212	00058	WP  	1999	2	12	AU981680         	2	19981221	G	7240		PLENUM          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  					TURBINE SECTION	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							PO3177C			(AUS) COMBUSTION CHAMBER (PLENUM) CASE CRACKED 11.1 MM (0.44 INCH) IN LENGTH BETWEEN THE 3RD AND 4TH FUEL NOZZLE, ADJACE	NT TO THE TURBINE SUPPORT DUCT MOUNTING FLANGE.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999021200059	19990212	00059	SW  	1999	2	12	AU981681         	1	19981221	G	5711	TC256	SPAR            			SWRNGN	SA226 	SA226TC     	8780404	SW  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					TC256					(AUS) DURING INSPECTION, A CRACK WAS FOUND IN THE SPAR ASSEMBLY EXTENDING FROM STRINGER NR 13.						2	L	7	2 	4T			RT	A8SW
1999021200060	19990212	00060	NM  	1999	2	12	AU981682         	1	19981217	G	5210	65B1605526	CONTROL CABLE   			BOEING	747   	747438      	       	NM  										PASSENGER DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 LT MAIN ENTRY DOOR CABLE LOCATED IN THE BODY TORQUE TUBE AREA FOUND BROKEN AS A RESULT OF CORROSION.						2	L	7	4 	4F			RT	A20WE
1999021200061	19990212	00061		1999	2	12	AU981683         	4	19981203	G	2565	416T23194	CLIP            		101656306   	BOEING	767   	767338      		NM  	GE    	CF6   	CF680C2A5   		NE  					ESCAPE SLIDE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 					PH0197					(AUS) ON REMOVAL OF THE LT 'OFF WING' ESCAPE SLIDE, THE RELEASE STRING TENSION BAR WAS FOUND ADRIFT WITHIN THE SLIDE COM	PARTMENT.  FURTHER INVESTIGATION FOUND THE ATTACHMENT BEARING P-CLIPS (7 OFF) SHEARED.					2	L	7	2 	4F	4	F	RT	A1NM    	E13NE
1999021200062	19990212	00062	NM  	1999	2	12	AU981684         	1	19981223	G	2611		SMOKE DETECTOR  			BOEING	747   	747438      		NM  										CARGO BAY	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AU	S 										(AUS) AFT CARGO HOLD SMOKE DETECTOR SENSOR FOUND COVERED OVER WITH TAPE.  FOUND DURING ROUTINE INSPECTION.						2	L	7	4 	4F			RT	A20WE
1999021200063	19990212	00063	EA  	1999	2	12	AU981685         	2	19981210	G	8530	LW11633	CYLINDER        			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			AU	S 					L2287815		L2287815			(AUS) DURING FLIGHT, THE ENGINE COMMENCED VERY ROUGH RUNNING.  GROUND INVESTIGATION FOUND NR 1 CYLINDER HAD CRACKED THRO	UGH 360 DEGREES FROM THE ATTACHMENT FLANGE TO THE FIRST FIN. THE CYLINDER REMAINED ATTACHED AS ONE END CRACK WAS APPROXI	MATELY 19 MM (0.75 INCH) ABOVE THE OTHER.  PART TC:  1,954.				1	L	7	1 	3O	3	O		A18SO   	E223
1999021200064	19990212	00064	EU  	1999	2	12	AU981686         	1	19981231	G	7603		ROD             			FOKKER	F28   	F28MK4000   	4990810	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					POWER LEVER	OUT OF ADJUST   	W				C				ABORTED TAKEOFF         				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			AU	S 										(AUS) DURING TAKEOFF, NR 2 ENGINE FAILED TO REACH 100 PERCENT THRUST.  GROUND INVESTIGATION FOUND THE ENGINE CONTROL ROD	 'D' OUT OF ADJUSTMENT, I.E. OFF THE MAXIMUM STOP.  34,454.					2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1999021200065	19990212	00065	EU  	1999	2	12	AU981687         	1	19981220	G	3240	A77126405	CONTROL CABLE   			FOKKER	F28   	F28MK4000   	4990810	EU  										BRAKE SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) DURING INSPECTION, THE CABLES TO BOTH NORMAL BRAKE CONTROL VALVES FOUND WORN - ONE OF THE CABLES HAD BROKEN STRAND	S EVIDENT.					2	L	7	2 	4F			RT	A20EU
1999021200066	19990212	00066	WP  	1999	2	12	AU981688         	2	19981205	G	7322	CHA31267	FLOAT           		A148HIM     	DHAVXX	DH82  	DH82AROBRTSN	2801002	WP  	DHAVXX	GIPSY 	GIPSYMAJOR1 	20004	WP  					CARBURETOR	FAULTY          	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			AU	S 					EM294		33			(AUS) DURING TAKEOFF, ENGINE SUFFERED POWER LOSS RESULTING IN FORCED LANDING AND DAMAGING AIRCRAFT. AN INTERNAL INSPECTI	ON OF THE CARBURETOR, FOUND A LARGE FUEL FILLED BUBBLE IN THE FLOAT'S VARNISH.  FURTHER INVESTIGATION FOUND THAT IT WAS 	POSSIBLE TO INDUCE STICKING OF THE FLOAT ASSEMBLY WHEN THE BUBBLE CAME IN CONTACT WITH THE FLOAT CHAMBER HOUSING.				1	Q	7	1 	3I	3	I		A8EU    	A8EU
1999021200067	19990212	00067	CE  	1999	2	12	AU981689         	1	19981215	G	2730	57341504	BRACKET         			CESSNA	441   	441         	2076020	CE  										ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) ELEVATOR TORQUE TUBE END RIB BRACKET CRACKED THROUGH TWO RIVETS AND ONE CRACK IN BETWEEN.  ALSO, CORROSION BUILD-U	P WAS EVIDENT BETWEEN SURFACE OF TORQUE TUBE AND BRACKET.					1	L	7	2 	3T			RT	A28CE
1999021200068	19990212	00068	EA  	1999	2	12	AU981690         	2	19981204	G	8520	75006	CRANKSHAFT      			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L967739A			(AUS) PRIOR TO HONING CRANKSHAFT TO 49.02 MM (1.930 INCHES) AND ON NDT INSPECTION, A CRACK OR INCLUSION ORIGINATING FROM	 A PIT WAS FOUND APPROXIMATELY 50.8 MM (2 INCHES) INSIDE FROM THE END.					1	L	7	1 	3O	3	O		2A13    	E274
1999021200069	19990212	00069	CE  	1999	2	12	AU981691         	1	19981230	G	2432	501743377	BATTERY         	GILLBATT    	G35         	CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  					E/E BAY	LIGHTNING STRIKE	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			AU	S 					501743377					(AUS) AIRCRAFT EXPERIENCED ELECTRICAL FAILURE IN-FLIGHT.  AFTER LANDING, BATTERY TERMINALS FOUND TO BE BURNT OFF AND THE	 STARTER HAD ENGAGED IN FLIGHT - THE STARTER WAS ALSO FOUND TO HAVE FAILED INTERNALLY.   POSSIBLE CAUSE ATTRIBUTED TO LI	GHTNING STRIKE.				1	H	7	1 	3O	3	O		A4CE    	E5CE
1999021200070	19990212	00070	SO  	1999	2	12	AU981692         	2	19981222	G	8530	653877	LIFTER          			CESSNA	210   	210N        	2073453	CE  	CONT  	O520  	IO520L      	17032	SO  					NR 6 CYLINDER	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			1148 		294770R		294770R			(AUS) NR 6 CYLINDER VALVE LIFTER WAS REMOVED AND FOUND DEFECTIVE - LIFTER FACE DETERIORATING DUE TO PITTING.  PART TC: 1	,148.					1	H	7	1 	3O	3	O		3A21    	E5CE
1999021200071	19990212	00071	EU  	1999	2	12	AU981693         	1	19981230	G	3320	31871	CONNECTOR       			BAG   	JETSTM	JETSTM3107  	1500215	EU  										CABIN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CABIN OVERHEAD FLURO LAMP CONNECTORS (3 OFF) AND WIRING FOUND TO BE DEFECTIVE - DISPLAYED OBVIOUS SIGNS OF HEATING	.  FOUND IAW AD/JETSTREAM 36 AMDT 1.					2	L	7	2 	4T			RT	BA15CAA
1999021200072	19990212	00072	CE  	1999	2	12	AU981694         	1	19981206	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING RT TRUNNION UPPER RADII CRACKED APPROXIMATELY 10 MM (0.394 INCH) IN LENGTH.  FOUND DURING NDI INSPECT	ION.  PART TC:  15,032.					1	L	7	2 	3T			RT	A28CE
1999021200073	19990212	00073	NE  	1999	2	12	AU981695         	2	19981226	G	7532	310334701	DIAPHRAGM       			CESSNA	208   	208         	2073702	CE  	PWA   	PT6   	PT6A114     	52043	NE  					BLEED VALVE	DAMAGED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			AU	S 					5Y037		PCE17463			(AUS) SMALL HOLES FOUND IN THE MOVING SECTION OF THE ENGINE BLEED VALVE DIAPHRAGM.  PART TC:  247.						1	H	7	1 	3T	3	T	NT	A37CE   	E4EA
1999021200074	19990212	00074	CE  	1999	2	12	AU981696         	1	19981116	G	3221	5842000211	TRUNNION        			CESSNA	441   	441         	2076020	CE  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NOSE LANDING LT TRUNNION UPPER RADII FOUND CRACKED APPROXIMATELY 7MM (0.276 INCH) IN LENGTH. FOUND DURING NDI INSP	ECTION.  PART TC:  1,195.					1	L	7	2 	3T			RT	A28CE
1999021200075	19990212	00075		1999	2	12	AU981697         	4	19980418	G	2565	7A144710	SLIDE           			BOEING	747   	747238B     	1384828	NM  										PASSENGER DOOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) NR 1 DOOR SLIDE (RT SIDE) FAILED TO INFLATE CORRECTLY WHEN TEST FIRING WAS CARRIED OUT. APPEARS THE SLIDE FOULED O	N THE DOOR BUSTLE.					2	L	7	4 	4F				A20WE
1999021200076	19990212	00076	EU  	1999	2	12	AU981698         	1	19981115	G	5330		SKIN            			BAG   	BAE146	BAE146200A  	1500266	EU  										BS 29	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) CRACK FOUND IN FUSELAGE SKIN APPROXIMATELY 19 MM (0.75 INCHES) LONG.  THE CRACK RAN THROUGH A RIVET HOLE JUST AFT 	OF FRAME 29 LHS, BETWEEN STRINGERS 12 AND 13.  FOUND IAW AD/BAE146-70.					2	H	7	4 	4F			RT	A49EU
1999021200077	19990212	00077	EU  	1999	2	12	AU981699         	1	19981212	G	3213	200429203	TORQUE LINK     			FOKKER	F28   	F28MK4000   	4990810	EU  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) THE UPPER NLG TORQUE LINK WAS FOUND CRACKED - ONE VISIBLE LATERAL CRACK ON EACH SIDE OF THE APEX LUBRICATION NIPPL	E LOCATION.  CRACKS WERE APPROXIMATELY 14 MM (0.551 INCH AND 12 MM (0.472 INCH) IN LENGTH.  PART TC:  57,137.					2	L	7	2 	4F			RT	A20EU
1999021200078	19990212	00078	EU  	1999	2	12	AU981700         	1	19981020	G	5753	HC579L0661000	PLATE           			BAG   	BAE146	BAE146300A  	1500267	EU  										TE FLAP	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) LEFT NR 3 FLAP FAIRING REAR OPERATING RODS FOUND FRACTURED UPON AIRCRAFT ARRIVAL. THE FAIRING ADJUSTER BOLT BARREL	 NUT WAS FOUND ADRIFT INSIDE THE FAIRING.  APPEARS TO HAVE BEEN INSUFFICIENT ENGAGEMENT OF THE ADJUSTER BOLT HEAD WITH I	TS LOCKING PLATE CAUSED BY EXCESSIVE SEALANT BETWEEN THE LOCKING PLATE AND THE FAYING SURFACE OF THE FAIRING.				2	H	7	4 	4F			RT	A49EU
1999021200079	19990212	00079	NM  	1999	2	12	AU981701         	1	19981224	G	5330		SKIN            			BOEING	747   	747312      	1384932	NM  										BS 500-520	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 										(AUS) FUSELAGE CONTACTED BY CARGO LOADING MACHINERY ADJACENT TO THE FORWARD CARGO DOOR, CAUSING THE FOLLOWING DAMAGE:  1	.2 INCH HOLES IN SKIN AT STA 520 - STA 540, EITHER SIDE OF STRINGER S40R.  2.  SKIN AND STRINGERS FROM STA 500 - STA 520	 ABOVE STRINGER S38R TO S44R.  3.  SKIN AND STRINGERS FROM STA 680 - STA 700 ABOVE STRINGER S38R TO S42R.				2	L	7	4 	4F			RT	A20WE
1999021200080	19990212	00080	NE  	1999	2	12	AU981703         	2	19981022	G	7261	9299M49G02	TUBE            								GE    	CF6   	CF680A      	30025	NE  					ENGINE OIL	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			AU	S 			5598 				580392			(AUS) ENGINE REMOVED DUE TO HIGH OIL CONSUMPTION.  THE COMPRESSOR REAR FRAME WAS DETACHED AND INVESTIGATION FOUND THE SU	MP OIL SUPPLY TUBE HAD BEEN WORN THROUGH BY AN ATTACHMENT 'P' CLIP.										4	F			E13NE
1999021200081	19990212	00081	NE  	1999	2	12	AU981704         	2	19981125	G	7240	9531M61G06	CASE            								GE    	CFM56 	CFM565A     	13802	NE  					ENGINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 			14413				731161			(AUS) ENGINE COMBUSTOR OUTER COWL FOUND WITH TWO SECTIONS OF COWL APPROXIMATELY 12.9 SQUARE CM (2 SQUARE INCHES) MISSING	.  ALSO, THE LIBERATED COWL PIECES HAD FRETTED SIGNIFICANTLY AGAINST THE ADJACENT FUEL NOZZLE STEMS.  FOUND IAW CFMI SB 	72-536.  PART TC:  14,413.									4	F			E29NE
1999021200082	19990212	00082	EA  	1999	2	12	AU981705         	2	19980710	G	8520		BUSHING         			CHILD 	S2    	S2APITTS    	0110201	NM  	LYC   	O360  	IO360A1A    	41514	EA  	HARTZL	HCC2Y	HCC2YK4     	GL  	ENGINE	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AU	S 							L318051A	AV8248A		(AUS) DURING MAINTENANCE, A GAP WAS FOUND BETWEEN THE REAR FACE OF THE CRANKSHAFT FLANGE AND SHOULDER OF PROPELLER STUD 	ATTACH BUSHINGS.  ALL BUSHINGS EXCEPT TWO INDEX BUSHINGS WERE FOUND PUSHED OUT OF SEATED POSITION.  BUSHINGS WERE FOUND 	TO BE TOO LONG AND BOTTOMING OUT IN PROPELLER HUB.				1	Q	7	1 	3O	3	O		A8SO    	1E10	5	C	P920
1998100200066	19981002	00066	SO  	1998	10	2	BTVR82598        	1	19980825	G	3340		LENS            	GRIMES      	3019591     	GULSTM	G1159 	G1159A      	3970109	SO  										FUSELAGE	BROKEN          	B			BTVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			GL	23	803CC	376  			0327	378				DURING A MAINTENANCE POST-FLIGHT, THE LEFT ENGINE N1 FAN SECTION WAS FOUND TO HAVE EXTENSIVE FOD.  IT WAS ALSO NOTED THE	 UPPER FUSELAGE STROBE TYPE ANTI-COLLISION LIGHT LENS WAS BROKEN WITH A LARGE PIECE MISSING.  FURTHER INSPECTION OF THE 	ENGINE INLET AREA REVEALED SMALL BITS OF RED GLASS IMBEDDED IN THE INLET COWL, ENGINE SPINNER, AND SEVERAL ENGINE FIRST 	STAGE FAN BLADES.  IT IS REASONABLE TO CONCLUDE THE BROKEN LENS CAUSED THE FOD.  REASON FOR THE LENS FAILURE IS CURRENTL	Y UNKNOWN AND IS UNDER INVESTIGATION.  (X)		2	L	7	2 	4F				A12EA
2000102400073	20001024	00073	EU  	2000	10	24	CA000801019      	3	19980122	G	6111		PROPELLER       	MUHBR       		RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  	MUHBR	MTV	MTV3BC      	EU  	PROPELLER BLADES	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			401  					L2592348A	96241		(CAN) LOOSE PROPELLER BLADES.						1	M	7	1 	3O	3	O	NC	EA67U   	1E4	5	C	USSR
2000102400153	20001024	00153	EU  	2000	10	24	CA000801020      	3	19981001	G	6111		PROPELLER       	MUHBR       		RHNFLU	EXT300	EA300L      	70218DG	EU  	LYC   	O540  	AEIO540L1B5 	41532	NE  	MUHBR	MTV	MTV3BC      	EU  	PROPELLER BLADES	LOOSE           	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			387  					L2594848A	97059		(CAN) LOOSE PROPELLER BLADES.						1	M	7	1 	3O	3	O	NC	EA67U   	1E4	5	C	USSR
2000112900328	20001129	00328	EA  	2000	11	29	CA001107013      	2	19980430	G	7414	S6RN2000	MAGNETO         	LYC         		BELL  	47    	47G4A       	1181031	SW  	LYC   	O540  	VO540B1B3   	41532	EA  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				648  		L225943					(CAN) MAGNETO HAS EXCESSIVE MAG DROP.						1	G	7	1 	3O	3	O	 	2H3     	E304
1998040200015	19980402	00015	EA  	1998	4	2	CA960223013      	2	19980312	G	8550	76354	OIL PUMP        			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENG OIL	CRACKED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			3192 	652  				L4004427A			(CAN) AFTER 2.5 HOUR FLIGHT, PILOT REPORTED OIL PRESSURE CREEPING DOWN DURING DESCENT.  GROUND RUN CARRIED OUT AND PRESS	URE MAINTAINED AT 70 TO 75 PSI.  WHILE  COMPASS SWING CARRIED OUT, PRESSURE DROPPED OFF AGAIN.  ENGINE REMOVED FOR OVERH	AUL.  REPORT FROM O/H SHOP STATED THAT OIL PUMP WAS CRACKED INTERNALLY.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998041700425	19980417	00425	NE  	1998	4	17	CA970210003      	2	19980317	G	7321	5001T39G29	FCU             								GE    	CF700 	CF7002D2    	30010	NE  					METERING VALVE	BAD VALVE       	W				D	E			RETURN TO BLOCK         	ENGINE SHUTDOWN         			X			ENGINE FLAMEOUT           			TX	TAXI/GRND HDL  	1			CA				49   				304505B			(CAN) ENGINE FLAMED OUT DURING TAXI.  FCU SENT FOR REPAIR.  O/H SHOP FOUND METERING VALVE FAULTY AND UNIT NEEDED NEW SEA	LS.  FCU CALIBRATED, NO OTHER FAULT.										4	F			E7EA
2000021200001	20000212	00001	GL  	2000	2	12	CA970505012      	2	19980416	G	7200		ENGINE          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE BAY	MALFUNCTIONED   	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			J			WARNING INDICATION        			HO	HOVERING       	1			CA			492  					CAE847044			(CAN) WHILE IN A 4 FOOT HOVER AT 100 PERCENT ROTOR AND NP RPM IN AUTOMATIC MODE, THE ENGINE WENT INTO AN UNCOMMANDED OVE	RSPEED OF 118.58 PERCENT THEN SHUT DOWN.  EMERGENCY LANDING CARRIED OUT SUCCESSFULLY.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998041700563	19980417	00563	WP  	1998	4	17	CA970521009      	2	19980319	G	7261	3615309101	OIL CAP         			LEAR  	35    	31A         	5170531	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					LT ENG OIL	LOOSE           	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CL	CLIMB          	1			CA			2946 					P99188			(CAN) LOSS OF OIL PRESSURE INDICATION ON LT ENGINE DURING CLIMB.  ENGINE PRECAUTIONARY SHUT DOWN CARRIED OUT.  FOUND LT 	ENGINE OIL DIPSTICK CAP NOT SECURE.  CLEANED ENGINE, REPLACED OIL CAP PACKING, AND RE-SERVICED ENGINE OIL SYSTEM.					2	L	7	2 	4F	4	F	RT	A10CE   	E6WE
1998041700592	19980417	00592	CE  	1998	4	17	CA970605003      	1	19980319	G	3246	40169	WHEEL           	CLEVELAND   	40169       	CESSNA	441   	441         	2076020	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			330  					P77306			(CAN) OUTBOARD WHEEL HAS A .500 INCH CRACK RUNNING FROM BASE OF BOLT HOLE COUNTER BORE TO INSIDE OF WHEEL .500 INCH ABOV	E O-RING AIR SEAL.  CRACK ALLOWED TUBELESS TIRE TO SLOWLY DEFLATE.  REPLACED.					1	L	7	2 	3T	4	T	RT	A28CE   	E4WE
1998041700593	19980417	00593	CE  	1998	4	17	CA970605006      	1	19980319	G	2730	55653422	PUSH ROD        			CESSNA	500   	560CESSNA   	2076750	CE  	PWA   	JT15  	JT15D5      	52112	NE  					ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			640  					PCE500171			(CAN) LEFT HAND ELEVATOR PUSH ROD SUSTAINED DAMAGE BY CONTACT BETWEEN THE INNER SIDE OF THE ROD AND THE ELEVATOR LOWER S	KIN STRUCTURE.  ROD DAMAGE WAS .003 INCH TO .004 INCH AND EXTENDED OVER A LENGTH OF .450 INCH.					2	L	7	2 	4F	4	F	RT	A22CE   	E25EA
1998050100141	19980501	00141	GL  	1998	5	1	CA970625001      	2	19980319	G	7260	6889701	GEARSHAFT       								ALLSN 	250C  	250C20      	03013	GL  					TORQUEMETER	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA								CAE800869BA			(CAN) SEVERAL CRACKS ORIGINATING FROM THE INNER SHOULDER AREA WORN TO APPROXIMATELY HALF THE THICKNESS FROM CONTACT WITH	 TORQUEMETER PISTON THRUST BEARING.  THESE CRACKS RUN RADIALLY, THEN INTO THE THIRTY TOOTH GEAR, THEN AXIALLY FULL LENGT	H OF THE GEAR.  THE WEB PORTION BETWEEN THE 30 AND 83 TOOTH EXHIBIT CRACKS BRANCHING BUT NOT EXTENDING INTO THE 83 TOOTH	 GEAR.								3	U			E4CE
1998040200094	19980402	00094	CE  	1998	4	2	CA970731023      	1	19980312	G	2497		WIRE HARNESS    			CESSNA	208   	208B        	2073701	CE  						HARTZL	H3B3M	HCB3M       	GL  	PITOT STATIC	CHAFED          	W				D				RETURN TO BLOCK         				B			SMOKE/FUMES/ODORS/SPARKS  			CL	CLIMB          	1			CA								PCE17166	GB59		(CAN) DURING CLIMB, THE CREW NOTED SPARKS AND SMOKE FROM THE LEFT HAND KICK PANEL BY THE PILOT'S KNEE.  INVESTGATION FOU	ND A CHAFED WIRE BUNDLE BY THE ALTERNATE PITOT STATIC SYSTEM.					1	H	7	1 	3T			 	A37CE   		5	C	P9NE
1998040200097	19980402	00097	CE  	1998	4	2	CA970731026      	1	19980312	G	6120	5038912131	PRESSURE SWITCH 			BEECH 	1900  	1900C       	1154161	CE  										AUTO FEATHER	MALFUNCTIONED   	W				K				NONE                    				J	O		WARNING INDICATION        	OTHER                     		TO	TAKEOFF        	1			CA			12865								(CAN) FLIGHT CREW REPORTED THAT THE AUTOFEATHER ARMING LIGHT FOR THE RT A/F SYSTEM WAS NOT ILLUMINATING.  SYSTEM TEST WA	S OK.  MAINTENANCE REPLACED THE RT HIGH PRESSURE SWITCH FOR RESPONSIBLE FOR TURNING THE LIGHT ON.  A/C SYSTEM WAS TESTED	 AND FOUND OK.				2	L	7	2 	4T			RT	A24CE
1998040200099	19980402	00099	CE  	1998	4	2	CA970807045      	1	19980312	G	2436	51530007B	REGULATOR       		51530007B   	BEECH 	90    	F90         	1152909	CE  	PWA   	PT6   	PT6A135     	52043	NE  	HARTZL	HCB4T	HCB4TN3     	GL  	DC SYSTEM	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			3414 					PCE92260	EA621		(CAN) CREW REPORTED ELECTRICAL BUS SEPARATION FOLLOWED BY AVIONICS CIRCUIT BREAKERS TRIPPING.  LEFT GENERATOR DEEMED TO 	BE THE CAUSE AND WAS ISOLATED.  MAINTENANCE FOUND THAT THE LEFT HAND GENERATOR CONTROL UNIT FAILED.					1	L	7	2 	4T	4	T		A31CE   	E4EA	6	C	P40EA
1998041700664	19980417	00664	CE  	1998	4	17	CA971104007      	1	19980331	G	3233	ADI79990035	PISTON ROD      		ADI79990033 	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG ACTUATOR	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3967 			ADI203M		PCE81498			(CAN) MAIN LANDING GEAR ACTUATOR LEAKING FLUID BETWEEN PISTON ROD AND ACTUATOR HOUSING.  DISASSEMBLY OF THE ACTUATOR REV	EALED CORROSION ON ROD AFFECTED THE"O" RING CAUSING THE HYDRAULIC LEAK.  NEW ACTUATOR INSTALLED.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998041700663	19980417	00663	SO  	1998	4	17	CA971104009      	1	19980331	G	2140	87D133	TUBE ASSY       	JANITROL    	65D792      	PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	PUNCTURED       	W				H				DEACTIVATE SYST/CIRCUITS				M			OVER TEMP                 			DE	DESCENT        	1			CA			526  			0414892					(CAN) DECAY TEST HAD BEEN CARRIED OUT ON HEATER.  PILOT CLOSED AIR INLET FOR A SHORT TIME CAUSING OVERHEATED CB TO POP. 	MAINTENANCE RESET OVERHEATED CB AND CLEARED IGNITER.  FUNCTIONAL TEST OF HEATER CARRIED OUT, HOWEVER, DECAY TEST CARRIED	 OUT WITH NEGATIVE RESULTS.  HEATER WAS REMOVED FOR FURTHER INSPECTION AND IT WAS FOUND THE INNER CAN WAS WARPED AND HAD	 A PUNCTURE.  A MORE FREQUENT INSPECTION OF THE HEATER IS RECOMMENDED TO PREVENT FUTURE PROBLEMS.			1	L	7	2 	3O				A20SO
1998100900150	19981009	00150	CE  	1998	10	9	CA971219024      	1	19980911	G	2752	505211954	PISTON          		505212234   	BEECH 	99    	C99         	1154006	CE  										ACTUATOR	INPROPER PART   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						712G81					(CAN) FLAP ACTUATOR PISTON WRONG PART NUMBER 50-5211954 IS AN ALUMINUM LIGHT DUTY PISTON AND NOT APPLICABLE TO ACTUATOR 	50-521223-4. THE CORRECT ITEM IS NUMBER 50-521195-8.  REPLACED.					1	L	7	2 	3T				A14CE
1998121800367	19981218	00367	GL  	1998	12	18	CA980122001      	2	19980118	G	7323	252476913	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			CA								CAE830588			(CAN) IN HOVER, N2 RPM CREEPING DOWN AND UNABLE TO REGAIN WITH BEEP SWITCH.  GOVERNOR ADJUSTED BY TECHNICIAN, BUT SAME P	ROBLEM PERSISTED.  GOVERNOR CHANGED.					1	G	7	1 	3U	3	U		H3WE    	E4CE
2001032100068	20010321	00068	SO  	2001	3	21	CA980225018      	1	19980216	G	2197		WIRE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					HEATER	MISINSTALLED    	W				H				DEACTIVATE SYST/CIRCUITS				W	K	B	INADEQUATE Q C            	FLUID LOSS                	SMOKE/FUMES/ODORS/SPARKS  	NR	NOT REPORTED   	1			CA											(CAN) IN FLIGHT FIRE IN REAR HEATER COMPARTMENT. HEATER SHUT DOWN DUE TO PASSENGERS AND CREW DETECTED SMELL. HEATER FAIL	ED DECAY TEST. IGNITER GASKET LEAKING, BAD VENT MOTOR, STILL RUNNING, ONE BRUSH GONE AND ARMATURE DAMAGED. FIRE SIGNS AN	D FUEL LEAK DETECTED ON POST INSTALLATION. WIRES BURNED ON TRIM INDICATION AND HEATER OPERATING SYSTEM. REPAIRED OR REPL	ACED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032100070	20010321	00070	EA  	2001	3	21	CA980302001      	1	19980211	G	2701	CSP832	CASTING         		C2CF1977AWD 	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					CONTROL COLUMN	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			20223								(CAN)  LOOSE RIVETS FOUND THAT HOLD THE TOP CASTING TO THE BOTTOM CONTROL COLUMN ASSEMBLY.  SEE IPC FIGURE NR 46. SUBMIT	TER SUGGESTS THAT THE PILOT USING THE SEAT BELT AS A GUST LOCK MAY BE THE CAUSE.					1	H	7	1 	3R	3	R	 	A806    	5E1
2001032100072	20010321	00072	EA  	2001	3	21	CA980302003      	1	19980217	G	3610	3035279	LINE            	PWA         	PT6A50      	DHAV  	DHC7  	DHC7103     	2802710	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	FLANGE	SEPARATED       	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J	 	ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA				2482 		86026					(CAN) AIRCRAFT WAS IN LEVEL FLIGHT WHEN THE NR 4 ENGINE LOST POWER AND DECELERATED TO IDLE. THE ENGINE WAS SHUTDOWN AND 	AN UNEVENTFUL LANDING WAS CARRIED OUT. POST FLIGHT INSPECTION FOUND A POST MOD P3 LINE SEPARATED AT THE FLANGE. REPLACEM	ENT OF THE LINE CORRECTED THE PROBLEM.				2	H	7	4 	4T	4	T	 	A20EA   	E4EA	6	C	P1NE
2001032100073	20010321	00073	CE  	2001	3	21	CA980302004      	1	19980223	G	5711		FASTENER        			BBAVIA	11    	11AC        	0191102	CE  	CONT  	A65   	A658        	17003	SO  					WING SPAR/RIB	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON INSPECTION RIB TO SPAR NAILS MISSING. FABRIC REMOVED AND IT APPEARS THAT THE FRONT SPAR HAD BEEN REPLACED AND T	HE NAILS WERE NOT INSTALLED.					1	H	7	1 	3O	3	O	 	A761    	E205
2001032100074	20010321	00074	SO  	2001	3	21	CA980302006      	2	19980213	G	8520	641931	BOLT            			CESSNA	421   	421C        	2076016	CE  	CONT  	O520  	GTSIO520L   	17032	SO  	MCAULY	3FF32	3FF32C501   	GL  	NR 2 CYLINDER	BROKEN          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				581  							(CAN) PILOT REPORTED AN OIL LEAK ON THE NR 1 ENGINE. ENGINE WASHED DOWN AND OIL LEAK WAS SEEN IN THE AREA OF NR 2 CYLIND	ER. FURTHER INSPECTION FOUND A THRU BOLT WAS FRACTURED. THE THRU BOLT WAS REPLACED AND THEAIRCRAFT RETURNED TO SERVICE.					1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P45GL
2001032100075	20010321	00075	GL  	2001	3	21	CA980302008      	3	19980220	G	6111		BLADE           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O		 	OTHER                     			IN	INSP/MAINT     	1			CA			9478 	5210 							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. BLADES NOT ANODIZED AT LAST OVERHAUL. CORROSION FOUND UNDER PAINT.						1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2001032100076	20010321	00076	WP  	2001	3	21	CA980302009      	2	19980302	G	7200		ENGINE          			BRAERO	DH125 	HS125700A   	4230170	EU  	GARRTT	TFE731	TFE7313R1H  	29001	WP  					NR 1	FAILED          	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			CA											(CAN) DURING CLIMB THROUGH 4000 FT, A LOUD BANG WAS HEARD FOLLOWED BY A VIBRATION. CREW OBSERVED NR 1 ENGINE SPOOLING DO	WN. #1 ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO AIRPORT. NR 1 ENGINE WAS EXAMINED BY MANTENANCE AND FOUND TO HAVE S	UFFERED MASSIVE FAILURE. ENGINE SENT FOR TEAR DOWN.				2	L	7	2 	4F	4	F	 	A3EU    	E6WE
2001032100077	20010321	00077	GL  	2001	3	21	CA980302010      	3	19980220	G	6111	FC84686R	BLADE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	SHANK	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1090 							(CAN) PROPELLER BLADES BADLY CORRODED IN THE SHANK AREA.						1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
1998032600566	19980326	00566	EA  	1998	3	26	CA980303002      	1	19980123	G	3220	165007	ACTUATOR        			DHAV  	DHC7  	DHC7*       		EA  										NLG DOWNLOCK	UNLOCKED        	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) AIRCRAFT IN RUN-UP AREA WITH ALL ENGINES RUNNING.  FLIGHT CREW COMPLETING CHECKLIST PRIOR TO FLIGHT.  FOR UNKNOWN 	REASON, PILOT PULLED 'EMERGENCY DOOR ACCESS PANEL'.  THIS RESULTED IN UNSAFE GEAR LIGHT IN CAUTION PANEL AND THEN COLLAP	SE OF NOSE GEAR.  UNDER INVESTIGATION BY MANUFACTURER.				2	H	7	4 	4T			RT	A20EA
2001032100080	20010321	00080	EA  	2001	3	21	CA980303006      	1	19980224	G	5246	21526061808	TORQUE TUBE     			CNDAIR	CL215 	CL2151A10   	       	EA  										ACCESS DOOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1503 								(CAN) LEFT HAND FORWARD TORQUE TUBE FOR THE WATER TANK DOOR MECHANISM, REMOVED FOR NDT TESTING DURING C CHECK. DYE PENET	RANT APPLIED TO FORWARD SHOULDER RADIUS OF BEARING SURFACE EXPOSING HIGHLIGHTED INTERMITTENT CRACKS AROUND ENTIRE AREA O	F BEARING SURFACE.				2	H	7	2 	4R			 	A14EA
2001032100081	20010321	00081	SO  	2001	3	21	CA980303007      	1	19980224	G	7120	77651300	MOUNT           			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					RT ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ENGINE MOUNT CRACKED NEAR BOTTOM RIGHT ENGINE MOUNT BUSHING. REPAIRED.						1	L	7	1 	3O	3	O	 	A18SO   	E223
2001032100082	20010321	00082	EA  	2001	3	21	CA980303008      	2	19980224	G	8530	LW16703	CYLINDER        	LYC         	O235L2C     	PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1872 			L2240115					(CAN) DURING REGULAR MAINTENANCE NR 2 CYLINDER WAS FOUND TO HAVE LOW COMPRESSION. THE CYLINDER WAS REMOVED AND CRACKS WE	RE FOUND ON BOTH SIDES OF THE BOTTOM SPARK PLUG HOLE. THE EXHAUST VALVE WAS ALSO FOUND BURNED.					1	L	7	1 	3O	3	O	 	A18SO   	E223
2001032100083	20010321	00083	NE  	2001	3	21	CA980305002      	2	19980225	G	7260	107000701	NUT             	LYC         	107022012   	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					GEAR DRIVE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						X4887					(CAN) DURING DISASSEMBLY OF THE ENGINE DUE TO ICE INGESTION, THE CARRIER ASSEMBLY WAS PULLED. CLOSER INSPECTION REVEALED	 THAT THE BEARING RETAINING NUT WAS SPINNING FREE (NO TORQUE) ON HE GEARSHAFT, HELD BY ONLY ONE TANG OF THE KEYWASHER. T	HE GEAR IN QUESTION IS AT THE 6 O''CLOCK POSITION, THE SOLID PART OF THE CARRIER ASSEMBLY.				1	G	7	1 	4U	4	U	 	H1SW    	E17EA
2001032100084	20010321	00084	NM  	2001	3	21	CA980305003      	1	19980302	G	3230	34629	CAP             		574205      	DHAV  	DHC8  	DHC8*       	       	NM  										SELECTOR VALVE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						519					(CAN) LANDING GEAR SELECTOR VALVE CAP CRACKED, LIFTING FROM BOSS ALLOWING O-RING TO BE BLOWN OUT AND SKYDROL HYDRAULIC F	LUID TO LEAK OUT.					2	H	7	2 	4T			RT	A13NM
2001032100085	20010321	00085	WP  	2001	3	21	CA980305004      	1	19980220	G	7930	6787149	SPACER          		501D13      	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13      	03004	GL  					NR 1 ENGINE	BLOCKED         	W				E	 	 	 	ENGINE SHUTDOWN         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			25062	7565 							(CAN) DURING FLIGHT, THE NR 1 ENGINE OIL PRESSURE AND QUANTITY DECREASED, OIL PRESSURE LIGHT CAME ON. ENGINE SHUT DOWN. 	MAINTENANCE INVESTIGATION REVEALED THAT THE TIE BOLT SPACER WAS BLOCKED (COKED) CAUSING THE OIL TO VENT OUT OF THE BREAT	HER. SPACER CLEANED AND REASSEMBLED AS PER MAINTENANCE MANUAL 72-1-3-1. AIRCRAFT GROUND RUN AND CHECKED SERVICEABLE.				2	L	7	2 	4R	4	T	 	6A6     	E282
1998041000394	19980410	00394	CE  	1998	4	10	CA980305006      	1	19980220	G	2440		CONTROL PANEL   			LEAR  	60    	60LEAR      	5170707	CE  										PWR RELAY NR 5	OVERHEATED      	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			511  								(CAN) GROUND POWER RELAY STUD NR 5 OVERHEATED CAUSING DAMAGE TO WIRES COMMON TO STUD AND LOSS OF POWER FROM GROUND POWER	 UNIT.  DAMAGE CAUSED BY NUT COMING LOOSE ON RELAY K7 STUD.  PART TC:  322.					2	L	7	2 	4F			RT	A10CE
2001032100087	20010321	00087	EA  	2001	3	21	CA980305007      	1	19980225	G	2420	756652A	RAM AIR TURB    	SUNDSTRANDAI		CNDAIR	CL600 	CL6002B19   	       	EA  	GE    	CF34  	CF343A1     	30015	NE  					AUX GENERATOR	FAILED          	W				O	 	 	 	OTHER                   				L	 	 	NO TEST                   			NR	NOT REPORTED   	1			CA						0465					(CAN) THE AIR DRIVEN GENERATOR (ADG) MANUALLY DEPLOYED FOR TEST. AFTER 10 MINUTES OF NORMAL OPERATION THE RPM DROPPED AN	D ADG WENT OFF LINE.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
2001032600227	20010326	00227	NM  	2001	3	26	CA980309001      	1	19980217	G	3230	34629	CAP             			DHAV  	DHC8  	DHC8*       	       	NM  										SELECTOR VALVE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						494					(CAN) LANDING GEAR SELECTOR VALVE CAP FOUND CRACKED. LIFTED FROM BOSS, O-RING FOUND BLOWN, SKYDROL HYDRAULIC FLUID LEAKI	NG.					2	H	7	2 	4T			RT	A13NM
2001032700001	20010327	00001	EU  	2001	3	27	CA980309002      	3	19980210	G	6111		BLADE           			ZLIN  	242   	Z242L       	9970204	EU  						MUHBR	MTV	MTV3BC      	EU  	PROPELLER	DELAMINATED     	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1781 								(CAN) DURING 100 HOUR INSPECTION AND IN COMPLIANCE WITH MT PROPELLER AD 94-098, ONE BLADE SHEATH WAS FOUND DELAMINATED A	PPROXIMATELY 2 AT THE TIP OF THE BLADE FACE SIDE AND APPROXIMATELY 1 ON RHE BACKSIDE. THE PROPELLER WAS REMOVED FROM SER	VICE AS PER THE AD.				1	L	7	1 	3O			0	A76EU   		5	C	USSR
2001032100091	20010321	00091	EU  	2001	3	21	CA980309003      	1	19980205	G	2750	677ONL312014	BOLT            			ZLIN  	242   	Z242L       	9970204	EU  										LT BELLCRANK	BENT            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1549 								(CAN) THE LT BELLCRANK BOLT FOUND BENT APPROXIMATELY 3 DEGREES IN MIDDLE. RT BOLT BENT APPROXIMATELY 5 DEGREES. REPLACED	.					1	L	7	1 	3O			0	A76EU
2001032200003	20010322	00003	GL  	2001	3	22	CA980309007      	3	19980224	G	6110		BEARING         			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1449 	448  							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE FOLLOWING PARTS WERE FOUND CORRODED: 2 BEARING SETS; 2 ACTUATING 	PINS; 2 PISTON PINS; 1 CYLINDER; 80 BALL BEARINGS AND ALL PROPELLER INTERNAL PARTS. THE SUBMITTER SUGGESTS THIS CORROSIO	N WOULD HAVE CAUSED A FAILURE IN A VERY SHORT TIME.				1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA
2001032200004	20010322	00004	GL  	2001	3	22	CA980309008      	3	19980223	G	6114	B24573	FORK            	HARTZL      	HCE2YR1BF   	PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	HUB	LACK OF LUBE    	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1683 			DK1214					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PITCH CHANGE FORK FOUND WORN, PROBABLY DUE TO LACK OF LUBRICATION.						1	L	7	1 	3O	3	O	 	A3SO    	E14EA	5	C	P9EA
2001032200005	20010322	00005	SO  	2001	3	22	CA980309009      	1	19980127	G	5521	4009000	RIB             	PIPER       	401401      	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ELEVATOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8700 			31116					(CAN) DURING INSPECTION CRACKS FOUND IN ELEVATOR INBOARD IN AREA OF TORQUE TUBE  ATTACHMENT HOLES. ELEVATOR MUST BE REMO	VED FOR VERIFICATION AND REPAIR.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032200009	20010322	00009	EA  	2001	3	22	CA980311001      	2	19980220	G	8530	3813	STUD            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2A   	41532	EA  					NR 3 CYLINDER	SEPARATED       	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			E	R	 	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA			5014 	1287 							(CAN) LOSS OF MANIFOLD PRESSURE AND ENGINE VIBRATION ON NR 1 ENGINE NECESSITATED ENGINE SHUTDOWN IN FLIGHT. POST FLIGHT 	INSPECTION FOUND THE NR 3 CYLINDER HOLD DOWN STUDS (P/NS 38-13 & 50-15) AND THROUGH BOLTS WERE PULLED FROM THE CRANKCASE	, CAUSING SEPARATION OF THE NR 3 CYLINDER FROM THE CRANKCASE. THE ENGINE WAS REMOVED AND AN OVERHAULED ENGINE WAS INSTAL	LED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032200010	20010322	00010	EA  	2001	3	22	CA980311002      	1	19980228	G	2435	APC230461121	SHAFT           	LUCAS       	23048004TM  	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					STARTER GEN	WRONG PART      	W				K	 	 	 	NONE                    				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				1297 		3105A					(CAN) AT O/H SHAFT IN USE WAS NOT CORRECT P/N FOR THIS MODEL GENERATOR.  THIS SHAFT IS 0.12 INCHES LONGER THAN THE CORRE	CT ONE, AND HAS A DIFFERENT LOCATION POINT FOR THE FAN AT THE ANTI-DRIVE END. COMMUTATOR WEAR WAS MEASURED TO BE ABOUT 3	 TIMES NORMAL SINCE LAST O/H AND LIKELY ATTRIBUTED TO VIBRATION CAUSED BY POOR FIT OF THE FAN. NOTE: THIS SUP HAS NO FUR	THER INFORMATION THAT CAN BE OBTAINED. IT HAS NOWBEEN CLOSED AS NO FURTHER INFORMATION IS AVAILBLE.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
2001032200011	20010322	00011	EU  	2001	3	22	CA980311003      	1	19980303	G	2435	230321511	TERMINAL BLOCK  			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER GEN	WRONG PART      	W				K	 	 	 	NONE                    				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				892  							(CAN) STARTER GENERATOR RECEIVED FOR OVERHAUL. FOUND LUCAS TERMINAL BLOCK (P/N 230321511) INSTALLED IN PLACE OF APC (P/N	 150S61061) THIS IS NOT APPROVED CHANGE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2001032200012	20010322	00012	SW  	2001	3	22	CA980311004      	1	19980303	G	6320	A3221	SENSOR          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					GEARBOX	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			11539	2768 							(CAN) DURING 1200 HOUR INSPECTION AN OIL MONITOR WAS FOUND CRACKED 360 DEG. OF RADIUS BETWEEN BOLT HEAD AND SHAFT.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200013	20010322	00013	CE  	2001	3	22	CA980311005      	1	19980301	G	3211	14818	MOTOR           			BEECH 	95    	E95         	1153410	CE  	LYC   	O360  	IO360B1B    	41514	EA  					MLG	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA				34   							(CAN) LANDING GEAR FAILED TO COMPLETELY RETRACT AFTER TAKEOFF. GEAR SELECTED DOWN AND NO MOVEMENT. GEAR RESELECTED UPN A	ND GEAR CIRCUIT BREAKER POPPED. FLY BY INDICATED GEAR DOWN. AIRCRAFT LANDED. GEAR RETRACT MOTOR REPLACED. ARMATURE BADLY	 ERODED, BRUSHES SHORT AND CARBON DEPOSIT IN CASE.				1	L	7	2 	3O	3	O	 	3A16    	1E10
2001032200014	20010322	00014	EA  	2001	3	22	CA980311006      	2	19980126	G	8530	LW19001	EXHAUST VALVE   		O5K21100    	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	STUCK           	W				A	 	 	 	UNSCHED LANDING         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				319  							(CAN) IN CRUISE AT 2,400 RPM THE ENGINE ABRUPTLY LOST 200 RPM AND BEGAN TO RUN VERY ROUGH. AFTER LANDING THE FAULT COULD	 NOT BE DUPLICATED. SUSPECT EXHAUST VALVE(S) STICKING INTERMITTENTLY. LYCOMING SERVICE BULLETIN 388B CARRIED OUT. ALL EX	HAUST VALVE GUIDES WERE REAMED AND TAPPET CLEARANCES CHECKED WITHIN LIMITS. ENGINE REASSEMBLED AND EXTENSIVE GROUND RUN-	UP CARRIED OUT. NO FAULT FOUND, AIRCRAFT RETURNED TO SERVICE.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2001032200015	20010322	00015	CE  	2001	3	22	CA980311007      	1	19980211	G	7603	98630561	THROTTLE CABLE  	LYC         	O235L2C     	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	POWER LEVER	JAMMED          	W				A			 	UNSCHED LANDING         				O	 	 	OTHER                     			AB	AEROBATIC      	1			CA						L2044115					(CAN) DURING PRACTICE STALLS AND SPIN RECOVERIES THE THROTTLE CONTROL JAMMED FULL ON.  AFTER LANDING THE THROTTLE WAS DI	SCONNECTED AT THE CARBURETOR. CARB LINKAGE OK BUT CABLE STILL JAMMED. CABLE REPLACED.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
2001032200016	20010322	00016	SO  	2001	3	22	CA980311008      	1	19980216	G	8120	4708849010R	CONTROLLER      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					TURBO CHARGER	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				796  							(CAN) DURING CRUISE DESCENT OUT OF 12,000 FEET A NOTICEABLE LOSS OF MANIFOLD PRESSURE (33 INCHES DOWN TO 17 INCHES) WAS 	EXPERIENCED ON NR 2 ENGINE. THE APPROPRIATE DRILL WAS CARRIED OUT AND THE ENGINE WAS KEPT RUNNING AS IT WAS PRODUCING PO	WER. AN UNSCHEDULED LANDING WAS MADE AND THE FAULT FOUND AND RECTIFIED.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032200017	20010322	00017	WP  	2001	3	22	CA980311009      	1	19980224	G	6310	369D25351	SPRAG CLUTCH    			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					CLUTCH ASSY	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			247  								(CAN) SPRAG IN SPRAG ASSEMBLY FOUND TO BE CRACKED. BROKEN PIECE FOUND INSIDE SPRAG ASSEMBLY.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2001032200018	20010322	00018	SW  	2001	3	22	CA980311010      	1	19980220	G	6700	206001115105	JACKSHAFT       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COLLECTIVE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			8091 								(CAN) CRACK DETECTED VISUALLY DURING INSPECTION. CRITICAL PART.  ATTACHES PILOTS COLLECTIVE STICK TO AIRFRAME.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200019	20010322	00019	WP  	2001	3	22	CA980311011      	1	19980120	G	6120	GSOS680	REGULATOR       			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	NR 2 PROPELLER	DAMAGED         	W				A	 	 	 	UNSCHED LANDING         				J		 	WARNING INDICATION        			CL	CLIMB          	1			CA				3584 							(CAN) NR 2 PROPELLER INTERMITTENT OVERSPEED. GOVERNOR REPLACED TWICE. FEEDBACK SHAFT REPLACED. PITCH LOCK VALVE REPLACED	. PINION REPLACED. REGULATOR REPLACED. PROBLEM SOLVED.					2	L	7	2 	4R	4	T	 	6A6     	E282	6	C	P898
2001032200020	20010322	00020	GL  	2001	3	22	CA980311016      	3	19980303	G	6111	L78CBA2	BLADE           			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2012 	735  							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. PROPELLER BLADES WERE REPAIRED IN THE FIELD AND FOUND TO BE BELOW MAN	UFACTURERS MINIMUM WIDTHS (LIMITS).					1	H	7	2 	3O	3	O	 	A6CE    	E1CE	5	C	P5EA
2001032200024	20010322	00024	NM  	2001	3	22	CA980311022      	1	19980304	G	3213	657276177	WASHER          			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					STRUT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1243 							(CAN) ON C-CHECK INSPECTION FOUND BEVELLED SIDE STRUT WASHER NOT INSTALLED. INSTALLED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
2001032200025	20010322	00025	CE  	2001	3	22	CA980311030      	1	19981102	G	8011	EBB75A	DRIVE GEAR      	PRESTOLITE  	MHB4016R    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	STARTER	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA			104  			7052411					(CAN) STARTER DRIVE SHEARED ON START, REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
2001032200027	20010322	00027		2001	3	22	CA980313002      	4	19980111	G	6122	A210786A	GOVERNOR        	WOODWARD    		DIAMON	DA20  	DA20A1      	       	GL  						HOFMAN	HOV352	HOV352F     	NE  	PROPELLER	FAULTY          	W				D	 	 	 	RETURN TO BLOCK         				L	 	 	NO TEST                   			TX	TAXI/GRND HDL  	1			CA						11469978					(CAN) PROPELLER DOES NOT CYCLE. PROPELLER GOVERNOR UNSERVICEABLE.						1	L	7	1 	3O			NT	TA4CH   		5	C	TP5BO
2001032200028	20010322	00028	GL  	2001	3	22	CA980313003      	1	19980116	G	5260	2052100300	STEP            			DIAMON	DA20  	DA20A1      	       	GL  										FUSELAGE	BROKEN          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1297 								(CAN) STEP SHEARED FROM FUSELAGE AT WELD TO FUSELAGE POINT. REPLACED.						1	L	7	1 	3O			NT	TA4CH
2001032200029	20010322	00029	GL  	2001	3	22	CA980313004      	1	19980116	G	7334	2028000800	SENSOR          			DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					FUEL PRESSURE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FUEL PRESSURE WARNING (ILLUMINATION), STEADY IN CLIMB. AFTER FLIGHT THE FUEL PRESSURE SENSOR WAS REPLACED AND THE 	ENGINE WAS GROUND RUN SERVICEABLE.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
2001032200030	20010322	00030	GL  	2001	3	22	CA980313005      	1	19980126	G	7334	2028000800	SENSOR          			DIAMON	DA20  	DA20A1      	       	GL  	ROTAX 	912   	ROTAX912    	55555	EU  					FUEL PRESSURE	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) FUEL PRESSURE WARNING (ILLUMINATION) IN FLIGHT. POST FLIGHT, THE FUEL PRESSURE SENSOR WAS REPLACED AND THE ENGINE 	WAS GROUND RUN SERVICEABLE.					1	L	7	1 	3O	3	I	NT	TA4CH   	EXPE3I
2001032200031	20010322	00031	CE  	2001	3	22	CA980313006      	1	19980220	G	3246	D30256	WHEEL           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					MLG	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5000 								(CAN) WHEEL FLANGE BOLTS PULLED FROM THEIR SOCKETS JAMMING WHEEL CAUSING DAMAGE. REPLACED.						1	H	7	1 	3O	3	O	NT	3A12    	E274
2001032200032	20010322	00032	GL  	2001	3	22	CA980313008      	1	19980224	G	6420	2815007413	SPINDLE         			ENSTRM	F28   	ENSTROM480  	       	GL  	ALLSN 	250C  	250C20      	03013	GL  					T/R HEAD	OUT OF ADJ      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) TAIL ROTOR HEAD ASSEMBLY FOUND TO BE INSTALLED APPROX. 10 DEGREES OUT OF ALIGNMENT IN A COUNTER CLOCKWISE DIRECTIO	N. LACK OF MASTER SPLINE MAKES THIS MISTAKE EASILY MADE.					1	G	7	1 	3O	3	U	NC	H1CE    	E4CE
2001032200044	20010322	00044	SO  	2001	3	22	CA980317018      	1	19980309	G	8120	4066109020	SEAL            	LYC         	TIO540A2B   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					TURBOCHARGER	LEAKING         	W				E	 	 	 	ENGINE SHUTDOWN         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA				2674 		L803061A					(CAN) THE NR 1 ENGINE BEGAN TO RUN ROUGH DURING CLIMB AND SMOKE WAS NOTICED IN THE EXHAUST DURING CRUISE. THE ENGINE WEN	T NORMALLY ASPERATED AND SHORTLY AFTER THE CREW NOTICED LOWER THAN NORMAL OIL PRESSURE, AT WHICH POINT THE ENGINE WAS SH	UTDOWN AS A PRECAUTION. POST FLIGHT INSPECTION REVEALED A FAILED OIL SEAL IN THE TURBOCHARGER TURBINE CAUSING OIL TO LEA	K INTO THE EXHAUST. THE TURBOCHARGER WAS REPLACED.			1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032200045	20010322	00045	CE  	2001	3	22	CA980317019      	1	19980312	G	3232	AA5C	ACTUATOR        			MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					MLG DOOR	FAILED          	W				A		 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA			517  								(CAN) DURING DEPARTURE THE FORWARD GEAR DOORS WOULD NOT OPEN, PREVENTING GEAR RETRACTION. INVESTIGATION FOUND THE FORWAR	D GEAR DOOR ACTUATOR WAS DEVELOPING INSUFFICIENT SPEED TO ENGAGE THE CLUTCH AND OPEN THE DOORS. THE ACTUATOR WAS REPLACE	D.				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE
2001032200046	20010322	00046	CE  	2001	3	22	CA980317020      	1	19980313	G	3233	AA5C	ACTUATOR        			MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					MLG DOOR	FAILED          	W				H	 	 	 	DEACTIVATE SYST/CIRCUITS				J	 	 	WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) OVERHAULED GEAR DOOR ACTUATOR INSTALLED TO RECTIFY A PREVIOUS PROBLEM. GROUND TEST OK. TEST FLIGHT FORWARD GEAR DO	ORS FAILED TO OPEN AND GEAR MANUALLYLOWERED. GROUND OPERATION NORMAL. INVESTIGATION REVEALED THAT THE ACTUATOR LIMIT SWI	TCH WIRES WERE MISLABELED DURING OVERHAUL. THE AUX LIMIT SWITCHES ARE BACK-UPS TO THE AIRFRAME MOUNTED LIMIT SWITCHES. D	URING FLIGHT THE AIR LOADES ON THE DOORS, THE ACTUATOR TRIPPED THE AUX LIMIT SWITCHES AS WELL AS THE AIRFRAME SWITCHES. 	SWITCH WIRES RELABELED AND INSTALLED CORRECTLY.		1	H	7	2 	3T	4	T	RT	A10SW   	E4WE
2001032200049	20010322	00049	GL  	2001	3	22	CA980317045      	2	19980205	G	7200		ENGINE          			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					LEFT	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				Y	J	 	ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) ON CLIMBOUT, LEFT TORQUE WAS 400 HP LOWER THAN RIGHT FOR THE SAME TIT SETTINGS OF 895 DEGREES. AT 7000 FEET LEFT E	NGINE DROPPED OFF, NTS''''ING AT 5500 RPM, FUEL FLOW AT 100 PPH. ENGINE RE-LIGHT ATTEMPTED ONCE AT 170 KIAS AND AGAIN AT	 200 KIAS UNSUCCESSFULLY. ENGINE E-HANDLED, DISCONNECTED EDC AS PER CHECK LIST AND LANDED WITHOUT INCIDENT.				2	L	7	2 	4R	4	T	 	6A6     	E282
2001032200050	20010322	00050	NE  	2001	3	22	CA980317051      	1	19980305	G	6420	7610105006042	PITCH HORN      			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					TAIL ROTOR	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7228 								(CAN) CRACK FOUND ON THE TAIL ROTOR BLADE PTCH HORNS. CRACK STARTED FROM THE OUTBOARD BASE OF THE PITCH HORN AND ENDED A	T THE INBOARD BASE OF PITCH HORN ALONG RADII OF THE CUFF OF THE PITCH HORN.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL
2001032200051	20010322	00051	EU  	2001	3	22	CA980317052      	2	19980115	G	7322	CCU83YOAY	FUEL CONTROL    			FRCHLD	F27   	F27F        	3373008	EA  	RROYCE	DART  	DART5297E   	54507	EU  					FUEL INLET	DAMAGED         	W				E	 	 	 	ENGINE SHUTDOWN         				K	J	 	FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA				3797 		B6846					(CAN) FUEL CONTROL UNIT WAS LEAKING. INLET SIDE FROM FUEL PUMP WAS ENLARGED CAUSING O RING ON TUBE TO ALLOW FUEL TO ESCA	PE. FCU WAS REPLACED WITH ONE OFH IGHER MOD STATUS. ROLLS ROYCE SUGGESTED THAT THE FCU WAS MOVING ON ITS THREE MOUNTS. N	EW UNIT HAD BUSHINGS INSTALLED TO PREVENT MOVEMENT.				2	H	7	2 	4T	4	T	 	7A1     	E297
2001032200052	20010322	00052	EA  	2001	3	22	CA980317053      	2	19980227	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	CRACKED         	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA			3085 	1647 							(CAN) AIRCRAFT WAS IN CRUISE WHEN PILOT HEARD A LOUD BANG ON THE NR 1 ENGINE. WITH LOSS OF 4 INCH MANIFOLD PRESSURE. THE	 ENGINE WAS MONITORED. AFTER LANDING A RUNUP AN INSPECTION FOUND A BLOWN OUT SPARK PLUG AND A CRACKED AND BURNT CYLINDER	. THE CYLINDER WAS REPLACED.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032200054	20010322	00054	CE  	2001	3	22	CA980317055      	1	19980310	G	3250	1018200141	LINK            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					NLG STEERING	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			13000								(CAN) DURING ROUTINE INSPECTION THE NLG STEERING LINK BRACKET FOUND CRACKED. NEW LINK RECEIVED IS MADE OF MUCH HEAVIER M	ATERIAL. REPLACED.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA
2001032200055	20010322	00055	WP  	2001	3	22	CA980317056      	1	19980216	G	2701	369H7354	COLL PITCH CNTR 			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TUBE	CORRODED        	W				O	 	 	 	OTHER                   				O	 	 	OTHER                     			NR	NOT REPORTED   	1			CA			7035 								(CAN) PILOT COLLECTIVE TUBE P/N 369H7354 HAD 2 AREAS OF EXCESSIVE WEAR AND ONE AREA OF EXCESSIVE CORROSION. COLLECTIVE F	RICTION GRIP AREA HAD .007 WEAR AND THROTTLE FRICTION AREA HAD .008 WEAR. CORROSION WAS FOUND ON THE BOTTOM END OF TUBE 	WHERE TUBE FITS INTO SOCKET AREA.				1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2001032200056	20010322	00056	NE  	2001	3	22	CA980317068      	2	19980222	G	7532	9550158260	BLEED VALVE     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	STUCK           	W				C	 	 	 	ABORTED TAKEOFF         				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA				325  							(CAN) BLEED VALVE CLOSING LATE AS IF STICKING IN OPEN OR PARTIALLY CLOSED POSITION. CLOSED INDICATION, LIGHT ON PANEL, N	OT ILLUMINATING UNTIL APPROXIAMTELY 99 PERCENT NG.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2001032200057	20010322	00057	EU  	2001	3	22	CA980317069      	1	19980123	G	6230	350A37100411	SWASHPLATE      			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					MAIN ROTOR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4016 								(CAN) ROTOR WAS TURNED WITH COWLING COVERS INSTALLED. APPARENTLY COVER SNAGGED A PIECE OF LOCKWIRE ON THE SWASHPLATE AND	 THE BROKEN END WENT UNNOTICED UNTIL IT HAD DAMAGED THE SWASHPLATE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2001032200060	20010322	00060	EU  	2001	3	22	CA980317072      	1	19980216	G	2840	645710032	TRANSMITTER     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL QUANTITY	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			106  								(CAN) FUEL GAUGE STICKING WHEN REFUELING AIRCRAFT. TAPPING THE TRANSMITTER WILL CAUSE THE FUEL QUANTITY INDICATOR TO MOV	E WHEN STUCK. FUEL QUANTITY TRANSMITTER REPLACED.					1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2001032200061	20010322	00061	EU  	2001	3	22	CA980317073      	1	19980226	G	2840	647510032	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL QUANTITY	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) GAUGE STICKING AT 50-70 PERCENT WHEN REFUELING AIRCRAFT. FUEL QUANTITY TRANSMITTER REPLACED.						1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2001032200062	20010322	00062	EU  	2001	3	22	CA980317074      	1	19980216	G	2840	647510032	TRANSMITTER     			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL QUANTITY	STUCK           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			100  								(CAN) FUEL QUANTITY IINDICATOR STICKING AT 20-50% RANGE IN FLIGHT AND WHEN REFUELING AIRCRAFT. FUEL QUANTITY TRANSMITTER	 REPLACED.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2001032200063	20010322	00063	GL  	2001	3	22	CA980317075      	2	19980128	G	7321	23034702	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				O	 	 	 	OTHER                   				Y	 	 	ENGINE STOPPAGE           			TX	TAXI/GRND HDL  	1			CA											(CAN) ENGINE HAD HUNG START AT 25% NG. MAX LIGHT OFF TEMP AFTER FCU ADJUSTMENT OF ONE FULL TURN. FCU HAS 0.0 HOURS SINCE	 OVERHAUL.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200064	20010322	00064		2001	3	22	CA980317076      	4	19980203	G	2562	C4000	SWITCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ELT	FAILED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ''G'' SWITCH FAILED CAUSING SPONTANEOUS ACTIVATION OF UNIT.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200065	20010322	00065	GL  	2001	3	22	CA980317077      	2	19980212	G	7250	6726656244	SNAP RING       	ALLSN       		HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					BEARING	MAKING METAL    	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			7826 	802  							(CAN) ENGINE PRODUCING METAL CHIPS IN OIL SYSTEM AND FILTERS. NUMBER 5 BEARING SNAP RING, P/N 6726656-244 AND SPACER P/N	 6848996-2 WERE FOUND LOOSE ON POWER TURBINE SHAFT.					1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2001032200066	20010322	00066	EU  	2001	3	22	CA980317078      	1	19980317	G	6420	105317381	SLEEVE          			BOLKMS	105   	BO105CBS    	5626008	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			4431 								(CAN) AIRCRAFT WAS WASHED IN HANGER AND THE FOLLOWING MORNING WAS TOWED OUTSIDE FOR FLIGHT. ON PRE START CHECK, TAIL ROT	OR PEDALS WERE LOCKED DUE TO TAIL ROTOR GRIPS FREEZING. OAT WAS -24C. O-RING TYPE SEALON INNER SLEEVE HAD WORNA GROOVE I	N SLEEVE, WHICH WHILE WITHIN LIMITS ALLOWED WATER TO SEEP INSIDE.				1	G	7	2 	3U	3	U	NC	H3EU    	E4CE
2001032200067	20010322	00067	GL  	2001	3	22	CA980317079      	2	19980113	G	7321	23034702	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				E	 	 	 	ENGINE SHUTDOWN         				X	J	 	ENGINE FLAMEOUT           	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				702  							(CAN) ENGINE FLAMED OUT DURING START AT 55% NG AND AT 35-40% NG ON SUBSEQUENT ATTEMPT. FUEL CONTROL UNIT REPLACED.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200068	20010322	00068	SW  	2001	3	22	CA980317080      	1	19980131	G	2550	206072903001	CONNECTOR       			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					CARGO HOOK	BURNED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CARGO HOOK RELEASE CABLE BURNT THROUGH DUE TO ARCING FROM DEFECTIVE PIN IN CARGO HOOK ELECTRICAL RELEASE CONNECTOR	 PLUG. WIRE WAS GROUNDING OUT THROUGH CARGO HOOK.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200069	20010322	00069	EU  	2001	3	22	CA980317081      	1	19980121	G	2910	704A33690004	BELT            			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					HYD SYSTEM	FAILED          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			517  								(CAN) AIRCRAFT RETURNED TO BASE SHORTLY AFTER TAKE OFF WITH REPORTED LOSS OF HYDRAULIC POWER. HYDRAULIC BELT HAD FAILED.						1	G	7	1 	3U	3	U	 	H9EU    	E19EU
2001032200070	20010322	00070	WP  	2001	3	22	CA980317082      	1	19980118	G	7714	369D24518	TACHOMETER      			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					COCKPIT	FAILED          	W				C	 	 	 	ABORTED TAKEOFF         				N	 	 	FALSE WARNING             			TO	TAKEOFF        	1			CA											(CAN) ROTOR RPM WAS READING LOW BY 30-40% AT GROUND IDLE. TROUBLESHOOTING INDICATED GAUGE FAILURE.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2001032200071	20010322	00071	GL  	2001	3	22	CA980317085      	2	19980114	G	7321	23024702	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	OUT OF ADJ      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) FCU RECEIVED WITH PAPERWORK TO INDICATE THE MAXIMIUM FLOW WAS SET TO 235 PPH AS PER INSTRUCTIONS. THE MAXIMUM FUEL	 FLOW SCREW WAS APPROX 1/16 DOWN FROM MAX MARK. CLOSER TO MAX MARK THEN MIN.					1	G	7	1 	3U	3	U	 	H2SW    	E4CE
2001032200072	20010322	00072	GL  	2001	3	22	CA980317086      	2	19980104	G	7323	23057870	GOVERNOR        			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TURBINE	MALFUNCTIONED   	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CL	CLIMB          	1			CA				674  							(CAN) GOVERNOR UNABLE TO MAINTAIN HIGHER POWER DEMAND WITHOUT DROOPING.						1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2001032200073	20010322	00073	SO  	2001	3	22	CA980317087      	2	19980128	G	7414		COUPLING        			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	MAGNETO	SHEARED         	W				D	 	 	 	RETURN TO BLOCK         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			4073 	74   							(CAN) MAGNETO APPEARS TO HAVE SEIZED, SHEARING DRIVE COUPLING. MAGNETO WAS REPLACED.						1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA
2001032200074	20010322	00074	EU  	2001	3	22	CA980317088      	1	19980219	G	6520	4639003007	SEAL            			BOLKMS	117   	BK117B1     	5626012	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					T/R GEARBOX	LEAKING         	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA			20   								(CAN) POST FLIGHT WALK AROUND REVEALED OIL LEAK OF TAIL ROTOR GEARBOX. DISAASEMBLY SHOWED THAT INPUT SEAL DUST SEAL LIP 	HAD PEELED OFF AND WENT INTO THE SEALING LIP ALLOWING GEARBOX TO LOOSE IT''''S OIL DURINGA 40 MINUTE FLIGHT. CHIP DETECT	OR WAS CLEAN AT THIS POINT, HOWEVER AFTER POST REASSEMBLY GROUND RUN, CHIP LIGHT ILLUMINATED. INSPECTION SHOWED EXCESSIV	E METAL ON DETECTOR.			1	G	7	2 	3U	3	U	 	H13EU   	E5NE10
2001032200075	20010322	00075	EA  	2001	3	22	CA980317089      	2	19980227	G	8530	15F1995735	PUSHROD         	LYC         	O540F1B5    	ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					ENGINE	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			264  			L2497740A					(CAN) WHILE CARRYING OUT LYCOMING SB 527C (RECALL OF PISTON PINS). THE NR 4 CYLINDER EXHAUST PUSH ROD WAS FOUND CRACKED 	AT THE TAPPET END. THE CRACK WAS APPROXIMATELY 12 MM LONG.					1	G	7	1 	3O	3	O	 	H11NM   	E295
2001032200076	20010322	00076	WP  	2001	3	22	CA980317090      	2	19980209	G	7260	8941191	COUPLING        	GARRTT      	TPE33110UA51						GARRTT	TPE331	TFE33112UHR 	 	WP  					ACCESSORY DRIVE	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						P54214					(CAN) UPON INSTALLING THE COUPLING ASSEMBLY INTO THE GEAR CASE OF ENGINE P-54214, IT WAS NOTICED THAT THE NTS TRIP PRESS	URE COULD NOT BE SET UP. FURTHER INVESTIGATION REVEALED THAT THE INTERNAL SPLINE THAT COUPLES THE QUILL SHAFT TO THE COU	PLING ASSY WAS TURNING INSIDE, THUS THE NTS PRESSURE COULD NOT BE SET UP. THE COUPLIG ASSY WAS PART OF NEW PART WITH 0 H	OURS AND 0 CYCLES.								4	T			E4WE
2001032200077	20010322	00077	WP  	2001	3	22	CA980317091      	2	19980309	G	7321	89778027	FCU             			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					ENGINE	MALFUNCTIONED   	W				E	 	 	 	ENGINE SHUTDOWN         				M	J	 	OVER TEMP                 	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA				1332 							(CAN) THE FUEL CONTROL WAS ON A FIELD EVALUATION FROM WOODWARD. THE PRESENT PROBLEM IS THAT ON START THE FUEL FLOW START	S AT 50 PPH AND CONTINUES TO INCREASE TO 100 PPH PUTTING TOO MUCH FUEL INTO THE ENGINEON START THUS AN OVERTEMP ON START	 IS NOTED.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
2001032200086	20010322	00086	SW  	2001	3	22	CA980318005      	1	19980309	G	2913	PV304426	PUMP            			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				2675 							(CAN) SPLINES FOUND WORN ON INSPECTION. UNIT S/N 491719C REPLACED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2001032200100	20010322	00100		2001	3	22	CA980318021      	4	19980205	G	6122	D210507V	GOVERNOR        			CESSNA	208   	208B        	2073701	CE  						MCAULY	3AF34C	3GFR34C703  	GL  	PROPELLER	INTERMITTENT    	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) FLIGHT CREW REPORTED PROPELLER SPEED LIMITED TO 1800 RPM DURING CRUISE. MAINTENANCE FOUND THE OVERSPEED GOVERNOR T	EST SOLENOID WAS ENGAGING INTERMITTENTLY WHICH CAUSED THE GOVERNOR TO LIMIT RPM.					1	H	7	1 	3T			 	A37CE   		5	C	P60GL
2001032200101	20010322	00101	CE  	2001	3	22	CA980318023      	1	19980206	G	7931	1013890235	TRANSDUCER      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					OIL PRESSURE	FAULTY          	W				K	 	 	 	NONE                    				J	 	 	WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			430  								(CAN) FLIGHT CREW REPORTED OIL PRESSURE ON NR 2 ENGINE WOULD ONLY GO TO 25 PSI. ALL OTHER ENGINE PARAMETERS WERE NORMAL.	 MAINTENANCE REPLACED THE OIL PRESSURE TRANSDUCER. SYSTEM CHECKED SERVICEABLE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998091100441	19980911	00441	CE  	1998	9	11	CA980318025      	1	19980217	G	7500	12938000113	VALVE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			491  					PCEPS0160			(CAN) DURING MAINTENANCE, THE RIGHT HAND ENGINE PRECOOLER VALVE WAS FOUND TO BE OPERATING INTERMITTENTLY CAUSING THE RT 	ENVIRONMENTAL LIGHT TO ILLUMINATE.  DEFECTIVE VALVE REPLACED AND SYSTEM CHECKED SERVICEABLE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
2001032200102	20010322	00102	CE  	2001	3	22	CA980318026      	1	19980217	G	2410	C6110080101	CONTROL UNIT    			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					ALTERNATOR	FAILED          	W				K	 	 	 	NONE                    				L	 	 	NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE STARTER WOULD ENGAGE WITH THE BATTERY SWITCH ON BUT THE STARTER SWITCH IN THE NORMAL POSITIO	N. ALTERNATOR CONTROL UNIT WAS FOUND TO BE STICKING. REPLACED.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA
2001032200103	20010322	00103	CE  	2001	3	22	CA980318027      	1	19980217	G	3060		CONNECTOR       			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					LT C/B PANEL	BURNED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION THE LT CB PANEL WAS ORENED AND A WIRE CONNECTION FOR THE PROP DEICE SYSTEM WAS FOUND BADLY BURNE	D. THE PROP SYSTEM FUNCTIONED BUT THE CONNECTION REQUIRED REPLACEMENT.					1	H	7	1 	3T	3	T	 	A37CE   	E4EA
2001032200104	20010322	00104	CE  	2001	3	22	CA980318029      	1	19980217	G	2420	1293800161	PANEL           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT GEN TIE	FAILED          	W				O	 	 	 	OTHER                   				B	 	 	SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA											(CAN) THE FLIGHT CREW NOTED THE LT GENERATOR TIE NOT INDICATING OPEN AS COMMANDED. LT POWER PANEL REPLACED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
2001032200105	20010322	00105	CE  	2001	3	22	CA980318030      	1	19980217	G	5753	35165050259	STRUCTURE       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					TE FLAPS	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RT OUTER FLAP REMOVED DUE TO CRACK ALONG THE TRAILING EDGE. CRACK REPAIRED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998091100442	19980911	00442	CE  	1998	9	11	CA980318031      	1	19980312	G	2110	206SZZC	BEARING         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					COMPRESSOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			454  					PCEPS0163			(CAN) DURING ROUTINE MAINTENANCE, THE AIR COMPRESSOR QUILL SHAFT BEARING INNER GREASE SEAL WAS FOUND TO BE LOOSE.  THE B	EARING ROTATES AT HIGH SPEEDS AND IS CRITICAL TO THE OPERATION.  THE DEFECTIVE BEARING WAS REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
2001032200106	20010322	00106	EU  	2001	3	22	CA980318032      	2	19980121	G	7230	RK36632	ELBOW           			BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    	 	EU  					NR 3 COMPRESSOR	CRACKED         	W				O	 	 	 	OTHER                   				R	J	 	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				4191 							(CAN) DURING CRUISE THE CREW NOTICED AN INCREASE IN TGT AND A DECREASE IN TORQUE. THE ENGINE WAS TRIMMED BACK TO LOWER T	HE TEMPERATURE. THE AIRCRAFT LANDED. POST FLIGHT INSPECTION FOUND THE NR 3 COMPRESSOR OUTLET ELBOW CRACKED RESULTING IN 	A 3/8. THE PART WAS REPLACED AND ATHE ENGINE GROUND RUN SERVICEABLE.				2	L	7	2 	3T	4	T	 	A24EU   	A196
2001032200109	20010322	00109	EA  	2001	3	22	CA980318035      	2	19980306	G	8520	LW18840	CAMSHAFT        			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1746 								(CAN) DURING A SCHEDULED 50 HOUR INSPECTION THAT CONTAINED TASKS REQUIRED TO COMPLY WITH THE ON CONDITION PROGRAM ESTABL	ISHED FOR THE ENGINE, A MODERATE AMOUNT OF VERY SMALL METAL PARTICLES WERE FOUND IN THE OIL FILTER ELEMENT. SUBSEQUENT I	NSPECTION OF THE OIL SYSTEM SUCTION STRAINER REVEALED A SMALL AMOUNT OF MUCH LARGER METAL PARTICLES. NR1 & 3 CYLINDERS W	ERE REMOVED TO INVESTIGATE THE SOURCE OF THE METAL CONTAMINATION. WITH THE CYLINDERS REMOVED INSPECTION REVEALED ABNORMA	L WEAR ON THE FRONT AND REAR LOBES OF THE CAMSHAFT AND THE TAPPETS WERE VERY BADLY SPALLED. THE ENGINE WAS REMOVED FOR R	EPAIR.	1	L	7	1 	3O	3	O	0	A76EU   	1E10
2001032200110	20010322	00110	EA  	2001	3	22	CA980318036      	2	19980306	G	7414	4761	MAGNETO         			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					RIGHT	FAILED          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA											(CAN) THE AIRCRAFT WAS EXPERIENCING BRIEF DURATIONS OF ENGINE SPUTTER MOSTLY ON CLIMB OUT. TROUBLESHOOTING COULD NOT ISO	LATE THE FAULT AND GROUND RUN COULD NOT DUPLICATE THE PROBLEM. THIS ENGINE IS EQUIPPEDWITH A LASAR IGNITION STC WHICH HA	D A SIMILAR DEFECT PREVIOUSLY. THE LEFT MAGNETO WAS CHANGED BUT THE DEFECT FREQUENCY AND DURATION INCREASED. THE SUBSEQU	ENT REPLACEMENT OF THE RIGHT HAND MAGNETO REC TIFIED THE PROBLEM. DURING THE TIMING OF THE RIGHT MAGNETO, THE LH MAGNETO	 WAS FOUND TO BE FAULTY, SO THE ORIGINAL LH MAGNETO WAS REINSTALLED.		1	L	7	1 	3O	3	O	0	A76EU   	1E10
2001032200111	20010322	00111	EA  	2001	3	22	CA980318037      	2	19980306	G	7414	4770	MAGNETO         			ZLIN  	242   	Z242L       	9970204	EU  	LYC   	O360  	AEIO360A1B6 	41514	EA  					RIGHT	FAILED          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA			107  								(CAN) THE AIRCRAFT WAS EXPERIENCING BRIEF DURATIONS OF ENGINE SPUTTER MOSTLY ON CLIMB OUT. TROUBLESHOOTING COULD NOT ISO	LATE THE FAULT AND GROUND RUN COULD NOT DUPLICATE THE PROBLEM. THIS ENGINE IS EQUIPPEDWITH A LASAR IGNITION STC WHICH HA	D A SIMILAR DEFECT PREVIOUSLY. THE LEFT MAGNETO WAS CHANGED BUT THE DEFECT FREQUENCY AND DURATION INCREASED. THE SUBSEQU	ENT REPLACEMENT OF THE RIGHT HAND MAGNETO REC TIFIED THE PROBLEM.			1	L	7	1 	3O	3	O	0	A76EU   	1E10
2001032200112	20010322	00112	EU  	2001	3	22	CA980318038      	1	19980308	G	2421	20A075	TERMINAL        			ZLIN  	242   	Z242L       	9970204	EU  										AC GENERATOR	BROKEN          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			1704 								(CAN) STUDENT PILOT ON CROSS COUNTRY TRAINING FLT HAD REACHED HIS DESTINATION. HE WAS IN PROGRESS OF COMPLETING AIR WORK	 WHEN HE OBSERVED THE NAV/COMM SYS DISPLAYS CYCLING ON AND OFF. MOMENTS LATER HIS GYROINSTRUMENTS ALL FAILED ALONG WITH 	ALL LIGHTING SYSTEMS. THE PILOT WAS LEFT WITH HIS ENG MANIFOLD PRESSURE AND RPM INDICATORS OPERATIONAL ALONG WITH TURN A	ND BANK INDICATOR THAT WAS NOW OPERATING ON I T''S EMERGENCY POWER SOURCE. THE PILOT LANDED WITH THE AID OF HIS FLASHLIG	HT. THE ALTERNATOR FIELD WIRE TERMINAL END AT THE ALTERNATOR HAD BROKEN CAUSING THE ALTERNATOR TO GO OFF LINE. REPAIRED.		1	L	7	1 	3O			0	A76EU
1998060500098	19980605	00098	CE  	1998	6	5	CA980318039      	1	19980224	G	8120	40727619	TURBINE         	GARRTT      	4652929002  	CESSNA	182   	TR182       	2072735	CE  	LYC   	O540  	O540L3C5    	41532	EA  					ENGINE TURBO	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			2203 			MHR0106		L2185440A			(CAN) TURBO WAS SENT FOR REPAIR DUE TO RUBBING OF COMPRESSOR ON CASING.  SHOP FOUND AUTOMOTIVE PARTS INSTALLED.						1	H	7	1 	3O	3	O	 	3A13    	E295
2001032200114	20010322	00114	NM  	2001	3	22	CA980318041      	1	19980311	G	2910	82920010363	LINE            		8290004005  	DHAV  	DHC8  	DHC8202     	2809007	NM  										RT WING ROOT	CRACKED         	W				O	 	 	 	OTHER                   				K	J	 	FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA			129  								(CAN) DURING GROUND RUN WHEN OPERAATING PTU A FAILURE OCCURRED IN THAT SYSTEM RESULTING IN THE LOSS OF NR 2 HYD. SYSTEM 	FLUID.MAINT. CREW NOTICED HYD. FLUID RUNNING OUT OF RT SIDE OF BELLY.  INSPECTION FOUND A CRACKED HYDRAULIC TUBE.  IT WA	S CRACKED COMPLETELY AROUND THE FLARE. IT WAS LOCATED IN THE RIGHT HAND WING ROOT, AT THE FIVE PORT FITTING.				2	H	7	2 	4T			RT	A13NM
1998073100350	19980731	00350	GL  	1998	7	31	CA980318042      	1	19980209	G	3222	2032200100	FORK ASSY       	DIAMON      		DIAMON	DA20A1	DA20A1      	05626UX	GL  										NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1000 								(CAN) NOSE LANDING GEAR CRACKED ON TOP AND BOTTOM OF THE INDIVIDUAL LEFT AND RIGHT NOSE WHEEL FORKS.   REPLACED.						1	L	7	1 	3O			NT	TA4CH
2001032600188	20010326	00188	NE  	2001	3	26	CA980318044      	3	19980311	G	6111	70096	ROLLER          	HAMSTD      												HAMSTD	22D	22D30       	NE  	PROPELLER BLADE	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				1    		T17347					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE BARREL WAS FOUND CORRODED. THE BRACKET BENT AND THE ROLLER BEARIN	GS WERE FOUND PITTED. THE BARREL AND ROLLERS WERE REPLACED AND THE BRACKET WAS STRAIGHTENED.															5	C	P736
2001032600189	20010326	00189	NM  	2001	3	26	CA980318045      	1	19980312	G	2910	82920010335	LINE            			DHAV  	DHC8  	DHC8202     	2809007	NM  										RT WING ROOT	CRACKED         	W				K	 	 	 	NONE                    				K	S	 	FLUID LOSS                	AFFECT SYSTEMS            		IN	INSP/MAINT     	1			CA			129  								(CAN) DURING REPAIR OF A PREVIOUSLY NOTED HYD. LEAK, ANOTHER LEAK FOUND AND TRACED TO ANOTHER LINE ON THE BOTTOM OF THE 	HYD. ACCUMULATOR FOR THE PARK BRAKE.IT WAS ALSO IN THE RIGHT HAND WING ROOT.PART RETURNED TO BRAD FOR INVESTIGATION.					2	H	7	2 	4T			RT	A13NM
2001032600191	20010326	00191	SO  	2001	3	26	CA980318052      	1	19980310	G	3411	1663334	LINE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					PITOT/STATIC SYS	CHAFED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			5707 								(CAN) LINE, PNEUMATIC RELAY TO TEE TO PILOTS DG AND ATTITUDE GYRO CHAFED BY LOCKWIRING ON HOUSING CONTROL SHAFT BEARING.	 EACH TIME THE CONTROL YOKE IS PULLED BACK THE HOSE CHAFES ON THE LOCKWIRE. REROUTED AND REPLACED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032600195	20010326	00195	SW  	2001	3	26	CA980318058      	1	19980311	G	7500	2762100009	LINE            	GARRTT      	TPE33111U611	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TFE33112UHR 	 	WP  	ROTOL	R321	R321482F8   	GL  	P3	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						44184C					(CAN) ON LAY OVER CHECK, SOOT WAS NOTICED IN ENGINE COWL.  THE P3 BLEED AIR LINE WAS FOUND CRACKED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
2001032600196	20010326	00196	SO  	2001	3	26	CA980318059      	1	19980222	G	3210	4204200	ARM             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					MLG	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			15721	15721							(CAN) DURING CLEANING OF MAIN LANDING GEAR CRACK NOTICED IN ARM OF LT GEAR RETRACTION ARM, RT GEAR SAME, CRACKS HARD TO 	DETECT DUE TO PAINT. CRACK RUNS FROM EDGE OF ARM TO SLOTTED HOLE. REPLACED.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
2001032600197	20010326	00197	SO  	2001	3	26	CA980325001      	2	19980305	G	8550	533106	SPRING          		532502A1    	CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011B     	17026	SO  					RELIEF VALVE	BROKEN          	W				O	 	 	 	OTHER                   				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			5    								(CAN) OIL PUMP SPRING BROKE INTO 5 PARTS DURING FLIGHT. THIS RESULTED IN A DROP IN OIL PRESSURE OF APPROXIMATELY 8-10 PS	I, WHICH REMAINED LOW. AS THIS SPRING WAS FROM OLD MILITARY STOCK, DATED 1970, IT WILLBE SENT FOR ANALYSIS TO TRY AND DE	TERMINE THE CAUSE OF THE FAILURE.				1	H	7	1 	3O	3	O	 	5A5     	E269
2001032600200	20010326	00200	SW  	2001	3	26	CA980325002      	1	19980306	G	2701	206001342001	CYCLIC CONTROL  			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					COCKPIT	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			7283 								(CAN) CRACK 1/16TH TO 1/8TH OF AN INCH FOUND ON UPPER RELIEF SLOT OF CYCLIC.						1	G	7	1 	3U	3	U	 	H2SW    	E4CE
1998090400001	19980904	00001	CE  	1998	9	4	CA980325003      	1	19980309	G	7931	533106	SPRING          			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			461  					T103412			(CAN) SPRING WAS BEING REMOVED FOR INSTALLATION ON ANOTHER AIRCRAFT.  NO INDICATION THAT THE SPRING WAS BROKEN.  REPLACE	D.					1	H	7	1 	3O	3	O		5A5     	E269
2001032600201	20010326	00201	EA  	2001	3	26	CA980325006      	1	19980304	G	5343		ATTACH FITTING  			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT MLG	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			18195								(CAN) FORWARD LEFT HAND LANDING GEAR ATTACH POINT FOUND CORRODED BEHIND FLOAT FITTING.TUBE AND ATTACH FITTING HAD LITTLE	 OR NO METAL LEFT.SB2/49 WAS COMPLIED WITH THIS AREA NOT CALLED UP IN INSPECTION FOR SB.THIS IS THIRD FINDING.					1	H	7	1 	3R	3	R	 	A806    	5E1
2001032600202	20010326	00202	GL  	2001	3	26	CA980325007      	2	19980315	G	7200		ENGINE          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE BAY	MALFUNCTIONED   	W				A	 	 	 	UNSCHED LANDING         				R		 	PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			CA								CAE831201			(CAN) PREVIOUSLY THIS AIRCRAFT HAD ENGINE ASSY REPLACED DUE TO A RAPID ENGINE DECELERATION ON 12/97. ENGINE WAS RE-INSTA	LLED AFTER HAVING A VIBRATION TESTCARRIED OUT. OTHER TESTS CARRIED OUT AND ENGINE RELEASED AS SERVICEABLE. AFTER FIVE HO	URS OF AIRCRAFT TIME, A YAW CONDITION BELIEVED TO BE AN ENGINE DECELERATION WAS CONFIRMED. NO ENGINE PARAMETERS WERE NOT	ED AND NO ENGINE OUT WARNING SYSTEM ENGAGED.AIRCRAFT GROUNDED PENDING INVESTIGATION.			1	G	7	1 	3U	3	U	 	H3WE    	E4CE
2001032600336	20010326	00336	SO  	2001	3	26	CA980325014      	2	19980305	G	8530	SA646303PIO	PISTON          			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	NR 1 CYLINDER	FAILED          	W				A	 	 	 	UNSCHED LANDING         				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA			1617 								(CAN) NR 2 ENGINE RAN ROUGH AFTER TAKEOFF, AIRCRAFT RETURNED TO BASE.  POST FLIGHT INSPECTION FOUND NO COMPRESSION ON TH	E NR 1 CYLINDER. THE NR 1 CYLINDER PISTON WAS FOUND BURNT ON THE SIDE. INSPECTION OF THE LT MAGNETO FOUND THE DISTRIBUTO	R BLOCK TO HAVE CARBON TRACK, PLUG FIRING CAUSING DETONATION AND BURNING THE SIDE OF THE PISTON.				1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA
2001032600337	20010326	00337	SO  	2001	3	26	CA980325015      	1	19980310	G	2752	452860	ROD END         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	TIO540C1A   	41532	EA  					ACTUATOR	LOOSE           	W				O	 	 	 	OTHER                   				D	 	 	INFLIGHT SEPARATION       			AP	APPROACH       	1			CA			1838 								(CAN) ACTUATOR ROD END FELL OFF DURING APPROACH CAUSING THE FLAPS TO RETRACT. LANDING COMPLETED WITHOUT INCIDENT. DAMAGE	 INCLUDED BREAKING P/N 17320-00 BLOCK AND SLIGHT DAMAGE TO THE THREADS ON P/N 1736-00.ALL PARTS REPLACED AND AIRCRAFT RE	TURNED TO SERVICE.				1	L	7	2 	3O	3	O	 	1A10    	E14EA
2001032600347	20010326	00347	SO  	2001	3	26	CA980325023      	2	19980308	G	7414	10391586	DISTRIBUTOR BLK 	BENDIX      	103492205   	CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	MAGNETO	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						PAS417					(CAN) MAGNETO WAS NOT OPERATING AND WAS SENT FOR REPAIR. INTERNAL INSPECTION REVEALED POINTS WERE WORN BEYOND LIMITS & M	AGNETO WAS FULL OF WATER & OIL DUE TO FAILURE OF BEARING SEAL. DEFECTIVE PARTS WERE REPLACED, MAGNETO REPLACED, UNIT RET	URNED TO SERVICE. 6 DAYS LATER SAME MAG WAS RETURNED FOR REPAIR. UPON TESTING, FOUND THERE WAS PROBLEM WITH DISTRIBUTOR 	BLOCK,AS NOT ALL LEADS WERE FIRING. INTERNAL INSP SHOWED A LARGE AMOUNT OF CARBON TRACKING CAUSED BY HIGH VOLTAGE SPARKS	 SEEKING A DIFFERENT PATH THAN TEST LEAD (A/C IGNITION LEAD). DISTRIBUTOR BLOCK WAS REPLACED.  MAGNETO RETURNED TO SERVI	CE.	1	L	7	2 	3O	3	O	 	A7CE    	E8CE	5	C	P22EA
2001032600356	20010326	00356	CE  	2001	3	26	CA980325024      	1	19980323	G	2121	62022RS1	BRUSHES         	DYNAMICAIR  	C316A       	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					ARMATURE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA						794					(CAN) BRUSHES FOUND WORN PAST USABLE LIMIT.  WHEN REPLACING BEARINGS FOUND WERE NOT OEM THEY SHOULD BE K271B202EL.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA
2001032600357	20010326	00357	SO  	2001	3	26	CA980325025      	2	19980306	G	8520	646286	EXHAUST VALVE   			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	WORN            	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			708  								(CAN) ENGINE RECEIVED FOR CRANKCASE REPAIR. ON DISASSEMBLY THE TIP OF THE EXHAUST VALVE STEMS, ON 2 CYLINDERS, WERE FOUN	D TO BELOW THE VALVE KEEPERS. THE VALVE KEEPERS WERE FOUND DAMAGED AND THE EXHAUST ROCKER ARMS WERE FOUND SEVERELY WORN.	 AS THE CYLINDERS WERE NOT DISASSEMBLED IT COULD NOT BE DETERMINED IF THE VALVE STEMS HAD WORN OR IF THE VALVE KEEPERS W	ERE FAILING. THE 2 CYLINDERS WERE RETURNED TO THE MANUFACTURER FOR INVESTIGATION.			1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA
2001032600358	20010326	00358	SO  	2001	3	26	CA980325026      	2	19980310	G	8520	642720	BEARING         			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	CRANKSHAFT	MISALIGNED      	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1501 								(CAN) METAL CONTAMINATION WAS PRESENT DURING THE ENGINE INSPECTION. NR 3 CYLINDER WAS REMOVED DUE TO LOW COMPRESSION. FU	RTHER INSPECTION FOUND THE NR 2 MAIN CRANKSHAFT BEARING OUT OF PLACE. THE ENGINE WAS REMOVED FROM SERVICE.					1	H	7	1 	3O	3	O	 	3A24    	E5CE	5	C	P47GL
2001032600359	20010326	00359	GL  	2001	3	26	CA980325027      	3	19980305	G	6114	B30012	STOP            	HARTZL      	HCB3TN3DY   											HARTZL	HCB3T	HCB3TN3     	GL  	PROP HUB	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			2775 	1224 		BU17834					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE INSIDE DIAMETER OF THE LOW STOP DAMAGED DUE TO T	HE IMPROPER INSTALLATION OF LOCK WIRE. THE SUBMITTER STATES THAT THIS CONDITION HAS LED TO FAILURES IN THE PAST.															6	C	P15EA
2001032700003	20010327	00003	GL  	2001	3	27	CA980325028      	3	19980305	G	6114	57D24773	HUB             			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B6   	41514	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	CORRODED        	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				662  							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER HUB WAS FOUND TO BE BADLY CORRODED IN THE O-RING AREA.						1	H	7	1 	3O	3	O	 	1A13    	1E10	5	C	P9EA
2001032600366	20010326	00366	GL  	2001	3	26	CA980325031      	3	19980318	G	6114		CYLINDER        			CESSNA	210   	210M        	2073450	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	3A32C	D3A32C88    	GL  	PROPELLER	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1820 	478  							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. INSPECTION FOUND THE CYLINDER OVERSIZE AND THE HUB CORRODED. THE HUB 	WAS NOT ANODIZED, NOR WAS THE PROPELLER MODIFIED TO OIL FILLED AS PER SERVICE BULLETIN 196A.					1	H	7	1 	3O	3	O	 	3A21    	E5CE	5	C	P21EA
1998090400005	19980904	00005	CE  	1998	9	4	CA980325032      	1	19980309	G	5541	053100669	SPAR            		053100681   	CESSNA	172   	172K        	2072430	CE  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RUDDER SKIN WRINKLED ON RIGHT SIDE APPROX 1.5 INCHES ABOVE LOWER HINGE POINT.  0.5 INCH CRACK IN RIGHT SIDE OF FOR	WARD SPAR.  REPLACED.					1	H	7	1 	3O			NT	3A12
2001032600370	20010326	00370	SW  	2001	3	26	CA980325037      	1	19980317	G	7722		CONNECTOR       			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	EGT HARNESS	COLD SOLDER JT  	W				O	 	 	 	OTHER                   				E	J	 	VIBRATION/BUFFET          	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) AIRCRAFT EXPERIENCED FALSE EGT READING WHICH CAUSED THE SRL TO BYPASS FUEL AND CAUSE THE RIGHT ENGINE TO SURGE. WI	RE FOUND WITH A COLD SOLDER JOINT ON TOP OF THE ENGINE IN THE EGT WIRING SYSTEM. WIRE REPAIRED AND AIRCRAFT SENT ON A TE	ST FLIGHT. AIRCRAFT RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	3PNE
2001032600381	20010326	00381		2001	3	26	CA980325040      	4	19980323	G	6122	1223890373	GOVERNOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROP OVERSPEED	FAULTY          	W				A	 	 	 	UNSCHED LANDING         				J	 	 	WARNING INDICATION        			CR	CRUISE         	1			CA			518  								(CAN)  AFTER CLIMB, WHILE CRUISE SETTINGS WERE BEING ESTABLISHED THE RIGHT HAND PROPELLER SPEED DROPPED TO 1550 RPM AND 	HELD THERE. FURTHER CORRECTION INITIATED WERE UNABLE TO MOVE THIS SETTING. AFTER AN UNEVENTFUL LANDING, MAINTENANCE DISP	ATCHED TO THE AIRCRAFT AND REPLACED THE OVERSPEED GOVERNOR ON THE RIGHT HAND ENGINE. THE ENGINES WERE GROUND RUN AND THE	 SYSTEMS CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2001032600384	20010326	00384	EU  	2001	3	26	CA980325049      	1	19980223	G	6410	332A12004501	BLADE           			SNIAS 	AS332 	AS332L      	8680809	EU  	TMECA 	MAKILA	MAKILA1A    	60040	EU  					TAIL ROTOR	DAMAGED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING DAILY INSPECTION AFTER FLIGHT IT WAS NOTICED THAT THE ELT ANTENNA WAS MISSING AND THAT ONE TAIL ROTOR BLADE	 WAS DAMAGED. THE DAMAGED AREA WAS APPROXIMATELY MID POINT OF THE INNER SURFACE OF THEBLADE. IT APPEARS THAT THE ELT ANT	ENNA MAY HAVE PUNCTURED THE SURFACE THEN RIPPED OUT TEARING THE SKIN.				2	G	7	2 	4U	4	U	 	H4EU    	E12NE
2001032600421	20010326	00421	SW  	2001	3	26	CA980325051      	1	19980311	G	6710	206010360001	NUT             			BELL  	206   	206L        	1181522	SW  										PITCH LINK	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PITCH CHANGE LINK NUTS (P/N MS35691-25) FOUND CRACKED. PROBABLE TIME ON NUTS 8841 HRS.						1	G	7	1 	3U			 	H2SW
1998100900158	19981009	00158	SO  	1998	10	9	CA980325052      	1	19980311	G	5280	42059000	DOOR            		42053       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L207261			(CAN) RIGHT OUTBOARD MLG DOOR CRACKED.  REPLACED.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900159	19981009	00159	CE  	1998	10	9	CA980325053      	1	19980317	G	2810	10192006137	VALVE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL FILLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE80867			(CAN) DURING MAINTENANCE, LEFT WING TIP FUEL CAP WAS REMOVED AND IT WAS NOTICED THE ANTI-SYPHON VALVE WAS DAMAGED.  IT A	PPEARS THE NOZZLE FROM THE FUEL TRUCK SOME HOW TIPPED BACK, IN TURN, BENDING AND SPLITTING THE BODY OF THE ANTI-SYPHON V	ALVE.  THE VALVE WAS REPLACED.				1	L	7	2 	4T	4	T		A24CE   	E4EA
2001032600422	20010326	00422	EA  	2001	3	26	CA980325054      	1	19980319	G	2830	21564085108	FUEL LINE       			CNDAIR	CL215 	CL2151A10   	       	EA  										FUEL DRAIN	CORRODED        	W				K	 	 	 	NONE                    				K	 	 	FLUID LOSS                			IN	INSP/MAINT     	1			CA			1354 								(CAN) FUEL LEAK FOUND IN THE FUEL DRAIN LINE FROM THE RIGHT COLLECTOR TANK.  THE LINE WAS SEVERELY CORRODED AND SHEARED 	WHEN MAINTENANCE TRIED TO REMOVE THEB NUT.THE SUBMITTER CHECKED HIS OTHER AIRCRAFT ANDFOUND THREE OF SIX CORRODED. MANUF	ACTURER CONTACTED.				2	H	7	2 	4R			 	A14EA
1998100900160	19981009	00160	SO  	1998	10	9	CA980325055      	1	19980316	G	3230	4752932	HINGE           		4752931     	PIPER 	PA31  	PA31350     	7103110	SO  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14582								(CAN) FOUND HAIRLINE CRACK IN RADIUS OF HINGE.  REPLACED.						1	L	7	2 	3O				A20SO
2001032600423	20010326	00423	NE  	2001	3	26	CA980325056      	2	19980316	G	7210	310703301	BEARING         	PWA         	PW120A      						PWA   	120   	PW120A      	 	NE  					REDUCTION G/B	SPALLED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				8784 		121348					(CAN)  REDUCTION GEARBOX  (RGB) WAS SHIPPED FOR REPAIR & INVEST. AFTER OPERATOR RPTED METAL CONTAMINATION OF RGB.RGB WAS	 DISASSEMBLED,CAUSE OF METAL CONTAMINATION WAS SPALLING OF OUTER RACE OF NR 15 BEARING.										4	T			E20NE
1998100900161	19981009	00161	CE  	1998	10	9	CA980330001      	1	19980107	G	3233	1EN516	SWITCH          	AIRIGHT     	11238002223 	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				1128 		601		PCEPS0132			(CAN) ON APPROACH, NO NOSE LANDING GEAR INDICATION.  AFTER SAFE LANDING, AIRCRAFT INSPECTED AND FERRY FLIGHT PERMIT ISSU	ED FOR RETURN TO MAINTENANCE BASE.  MAINTENANCE TROUBLESHOOTING REVEALED THE INTERNAL NOSE LANDING GEAR MICROSWITCH IN T	HE ACTUATOR WAS AT FAULT.  THE ACTUATOR WAS REPLACED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900162	19981009	00162	CE  	1998	10	9	CA980330002      	1	19980317	G	3233	1EN516	SWITCH          	AIRIGHT     	11238002223 	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ACTUATOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA				828  		675		PCEPS0156			(CAN) DURING APPROACH, NO DOWNLOCK INDICATION FOR NOSE LANDING GEAR.  AFTER OVER FLYING THE TOWER, LIGHT INDICATION CAME	 ON.  MAINTENANCE INSPECTED THE NOSE GEAR SWITCHES AND LANDING GEAR RETRACTION TESTS CARRIED OUT. UNABLE TO DUPLICATE FA	ULT.  SUSPECT INTERNAL MICROSWITCH OF NOSE LANDING GEAR ACTUATOR AT FAULT.  PRECAUTIONARY ACTUATOR REPLACEMENT CARRIED O	UT.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
2001032600424	20010326	00424	NE  	2001	3	26	CA980330003      	2	19980312	G	8520	16475	CRANKCASE       	PWA         	R985AN14B   	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					AFT WEB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				769  		JP211265					(CAN) DURING ROUTINE INSPECTION ALUMINUM FLAKES WERE FOUND IN THE OIL SCREEN. THERE WAS ALSO SEVERAL PIECES OF ALUMINUM 	IN THE OIL FILTER CAP AND IN THE SUMP PLUGS. REMOVAL OF THE NR 1 CYLINDER, TO FACILITATE THE INVESTIGATION, REVEALED THE	 MAIN CRANKCASE REAR WEB WAS COMPLETELY CRACKED CIRCUMFERENCIALLY AROUND THE MAIN BEARING JOURNAL, WITH ANOTHER CRACK IN	ITIATING FROM THE BEARING AREA. NO UNUSUAL VIBRA TIONS OR INDICATIONS WERE REPORTED BY THE PILOT.			1	H	7	1 	3R	3	R	 	A806    	5E1
1998100900163	19981009	00163	SO  	1998	10	9	CA980330004      	1	19980321	G	2820		LINE            			PIPER 	PA18  	PA18A150    	7101837	SO  	LYC   	O320  	O320A2A     	41508	EA  					FUEL SYSTEM	ABRADED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				34   				127927			(CAN) FUEL VENT LINE ABRADED BY FLAP CABLE.  FABRIC MUST BE REMOVED TO SEE LINE.  FUEL LEAKED OUT ON REFUELING.						1	H	7	1 	3O	3	O		1A2     	E274
2001032600425	20010326	00425	EA  	2001	3	26	CA980330005      	2	19980216	G	7314	025323101	SHAFT           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  					FUEL PUMP	STRIPPED        	W				E	A	 	 	ENGINE SHUTDOWN         	UNSCHED LANDING         			Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA				1773 							(CAN) DURING FLIGHT THE NR 1 ENGINE LOST POWER. INFLIGHT SHUTDOWN PROCEDURES WERE CARRIED OUT BY THE FLIGHT CREW AND SIN	GLE ENGINE LANDING CARRIED OUT AT DESTINATION. POST FLIGHT INSPECTION REVEALED NO FUEL DELIVERY TO THE FUEL CONTROL UNIT	. AN INSPECTION OF THE FUEL PUMP REVEALED THE INTERNAL DRIVE STRIPPED, PREVENTING FUEL DELIVERY.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA
1998090400006	19980904	00006	CE  	1998	9	4	CA980330006      	1	19980313	G	3213	07410017	STRUT           		07410017    	CESSNA	180   	180A        	2072604	CE  						MCAULY	D3A34	D3A34C401   	GL  	LT MLG	FRACTURED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA									960474		(CAN) ON LANDING, THE LEFT STRUT FRACTURED 4 INCHES ABOVE THE AXLE, AIRCRAFT ON SKIS.  UPPER LEG FELL ON SKI AND COMPLET	ED THE ROLL OUT.  NO SUBSEQUENT DAMAGE TO AIRCRAFT.  REPLACED.					1	H	7	1 	3O				5A6     		5	C	P47GL
2001032600432	20010326	00432	EU  	2001	3	26	CA980330007      	1	19980323	G	2435	230321920	ARMATURE        			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					STARTER GEN	WRONG PART      	W				K	 	 	 	NONE                    				W		 	INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				892  							(CAN) ARMATURE SHOWED SIGNS OF RUBBING ON POLE SHOES IN FIELD HOUSING. DAMAGE OCCURRED AT 4.8 HOURS TSO DUE TO BEARING F	AILURE.					1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
2001032600433	20010326	00433	NM  	2001	3	26	CA980330008      	1	19980325	G	7921		OIL COOLER      			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  	HAMSTD	14SF	14SF7       	NE  	NR 2 ENGINE	LEAKING         	W				E	 	 	 	ENGINE SHUTDOWN         				J	K	 	WARNING INDICATION        	FLUID LOSS                		CR	CRUISE         	1			CA			15027								(CAN) IN CRUISE THE NR 2 ENGINE LOW OIL PRESSURE LIGHT CAME ON ACCOMPANIED BY FLUCTUATIONS IN OIL PRESSURE INDICATION. E	NGINE POWER WAS REDUCED, BUT WHEN THE OIL PRESSURE DROPPED BELOW 40 PSI THE ENGINE WAS SHUTDOWN. POST FLIGHT INSPECTION 	FOUND THE NR 2 ENGINE OIL QUANTITY LOW DUE TO OIL LEAKS IN THE OIL COOLER. THE OIL COOLER WAS REPLACED. THE OIL WAS REPL	ENISHED. THE OIL COOLER CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE	6	C	P7NE
1998100900164	19981009	00164	CE  	1998	10	9	CA980330009      	1	19980306	G	5230		DOOR            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3A     	NE  	CARGO BAY	NOT LOCKED      	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			TO	TAKEOFF        	1			CA								PCE114296	HJ448		(CAN) ON TAKEOFF, CREW FELT AND HEARD BUFFETING IN THE AIRFRAME.  NO LIGHT INDICATIONS SUGGESTING A PROBLEM.  ON RETURN 	TO DEPARTURE BASE AND LEAVING AIRCRAFT, IT WAS NOITICED THE AFT CARGO DOOR WAS OPEN.  MAINTENANCE ALSO NOTICED THE CARGO	 DOOR ANNUNCIATOR LIGHT ILLUMINATION WAS AT 50 PERCENT AND TEST FUNCTION WORKED FINE.  IT WAS ESTABLISHED THAT THE DOOR 	WAS NOT CHECKED FOR POSITIVE LOCKING AS STATED IN THE 1990D STANDARD OPERATING PROCEDURES.  REPAIR TO THE DOOR AND ADJAC	ENT AREA CARRIED OUT AND DOOR WARNING SYSTEM CHECKS OKAY.		2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
2001032600434	20010326	00434	NE  	2001	3	26	CA980330010      	3	19980318	G	6111	6101A15	BLADE           	HAMSTD      	2D30237     	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	PROPELLER	CUT             	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3322 	942  		112294					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. LEADING EDGES OF PROPELLER BLADES WERE FOUND SPRAY CUT. THE BLADES WE	RE TRIMMED.					1	H	7	1 	3R	3	R	 	A806    	5E1	5	C	P206
2001032600435	20010326	00435	GL  	2001	3	26	CA980330011      	3	19980320	G	6114	5263	SEAL            	MCAULY      	2A34C203    	CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	HUB	SCORED          	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			833  	326  		775104					(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE CYLINDER WAS FOUND SCORED IN THE SEAL AREA.						1	H	7	1 	3O	3	O	 	3A17    	E1CE	5	C	P3EA
2001032600436	20010326	00436	EU  	2001	3	26	CA980330012      	1	19980323	G	2720	NB32B117	HOUSING         		NB456967    	BNORM 	BN2   	BN2B21      	7080221	EU  	LYC   	O540  	IO540K1B5   	41532	EA  					RUDDER LEVER	LOOSE           	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			3348 								(CAN) PORT SIDE BEARING HOUSING WAS MOVING ON ITS MOUNTING IN THE RUDDER LEVER. MOVEMENT ALLOWED AS A RESULT OF MOUNTING	 HARDWARE WORKING LOOSE.					1	H	7	2 	3O	3	O	 	A17EU   	1E4
1998100900165	19981009	00165	CE  	1998	10	9	CA980330013      	1	19980327	G	3230	503801145	SPLINE          			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					MLG MOTOR	STRIPPED        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								PCE22479			(CAN) AFTER TAKEOFF, LANDING GEAR SELECTED UP RED LIGHT REMAINED ON IN HANDLE.  GEAR SELECTED TO DOWN POSITION AND RED L	IGHT STILL REMAINED ON, NO GREEN LIGHTS.  GEAR LOWERED MANUALLY.  THIS A/C IS NOT MODIFIED TO HYDRAULIC GEAR AND STILL U	SES ORIGINAL BEECH ELECTRO MECHANICAL GEAR OPERATION.				1	L	7	2 	3T	3	T		3A20    	E4EA
1998100900166	19981009	00166	CE  	1998	10	9	CA980330014      	1	19980318	G	5740	817911018	NUT             		10140261    	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7749 					PCE40423			(CAN) WHILE COMPLYING WITH AD CF-81-25R, FLUORESCENT PENETRANT INSPECTION SHOWED NUT ON THE RT UPPER AFT WING BOLT WAS C	RACKED.  THE NUT WAS ALSO FOUND TO BE THREAD BOUND WHEN TORQUED TO SPECIFICATIONS.  A NEW WING BOLT KIT WAS INSTALLED WH	ICH CORRECTED THE PROBLEM.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900167	19981009	00167	CE  	1998	10	9	CA980330015      	1	19980318	G	5740		ANGLE           		50160018    	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE40241			(CAN) ON ROUTINE WING INSPECTION, THE RT OUTBOARD FLAP INBOARD FLAP HANGER, LOWER CLIPS P/N 35-115 396-1 AND -3 WERE FOU	ND TO BE TORN AT HANGER RIVET ATTACHMENTS AND THE LOWER PORTION OF THE HANGER TO SPAR ATTACHMENT ANGLES P/N 35-115398-1 	AND -3 WERE TORN AWAY FROM THE SPAR.  ANGLES AND CLIPS REPLACED.  ON FURTHER INVESTIGATION, THE LT OUTBOARD FLAP INBOARD	 HANGER HAD SIMILAR DAMAGE AND ANOTHER A100 IN THE FLEET ALSO REQUIRED REPAIRS TO SAME COMPONENTS.			1	L	7	2 	3T	4	T		A14CE   	E4EA
2001032600444	20010326	00444	NM  	2001	3	26	CA980330016      	1	19980325	G	2421	31708001A	GENERATOR       			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      	 	NE  					NR 2 ENGINE	FAILED          	W				O	 	 	 	OTHER                   				H	 	 	ELECT. POWER LOSS-50 PC   			LD	LANDING        	1			CA				3421 							(CAN) DURING LANDING THE RT AC GENERATOR WENT OFF LINE. THE CIRCUIT BREAKER WAS FOUND POPPED AND COULD NOT BE RESET. ON 	LANDING THE ENGINE MONITOR FLAGS FOR THE CHIP DETECTOR AND THE FILTERS WERE FOUND TRIPPED. ALL CHIP DETECTORS WERE INSPE	CTED AND COPPER PARTICLES WAS FOUND IN THE AC GENERATOR CHIP DETECTOR AND A SMALL QUANTITY WAS FOUND IN THE SCAVENGE OIL	 FILTER. THE OIL SYSTEM WAS FLUSHED. THE SCAVENGE AND MAIN OIIL FILTERS WERE REPLACED. THE AC GENERATOR WAS REPLACED. TH	E OIL SYSTEM WAS REPLENISHED AND AFTER GROUND RUN SERVICEABLE. THE AIRCRAFT WAS RETURNED TO SERVICE.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
2001032600439	20010326	00439	GL  	2001	3	26	CA980330017      	3	19980320	G	6114	C5263	CYLINDER        			CESSNA	180   	180K        	2072624	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	PROP HUB	SCRATCHED       	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			1567 	470  							(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE CYLINDER WAS FOUND SCRATCHED AND THE BLADE PITCH LOCK DISTRIBUTIO	N WAS FOUND OUT OF MANUFACTURERS LIMITS AS PER THE OVERHAUL MANUAL.					1	H	7	1 	3O	3	O	 	5A6     	E273	5	C	P3EA
1998100900168	19981009	00168	CE  	1998	10	9	CA980330018      	1	19980129	G	5410		INTAKE          		1019100241  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE80401			(CAN) DURING DAILY INSPECTION, IT WAS FOUND THAT THE RAM AIR RECOVERY VANE P/N 81-3103-109 WAS LOOSE AND THE NACELLE ARE	A WHICH SUPPORTS THE VANE WAS CRACKED.  NACELLE CRACKS WERE REPAIRED PER STANDARD REPAIR PRACTICES AND NEW VANE INSTALLE	D.				1	L	7	2 	4T	4	T		A24CE   	E4EA
2001032600440	20010326	00440	EA  	2001	3	26	CA980330019      	2	19980208	G	7532	310092205	BLEED VALVE     	PWA         		BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NR 1 ENGINE	FAULTY          	W				O	 	 	 	OTHER                   				R	 	 	PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				2755 							(CAN) DURING CLIMB THE NR 1  ENGINE WAS TEMPERATURE LIMITED. THE NR 1 ENGINE POWER LEVER WAS STAGGERED 1 INCH BEHIND ITS	 NORMAL POSITION. FLIGHT CONTINUED AT REDUCED POWER TO NEXT AVAILABLE AIRPORT. NO FAULT FOUND ON GROUND RUN, BOTH BLEED 	VALVES (P/NS 310092205 & 310092302) WERE REPLACED AND THE T5 SYSTEM WAS CHECKED AS A PRECAUTION. NO FURTHER PROBLEMS WER	E ENCOUNTERED.			1	L	7	2 	4T	4	T	 	A24CE   	E4EA
1998100900169	19981009	00169	CE  	1998	10	9	CA980330020      	1	19980211	G	3230		VALVE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					MLG	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA								PCE80401			(CAN) AFTER TAKEOFF IN MINUS 42 DEGREES CENTIGRADE AND BLOWING SNOW, THE LANDING GEAR TOOK 3 CYCLE ATTEMPTS TO RETRACT. 	 SUBSEQUENT RETRACTIONS WERE NORMAL AS THE AIRCRAFT APPROACHED WARMER CLIMATES.  BEFORE LANDING AT HOME BASE, AND GEAR E	XTENSION, A NOISE SIMILAR TO AN AIR LEAK WAS HEARD.  IT WAS DETERMINED THE THERMAL HYDRAULIC RELIEF VALVE WAS OPERATING 	AT A LOW PRESSURE.  VALVE WAS REPLACED.			1	L	7	2 	4T	4	T		A24CE   	E4EA
1998041700638	19980417	00638	SO  	1998	4	17	CA980330021      	1	19980325	G	5751	4019016	SPAR            		4020042     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   									AIL INB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12327			316435					(CAN) PIPER SB 974 HAD BEEN COMPLETED AS TERMINATING ACTION FOR AWD 92-21-03.  NEW HINGE INSTALLED.  CRACK WAS FOUND AS 	A RESULT OF A FLEET INSPECTION DUE TO CRACKING OF ANOTHER AIRCRAFT IN THE FLEET.  REF:  SDR CA980330022, SDR CA980330023	.  AIRCRAFT TT:  12,156 HOURS.				1	L	7	2 	3O				A20SO
1998041700637	19980417	00637	SO  	1998	4	17	CA980330022      	1	19980325	G	5751	4019016	SPAR            		4020042     	PIPER 	PA31  	PA31350     	7103110	SO  										AIL INB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9583 			316180					(CAN) PIPER SB 974 HAD BEEN COMPLETED AND HINGE P/N 74461-02 HAD BEEN INSTALLED.  THIS WAS TERMINATING ACTION FOR AWD 96	-21-03.  THE CRACK WAS FOUND DURING A RE-SKINNING OF THE AILERON.  FOUR OTHER AILERONS ON THE FLEET WERE INSPECTED AND T	HREE WERE FOUND CRACKED.  REF:  SDR CA980330023, SDR CA980330021.  AIRCRAFT TT:  8,362 HOURS.				1	L	7	2 	3O				A20SO
1998041700636	19980417	00636	SO  	1998	4	17	CA980330023      	1	19980325	G	5751	4019017	SPAR            		4020043     	PIPER 	PA31  	PA31350     	7103110	SO  										AIL INB HINGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9583 			318117					(CAN) SB 974 HAD BEEN COMPLIED WITH AS TERMINATING ACTION FOR AWD 96-21-03.  NEW  PARTS WERE INSTALLED.  CRACK WAS FOUND	 AS A RESULT OF A FLEET INSPECTION AFTER CRACKS FOUND ON ANOTHER AIRCRAFT.  REF:  SDR CA98033021, SDR CA98033022.  AIRCR	AFT TT:  8,362 HOURS.				1	L	7	2 	3O				A20SO
2001032600441	20010326	00441	EA  	2001	3	26	CA980330024      	2	19980318	G	7322	15223	PLUG            	PREAIR      	MA4SPA      	PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					IDLE DRILL	MISSING         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA				396  		CK13246					(CAN) DURING INSPECTION A BLUE FUEL STAIN WAS SEEN ON THE CARBURETOR. FURTHER INVESTIGATION REVEALED THE IDLE DRILL PLUG	 SCREW WAS MISSING. THE CARBURETOR WAS SENT FOR REPAIR.					1	L	7	1 	3O	3	O	 	2A13    	E274
2001032600442	20010326	00442	EA  	2001	3	26	CA980331001      	1	19980331	G	8120		SEAL            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R1340*      	52016	NE  					SUPERCHARGER	FAILED          	W				O	 	 	 	OTHER                   				K	 	 	FLUID LOSS                			DE	DESCENT        	1			CA											(CAN) ENGINE PROBLEM ON DESCENT. SUSPECT BLOWER (SUPERCHARGER) SEAL FAILURE.						1	H	7	1 	3R	3	R	 	A815    	5E2
2001032600443	20010326	00443	SW  	2001	3	26	CA980331002      	1	19980325	G	7603	111B0100	CONNECTOR       		3219012096  	SWRNGN	SA227 	SA227AC     	8780603	SW  										ROD END	BROKEN          	W				E	 	 	 	ENGINE SHUTDOWN         				O	 	 	OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE ATTEMPTING TO REMOVE THE PROP OFF THE START LOCKS, THE PILOT FOUND THE LEFT ENGINE POWER LEVER DIFFICULT TO 	MOVE. EFFORT TO MOVE THE CONTROL RESULTED IN AN ENGINE OVERSPEED AND THE ENGINE WAS SHUT DOWN BY PULLING THE STOP AND FE	ATHER CONTROL.  INSPECTION FOUND THE POWER LEVER BALL JOINT, WHICH IS MOUNTED IN THE ENGINE CONTROL CONSOL, WAS BENT AND	 BROKEN.			2	L	7	2 	4T			RT	A8SW
1998071400053	19980714	00053	NM  	1998	7	14	CA980331005      	1	19980314	G	2923	849557	HYD PUMP        			DHAV  	DHC8  	DHC8202     	2809007	NM  										AUX HYD SYS	FAILED          	W				K				NONE                    				K	J		FLUID LOSS                	WARNING INDICATION        		DE	DESCENT        	1			CA											(CAN) ON DESCENT AND APPROACH, NR 2 STANDBY POWER UNIT CAUTION LIGHT ON.  NR 2 HYDRAULIC QUANTITY WENT TO ZERO.  NR 22 S	PU AND ASSOCIATED FILTERS AND CHECK VALVES REPLACED.					2	H	7	2 	4T			RT	A13NM
1998071400054	19980714	00054	GL  	1998	7	14	CA980331007      	3	19980327	G	6111	3054	FERRULE         			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C66     	GL  	PROP BLADE	MISDRILLED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			343  						807142		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND THE PROPELLER BLADE FERRULE HAD FIVE LINK PIN HOLES	 DRILLED.  THE MAXIMUM PERMITTED IS FOUR.					1	H	7	1 	3O			NC	5A6     		5	C	P3EA
1998071400055	19980714	00055	GL  	1998	7	14	CA980331008      	3	19980325	G	6111	C4902	RETAINING NUT   			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C66     	GL  	PROP BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1366 	765  					766629		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  TWO PROPELLER BLADES RETAINING NUTS WERE FOUND CRACKED. THIS COULD H	AVE CAUSED A LOSS OF TWO PROPELLER BLADES IN THE EVENT OF TOTAL NUT FAILURES.					1	H	7	1 	3O			NC	5A6     		5	C	P3EA
1998042900021	19980429	00021	EU  	1998	4	29	CA980331009      	1	19980323	G	5730		SKIN            			PILATS	PC12  	PC12        	7090550	EU  										LT & RT WING	DAMAGED         	W				O				OTHER                   				J	K		WARNING INDICATION        	FLUID LOSS                		AP	APPROACH       	1			CA											(CAN) AIRCRAFT CRUISING AT FL 280 FOR APPROX 4.5 HOURS.  ON DESCENT AT 2,500 FEET A LOUD BANG WAS HEARD.  THE PILOT NOTI	CED BOTH TOP SURFACES OF THE WINGS WERE CAVED IN.  LANDING SUCCESSFULLY CARRIED OUT.  GROUND INSPECTION REVEALED APPROX 	A 2 INCH DEPRESSION ON THE SKINS.  A MANDATORY SB 28-003 HAD BEEN CARRIED OUT IN DEC 1997.  FUEL WAS NOTICED LEAKING FRO	M POPPED RIVETS.  FUEL VENT SYSTEM SEEMED OK ON GROUND.  AD SUBSEQUENTLY RELEASED TO DIRECT THE DRILLING OF SMALL HOLES 	IN THE FILLER CAPS (98-086).		1	L	7	1 	3T			RT	A78EU
1998041700633	19980417	00633	CE  	1998	4	17	CA980331012      	1	19980326	G	2913	75250631139	PUMP            			CESSNA	650   	650         	2076802	CE  										LT HYD	LOW PRESSURE    	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			3386 								(CAN) AFTER TAKEOFF, THE LEFT HAND HYDRAULIC LOW PRESSURE LIGHT CAME ON.  LT HYDRAULIC PUMP CHANGED AND GROUND RUN OK. L	T UNLOADING VALVE TO BE CHANGED WHEN PARTS AVAILABLE.   PARTS TC:  1,962.					2	L	7	2 	4F				A9NM
1998041700632	19980417	00632	NM  	1998	4	17	CA980331014      	1	19980320	G	5241	65561502	FRAME           		6556102     	BOEING	727   	727212      	138407G	NM  										GALLEY DOOR	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA						685					(CAN) RIGHT FORWARD GALLEY DOOR FRAME CRACKED AT TOP CORNER APPROX 6 INCHES LONG.  DOOR REPLACED.						2	L	7	3 	4F				A3WE
1998041700631	19980417	00631	NM  	1998	4	17	CA980331015      	1	19980320	G	2822	2580003	FUEL PUMP       			BOEING	737   	7372A9C     	1384495	NM  										LT MAIN FWD	FAILED          	W				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) EN ROUTE AT 22,000 FEET, THE LT MAIN FORWARD BOOST PUMP BREAKER TRIPPED.  TEN MINUTES LATER, THE LT AFT BOOST PUMP	 TRIPPED THE CIRCUIT BREAKER.  FLT CREW C/W CHECK LIST AND OPENED THE CROSSFEED VALVE.  FIVE MINUTES LATER, THE RT MAIN 	AFT FUEL BOOST PUMP CIRCUIT BREAKER TRIPPED.  CREW DECLARED AN EMERGENCY AND LANDED OK.  FUEL SAMPLES DID NOT REVEAL ANY	 WATER.  THREE FUEL PUMPS REPLACED.			2	L	7	2 	4F				A16WE
1998071600002	19980716	00002	EA  	1998	7	16	CA980331020      	1	19980324	G	2710	NAS42DD535FC	GUARD PIN       			CNDAIR	CL215 	CL2156B11415		EA  										AILERON	CHAFED          	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			27   								(CAN) AILERON HAD BEEN ROUTED OVER ITS GUARD PIN.  CABLE HAD CHAFED ITS WAY THROUGH THE PIN.  ONCE PIN WAS REMOVED, THE 	CABLE TENSION DROPPED FROM 90 POUNDS TO 25 POUNDS.  PIN IS LOCATED AT LT WS 462.					2	H	7	2 	4T			RT	A14EA
1998100900170	19981009	00170	SO  	1998	10	9	CA980331021      	1	19980309	G	7602	455361	CABLE           		455361      	PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	MIXTURE CONTROL	STIFF           	W				K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA			2755 					305237	AM1605		(CAN) BOTH PROP AND MIXTURE CONTROL CABLES VERY STIFF.  AREA BEHIND TURBO BADLY CORRODED.  CABLES REPLACED.						1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920
1998071400061	19980714	00061	NE  	1998	7	14	CA980331024      	2	19980320	G	7261	310137101	BEARING         								PWA   	118   	PW118       		NE  					OIL PUMP	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18998	9089 				115376			(CAN) OPER REPORTED METAL CONTAMINATION OF RGB.  RGB  FOUND COMPLETELY CLEAN WITH NO SIGN OF METAL CONTAMINATION.  TURBO	MACHINE CHIP DETECTOR  CHECKED, FOUND A SINGLE FLAKE OF SHINY METAL .  FILTERS CHECKED FOR CONTENT ANALYSIS.  TURBOMACHI	NERY FILTER FND HEAVILY CONTAMINATED WITH M50 MAT'L.   SOURCE OF METAL CONTAM IDENTIFIED FROM A SPALLED OIL PUMP DRIVE B	RG.  SECONDARY DAMAGE NOT EXTENSIVE, RESTRICTED TO COMPONENTS IN ACCY G/B OF REAR INLET CASE.  BRG NEVER REPLACED.  ORIG	 BRG FITTED TO ENG AT NEW PRODUCTION.  ENG HAS HISTORY OF VIBRATION , POSSIBLE OIL PUMP DR BRG SUSTAINED DAMAGE OR REACH	ED ITS LIFE-LIMIT.  PART TC:  19,018.						4	T			E20NE
1998041700627	19980417	00627	NM  	1998	4	17	CA980331025      	1	19980320	G	2822	2580005	PUMP            			BOEING	737   	7372A9C     	1384495	NM  										NR 1 & 2 BOOST	FAILED          	W				A				UNSCHED LANDING         				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) AIRCRAFT EN ROUTE AT 33,000 FEET.  THE LT MAIN FUEL BOOST PUMP BREAKER TRIPPED.  TEN MINUTES LATER THE LT AFT BOOS	T PUMP CIRCUIT BREAKER TRIPPED.  CROSS- FEED SELECTED.  FIVE MINUTES LATER, THE RT AFT PUMP CIRCUIT BREAKER TRIPPED.  CR	EW DECLARED EMERGENCY AND LANDED.  THE NR 1 FORWARD AND AFT AND THE NR 2 FWD AND AFT PUMPS REPLACED.				2	L	7	2 	4F				A16WE
1998071400062	19980714	00062	EA  	1998	7	14	CA980331026      	2	19980306	G	8520	72877	TAPPET BODY     								LYC   	O360  	AEIO360A1B6 	41514	EA  					ENGINE CAMSHAFT	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1746 					L2663251A			(CAN) DURING A SCHEDULED 50 HR INSP THAT CONTAINED TASKS REQUIRED TO C\W THE ON CONDITION PROGRAM ESTABILSHED FOR THE EN	GINE.  A MODERATE AMT OF  SMALL METAL PARTICLES FOUND IN OIL FILTER ELEMENT.  SUBSEQUENT INSP  OF THE OIL SYSTEM SUCTION	 STRAINER REVEALED A SMALL AMOUNT OF MUCH LARGER METAL PARTICLES.   NR 1 AND NR 3 CYLINDERS  REMOVED .  WITH THE CYLINDE	RS REMOVED, INSPECTION REVEALED ABNORMAL WEAR ON  FRONT AND REAR LOBES OF THE CAMSHAFT AND THE TAPPETS WERE VERY BADLY S	PALLED.  THE ENGINE WAS REMOVED FOR REPAIR.							3	O			1E10
1998073100351	19980731	00351	SW  	1998	7	31	CA980402001      	1	19980311	G	6230	214010400111	SHIM            			BELL  	214   	214B1       	1182105	SW  										SWASHPLATE	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				1    							(CAN) TWENTY HOURS TIME SINCE OVERHAUL.  SWASHPLATES FOUND WITH SHIM INSTALLED UNDER OUTER RING.  THIS GAVE THE IMPRESSI	ON OF PROPER SWASHPLATE FRICTION, BUT THE PINCH FIT OF THE BEARING BY THE RING WAS LOST.  THIS ALLOWED THE BEARING TO FL	OAT ON THE INNER RING.				2	G	7	1 	4U			 	H6SW
1998073100352	19980731	00352	WP  	1998	7	31	CA980402002      	1	19980325	G	6710	269A1221	BEARING         			HUGHES	269   	269C        	4470504	WP  										M/R PITCH LINK	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1085 								(CAN) ROUGHNESS FOUND DURING INSPECTION.  PITCH HOUSING DISASSEMBLED AND INBOARD OUTER RACE FOUND CRACKED.						1	G	7	1 	3O				4H12
1998041700626	19980417	00626	EU  	1998	4	17	CA980402003      	1	19980326	G	2435		GROUND STUD     			ISRAEL	1124  	1124        	4500102	EU  										R/H START/GEN	ARCING          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			IN	INSP/MAINT     	1			CA			5204 								(CAN) ERRATIC ENGINE ROTATION AND A CLUNKING SOUND AT THE VERY BEGINNING OF ATTEMPTED ENGINE START, THE ENGINE START WAS	 THEN ABORTED.  DURING SEVERAL ATTEMPTS TO START THE ENGINE THERE WAS NO SOUND OR ENGINE ROTATION ON PRESSING THE STARTE	R SWITCH.  DURING INSPECTION, THE STARTER GENERATOR GROUND ATTACHMENT POINT WAS FOUND BADLY BURNT.				2	M	7	2 	4F				A2SW
2001032600448	20010326	00448	WP  	2001	3	26	CA980402018      	1	19980316	G	5551	34085101519	FITTING         		STC440      	CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13D     	03004	GL  					HORIZONTAL STAB	CRACKED         	W				K	 	 	 	NONE                    				O	 	 	OTHER                     			IN	INSP/MAINT     	1			CA			56490								(CAN) DURING ROUTINE INSPECTION OF THE TAIL, THE LH FWD UPPER STABILIZER ATTACHMENT FITTING WAS FOUND CRACKED. DEFECTIVE	 FITTING REPLACED AND NO OTHER FAULTS FOUND. A/C FLOWN AND NO VIBRATION FELT.					2	L	7	2 	4R	4	T	 	6A6     	E282
1998100900171	19981009	00171	SO  	1998	10	9	CA980402019      	1	19980325	G	5751	4019017	SPAR            		4020042     	PIPER 	PA31  	PA31350     	7103110	SO  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9584 			316180					(CAN) AILERON FRONT SPAR FOUND CRACKED.  FOUND DURING REBUILD.  AD 96-21-03 MANDATED SB 974 INSTALLATION OF BRACKET WHIC	H TERMINATED REPEAT INSPECTION.  REPAIRED.					1	L	7	2 	3O				A20SO
1998100900172	19981009	00172	SO  	1998	10	9	CA980402020      	1	19980325	G	5751	4019017	SPAR            		4020043     	PIPER 	PA31  	PA31350     	7103110	SO  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9584 			318117					(CAN) AILERON FRONT SPAR FOUND CRACKED.  FOUND DURING REBUILD.  AD 96-21-03 MANDATED SB 974 THE INSTALLATION OF BRACKET 	WHICH TERMINATED REPEAT INSPECTION.   REPAIRED.					1	L	7	2 	3O				A20SO
1998100900173	19981009	00173	SO  	1998	10	9	CA980402021      	1	19980325	G	5751	4019016	SPAR            		4020042     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12328			316435		RL478761A			(CAN) AILERON FRONT SPAR FOUND CRACKED.  FOUND DURING REBUILD.  AD 96-21-03 MANDATED SB 974 THE INSTALLATION OF BRACKET 	WHICH TERMINATED REPEAT INSPECTION.  REPAIRED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998073100360	19980731	00360	SW  	1998	7	31	CA980402023      	1	19980323	G	3250	3282030004	WIRING HARNESS  			SWRNGN	SA227 	SA227AC     	8780603	SW  										NOSE STEERING	FAILED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			383  								(CAN) NOSE WHEEL STEERING WAS FAILING INTERMITTENLY MORE SO WHEN IN A HARD LEFT TURN.  WIRING HARNESS FOUND FAILING.  TH	IS WIRE HARNESS IS PART OF SB 227-32-030 WHICH WAS INSTALLED IN JANUARY OF 1998.					2	L	7	2 	4T			RT	A8SW
1998073100361	19980731	00361	NE  	1998	7	31	CA980402025      	2	19980325	G	7210	310924401	BEARING         								PWA   	120   	PW120A      		NE  					RGB NR 15	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			19776	1258 				120696			(CAN) ENGINE REMOVED AND SENT FOR INVESTIGATION AFTER A LARGE NUMBER OF SHINY METAL FLAKES NOTED IN THE RGB SCAVENGE FIL	TER AND ON THE RGB CHIP DETECTOR.  DISASSY OF THE RGB FOUND CAUSE OF THE METAL CONTAMINATION AS A HEAVILY SPALLED NR 15 	BEARING OUTER RACE.  THE RINGS OF ELECTRICAL DISCHARGE PITS AROUND THE OUTER RACE AND AROUND THE ROLLERS OF THE BEARING 	INDICATE THAT THIS SPALLING AROSE AS A RESULT OF ELECTRICAL DISCHARGE DAMAGING THE SURFACE OF THE RACE WITH SUBSEQUENT F	ATIGUE AND LOSS OF MATERIAL.  THE MAGNETISM FOUND WAS SLIGHT, IN FACT, NO MEASURABLE MAGNETISM WAS FOUND, SO THIS RULES 	OUT A LIGHTNING STRIKE. THE CAUSE OF THE SPALLING OF THE NR 15 BEARING WAS NOT DETERMINED.  PART TOTAL CYCLES:  27,497.						4	T			E20NE
1998073100363	19980731	00363	GL  	1998	7	31	CA980403002      	3	19980327	G	6111	C4451	THREADS         			CESSNA	185   	185A        	2072804	CE  						MCAULY	3A32C	D3A32C90    	GL  	FERRULE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			360  						921648		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADE FERRULES FOUND CORRODED IN THE THREADED AREA.						1	H	7	1 	3O				3A24    		5	C	P21EA
1998073100366	19980731	00366	SW  	1998	7	31	CA980403005      	1	19980324	G	7722	8974691	HARNESS         			SWRNGN	SA227 	SA227AC     	8780603	SW  										LT ENGINE	WORN            	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) SHORTLY AFTER TAKEOFF, THE LEFT EGT WENT TO  ZERO AND THE FUEL BYPASS LIGHT FLICKERED.  THE EGT HARNESS WAS FOUND 	RUBBING AGAINST THE ENGINE.  ONE OF THE HARNESS STANDOFFS WAS BENT TOWARDS ENGINE ALLOWING THE WIRE TO CHAFE ON BRACKET.	  THIS BRACKET SETUP COULD NOT BE FOUND IN IPC.  ENGINE WAS A RENTAL AND CAME CONFIGURED LIKE THAT.				2	L	7	2 	4T			RT	A8SW
1998090400007	19980904	00007	CE  	1998	9	4	CA980403006      	1	19980326	G	2701	05131682	WHEEL           		0411214     	CESSNA	172   	172C        	2072408	CE  	CONT  	O300  	O300D       	17022	SO  					CO PILOT	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			AB	AEROBATIC      	1			CA								24988DD			(CAN) DURING FLIGHT TRAINING IN SPINS THE COPILOT'S CONTROL WHEEL RIGHT HANDLE CRACKED OFF.   AIRCRAFT RETURNED TO BASE.	  REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E253
1998073100368	19980731	00368	EA  	1998	7	31	CA980406002      	1	19980313	G	5341	22D00711	TUBE            			SCWZER	SG2   	SGS233A     	8051606	EA  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2279 								(CAN) PRIOR TO RESKINNING, MAGNETIC PARTICLES CHECK OF TUBE REVEALED STRESS CRACKS.						1	K	0	0 					G2EA
1998090400008	19980904	00008	NM  	1998	9	4	CA980406003      	1	19980330	G	2701	1083041100	CONTROL COLUMN  			UNIVAR	108   	1082        	9230406	NM  	FRNKLN	6A4165	6A4165B3    	27025	EA  	MCAULY	1A170	1A170DM     	GL  	COCKPIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1734 					30731	P285		(CAN) WHILE PAINT STRIPPING THE CONTROL COLUMN A PIN HOLE APPEARED.  REMOVING THE ALUMINUM PLUG, A LINE OF CORROSION WAS	 FOUND HALF WAY AROUND THE INSIDE OF THE COLUMN AT THE HEIGHT OF THE PLUG.  CORROSION WAS THROUGH AT THE PIN HOLE AND GR	ADUALLY LESS TO THE SIDES.  REPLACED.				1	H	7	1 	3O	3	O		A767    	E238	5	N	P857
1998073100382	19980731	00382	NE  	1998	7	31	CA980406023      	2	19980219	G	7322	0164448390	FCU             	TURBOMECA   	0164448390  	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA				399  		327B		840			(CAN) ROTOR RPM WOULD DROP AS LOW AS 377 RPM EACH TIME A POWER DEMAND WAS MADE.  NR WOULD ALWAYS RECOVER WITHIN 3-4 SECO	NDS.  FCU REPLACED.					1	G	7	1 	3U	3	U		H9EU    	E19EU
1998073100383	19980731	00383	GL  	1998	7	31	CA980406025      	2	19980403	G	7230	23005200	SCROLL          		23005200    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					COMPRESSOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1059 		CAC70614		CAE860407			(CAN) CRACK FOUND IN COMPRESSOR SCROLL AT 2 O'CLOCK POSITION APPROXIMATELY 1.5 INCHES LONG.  ALSO FOUND BLEED VALVE MOUN	T SCREW THREADS DAMAGED.   SUBMITTER STATED THIS IS THE THIRD INSTANCE THAT A CRACK HAS BEEN FOUND IN THIS AREA OF THE 2	50-C28 ENGINE BY THE REPORTING ENGINEER.				1	G	7	1 	3U	3	U		H2SW    	E1GL
1998073100384	19980731	00384	GL  	1998	7	31	CA980406026      	2	19980308	G	7313	23031899	NOZZLE          		23031899    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					TURBINE 1ST STG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1091 		CAT70378		CAE860407			(CAN) UPON REMOVAL OF TURBINE TO FACILITATE COMPRESSOR CHANGE, FIRST STAGE NOZZLE DOME WAS CRACKED IN CENTER AREA.  FIRS	T STAGE NOZZLE WAS CRACKED ON THE OUTER RING AT 2 ADJACENT VANES.  THE OVERHAUL SHOP FOUND A CRACK IN THE EXHAUST COLLEC	TOR/TURBINE SUPPORT AND BURNING CONSISTANT WITH AN UNEVEN FUEL NOZZLE SPRAY PATTERN. THE FUEL NOZZLE HAD BEEN REPLACED E	ARLIER DUE TO ERRATIC STARTS.			1	G	7	1 	3U	3	U		H2SW    	E1GL
1998073100385	19980731	00385	EU  	1998	7	31	CA980406028      	1	19980115	G	7160		DEFLECTOR       	TURBOMECA   	0292502390  	SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2087 					258			(CAN) DEFLECTOR CENTRAL ATTACHMENT AREA FOUND TO HAVE A SMALL CIRCUMFERENTIAL CRACK AROUND HOLE APPROXIMATELY .1250 INCH	 - .1875 INCH OUTBOARD.  ON APPLYING LIGHT FINGER PRESSURE, THE WHOLE CENTRAL AREA BROKE AWAY AND POPPED OUT.					1	G	7	1 	3U	3	U		H9EU    	E19EU
1998073100386	19980731	00386	SW  	1998	7	31	CA980406036      	1	19980302	G	6330	AN820	MOUNT           			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ISOLATION MOUNT FOUND WITH DEEP SCORES AXIALLY AND RADIALLY.						1	G	7	1 	3U				H2SW
1998073100387	19980731	00387	SW  	1998	7	31	CA980406037      	1	19980320	G	6330	LM70007	PLATE           			BELL  	206   	206B        	1181511	SW  										MAIN ROTOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) PLATE FROM PREVIOUS ISOLATION MOUNT LEFT IN PLACE ON TRANSMISSION DECK WHEN NEW MOUNT INSTALLED.						1	G	7	1 	3U			 	H2SW
1998073100388	19980731	00388	CE  	1998	7	31	CA980406038      	1	19980325	G	2434	ALV9510R	BOLT            	PRESTOLITE  	ALV9510R    	CESSNA	421   	421B        	2076014	CE  						MCAULY	3AF34C	3AF34C92    	GL  	ALTENATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			129  			5085021			851432		(CAN) DURING ANNUAL INSPECTION IT WAS FOUND THAT ONE ALTERNATOR THROUGH BOLT HAD BROKEN OFF PART WAY UP THE THREAD AREA 	JUST OUTSIDE OF THE END FRAME CASTING.  THIS SAME ALTERNATOR HAD ANOTHER BOLT FAIL AT APPROXIMATELY 10 HOURS. BOLTS REPL	ACED WITH OEM STOCK.  WHEN THE BROKEN BOLT WAS DRILLED OUT, IT APPEARED TO BE QUITE SOFT.				1	L	7	2 	3O				A7CE    		5	C	P22EA
1998073100389	19980731	00389	EA  	1998	7	31	CA980406046      	2	19980307	G	7200		ENGINE          			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NR  1	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA				4428 				PCE81271			(CAN) DURING CLIMB, THE AIRCRAFT YAWED TO THE LEFT.  THE NR 1 ENGINE OVERTEMPED.  THE ENGINE WAS SHUTDOWN AND THE AIRCRA	FT RETURNED TO BASE.  POST-FLIGHT INSPECTION FOUND THE ENGINE HAD AN INTERNAL FAILURE RESULTING IN ENGINE PARTS EXITING 	THE ENGINE THROUGH THE EXHAUST STACKS.				1	L	7	2 	4T	4	T		A24CE   	E4EA
1998100900180	19981009	00180	CE  	1998	10	9	CA980406047      	1	19980327	G	5210	504300431329	SUPPORT         		50430043617 	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					PASSENGER DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE51162			(CAN) RIVETS ATTACHING DOOR HINGE TO DOOR SUPPORT CRACKED AT RIVET HOLES.  SUPPORT REPLACED.						1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900181	19981009	00181	CE  	1998	10	9	CA980406048      	1	19980330	G	2731		CONTROL CABLE   			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ELEVATOR	TWISTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCEP0165			(CAN) DURING ROUTINE MAINTENANCE, THE ELEVATOR CONTROL TRIM CABLES WERE FOUND TWISTED AROUND EACH OTHER.  THE CABLES WER	E DISCONNECTED AT MID-FUSELAGE AND UNTWISTED.  CABLES RE-TENSIONED AND CHECKED SERVICEABLE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998091100443	19980911	00443	CE  	1998	9	11	CA980406049      	1	19980402	G	3040		CONNECTOR       			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					WINDSCREEN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING ROUTINE MAINTENANCE, THE LEFT HAND (LT) WINDSHIELD HEAT DID NOT WORK.  TROUBLESHOOTING OF SYSTEM REVEALED W	IRES H15B8 AND H23B8 AT CANNON PLUG J195 WERE CORRODED.  WIRES REPAIRED AND TESTED SERVICEABLE.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998080700098	19980807	00098	EA  	1998	8	7	CA980406051      	1	19980330	G	2910		TUBE            			DHAV  	DHC7  	DHC7*       		EA  										NR 2 HYD SYS	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				K	J		FLUID LOSS                	WARNING INDICATION        		TX	TAXI/GRND HDL  	1			CA											(CAN) AT THE END OF THE LANDING ROLL IT WAS NOTICED THAT NR 2 HYDRAULIC QUANTITY GAUGE WAS AT ZERO.  THEN WHEN TAXIING O	NTO RAMP, THE NR 1 HYDRAULIC PUMP FAILED.  INVESTIGATION FOUND A HYDRAULIC LINE BADLY CHAFED WITH A SMALL HOLE ALLOWING 	NR 2 SYSTEM TO DRAIN MOST FLUID.  IT IS BELIEVED THAT GEAR SELECTION AND LOWERING CAUSED THE CHAFED LINE TO FINALLY BURS	T.			2	H	7	4 	4T			RT	A20EA
1998080700099	19980807	00099	NE  	1998	8	7	CA980406053      	2	19980318	G	7250	311530101	BLADE           								PWA   	120   	PW120       		NE  					TURBINE	FRACTURED       	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			NR	NOT REPORTED   	1			CA			10202					121229			(CAN) THE TURBOMACHINERY WAS SENT FOR REPAIR AFTER AN INFLIGHT SHUTDOWN.  THERE WAS A REPORT OF A RISE IN T6 DURING THE 	SHUTDOWN, BUT NO OVERTEMP.  THE CAUSE OF THE INFLIGHT SHUTDOWN WAS THE LOSS OF THE HP TURBINE BLADES AND CONSEQUENTLY TH	E DRIVE TO THE FUEL PUMP, HMU AND THE GENERATOR.  THE CAUSE OF THE HP TURBINE BLADES FAILURE IS NOT PRESENTLY KNOWN, BUT	 A PRIMARY FAILURE OF ONE OR MORE OF THE HP TURBINE BLADES IS THE MOST LIKELY CAUSE.								4	T			E20NE
1998090400009	19980904	00009	CE  	1998	9	4	CA980407001      	1	19980402	G	3246	161109	WHEEL HALF      	PARKERHANFIN	40169       	CESSNA	441   	441         	2076020	CE  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) INBOARD WHEEL HALF CRACKED FROM BOLT HOLE TO AREA OF WHEEL HALF ABOVE O-RING AIR SEAL ALLOWING TUBELESS TIRE TO SL	OWLY DEFLATE.  REPLACED.					1	L	7	2 	3T			RT	A28CE
1998080700100	19980807	00100	NE  	1998	8	7	CA980407002      	1	19980402	G	5302	S6120762651	FITTING         			SKRSKY	S61   	S61N        	8142104	NE  										TAIL BOOM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SEVERE INTERGRANULAR CORROSION AND CRACKING BETWEEN RIVET HOLES.  THESE FITTINGS ARE SUBJECT TO 2 DIFFERENT SB'S 6	1B20-28 AND 61B20-30A.  EITHER OF THESE SHOULD HAVE CAUGHT THESE CRACKS A LOT EARLIER.					2	G	7	2 	4U				1H15
1998100900182	19981009	00182	SO  	1998	10	9	CA980407003      	1	19980330	G	7712	51198	INDICATOR       	BENDIX      	35712146004 	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					COCKPIT	STICKING        	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA				1710 		88		PCE41649			(CAN) PILOT ABORTED TAKEOFF DUE TO LEFT ENGINE TORQUE READING ERRATIC.  INDICATOR REPLACED AND SYSTEM CALIBRATED.						1	L	7	2 	3T	4	T		A8EA    	E4EA
1998100900183	19981009	00183	CE  	1998	10	9	CA980407006      	1	19980330	G	3220	00282001631	DRAG BRACE      			BEECH 	95    	D95A        	1153408	CE  	LYC   	O360  	IO360B1B    	41514	EA  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L285951A			(CAN) NOSE LANDING GEAR UPPER DRAG BRACE FOUND CRACKED ON INSPECTION.						1	L	7	2 	3O	3	O		3A16    	1E10
1998051500068	19980515	00068	EA  	1998	5	15	CA980407007      	2	19980212	G	8500		ENGINE          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					POWER SECT	MAKING METAL    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1112 				L2691136A			(CAN) ENGINE REMOVED DUE TO NON-FERROUS METAL IN THE OIL SCREEN.  ENGINE SHIPPED FOR REPAIR.  REPORT TO FOLLOW.						1	H	7	1 	3O	3	O		A21CE   	E286
1998090400010	19980904	00010	CE  	1998	9	4	CA980407008      	1	19980327	G	7120	04511201	MOUNT           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5387 					900405OH	K19780		(CAN) ENGINE MOUNT ARM FROM LOWER LEFT FIREWALL TO NOSE GEAR CRACKED AT FIREWALL.  POSSIBLY DUE TO CROSS WIND LANDING. R	EPAIRED.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998080700104	19980807	00104	EA  	1998	8	7	CA980407012      	2	19980328	G	7314	RG9080	FUEL PUMP       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								L161761			(CAN) AFTER OVERHAULED ENGINE WAS INSTALLED, A LEAK CHECK WAS CARRIED OUT.  WHEN AIRCRAFT BOOSTER PUMPS WERE TURNED ON, 	FUEL POURED FROM THE ENGINE DRIVEN FUEL PUMP THROUGH THE BASE DRAIN LINE.  THE FUEL PUMP WAS REPLACED AND THE FAILED PUM	P WAS RETURNED TO THE ENGINE OVERHAULER.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900184	19981009	00184	SO  	1998	10	9	CA980407013      	1	19980328	G	3233	455933	ACTUATOR        		455933      	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MLG	CRACKED         	W				O				OTHER                   				L			NO TEST                   			CL	CLIMB          	1			CA				432  		273424		L372748			(CAN) PILOT REPORTED LANDING GEAR LIGHT COMING ON IN-FLIGHT AND AFTER GEAR RECYCLED.  HYDRAULIC LEAK AROUND PISTON SEAL.	  TWO CRACKS IN BARREL AT BLOCK END, NO SIGNS OF LEAK.  REPLACED.					1	L	7	2 	3O	3	O		1A10    	1E4
1998050801414	19980508	01414	NE  	1998	5	8	CA980407014      	2	19980331	G	7200		ENGINE          			BOEING	727   	727212      	138407G	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2	FAILED          	W				C	E	F	D	ABORTED TAKEOFF         	ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      	RETURN TO BLOCK         	A	T		FLAME/FIRE                	ENGINE CASE PENETRATION   		TO	TAKEOFF        	1			CA			42895	13899				689976			(CAN) DURING TAKEOFF, NR 2 ENGINE FAILED WITH SUBSEQUENT FIRE WARNING.  TAKEOFF WAS REJECTED.  FIRE DRILL AND EVACUATION	 CARRIED OUT.  FURTHER REPORT TO FOLLOW.  PART TC:  19,706.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1998080700106	19980807	00106	SO  	1998	8	7	CA980407016      	1	19980103	G	2910	12035015013	LINES           			EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	RT NACELLE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10347					115667	880529		(CAN) ON 'C' CHECK FOUND HYDRAULIC TUBES TOUCHING EACH OTHER AND CHAFING.  TUBES LOCATED AT OUTBOARD OF RIGHT ENGINE NAC	ELLE, AT ACCESS PANEL 44ZCR AND 44ZAR.  ALSO, TWO OTHER LINES, P/N'S 120-35193-001 AND 120-35193-003.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998080700108	19980807	00108	EU  	1998	8	7	CA980407018      	1	19980207	G	3150	9717518275	CONNECTOR       			PILATS	PC12  	PC12        	7090550	EU  										COCKPIT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2940 	2940 							(CAN) PILOTS REPORTED THAT AIR GROUND WARNING LIGHT WOULD COME ON OCCASIONALLY AFTER TAKEOFF AND THEN GO AWAY.  MAINTENA	NCE FOUND THE PINS IN CONNECTOR PB101 LT FUSELAGE WING CORRODED.  PINS M, V, AND K WERE REPLACED.   SYSTEM FUNCTION CHEC	KED SERVICEABLE.				1	L	7	1 	3T			RT	A78EU
1998080700109	19980807	00109	EU  	1998	8	7	CA980407019      	1	19980219	G	3260	9321921045	BOLT            			PILATS	PC12  	PC12        	7090550	EU  										WOW SHAFT	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1063 	1063 							(CAN) PILOT REPORTED AIR GROUND WARNING AFTER TAKEOFF.  PILOT RESET CIRCUIT BREAKERS AND EVERYTHING RETURNED TO NORMAL. 	 UPON RETURN TO MAIN BASE, MAINTENANCE NOTICED PORT WEIGHT ON WHEEL TARGET SHAFT BOLT SHEARED.  BOLT WAS REPLACED AND AI	RCRAFT PUT ON JACKS AND CHECKED SERVICEABLE.  SUBMITTER STATES THIS IS THE SECOND TIME THEY HAVE A FAILURE OF THIS BOLT.	  BOLTS SENT TO MANUFACTURER FOR INVESTIGATION.			1	L	7	1 	3T			RT	A78EU
1998080700110	19980807	00110	EU  	1998	8	7	CA980407020      	1	19980314	G	3201	311390PT2	FAIRING         			PILATS	PC12  	PC12        	7090550	EU  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1282 	1282 							(CAN) DURING WHEEL SERVICING, FOUND FAIRING LOOSE ON WHEEL ASSEMBLY.  INSPECTION FOUND THAT FAIRING WAS CRACKED IN SEVER	AL PLACES.  ALL CRACKS WERE LOCATED AT THE FAIRING MOUNTING HOLES.  SUBMITTER RECOMMENDS THAT FAIRING SHOULD BE INSPECTE	D FOR CRACKS EACH 200 HOURS IN COMBINATION WITH WHEEL BEARING INSPECTION.				1	L	7	1 	3T			RT	A78EU
1998061600002	19980616	00002		1998	6	16	CA980407021      	3	19980326	G	6112	3E23602	DEICE LEAD      			PILATS	PC12  	PC12        	7090550	EU  										PROP	SHORTED         	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA			382  								(CAN) THE PILOT REPORTED THAT WITH THE PROPELLER DE-ICE ON THE ANNUNCIATOR DE-ICE WARNING WILL FLASH.  THIS IS AN INTERM	ITTENT PROBLEM.  TROUBLESHOOTING REVEALED A SHORT BETWEEN THE INDIVIDUAL LEADS, ALTHOUGH NO VISIBLE DEFECT IS APPARENT O	N THE LEADS.  THE LEADS WERE REPLACED AND THE DEFECT CLEARED.				1	L	7	1 	3T			RT	A78EU
1998080700111	19980807	00111	NE  	1998	8	7	CA980407022      	2	19980317	G	7210	311468201	GEAR            								PWA   	120   	PW120A      		NE  					RGB	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17412	11966				120872			(CAN) REDUCTION GEARBOX (RGB) WAS SENT FOR INVESTIGATION AFTER REPORTS THE RGB WAS MAKING METAL.  DISASSEMBLY OF THE RGB	 FOUND THE SOURCE OF THE METAL WAS THE SPALLING OF THE FIRST STAGE GEARS.  THERE WAS NO CONTRIBUTING FACTORS TO THE SPAL	LING OF THE FIRST STAGE GEARS, HOWEVER, THE RGB INPUT SHAFT HAD 2501.5 HOURS AND THE 1ST STAGE HELICAL GEARS EACH HAD 17	,411.8 HOURS.  ONCE THE 1ST STAGE HELICAL GEARS FAILED, THE RGB INPUT SHAFT WOULD SUFFER SECONDARY TOOTH DAMAGE.  SECOND	ARY DAMAGE WAS ALSO SUFFERED TO THE NR 11 BEARING.  THE NR 8 AND NR 9 BEARINGS WERE ALSO REPLACED AS A PRECAUTIONARY MEA	SURE.						4	T			E20NE
1998071400063	19980714	00063	CE  	1998	7	14	CA980407023      	1	19980323	G	3242	1338932	STATOR          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT BRAKE	CRACKED         	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				331  							(CAN) AIRCRAFT LANDED NORMALLY BUT WHILE TURNING AROUND AFTER TAXIING, THE LT WHEEL LOCKED UP.  BRAKING WAS NORMAL DURIN	G LANDING.  WHEN MAINTEANCE REMOVED BRAKE, THE DISK-STATOR (P/N 133-893-2) WAS FOUND CRACKED IN THE AREA OF A KEY SLOT I	N THE STATOR.  BOTH MAIN WHEELS WERE REPLACED AND LT BRAKE WAS REPLACED AND BLED.  PART TC:  498.				1	L	7	2 	4F	4	F		A22CE   	E1NE
1998080700116	19980807	00116	NE  	1998	8	7	CA980415006      	2	19980408	G	7320	39680010	ACTUATOR        			AIRBUS	320   	A320211     	3930320	EU  	CFMINT	CFM56 	CFM565A1    		NE  					NR 2 ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			17840	17840				731584			(CAN) FOUND NR 2 ENGINE LEAKING FUEL WHEN DOING WALKAROUND.  TRACED LEAK TO VBV ACTUATOR MOTOR.  REPLACED MOTOR, ENGINE 	RUN CARRIED OUT AND FUNCTIONALLY AND LEAK CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F	RT	A28NM   	E29NE
1998080700119	19980807	00119	NE  	1998	8	7	CA980415012      	2	19980330	G	7320	714810	VALVE           			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					NR 1 ENGINE	MALFUNCTIONED   	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA				4309 				657265			(CAN) DURING ENGINE SPOOL-UP IN PREPARATION TO TAKEOFF, NR 1 ENGINE EXPERIENCED MULTIPLE COMPRESSOR STALLS.  AIRCRAFT RE	TURNED TO THE RAMP.  ENGINE INSPECTED FOR DAMAGE AND F.O.D.  NO DISCREPANCIES FOUND.  FUEL PRESSURIZATION AND DUMP VALVE	 ADJUSTED.   ENGINE RUN-UP TO CONFIRM OPERATION AFTER ADJUSTMENTS.  ACCELERATION CHECK, CONFIDENCE CHECK, AND POWER LEVE	R RESPONSE CHECKED SERVICEABLE.  AIRCRAFT RELEASED FOR SERVICE.			2	L	7	3 	4F	4	F		A3WE    	E2EA
1998080700120	19980807	00120	NE  	1998	8	7	CA980415013      	2	19980330	G	7314	430112810	PUMP            								LYC   	LTS101	LTS101650B1 	41560	NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			772  					LE45189E			(CAN) AFTER COMPLETING 300 HOUR INSPECTION WHICH INCLUDES REMOVAL OF THE FUEL PUMP FOR SPLINE INSPECTION AND RE-GREASE, 	OPERATION OF PRIME PUMP PRODUCED LEAK AT PUMP AND GEARBOX SPLIT LINE (NOT SEAL DRAIN LINE).										3	U			E5NE
1998080700121	19980807	00121	NM  	1998	8	7	CA980415014      	1	19980403	G	3234	34629	CAP             		574205      	DHAV  	DHC8  	DHC8*       		NM  										LG SELECT VALVE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						519					(CAN) LANDING GEAR SELECTOR VALVE FOUND WITH A CRACKED CAP CAUSING A MAJOR EXTERNAL LEAK OF SKYDROL FLUID.  THIS IS SECO	ND OCCURRENCE FOUND AT THIS FACILITY.					2	H	7	2 	4T			RT	A13NM
1998080700122	19980807	00122	NE  	1998	8	7	CA980415015      	2	19980406	G	7421	3037946	IGNITER         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 2 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			33   								(CAN) DURING START ATTEMPT, THE NR 2 ENGINE FAILED TO IGNITE.  MAINTENANCE FOUND THE RIGHT HAND IGNITION EXCITER PLUG WA	S FAULTY.  THE EXCITER WAS REPLACED AND THE AIRCRAFT WAS RELEASED FOR SERVICE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998080700123	19980807	00123	NE  	1998	8	7	CA980415016      	2	19980406	G	7421	3037946	IGNITER         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 1 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			37   								(CAN) DURING NORMAL START, THE NR 1 ENGINE FAILED TO IGNITE.  MAINTENANCE REPLACED THE LEFT HAND IGNITION EXCITER AND TH	E AIRCRAFT WAS REPLEASED FOR SERVICE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998080700124	19980807	00124	NE  	1998	8	7	CA980415017      	2	19980406	G	7421	3037946	IGNITER         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 2 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12   					PCEPS0163			(CAN) DURING START, THE RIGHT HAND CIRCUIT BREAKER FOR THE IGNITION EXCITER TRIPPED REPEATEDLY.  THE EXCITER WAS REPLACE	D AND THE AIRCRAFT WAS RELEASED FOR SERVICE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998080700126	19980807	00126		1998	8	7	CA980415019      	1	19980410	G	7722	8974697	HARNESS         								GARRTT	TPE331	TPE33111U   	01514	WP  	MCAULY	4HFR34	4HFR34C652  	NE  	EGT/TIT SYSTEM	WORN            	W				K				NONE                    				N			FALSE WARNING             			CR	CRUISE         	1			CA								P44727	881055		(CAN) EGT ON AIRCRAFT WAS FLUCTUATING AND GOING TO ZERO.  EGT HARNESS WIRE WAS FOUND FATIGUED CAUSING FLUCTUATING EGT. H	ARNESS REPLACED.										4	T			E4WE	6	C	3PNE
1998080700127	19980807	00127	EA  	1998	8	7	CA980415020      	2	19980324	G	8530		CYLINDERS       			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	FAILED          	W				E	B			ENGINE SHUTDOWN         	EMER. DESCENT           			R	Y	J	PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           	WARNING INDICATION        	AP	APPROACH       	1			CA			1566 					L1378839A	735155		(CAN) ON APPROACH, THE ENGINE EXPERIENCED POWER LOSS, WITH ENGINE PERFORMANCE DETERIORATING THE ENGINE FAILED AND THE AI	RCRAFT GLIDED TO A SAFE LANDING.  POST-FLIGHT ENGINE COMPRESSION TEST REVEALED ALL FOUR CYLINDERS HAD LOW COMPRESSION. T	HE CYLINDERS AND PISTONS WERE REMOVED AND SENT FOR REPAIR.  AFTER REPAIR, THE CYLINDERS WERE REPLACED.  THE ENGINE WAS G	ROUND RUN SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998080700128	19980807	00128	SO  	1998	8	7	CA980415022      	1	19980306	G	2435	2CM3061	START/GEN       	GE          		EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  					NR 2 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA				352  				PCE56398			(CAN) NR 2 ENGINE STARTER GENERATOR WAS UNSERVICEABLE AND CAUSING VIBRATION ON THE ENGINE CAUSING THE SHUTDOWN OF THE EN	GINE IN-FLIGHT, AS A PRECAUTIONARY MEASURE.  POST-FLIGHT THE STARTER GENERATOR WAS REPLACED.					1	L	7	2 	4T	4	T		A21SO   	E4EA
1998080700129	19980807	00129	EA  	1998	8	7	CA980415023      	2	19980310	G	7322		PY LINE         			EMB   	110   	EMB110P2    	3260124	SO  	PWA   	PT6   	PT6A34      	52043	EA  					NR 2 ENGINE	CRACKED         	W				K				NONE                    				R	E		PARTIAL RPM/PWR LOSS      	VIBRATION/BUFFET          		NR	NOT REPORTED   	1			CA								PCE56398			(CAN) DUE TO EXCESSIVE VIBRATION ON NR 2 ENGINE CAUSED BY FAULTY STARTER/GENERATOR, THE PY LINE CRACKED RESULTING IN A D	ROP IN NG.					1	L	7	2 	4T	4	T		A21SO   	E4EA
1998080700130	19980807	00130	NE  	1998	8	7	CA980415025      	2	19980331	G	7250	310873701	BOLT            								PWA   	118   	PW118       		NE  					STUB SHAFT	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6003 					115434			(CAN) ENGINE SENT FOR REPAIR AFTER OPERATOR REPORTED ACCESSORY GEARBOX/HP ROTATING ASSY HAD SEIZED.  ON DISASSY, FOUND E	NGINE LEAKING OIL AND SEIZURE OF ACCESSORY GEARBOX/HP ROTATING ASSY WAS CAUSED BY DEBRIS FROM FAILURE OF 2 HIGH PRESS ST	UBSHAFT BOLTS JAMMING HP ROTOR ASSY.   APPEARS TO BE A PRIMARY FAILURE OF HP STUBSHAFT BOLTS DUE TO HIGH TIME ON BOLTS (	6003.4 HRS) AND PRE-SB 23121/21324 STATUS.  THE 3 REMAINING BOLTS SHOWED CRACKS UNDER HEAD.  SECONDARY IMPACT DAMAGE WAS	 SUFFERED TO HP STUBSHAFT AND VANE RING INNER FRONT SUPPORT HOUSING.  SECONDARY RUBBING DAMAGE WAS CAUSED TO SEVERAL AIR	 AND OIL SEALS IN NR 5 BEARING AREA AND HP IMPELLER.  COULD NOT DETERMINE IF OIL LEAK RESULTED DUE TO HP BOLTS FAILURE.						4	T			E20NE
1998090400013	19980904	00013	CE  	1998	9	4	CA980416003      	1	19980324	G	2910	S1236C60130	HOSE            			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	HYDRAULIC SYS	SEPARATED       	W				O				OTHER                   				G	J	K	MULTIPLE FAILURE          	WARNING INDICATION        	FLUID LOSS                	AP	APPROACH       	1			CA			3074 						950631		(CAN) IN PREPARATION FOR LANDING, THE FLAPS SELECTED AND GEAR SELECTED.  THE MAIN GEAR FULLY EXTENDED AND TWO GREEN LIGH	TS, THE NOSE IN TRANSIT LIGHT REMAINED ON AND THE NOSE GEAR OBSERVED IN THE NACELLE.  EMERGENCY EXTENSION CARRIED OUT AN	D AIRCRAFT LANDED OK.  LEFT GEAR EXTENDED HOSE SEPARATED FROM THE UNION.  REPLACED.				1	L	7	2 	3O				A25CE   		5	C	P45GL
1998091100444	19980911	00444	CE  	1998	9	11	CA980416005      	1	19980331	G	3230		CONNECTOR       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					LT MLG	CORRODED        	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) AFTER SELECTING GEAR DOWN, THE LEFT MAIN AND NOSE GEAR DOWN AND  LOCKED INDICATORS WERE NOT ILLUMINATED.  EMERGENC	Y PROCEDURES CARRIED OUT AND A/C LANDED SAFELY.  MAINTENANCE CHECK FOUND CANNON PLUG P163/815AT MID FUSELAGE CORRODED. C	ANNON PLUG CLEANED AND SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998080700133	19980807	00133	EA  	1998	8	7	CA980416007      	2	19980406	G	7322		VALVE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CARBURETOR	BLOCKED         	W				A	E	B		UNSCHED LANDING         	ENGINE SHUTDOWN         	EMER. DESCENT           		W	E		INADEQUATE Q C            	VIBRATION/BUFFET          		CL	CLIMB          	1			CA				595  				RL5776T	79756		(CAN) ON TAKEOFF, AT 1,100 FEET, THE ENGINE QUIT.  THE PILOT RESTARTED THE ENGINE, BUT IT RAN ROUGH AND WOULD NOT EXCEED	 1,700 RPM.  PILOT RETURNED TO BASE.  THE CARBURETOR WAS REMOVED AND TWO STONES, OF A SMOOTH CYLINDRICAL SHAPE OF PORCEL	AIN OR CERAMIC LIKE MATERIAL, WERE FOUND SITTING ON TOP OF THE BUTTERFLY VALVE.  REMOVAL OF THE STONES AND REINSTALLATIO	N OF THE CARBURETOR RECTIFIED THE PROBLEM.  THE MANUFACTURER WAS CONTACTED AND STATED THAT THESE TYPE OF STONES WERE USE	D DURING OVERHAUL TO DEBUR PARTS.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998080700134	19980807	00134	GL  	1998	8	7	CA980416008      	3	19980313	G	6112	4E11883	DEICER BOOT     			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	LT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1481 						DJ9380A		(CAN) PILOT REPORTED LOW AMP INDICATION ON THE PROP DE-ICE DURING ONE OF THE CYCLES.  GROUND CHECK SHOWED THE LEFT PROP 	NR 2 BLADE PARTLY EFFECTIVE.  INSPECTION OF THE PROP SHOWED A BUSTER NEAR THE ENTRY OF THE HEATING ELEMENT.  REMOVAL OF 	THE BOOT CONFIRMED AN INTERNAL SHORT.  FURTHER INSPECTION SHOWED EVIDENCE OF STONE DAMAGE TO THE DEICER BOOTS.  THE SUBM	ITTER SUGGESTS THAT POOR MATERIAL USED IN THE CARE AND MAINTENANCE OF RUNWAYS AND TARMACS IS THE POSSIBLE CAUSE OF THE S	TONE DAMAGE.		1	L	7	2 	3O				A20SO   		5	C	P33EA
1998080700135	19980807	00135	SO  	1998	8	7	CA980416009      	1	19980406	G	7170	LW120984124	DRAIN LINE      			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NR 2 CYLINDER	CHAFING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								RL47562			(CAN) FUEL DRAIN LINE OF NR 2 CYLINDER RUBBED (CHAFED) AGAINST THE PROPELLER ACCUMULATOR AND RISKED RUPTURING THE DRAIN 	INJECTION LINE.  THIS LINE IS LESS THAN 4 INCHES FROM THE EXHAUST SYSTEM AND CONSTITUTES A HIGH RISK OF ENGINE FIRE IF T	HE DRAIN INJECTOR LINE RUPTURED.				1	L	7	2 	3O	3	O		A8EA    	E19EA
1998080700136	19980807	00136	NM  	1998	8	7	CA980416010      	1	19980406	G	2612		WIRE            			BOEING	727   	727217      	1384061	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 3 ENGINE	CHAFED          	W				A	E	J		UNSCHED LANDING         	ENGINE SHUTDOWN         	DUMP FUEL               		N			FALSE WARNING             			CL	CLIMB          	1			CA								688128			(CAN) DURING CLIMB, NR 3 ENGINE FIRE WARNING INDICATION AT APPROXIMATELY 2,000 FEET.  ENGINE START LEVER MOVED TO CUT-OF	F POSITION AND FIRE WARNING INDICATION EXTINGUISHED.  FUEL DUMPED AND AIRCRAFT LANDED.  WIRE CHAFED UNDER CLAMP, WIRE RE	PAIRED.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998100900186	19981009	00186	CE  	1998	10	9	CA980416012      	1	19980310	G	3242	30204A	BRAKE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					MLG	SEIZED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			2935 					GGMPS0123			(CAN) IN REPLACING NR 3 TIRE DUE TO TIRE BURST, THE BRAKE ASSEMBLY WAS FOUND SEIZED.  NEW BRAKE ASSY AND TIRE INSTALLED.	  PART TC:  3,446.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998080700138	19980807	00138	CE  	1998	8	7	CA980416013      	1	19980317	G	2150	365550039	COMPRESSOR      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 2 ENGINE	DAMAGED         	W				K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			CA			3992 					GGMPS0123			(CAN) THE AIR CONDITIONER COMPRESSOR, ON THE NR 2 ENGINE, WAS DAMAGED ON THE FRONT OF ITS LEFT SIDE BY RUBBING OF THE PR	OPELLER CONTROL AND THE CONDITION CONTROL CABLES.  THESE TWO CABLES ARE COVERED BY A METAL SHEATH.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998091100445	19980911	00445	CE  	1998	9	11	CA980416014      	1	19980319	G	3340	MS274321	BRACKET         	RAYTHN      	1143641371  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG WW	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3404 					GGM114476			(CAN) TAXI LIGHT HOUSING BRACKET FOUND BROKEN.  THIS CONDITION COULD INTERFERE WITH THE NOSE LANDING GEAR EXTENSION OR R	ETRACTION.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900187	19981009	00187	CE  	1998	10	9	CA980416015      	1	19980402	G	3242	30204A	BRAKE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 3 WHEEL	SEIZED          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			2204 	236  				GGM114476			(CAN) DURING AN INSPECTION, IT WAS FOUND THAT NR 3 WHEEL WAS DIFFICULT TO ROTATE.  FURTHER CHECKING INDICATED THE BRAKE 	ASSY WAS THE CAUSE AND WAS REPLACED.  PART TC:  2,595.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900188	19981009	00188	CE  	1998	10	9	CA980416016      	1	19980314	G	3242	30204A	BRAKE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					MLG	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1751 					GGMPS0054			(CAN) IN REPLACING NR 4 TIRE, FOUND THE BRAKE ASSEMBLY OF THAT WHEEL WAS SEIZED.  PART TC:  2,044.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900189	19981009	00189	CE  	1998	10	9	CA980416017      	1	19980319	G	2823	1183890051	VALVE           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					FUEL SYSTEM	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3470 					GGMPS0054			(CAN) IN REPLACING A FIREWALL FUEL SHUT-OFF VALVE, IT WAS FOUND THAT THE VALVE LEVER COULD CONTACT THE FUEL FILTER SUPPO	RT BRACKET WHEN IN THE CLOSED POSITION.  IN THIS STATE, THE VALVE LEVER COULD NOT RETURN TO THE OPEN POSITION.  PART TC:	  4,140.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900190	19981009	00190	CE  	1998	10	9	CA980416018      	1	19980406	G	2750	BZ7RW82255518T	SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					TE FLAP	FAILED          	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA								GGMPS0054			(CAN) AFTER TAKEOFF, WHEN FLAPS SELECTED FROM 17 DEGREES TO ZERO DEGREES, THE FLAPS DID NOT RETRACT.  AIRCRAFT RETURNED 	TO BASE AND LANDED SAFELY.  MAINTENANCE CHECK FOUND FLAP ASYMMETRY SWITCH WAS DEFECTIVE.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900191	19981009	00191	CE  	1998	10	9	CA980416019      	1	19980403	G	3251	993880047	ACTUATOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG STEERING	INOPERATIVE     	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								GGMPS0025			(CAN) PILOT REPORTED LOSING NOSE WHEEL STEERING.  MAINTENANCE CHECK REVEALED THE PLUG ON THE ACTUATOR WAS NOT SECURE PRE	VENTING THE ACTUATOR FROM EITHER ENGAGING OR DISENGAGING.  IN THIS STATE THE ACTUATOR WAS NOT CONNECTED TO THE NOSE WHEE	L STEERING UNIT.  NEW ACTUATOR INSTALLED.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900192	19981009	00192	SO  	1998	10	9	CA980416021      	1	19980402	G	3230	6775300	BRACKET         		6792632     	PIPER 	PA44  	PA44180     	7104402	SO  										LT MLG	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING, THE PILOT NOTED THAT THE LEFT GEAR DOWN LIGHT WOULD FLICKER OCCASIONALLY AND THE HYDRAULIC PUMP WOU	LD COME ON.  AIRCRAFT PUT ON JACKS AND INSPECTED.  THE TAB WAS FOUND BROKEN OFF THE LEFT GEAR DOWNLOCK SPRING ATTACHMENT	 BRACKET.  REPLACED.				1	L	7	2 	3O				A19S0
1998080700139	19980807	00139	NE  	1998	8	7	CA980417001      	2	19980403	G	8530		HEAD            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NR 9 CYLINDER	SEPARATED       	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA				416  				5127			(CAN) ON TAKEOFF, THE PILOT HEARD A POP AND THE ENGINE HAD A POWER LOSS.  ON RETURN TO RAMP, INSPECTION FOUND THE NR 9 C	YLINDER HEAD SEPARATED FROM THE BARREL.  THE CYLINDER ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	H	7	1 	3R	3	R		A806    	5E1
1998080700140	19980807	00140		1998	8	7	CA980417002      	1	19980408	G	2822	478360	PUMP            																	FUEL SYSTEM	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			1446 					4412707			(CAN) ON GROUND, POWER WAS APPLIED AND THE FUEL PUMP DID NOT ENERGIZE.  THE ELECTRICAL FUEL PUMP WAS REPLACED.
1998090400014	19980904	00014		1998	9	4	CA980417003      	1	19980409	G	7430	A5102	SWITCH          								ROTAX 	912   	ROTAX912    	55555	EU  					IGNITION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1468 					4380628			(CAN) ENGINE FAILED TO TURN OVER WHEN IGNITION TURNED ON.  SWITCH REPLACED.											3	I			EXPE3I
1998090400015	19980904	00015	CE  	1998	9	4	CA980417016      	1	19980408	G	3230	12805042	DOWNLOCK        			CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C214   	GL  	LT MLG	LEAKING         	W				L				ABORTED APPROACH        				J			WARNING INDICATION        			AP	APPROACH       	1			CA			3708 						810983		(CAN) LEFT DOWNLOCK ACTUATOR NOT GOING FULL TRAVEL, LEFT GEAR PARTIALLY LOCKED, BUT MICROSWITCH NOT ACTIVATED IF FULL TR	AVEL NOT REACHED.  NEW SEALS INSTALLED.  SWING SERVICEABLE.					1	H	7	1 	3O			RT	3A13    		5	C	P7EA
1998080700153	19980807	00153	WP  	1998	8	7	CA980417017      	1	19980408	G	2421	2CM353CIJ	SHAFT           			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					AC GENERATOR	SHEARED         	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA				752  				501678			(CAN) DURING CRUISE, LT ALTERNATOR LIGHT CAME ON.  GENERATOR WOULD NOT RESET.  MAINTENANCE INVESTIGATION FOUND THAT THE 	SHAFT WAS SHEARED.  THE GENERATOR WAS NOT FOUND TO BE SEIZED.					2	L	7	2 	4R	4	T		6A6     	E282
1998100900193	19981009	00193	CE  	1998	10	9	CA980421001      	1	19980326	G	3230	1EN1186	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					NLG DOWNLOCK	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA			1831 					PCE71129			(CAN) WHEN GEAR SELECTED DOWN NO GREEN LIGHT FOR NOSE GEAR DOWNLOCK.  ALSO, THERE WAS NO RED UNSAFE LIGHT OR ANY HYD ON 	ANNUNCIATOR LIGHT.  GEAR RECYCLED, STILL THE SAME AND BULBS OK.  GEAR BLOWN DOWN.  AIRCRAFT LANDED OK.  FOUR HOURS LATER	 THE GREEN LIGHT WAS ON.  SUBMITTER SUSPECTS COLD SOAKING OF SWITCH.  SWITCH REPLACED.  PART TC:  1,471.				1	L	7	2 	4F	4	F		A22CE   	E1NE
1998050801416	19980508	01416	NE  	1998	5	8	CA980421002      	2	19980330	G	7313		FUEL NOZZLE     			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  					NR 2 ENG	TORCHING        	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				142  				PCE12390			(CAN) DURING CLIMB AFTER TAKEOFF, NR 2 ENGINE POWER ROLLED BACK FROM 1244 POUNDS TORQUE TO 800 POUNDS, T5 TEMPERATURE WA	S 670C AND NG WAS 81 PERCENT.  PILOT RETURNED TO BASE.  POWER SECTION REMOVED FOR HSI AND EXTENSIVE TORCHING DAMAGE WAS 	FOUND ON THE COMPRESSOR TURBINE GUIDE VANES AND THE TURBINE WHEEL.  THE POWER TURBINE AND GUIDE VANES WERE ALSO DAMAGED.	  THE DAMAGE WAS SUSPECTED TO HAVE BEEN CAUSED BY A FUEL NOZZLE TORCHING (FUEL STREAMING INSTEAD OF SPRAYING).  THE ENGI	NE WAS 142 HOURS FROM AN HSI, WITH THE FUEL NOZZLES CLEANED AND FLOW CHECKED.  THE PARTS WERE RETURNED FOR EVALUATION.		1	L	7	2 	3T	3	T	RT	A7CE    	E4EA
1998081900002	19980819	00002	EA  	1998	8	19	CA980421003      	2	19980406	G	7414		GASKET          								LYC   	O360  	IO360LYC*   	41514	EA  					RT MAGNETO	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			35   					L2741351A			(CAN) OIL LEAK FROM RT MAGNETO.  MAGNETO AND GASKET REMOVED AND THE PROBLEM WAS FOUND TO BE A PIECE OF THE TAIL END OF A	 COTTER PIN EMBEDDED IN THE MAGNETO GASKET.										3	O			1E10
1998100900194	19981009	00194	SW  	1998	10	9	CA980421004      	1	19980409	G	6322	J33C32	BEARING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					BLOWER	ROUGH           	W				O				OTHER                   				E			VIBRATION/BUFFET          			IN	INSP/MAINT     	1			CA			510  					LE07592			(CAN) VIBRATION FROM OIL COOLER BLOWER.  BOTH BEARINGS DRY AND ROUGH RUNNING.  BEARING SEALS BROKEN.						1	G	7	1 	4U	4	U		H1SW    	E17EA
1998080700154	19980807	00154	EU  	1998	8	7	CA980421005      	1	19980328	G	5522	B332200B00C	SKIN            			DORNER	DO228 	DO228202    	2992030	EU  	GARRTT	TPE331	TPE3315     	01514	WP  					ELEVATOR	DAMAGED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			C	E	F	F.O.D.                    	VIBRATION/BUFFET          	FLT CONT AFFECTED         	CR	CRUISE         	1			CA			770  					P39245			(CAN) DURING CRUISE IN STILL AIR, AIRCRAFT STRUCK BY LIGHTNING.  IT APPEARS TO HAVE ENTERED VHF COMM ANTENNA ON FORWARD 	FUSELAGE BELLY.  EXIT POINT WAS AT RIGHT ELEVATOR TRAILING EDGE.  A SMALL AREA AT EXIT POINT WAS MELTED INTO A BLOB.  TH	E AFT HALF OF THE ELEVATOR TIP TOP AND BOTTOM HAD TOTALLY BEEN BLOWN OFF.  APPROX  80 PERCENT OF AREA OF THE RIGHT ELEVA	TOR WAS RENDERED USELESS DUE TO EITHER TORN FABRIC OR FABRIC DEBONDING FROM ELEVATOR.  OTHER DAMAGE INCLUDED, 1 COMM ANT	ENNA, 2 ADF ANTENNAS, 3 STATIC WICKS, 1 LANDING LIGHT, 1 TRANSPONDER.  CREW NOTED AIRCRAFT ONLY ABLE TO CONTROL IN SLOW 	FLIGHT WITH ONLY CREW ON BOARD.  EMERGENCY LANDING NECESSARY.	2	H	7	2 	4T	4	T	RT	A16EU   	E4WE
1998120400015	19981204	00015	GL  	1998	12	4	CA980421007      	2	19980413	G	7320	23056935V	FCU             	BENDIX      		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					ENGINE	FAILED          	W				B				EMER. DESCENT           				R			PARTIAL RPM/PWR LOSS      			HO	HOVERING       	1			CA				2208 		334417		CAE823343			(CAN) HELICOPTER IN HOVER, ENGINE DECELERATED TO IDLE.  THROTTLE CONTROL IN FULL POSITION.  PILOT AUTOROTATED TO RAMP. T	HROTTLE ROLLED BACK TO IDLE AND THEN BACK TO FULL AND ENGINE RESPONDED NORMALLY.  FUEL AND AIR OF FCU AND GOVERNOR WERE 	LEAK CHECKED OK.  FCU AND POWER TURBINE GOVERNOR WERE REPLACED.  ALSO, THE COMBUSTION LINER AND FUEL NOZZLE WERE REPLACE	D.  PART TC:  1,852.			1	G	7	1 	3U	3	U		H2SW    	E4CE
1998080700159	19980807	00159	EA  	1998	8	7	CA980421012      	1	19980403	G	5530	C2FS569A	BRACKET         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					BS 186	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9326 					JP211065			(CAN) DURING 700 HOUR INSPECTION, VERTICAL STABILIZER FRONT FIN PICKUP AT STA 186.40 WAS FOUND CRACKED.  CRACK EXTENDED 	ALONG BOTH WELDED JOINTS BETWEEN SIDE WEBS AND UPPER NUT FACE.					1	H	7	1 	3R	3	R		A806    	5E1
1998082800141	19980828	00141	NM  	1998	8	28	CA980421020      	1	19980409	G	2913	570347	PUMP            	VICKERS     		DHAV  	DHC8  	DHC8102     	2809003	NM  										NR 2	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF THROUGH 140 KNOTS, THE NR 2 HYDRAULIC PRESSURE CAUTION LIGHT, THE RUDDER PRESSURE, AND RUDDER FULL P	RESSURE CAUTION LIGHTS CAME ON.  ON APPROACH, THE CAUTION LIGHTS WENT OUT.  INVESTIGATION FOUND THE ENGINE DRIVEN PUMP H	AD A SPLIT FLANGE.				2	H	7	2 	4T			RT	A13NM
1998082800142	19980828	00142	GL  	1998	8	28	CA980421021      	3	19980413	G	6111	7557M1	BLADE           			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				6047 					83178		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE AND CORROSION WAS FOUND ON THE LEADING EDGE AND THE FAC	E OF THE PROPELLER BLADES.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1998082800143	19980828	00143	GL  	1998	8	28	CA980421022      	3	19980414	G	6111		BLADE           			MOONEY	M20   	M20J        	5870219	SW  						MCAULY	2D34C	B2D34C214   	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2730 	431  					779997		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THE PROPELLER BLADES WERE FOUND WITH EXTENSIVE STONE/ROCK DAMAGE. TH	E BLADES WERE NOT REPAIRED.					1	L	7	1 	3O				2A3     		5	C	P7EA
1998090400016	19980904	00016	CE  	1998	9	4	CA980421023      	1	19980414	G	5313	05131323	STRINGER        			CESSNA	172   	172I        	2072426	CE  										FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4829 								(CAN) ON INSPECTION, THE LEFT HAND UPPER ENGINE RAIL CRACKED WHERE THE ENGINE MOUNT BOLT CONNECTS.						1	H	7	1 	3O			NT	3A12
1998082800144	19980828	00144	NE  	1998	8	28	CA980421024      	3	19980415	G	6114	524278	RING            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134053     	52016	NE  	HAMSTD	3D	3D40        	NE  	PROPELLER	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			3510 	635  				P325619A	N404381		(CAN) CHAFING RINGS WERE FOUND BROKEN DUE TO IMPROPER FIELD ASSEMBLY.  BARREL BLOCKS BROKEN.  SHAFTS DAMAGED DUE TO POOR	 TRAINING IN FIELD TO DO PROPELLER SHOP WORK.					1	H	7	1 	3R	3	R	 	A815    	5E2			A815
1998082800145	19980828	00145	EA  	1998	8	28	CA980421025      	3	19980415	G	6111		BLADE           			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4J     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1745 	142  				L1832736A	16415KAB		(CAN) PROPELLER RECEIVED FOR FIVE YEAR CORROSION INSPECTION.  PAINT REMOVED FROM THE PROPELLER AND A LARGE AMOUNT OF COR	ROSION WAS FOUND ON THE THRUST FACE OF THE PROPELLER.  EXTRA WORK WAS REQUIRED TO REMOVETHE CORROSION.  THE PROPELLER WA	S RETURNED TO SERVICE.				1	L	7	1 	3O	3	O		A1CE    	E286	5	N	P4EA
1998082800146	19980828	00146	GL  	1998	8	28	CA980421026      	3	19980416	G	6111	C4902	NUT             			CESSNA	180   	180B        	2072606	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	BLADE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			356  	229  				8153604	850886		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  BLADE RETAINING NUT WAS FOUND CRACKED.  THE FAILURE OF THE RETAINING	 NUT COULD CAUSE BLADE SEPARATION.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1998100900195	19981009	00195	CE  	1998	10	9	CA980421027      	1	19980416	G	5610	50420066317	WINDOW          			BEECH 	90    	65A90       	1152908	CE  	PWA   	PT6   	PT6A20      	52043	EA  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE20621			(CAN) CRACK FOUND ON INSPECTION PER SAFETY COMMUNIQUE NR 142 ISSUED BY RAYTHEON AIRCRAFT COMPANY DATED NOVEMBER, 1997.						1	L	7	2 	3T	3	T		3A20    	E4EA
1998073100391	19980731	00391	SW  	1998	7	31	CA980422002      	1	19980402	G	7920	70010L000V174	HOSE            			BELL  	212   	212         	1181420	SW  										OIL COOLER	SPLIT           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) OIL HOSE WITH EXCESSIVE LEAKING DURING CHECK.  FOUND RUBBER CORE PROTRUDING THROUGH STAINLESS STEEL BRAIDS.						1	G	7	1 	4U				H4SW
1998073100392	19980731	00392	SW  	1998	7	31	CA980422003      	1	19980402	G	6410	212010750105	BLADE           			BELL  	212   	212         	1181420	SW  										TAIL ROTOR	DELAMINATION    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3376 								(CAN) T/R BLADE HEAVY COATING STARTED PEELING UNTIL DELAMINATION OCCURRED.						1	G	7	1 	4U				H4SW
1998073100393	19980731	00393	SW  	1998	7	31	CA980422004      	1	19980402	G	6300	212040005103	BOOT            			BELL  	212   	212         	1181420	SW  										DRIVE SHAFT	MELTED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) DRIVESHAFT BOOT SUSPECTED OF LEAKING.  UPON REMOVAL OF DRIVESHAFT, BOOT FOUND TOTALLY MELTED AND METAL PART OF BOO	T HAD DISCOLORATION.					1	G	7	1 	4U				H4SW
1998120400016	19981204	00016	EU  	1998	12	4	CA980422005      	1	19980415	G	2435	03601018	BEARING         	LUCAS       	23080005    	BRAERO	DH125 	HS125700A   	4230170	EU  										START/GEN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3957					(CAN) PREMATURE BEARING FAILURE AT 557 HOURS TSO, CAUSING IRREPAIRABLE DAMAGE TO ARMATURE.						2	L	7	2 	4F				A3EU
1998082800151	19980828	00151	EA  	1998	8	28	CA980422008      	1	19980408	G	2910	82920010363	LINE            			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					HYDRAULIC SYS	SEVERED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			K	G	J	FLUID LOSS                	MULTIPLE FAILURE          	WARNING INDICATION        	CR	CRUISE         	1			CA			15   					AE0006			(CAN) ON MAINTENANCE FLIGHT WHILE DOING AN ALTERNATE GEAR EXTENSION AND THE NR 2 HYDRAULIC SYSTEM WAS AT ZERO PRESSURE. 	 TO CLOSE GEAR DOORS POWER TRANSFER UNIT WAS TURNED ON TO RE-PRESSURIZE NR 2 SYSTEM.  OK FOR A COUPLE OF SECONDS, THEN I	NDICATING LOST.  DOORS STAYED OPEN.  NR 2 ENGINE HAD BEEN SHUTDOWN ALSO AS PART OF PROCEDURE, IT WAS RESTARTED.   NR 2 H	YDRAULIC PRESSURE STILL AT ZERO AND QUANTITY STARTED TO FALL OFF.  FOUR CAUTION LIGHTS ON.  NR 2 ENGINE HYDRAULIC PUMP, 	NR 1 DC GENERATOR, ROLL SPOILER HYDRAULIC, AND NOSE STEERING.  NR 1 GENERATOR FELL OFF-LINE AND WOULD NOT RESET.  NR 2 E	NGINE SHUT DOWN AGAIN TO STOP ANY FURTHER PROBLEMS WITH NR 2 HYDRAULIC SYSTEM.  EMERGENGY DECLARED AND ACFT LANDED OK.	2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998082800152	19980828	00152	NE  	1998	8	28	CA980422009      	2	19980413	G	7230	310815201	BEARING         								PWA   	118   	PW118       		NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17211	2355 				115243			(CAN) TURBOMACHINE WAS SENT FOR INVEST AND REPAIR AFTER OPERATOR REPORTED TURBOMACHINE  MAKING METAL.  DISASSY OF TURBOM	ACHINE FOUND NR 5 BEARING IN POOR OVERALL CONDITION, BUT NO IMMEDIATE APPARENT MATERIAL LOSS.  AFTER CLEANING, A MORE DE	TAILED INSP FOUND 3 ROLLER BEARING TANGS ON SEPARATOR BROKEN AND MISSING AND TOP EDGES OF A NUMBER OF OTHER TANGS SHOWIN	G EVIDENCE OF RUBBING AND ABRASION WITH MATERIAL LOSS.  THIS WAS SOURCE OF METAL CONTAMINATION.  TANGS SHOULD BE CLEAR O	F ALL OTHER SURFACES IN A TYPICAL BEARING AND NO UNUSUAL WEAR FOUND IN ROLLER POCKETS OF THIS BEARING.  IT APPEARS FAULT	 LAYS IN CLEARANCES BETWEEN ROLLER CAGE AND RACES AND/OR ROLLERS ON THIS BEARING.  PART TC:  23,641.						4	T			E20NE
1998082800153	19980828	00153	NE  	1998	8	28	CA980422010      	2	19980330	G	7230	310815201	BEARING         								PWA   	118   	PW118       		NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16051	9499 				115310			(CAN) ENG SENT FOR INSP AND REPAIR AFTER OPERATOR REPORTED HIGH OIL CONSUMPTION AND A RUMBLING NOISE FROM ENG.  DISASSY 	OF TURBOMACHINE FOUND PRIMARY CAUSE OF RUMBLING NOISE WAS FAILURE OF NR 5 BEARING.  3 ROLLERS SEVERELY WORN, FRETTED AND	 CAGE BROKEN IN 4 PIECES.  LOSS OF POSITION OF NR 5 BEARING CAUSED AN IMBALANCE OF AIR/OIL SEALS CAUSING OIL TO FLOOD MO	ST OF AIR CAVITIES IN ENG.  BEARING WAS ORIG TO ENG AT NEW MFG:  NR 5 BEARING OIL NOZZLES FLOWED FREELY WHEN TESTED AND 	OIL STARVATION IS NOT SUSPECTED.  THERE WAS LITTLE EVIDENCE OF COKING IN ENG.  MAGNETIC METAL FILINGS WERE FOUND IN OIL 	AND CHIP DETECTOR HAD BEEN BRIDGED.  OIL ANALYSIS CONFIRMED MAJOR AMOUNT OF M50 (NR 5 BEARING).  PART TC:  21,885.						4	T			E20NE
1998082800154	19980828	00154	NE  	1998	8	28	CA980422011      	2	19980413	G	7210	310960701	GEAR            								PWA   	120   	PW120       		NE  					GEARBOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16588					120939			(CAN) REDUCTION GEARBOX (RGB) WAS SENT FOR INVESTIGATION AND REPAIR AFTER THE OPERATOR REPORTED THE RGB WAS MAKING METAL	. THE RGB WAS DISASSEMBLED AND THE CAUSE OF THE METAL CONTAMINATION WAS FOUND TO BE THE SPALLING OF THE FIRST STAGE HELI	CAL GEARS.  THE SPALLING PATTERN SEEN ON THE GEAR TEETH WAS TYPICAL OF EXCESSIVE WEAR.  THIS WAS A VERY HIGH TIME RGB (1	6587.6 HOURS) SINCE NEW WITH NO OVERHAULS. CONSIDERING THE HIGH TIME, THIS APPEARS TO HAVE BEEN A PRIMARY FAILURE OF THE	 GEARS DUE TO NORMAL OPERATIONAL WEAR.   PART TC:  18,399.							4	T			E20NE
1998082800156	19980828	00156	EA  	1998	8	28	CA980424006      	1	19980420	G	5610	601R330339	WINDSCREEN      	PPG         		CNDAIR	CL600 	CL6002B19   		EA  										COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			12   			97259H5618					(CAN) DURING CUSTOMER ACCEPTANCE FLIGHT, THE PILOT'S WINDSHIELD CRACKED IN FLIGHT.  PRESSURIZATION AT 3 PSI, AT 14,500 F	EET AND 280 KIAS.  THREE CRACKS ALONG THE LOWER FRAME AND ONE CRACK ACROSS WINDSHIELD.  PART TC:  16.					2	L	7	2 	4F			RT	A21EA
1998082800166	19980828	00166	EA  	1998	8	28	CA980424018      	2	19980415	G	8520	75010	CRANKSHAFT      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				805  				L2847827A			(CAN) INSPECTION OF CRANKSHAFT CARRIED OUT AS PER LYCOMING SERVICE BULLETIN 505B.  CORROSION PITS WERE FOUND.   AREA HON	ED, PITS WERE REMOVED AND PROTECTIVE COATING WAS APPLIED PER LYCOMING SB 530.					1	L	7	1 	3O	3	O		2A13    	E274
1998082800167	19980828	00167	EA  	1998	8	28	CA980424019      	2	19980415	G	8520	75010	CRANKSHAFT      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1920 				L1825927A			(CAN) INSPECTION OF CRANKSHAFT CARRIED OUT PER LYCOMING SERVICE BULLETIN 505B.  CORROSION PITS WERE FOUND.  FLUORESCENT 	PENETRANT INSPECTION CARRIED OUT. NO CRACKS NOTED.					1	L	7	1 	3O	3	O		2A13    	E274
1998082800168	19980828	00168	EA  	1998	8	28	CA980424020      	2	19980415	G	8520	75010	CRANKSHAFT      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1427 				L3448727A			(CAN) INSPECTION OF CRANKSHAFT CARRIED OUT PER LYCOMING SERVICE BULLETIN 505B.  CORROSION PITS WERE FOUND.  AREA  HONED,	 PITS WERE REMOVED AND PROTECTIVE COATING WAS APPLIED PER LYCOMING SB 530.					1	L	7	1 	3O	3	O		2A13    	E274
1998082800169	19980828	00169	EA  	1998	8	28	CA980424021      	2	19980415	G	8520	LW17060	CRANKSHAFT      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				522  				L3663127A			(CAN) INSPECTION OF CRANKSHAFT CARRIED OUT PER LYCOMING SERVICE BULLETIN 505B.  CORROSION PITS WERE FOUND.  FLUORESCENT 	PENETRANT INSPECTION CARRIED OUT.  NO CRACKS NOTED.					1	L	7	1 	3O	3	O		2A13    	E274
1998082800171	19980828	00171	EA  	1998	8	28	CA980430002      	2	19980415	G	8520		CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2139 					L402176	733208		(CAN) WHILE CARRYING OUT AD 98-02-08 (LYCOMING SB 505B), INITIAL INSPECTION FOUND MODERATE AMOUNTS OF PITTING IN THE INS	IDE DIAMETER OF THE CRANKSHAFT.  NDT TESTING, PER THE SB, DETECTED TWO CRACKS, ONE .25 LONG, THE SECOND .50 LONG. THE EN	GINE WAS REMOVED.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998082800172	19980828	00172	SO  	1998	8	28	CA980430004      	2	19980309	G	8530		CYLINDER        			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				897  				247554R			(CAN) ENGINE RUNNING ROUGH IN-FLIGHT.  POST-FLIGHT INSPECTION FOUND A CYLINDER CRACKED AROUND THE EXHAUST VALVE SEAT.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998090400017	19980904	00017	CE  	1998	9	4	CA980430005      	1	19980408	G	3246	256692	WHEEL           		XPM12       	CESSNA	185   	A185F       	2072821	CE  						MCAULY	3A32C	D3A32C90    	GL  	TAIL	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			41   			7856			756229		(CAN) AIRCRAFT ON SKIS.  WHILE LANDING, THE PILOT HEARD A BANG FROM THE BACK OF THE AIRCRAFT WHEN THE TAIL WHEEL TOUCHED	 DOWN.  LANDING COMPLETED OK. THE TAIL WHEEL ASSY HAD BROKEN OFF THE TAIL SPRING AND STILL ATTACHED TO THE STEERING CABL	ES. THE HUB HAD BROKEN INTO FOUR PIECES AND THREE WERE RECOVERED AND SENT TO THE MANUFACTURER FOR ANALYSIS.  PART TC:  2	0.			1	H	7	1 	3O				3A24    		5	C	P21EA
1998091100446	19980911	00446	CE  	1998	9	11	CA980430007      	1	19980409	G	3230	1158100717	SEAL            		998100547   	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					RT MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE50074			(CAN) MAIN LANDING GEAR DRIVE SHAFT RT INBD FOUND GROOVED DUE TO MISALIGNMENT OF THE MAIN LANDING GEAR, GEARBOX AND MOTO	R ASSEMBLY.  THE TORQUE SHAFT WAS NOT CENTERED IN THE PRESSURE SEAL, RESULTING IN WEAR/DAMAGE TO THE SEAL AND LEAVING TH	E SHAFT IN DIRECT CONTACT WITH THE SEALS METAL FINGERS.  THIS CONDITION COULD LEAD TO EARLY SHAFT FAILURE.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998091100447	19980911	00447	SO  	1998	9	11	CA980430009      	1	19980416	G	3213	AN17642	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	BROKEN          	W				A				UNSCHED LANDING         				E	D	J	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	WARNING INDICATION        	TO	TAKEOFF        	1			CA				135  							(CAN) PILOT REPORTED A VIBRATION AT AND JUST PRIOR TO ROTATION.   RED INTRANSIT LIGHT CAME ON, FLY BY INDICATED THAT THE	 LT MLG WAS NOT FULLY RETRACTED.  GEAR LOWERED AND A/C LANDED. THE HEAD AND A .75  INCH OF BOLT FOUND ON RUNWAY.  LT MLG	 UPPER TORQUE LINK BOLT REPLACED.				1	L	7	2 	3O				A20SO
1998090400018	19980904	00018	CE  	1998	9	4	CA980430010      	1	19980420	G	3242	07308500	PLATE           		03018200    	CESSNA	208   	208B        	2073701	CE  										MLG	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			10   								(CAN) PRESSURE PLATE FOUND INSTALLED BACKWARDS PLACING THE ORGANIC LINING AGAINST THE BRAKE PISTONS AND THE STEEL BACKSI	DE OF THE PRESSURE PLATE CONTACTING THE BRAKE DISC.  ON BRAKING, THE FRICTION OF STEEL ON STEEL WAS CAUSING METAL TRANSF	ER.  NO INDICATION FROM PILOTS OF ANY OPERATIONAL MALFUNCTION.  REPLACED.  PART TC:  25.				1	H	7	1 	3T			 	A37CE
1998082800174	19980828	00174	SO  	1998	8	28	CA980430013      	2	19980324	G	8500		ENGINE          			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CRUISE	POWER LOSS      	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				1586 				250800A			(CAN) THE ENGINE WAS RUNNING ROUGH LOSING 400 RPM'S AT LEVEL FLIGHT.  ANY NOSE UP MOVEMENT CAUSED LOSS OF 300-500 RPM'S.	  THE ENGINE WAS INSPECTED AND NO FAULTS WERE FOUND. THE ENGINE CYLINDER COMPRESSION WAS GOOD (OVER 75 PSI ON ALL CYLIND	ERS).  THE ENGINE WAS REMOVED FOR OVERHAUL.				1	H	7	1 	3O	3	O		3A19    	E252
1998082800175	19980828	00175	NE  	1998	8	28	CA980430014      	2	19980416	G	7530	451077	LINE            			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	SHEARED         	W				C				ABORTED TAKEOFF         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA								702235			(CAN) NR 2 ENGINE WOULD NOT DEVELOP FULL POWER.  HP BLEED CONTROL LINE CRACKED AND SHEARED OFF AT 13TH STAGE CONNECTION.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1998082800180	19980828	00180	NM  	1998	8	28	CA980430019      	1	19980304	G	3230	66139292	WASHER          		6517657     	BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					LT MLG	MISSING         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								P689955			(CAN) WASHER MISSING FROM LEFT MLG SIDE STRUT. INSTALLED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998082800181	19980828	00181	NM  	1998	8	28	CA980430020      	1	19980305	G	2730	6526658	HINGE           			BOEING	727   	727260      	       	NM  	PWA   	JT8   	JT8D17      	52049	NE  					ELEVATOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								P689955			(CAN) ALL ELEVATOR HINGE BALANCE PANELS WORN, WORN SEALS AND INCORRECT HARDWARE.  REPLACED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998082800182	19980828	00182	NM  	1998	8	28	CA980430021      	1	19980417	G	3244	501K021	TIRE            			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 1 MLG	SEPARATED       	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			586  	201  							(CAN) ON LANDING, LOST NR 1 MAIN WHEEL OUTER CASING.  MAIN OUTER DOOR SKIN DAMAGED, INNER FLAP CENTER CANOE, HONEYCOMB P	ANEL ABOVE NR 1 MLG DAMAGED, DENTS ON INNER TE FLAP.  PIECE OF PALLET LOCK 1 INCH BY 2.5 INCHES FOUND INSIDE DAMAGED CAN	OE, APPEARS TO HAVE FRESH DAMAGE, RUBBER, GRASS RESIDUE ON IT.  REPAIRED.  PART TC:  586.				2	L	7	3 	4F	4	F		A3WE    	E2EA
1998082800183	19980828	00183	EA  	1998	8	28	CA980430022      	1	19980420	G	5740	C3W635	ATTACH PLATE    			DHAV  	DHC3  	DHC3        	2800202	EA  										RT/LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12905								(CAN) DURING INSPECTION, A SMALL CHIP OF PAINT FOUND ON RIGHT WING FRONT LUG PLATE OUTBOARD OF LUG ATTACH.  CLOSER INSPE	CTION, UNCOVERED EVIDENCE OF STRESS CORROSION AND .1875 INCH FORE AND AFT CRACK ON THE PLATE EXTENDING .25 INCH  VERTICA	LLY.  LEFT WING FRONT LUG PLATE ON THE SAME AIRCRAFT WAS INSPECTED AND ALSO FOUND TO HAVE STRESS CORROSION HIDDEN UNDER 	PAINT.  LEFT WING P/N C3W63-5 AND RIGHT WING P/N C3W63-6.			1	H	7	1 	3R				A815
1998082800184	19980828	00184	GL  	1998	8	28	CA980430023      	3	19980423	G	6114	C5262	HUB             			UNIVAR	108   	1082        	9230406	NM  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			537  	99   				489712K4	713256		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CYLINDER SUPPORT WAS FOUND BENT AND THE CYLINDER WAS WORN.						1	H	7	1 	3O	3	O		A767    	E273	5	C	P3EA
1998090400019	19980904	00019	GL  	1998	9	4	CA980430024      	1	19980422	G	2720	2027220500	RUDDER PEDAL    			DIAMON	DA20A1	DA20A1      	05626UX	GL  										COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1093 								(CAN) WHILE INSPECTING THE RUDDER PEDAL ASSEMBLIES, THE PILOTS AND COPILOTS PEDALS WERE SLIGHTLY BENT FORWARD.  FURTHER 	INSPECTION REVEALED CRACKS JUST ABOVE THE PIVOT POINTS.  REPLACED.					1	L	7	1 	3O			NT	TA4CH
1998082800185	19980828	00185	GL  	1998	8	28	CA980430025      	3	19980421	G	6111		BLADE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1612 					L95476	729539		(CAN) DURING OVERHAUL, THE PROPELLER CAMBER FACE IS RESURFACED BY GRINDING. DURING THE GRINDING PROCESS CORROSION WAS FO	UND.. THERE WAS EXTRA GRINDING REQUIRED TO REMOVE THE CORROSION. THE PROPELLER CONTINUED IN SERVICE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998091100448	19980911	00448	CE  	1998	9	11	CA980430026      	1	19980128	G	5311		FRAME           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					BS 207	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16722					PCE57492			(CAN) DURING FUSELAGE INSPECTION, CRACKS WERE FOUND ON FRAME AT STATION 207.35 AT FLOOR LEVEL RT AND LT SIDES.  THE CRAC	K WAS FROM A RADIUS OF A CUT-OUT IN THE FRAME THAT ALLOWS A RIB TO PASS THROUGH IT.  A DOUBLER WAS INSTALLED IAW MANUFAC	TURERS REPAIR.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998091100449	19980911	00449	CE  	1998	9	11	CA980430027      	1	19980403	G	5620	50420013557	RETAINER        		11543010025 	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					WINDOW	DISBONDED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12879					PCE50339			(CAN) DURING A 13,000 CYCLE FUSELAGE INSPECTION, IT WAS DISCOVERED THAT THE BONDING MATERIAL OF THE CIRCULAR WINDOW RETA	INER WAS CRACKED 3/4 OF THE CIRCUMFERENCE. THE POLARIZED WINDOWS AND THE OUTER WINDOW WERE REMOVED, THE BONDED RETAINER 	COULD BE LIFTED FROM THE A/C SKIN.  THE RETAINER WAS REPAIRED IAW BEECH MAINTENANCE MANUAL CHAPTER 56-20-00, PAGE 205, I	NSPECTION & REPAIR OF WINDOW ATTACHMENT FRAME.  PART TC:  13,437.			1	L	7	2 	3T	4	T		A14CE   	E4EA
1998090400020	19980904	00020	CE  	1998	9	4	CA980430030      	1	19980416	G	3230	504501019	TORQUE TUBE     			CESSNA	402   	402B        	207590P	CE  										LT MLG	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, THE CONTROL TOWER INFORMED THE PILOT THAT THE LEFT MLG WAS DOWN.  AIRCRAFT RETURNED TO BLOCKS.  INV	ESTIGATION REVEALED THAT THE CROSS SHAFT WAS CRACKED AND DISTORTED.  REPLACED.					1	L	7	2 	3O				A7CE
1998082800189	19980828	00189		1998	8	28	CA980430032      	1	19980421	G	6120	687045021	SEAL            	AERODUCT    	6505619     						ALLSN 	501D  	501D13D     	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	PROPELLER	PINCHED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			J			WARNING INDICATION        			DE	DESCENT        	1			CA								500964	HC2070		(CAN) DURING A SIMULATED EMERGENCY DESCENT THE PILOT DETECTED AN OVERSPEED OF THE NR 1 ENGINE. EMERGENCY PROCEDURES WERE	 CARRIED OUT AND THE ENGINE WAS SHUTDOWN AND THE PROPELLER FEATHERED. THE TRAINING MISSION WAS ABORTED AND THE AIRCRAFT 	LANDED.  THE OVERSPEED WAS ATTRIBUTED TO A PINCHED O-RING ON ONE OF THE PROPELLER REGULATING VALVES.									4	T			E282	6	C	P898
1998091100450	19980911	00450	CE  	1998	9	11	CA980430034      	1	19980422	G	5730	00011010922	SKIN            		000110105604	BEECH 	55    	E55         	1152732	CE  	CONT  	O520  	IO520CB     	17032	SO  					LT/RT WINGS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7156 					298777R			(CAN) ON THE LT AND RT WING LEADING EDGE SKIN, A 3 CM CRACK WAS FOUND IN THE LOWER INBOARD FORWARD LEADING EDGE SKIN.  T	HE CRACK IS LOCATED OUTBOARD OF LEADING EDGE ATTACHMENT SCREW P/N AN525-8R12 ITEM 13 OF IPC FIGURE 20-01-4 PAGE 57-20-01	-4.  CRACK IS PROGRESSING FORWARD TOWARD THE 1 INCH HOLE IN THE SKIN FOR MAIN FUEL CELL DRAIN COCK.  BEECH ENGINEERING C	ONTACTED REGARDING REPAIR SCHEME.			1	L	7	2 	3O	3	O		3A16    	E5CE
1998060500100	19980605	00100	EU  	1998	6	5	CA980430037      	1	19980407	G	3520	9571212211	HEAD            	SCOTT       	9571212211  	PILATS	PC12  	PC12        	7090550	EU  										OXY SYS	BLOWN PLUG      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3494 			3779					(CAN) WHILE SERVICING THE OXYGEN SYSTEM AT APPROX 1600 PSI, THE OVER PRESSURE PLUG BLEW ALSO DISCHARGING THE BOTTLE AND 	BLOWING OUT THE DISCHARGE RELIEF INDICATOR.  CAUSE UNKNOWN.  BOTTLE RETURNED TO MANUFACTURER.  PARTS REPLACED.  PART TC:	  2,555.				1	L	7	1 	3T			RT	A78EU
1998100900198	19981009	00198	SO  	1998	10	9	CA980430038      	1	19980414	G	2820	642697	TUBE ASSY       			PIPER 	PA28  	PA28R201T   	7102813	SO  	CONT  	O360  	TSIO360F    	17025	SO  	HARTZL	HCC2Y	BHCC2YF1    	GL  	FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			2766 					305237	AM1605		(CAN) TUBE CRACKED UNDER CLAMP.  NOT VISIBLE WITH CLAMP ON.  REPLACED.						1	L	7	1 	3O	3	O		2A13    	E9CE	5	C	P920
1998100900199	19981009	00199	SO  	1998	10	9	CA980430039      	1	19980417	G	5610	4154300	WINDSHIELD      			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA								L207261			(CAN) IN CRUISE, THE PILOT HEARD A LOUD BANG AND NOTED THAT THE LT WINDSHIELD HAD A 6 INCH CRACK IN THE CENTER.  AIRSPEE	D WAS REDUCED AND THE CRACK PROGRESSED ACROSS THE WINDSHIELD.  ON APPROACH, HEAT WAS APPLIED AND A U-SHAPE CRACK APPEARE	D AT THE ELEMENT.  REPLACED.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998082800192	19980828	00192	EA  	1998	8	28	CA980504004      	2	19980427	G	8530	LW11775	PISTON PIN PLUG 			PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					NR 2 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				798  				L58061			(CAN) DURING INSPECTION, EXCESSIVE NON-FERROUS METAL (SLIVERS) WAS FOUND IN THE OIL SCREEN. FURTHER INSPECTION FOUND THE	 NR 2 CYLINDER PISTON PIN PLUG BADLY WORN.					1	L	7	1 	3O	3	O	RT	A20SO   	E14EA
1998082800193	19980828	00193	CE  	1998	8	28	CA980504005      	1	19980427	G	7931		VALVE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NR 1 ENGINE	LOOSE           	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA								PCE80289			(CAN) PILOT REPORTED THE NR 1 ENGINE OIL AND TORQUE PRESSURE DROPPED TO ZERO.   NR 1 ENGINE PROP RPM FROM 1900 TO 1500. 	 N1 AND ITT WERE NORMAL. THE ENGINE WAS SHUTDOWN WITHIN MINUTES.  POST- FLIGHT INSPECTION FOUND NR 1 ENGINE OIL PRESSURE	 RELIEF VALVE TO BE UNSECURED.  THE RELIEF VALVE WAS RESECURED.  ALL FILTERS WERE INSPECTED AND CLEANED.  THE ENGINE WAS	 RUN-UP AND THE VALVE AND FILTERS WERE CHECKED SERVICEABLE.			1	L	7	2 	4T	4	T		A24CE   	E4EA
1998060500101	19980605	00101	EU  	1998	6	5	CA980504006      	1	19980427	G	2822	SPE8275	CASE            	PLESSEY     	BPIRSMK6    	BRAERO	748   	HS7482A     	4231001	EU  										PUMP BORE	MISREPAIRED     	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						44362					(CAN) LOCALLY MANUFACTURED BUSHING P/N 501-2-12072 BECAME LOOSE AND ROTATED IN CASING.  CASING ALSO RE-SLEEVED.						2	L	7	2 	3T			 	A24EU
1998091100451	19980911	00451	CE  	1998	9	11	CA980504007      	1	19980422	G	7797	HDJB	WIRE            			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					FUSE HOLDER	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			CA			11740					PCE32531			(CAN) DURING TAKEOFF, BOTH LT AND RT TORQUE INDICATORS FAILED.  MAINTENANCE TRACED THE PROBLEM TO A BROKEN WIRE ON INLIN	E FUSE HOLDER BEHIND INSTRUMENT PANEL. THIS FUSE SUPPLIES AC POWER TO BOTH TORQUE METER CIRCUIT BREAKERS ON THE BREAKER 	PANEL.  WIRE REPAIRED.  SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998082800195	19980828	00195	NE  	1998	8	28	CA980504010      	3	19980421	G	6111		BEARING         			CNDAIR	CL215 	CL2151A10   		EA  						HAMSTD	43E	43E60       	NE  	PROPELLER	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2112 					169593		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THE PROPELLER BLADE BEARING RACE WAS FOUND PITTED IN THE RETENTION A	REA.  SMALL SURFACE CRACKS FROM THE PITTED AREA REQUIRED GRINDING OF BOTH RINGS TO MINIMUM, IF THE CRACKS WERE LEFT THEY	 WOULD PROGRESS TO COMPLETE RING FAILURE.				2	H	7	2 	4R				A14EA   		6	C	P871
1998082800196	19980828	00196	GL  	1998	8	28	CA980504011      	3	19980427	G	6111	L7666A2	BLADE           			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1094 	83   				L707951A	CH9468		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  BOTH PROPELLER BLADES WERE FOUND BADLY NICKED FROM FOD.  FIELD REPAI	RS WERE NOT MADE IN ACCORDANCE WITH THE HARTZELL MANUAL.					1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P920
1998082800197	19980828	00197	GL  	1998	8	28	CA980504012      	3	19980424	G	6111	3411	BEARING         													MCAULY	D3A34	D3A34C403   	GL  	PROPELLER	GALLED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1090 	57   					7710337		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THE PROPELLER BLADE BEARINGS WERE FOUND DAMAGED WITH PITTING AND GAL	LING.  THE BEARINGS WERE REPLACED.															5	C	P47GL
1998082800198	19980828	00198	GL  	1998	8	28	CA980504013      	3	19980423	G	6111	S90AT2	BLADE           			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			930  	297  				226662R	784822		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADES AND FERRULES (P/N 3054) WERE FOUND CORRODED. THE	 PROPELLER BLADES WERE TRIMMED AND THE FERRULES WERE REPLACED.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1998060500102	19980605	00102		1998	6	5	CA980504014      	4	19980409	G	3414	211401150	INDICATOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  										BOTH AIR SPEED	FAILED          	W				K				NONE                    				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) BOTH AIRSPEED INDICATORS FAILED.   NEEDLE AND DRUM INDICATIONS VARIED FROM 0 TO 210 KNOTS IN TURBULENT CONDITIONS,	 WITH LIGHT ICING.  SYSTEM RETURNED TO NORMAL IN CLEAR AIR.					2	H	7	2 	4T			RT	A13NM
1998060500103	19980605	00103		1998	6	5	CA980504015      	4	19980409	G	3414	211401150	INDICATOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  										AIR SPEED	FAILED          	W				K				NONE                    				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) BOTH AIRSPEED INDICATORS FAILED, NEEDLE AND DRUM INDICATIONS VARIED FROM 0-210 KNOTS IN TURBULENT CONDITIONS, WITH	 LIGHT ICING.  SYSTEM RETURNED TO NOMRAL IN CLEAR AIR.  SIMILAR CONDITIONS ON ANOTHER AIRCRAFT IN SAME AREA.					2	H	7	2 	4T			RT	A13NM
1998091100452	19980911	00452	CE  	1998	9	11	CA980504016      	1	19980424	G	5610	9031002P	WINDSCREEN      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								PCE50250			(CAN) AFTER TAKEOFF WHEN THE A/C BEGAN TO PRESSURIZE, THE CO-PILOT NOTICED THE RT WINDSHIELD BEGINNING TO CRACK ON THE O	UTBOARD EDGE.  A/C DEPRESSURIZED AND RETURNED SAFELY TO BASE.  MAINTENANCE REPLACED THE CRACKED WINDOW AND NOTICED A SMA	LL CHIP ON IT.  FLEET INSPECTED WITH NO FURTHER PROBLEMS.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998060500104	19980605	00104	EA  	1998	6	5	CA980504017      	1	19980427	G	3200		LANDING GEAR    			DHAV  	DHC8  	DHC8311     	1386006	EA  										MLG	COLLAPSED       	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WITH BOTH ENGINES RUNNING PRIOR TO THE FIRST FLIGHT OF THE DAY, THE CREW CARRIED OUT A SYSTEM CHECK OF THE MANUAL 	PTU TEST PER FLIGHT MANUAL.  AT THIS TIME, BOTH MAIN LANDING GEARS COLLAPSED.					2	H	7	2 	4T			RT	A13NM
1998100900202	19981009	00202	SO  	1998	10	9	CA980504018      	1	19980429	G	2710	AN15516	TURNBUCKLE      			PIPER 	J3    	J3C65       	7100510	SO  	CONT  	C90   	C9012F      	17009	SO  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								900181			(CAN) ONE INCH CRACK IN TURNBUCKLE BARREL STARTING FROM LT THREAD END.  REPLACED.						1	H	7	1 	3O	3	O		A691    	E252
1998082800199	19980828	00199	GL  	1998	8	28	CA980504019      	3	19980429	G	6111	C3411	BEARING         			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C307  	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3011 	941  				352791	807307		(CAN) PROPELLER RECEIVED FOR FIVE YEAR CORROSION INSPECTION.  INSPECTION FOUND NR 1 BLADE BEARING RACE CORRODED.  BEARIN	G RACE REPLACED.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
1998082800200	19980828	00200	NM  	1998	8	28	CA980504021      	1	19980504	G	3213	S1106530055	SCRAPER RING    		657276177   	BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1247 		BN0637		P689955			(CAN) MLG STRUT SCRAPER RING COMING OUT OF GLAND NUT.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998091100453	19980911	00453	CE  	1998	9	11	CA980504022      	1	19980428	G	5320	504300431183	INTERCOSTAL     			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE50021			(CAN) THE INTERCOSTAL BRACKET LOCATED UNDER THE CABIN DOOR POST BRACKET WAS FOUND CRACKED.  THE CRACK IS ATTRIBUTED TO L	OADS PLACED ON THE DOOR POST BY PASSENGERS AND CREW EXITING THE A/C AND USING THE DOOR POST FOR SUPPORT.  THE INTERCOSTA	L WAS FOUND CRACKED ON BOTH LOCATIONS LT AND RT SIDES OF THE DOOR AND ON TWO SEPARATE DOORS.  CRACKED INTERCOSTALS REPLA	CED.			1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900203	19981009	00203	SO  	1998	10	9	CA980504023      	1	19980420	G	2140	751817	WHEEL           			PIPER 	PA31  	PA31350     	7103110	SO  										BLOWER	DISINTEGRATED   	W				H				DEACTIVATE SYST/CIRCUITS				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				797  							(CAN) HEATER REPORTED NOISY.  BRUSHES REPLACED.						1	L	7	2 	3O				A20SO
1998082800202	19980828	00202	EA  	1998	8	28	CA980504026      	2	19980428	G	8530	LW12427	CYLINDER        			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					ENGINE	CRACKED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			1932 					L2157036A			(CAN) FOUND THE ALUMINUM HEAD ON NR 3 CYLINDER CRACKED AT THE TOP OF THE STEEL BARREL.						1	L	7	1 	3O	3	O		A1CE    	E286
1998082800203	19980828	00203	SW  	1998	8	28	CA980504028      	1	19980425	G	3246	LM2974920629	BEARING         	BFGOODRICH  	31418       	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	NLG	SEIZED          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				271  		1381		P44424C	DRG57282		(CAN) DURING TAXI, THE AIRCRAFT VEERED TO THE RIGHT.  THE NR 2 NOSE WHEEL BEARINGS HAD SEIZED ONTO THE AXLE.  AXLE, NOSE	 WHEEL, AND BEARINGS REPLACED.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
1998100900204	19981009	00204	SO  	1998	10	9	CA980504029      	1	19980427	G	5320	6241100	SUPPORT         			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8536 					L4250727A			(CAN) BAGGAGE DOOR HINGE AND FLOOR SUPPORT CHANNEL CRACKED.  REPAIRED.						1	L	7	1 	3O	3	O		2A13    	E274
1998100900205	19981009	00205	SO  	1998	10	9	CA980506003      	1	19980430	G	5521	4595111	SPAR            		5501620     	PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9046 			31T720		PCE92516			(CAN) LEFT ELEVATOR SPAR CRACKED IN 2 PLACES AT OUTBOARD HINGE ATTACH POINT UNDER HINGE.  REPAIRED.						1	L	7	2 	3T	4	T	RT	A8EA    	E4EA
1998082800205	19980828	00205	NE  	1998	8	28	CA980506004      	2	19980422	G	7321		FCU             			CESSNA	208   	208B        	2073701	CE  	PWA   	PT6   	PT6A114     	52043	NE  					FUEL SYSTEM	FAILED          	W				E				ENGINE SHUTDOWN         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CL	CLIMB          	1			CA			1227 					PC0501			(CAN) DURING CLIMB THROUGH 9,000 FEET, THE ENGINE CEASED OPERATION WITHOUT WARNING, AS IF THE CONDITION LEVER HAD BEEN M	OVED TO THE CUTOFF POSITION.  AN ATTEMPTED RE-LITE WAS UNSUCCESSFUL.  POST-FLIGHT INSPECTION FOUND THE P3 LINE FROM THE 	GAS GENERATOR TO THE P3 FILTER HOUSING TO BE COMPLETELY OBSTRUCTED BY AN UNIDENTIFIED SUBSTANCE.  THE P3 FILTER WAS CLEA	N.  FOLLOWING REPLACEMENT OF THE P3 LINE, THE ENGINE RAN BUT WOULD NOT MAINTAIN TAKEOFF POWER. THE FCU WAS REPLACED AND 	THE ENGINE RAN NORMALLY. THE FCU IS BEING RETURNED FOR INVESTIGATION.  PART TC:  2,324.		1	H	7	1 	3T	3	T		A37CE   	E4EA
1998100900206	19981009	00206	CE  	1998	10	9	CA980506005      	1	19980409	G	2460	A24P170J	WIRE            	RAYTHN      	1293800161  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					DC SYSTEM	MISROUTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			4308 					GGM114452			(CAN) IN REFERENCE TO ELECTRICAL LOAD DISTRIBUTION, DC POWER RIGHT WIRING DIAGRAM MANUAL ATA 24-61-02, WIRE NR A2-4-P170	-J WAS CONNECTED TO TERMINAL NR 5 INSTEAD OF TERMINAL NR 4.  IN THIS SITUATION, THE RIGHT GENERATOR WAS HARD TO COME ON 	LINE AFTER ENGINE START.  THIS OCCURRED ONLY AFTER BATTERY START WITHOUT GROUND POWER.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900207	19981009	00207	CE  	1998	10	9	CA980506006      	1	19980409	G	2497	A24P170J	WIRE            	RAYTHN      	1293800161  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					DC SYSTEM	MISROUTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			4199 					GGM114476			(CAN) IN REFERENCE TO ELECTRICAL LOAD DISTRIBUTION, DC POWER RIGHT WIRING DIAGRAM MANUAL ATA 24-61-02, WIRE NR A2-4P170-	J WAS CONNECTED TO TERMINAL NR 5 INSTEAD OF TERMINAL NR 4.  IN THIS SITUATION, THE RIGHT GENERATOR WAS HARD TO COME ON L	INE AFTER AN ENGINE START.  THIS OCCURRED ONLY AFTER A BATTERY START WITHOUT GROUND POWER.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998091100454	19980911	00454	CE  	1998	9	11	CA980506007      	1	19980409	G	2430	A24P17OJ	WIRE            	RAYTHN      	1293800161  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					DC SYSTEM	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4177 					GGMPS0123			(CAN) IN REFERENCE TO ELECTRICAL LOAD DISTRIBUTION, DC POWER LEFT WIRING DIAGRAM MANUAL ATA 24-61-02, WIRE NR A2-4-P170-	J WAS CONNECTED TO TERMINAL NR 5 INSTEAD OF TERMINAL NR 1.  IN THIS SITUATION, THE LEFT GENERATOR WAS HARD TO COME ON LI	NE AFTER THE ENGINE START. THIS OCCURRED ONLY AFTER BATTERY START WITHOUT GROUND POWER.  PART TC:  4,966.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900208	19981009	00208	CE  	1998	10	9	CA980506008      	1	19980409	G	2497	A24P170J	WIRE            	RAYTHN      	1293800161  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					DC SYSTEM	MISROUTED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			3919 					GGMPS0025			(CAN) IN REFERENCE TO ELECTRICAL LOAD DISTRIBUTION, DC POWER LEFT WIRING DIAGRAM MANUAL ATA 24-61-02, WIRE NR A2-4-P170-	J WAS CONNECTED TO TERMINAL NR 5 INSTEAD OF TERMINAL NR 1.  IN THIS SITUATION THE LEFT GENERATOR WAS HARD TO COME ON LIN	E AFTER ENGINE START.  THIS OCCURRED ONLY AFTER A BATTERY START WITHOUT GROUND POWER.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900209	19981009	00209	SO  	1998	10	9	CA980506010      	1	19980429	G	8120	LW12127	TRANSITION      		LW12127     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					TURBOCHARGER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1427 					RL194661			(CAN) TURBOCHARGED TRANSITION HEADER LOOSING POWER. TRANSITION REMOVED, FOUND CRACKED INSIDE AND HAD BEEN PREVIOUSLY REP	AIRED, WELD LIFTING AND CRACKING.  REPAIRED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998082800207	19980828	00207	SW  	1998	8	28	CA980507001      	1	19980309	G	6220		FRICTION DAMPER 			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CPPS61186			(CAN) BOTH EARS OF ATTACHMENT LUG BROKEN OFF DUE TO CRACKING THROUGH BOLT HOLES.  DAMPER NO LONGER ATTACHED TO AIRFRAME.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998082800208	19980828	00208	SW  	1998	8	28	CA980507002      	1	19980419	G	7312	3020803	FUEL HEATER     			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA				4626 				CPPS62523			(CAN) ENGINE HAD 10 PERCENT - 30 PERCENT TORQUE FLUCTUATION AND FLAMED OUT.  SUSPECTED CAUSE WAS FUEL OIL HEATER, WHICH 	CAUSED EXCESSIVE HIGH FUEL TEMPERATURE AND OCCURRENCE OF CAVITATION. THE FUEL OIL HEATER WAS SENT FOR INVESTIGATION.					1	G	7	1 	4U	4	U	 	H4SW    	E22EA
1998090400021	19980904	00021	CE  	1998	9	4	CA980507003      	1	19980422	G	7820	5000127B3	MUFFLER         	WALLCOLMNY  	5000127B3   	CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1104 			96381		L4570027A			(CAN) TOP INBOARD SEAM CRACKED. THIS SEAM IS VERY HARD TO SEE SINCE IT IS HIDDEN BY THE OVERBOARD EXHAUST STACK AND THE 	OVERLAPPING PLATE.  ONLY TWO .250 INCH HOLES TO INSPECT THIS PORTION OF THE SEAM.  REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998082800209	19980828	00209	WP  	1998	8	28	CA980507004      	1	19980425	G	6220	33003	DAMPER ARM      			HILLER	UH12  	UH12E       	4360122	WP  	ALLSN 	250C  	250C20B     	03013	GL  					MAIN ROTOR	FRACTURED       	W				A				UNSCHED LANDING         				F	D		FLT CONT AFFECTED         	INFLIGHT SEPARATION       		HO	HOVERING       	1			CA								CAE840205			(CAN) A COMPLETE FRACTURE OCCURRED CAUSING THE ARM TO FAIL IN 2 PIECES. THE DAMPER ARM HOLDS A VIBRATION ABSORBING WEIGH	T TO A FLIGHT CONTROL. THE FAILURE OF THE ARM DOES NOT AFFECT CONTROLLABILITY EXCEPT FOR INCREASED CYCLIC CONTROL VIBRAT	ION, HOWEVER, THE LIKELIHOOD OF THE WEIGHT JAMMING THE CONTROL IS HIGH.				1	G	7	1 	3O	3	U		4H11    	E4CE
1998100900210	19981009	00210	CE  	1998	10	9	CA980507005      	1	19980428	G	3230	M710501	MOTOR           		1013800519  	BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					LT MLG	FAILED          	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA				589  							(CAN) LANDING GEAR WOULD NOT EXTEND ON DOWN SELECTION.  LANDING GEAR EXTENDED MANUALLY AND A/C LANDED SAFELY.  MAINTENAN	CE TROUBLESHOOTING REVEALED AN OPEN 60 AMP CIRCUIT BREAKER LOCATED IN THE LT WING.  THIS CB POWERS THE LANDING GEAR MOTO	R.  CIRCUIT BREAKER RESET, LANDING GEAR INSPECTED AND SEVERAL RETRACTION TESTS CARRIED OUT SATISFACTORILY.  ON RETURN TO	 BASE, LANDING GEAR EXTENDED NORMALLY ON SELECTION.  HOWEVER, IT APPEARED THE LANDING GEAR MOTOR WAS LABORING NEAR END O	F THE CYCLE.		2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998082800210	19980828	00210	EU  	1998	8	28	CA980507007      	2	19980424	G	7520	922253	COOLING HOSE    								ROTAX 	912   	ROTAX912    	55555	EU  					COOLING SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1014 					4076163			(CAN) INSPECTION FOUND LEAK FROM CRACKED HOSE WHICH SUPPLIES COOLANT TO NR 1 AND NR 2 CYLINDERS.  HOSE CRACK WAS UNDER A	 CLAMP.  THE LINE/HOSE WAS REPLACED.										3	I			EXPE3I
1998082800211	19980828	00211	GL  	1998	8	28	CA980507008      	3	19980501	G	6111		BLADE           			CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7861 	1107 					DE112		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CORROSION AND STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998082800212	19980828	00212	GL  	1998	8	28	CA980507009      	3	19980430	G	6111	FJC7666A2R	BLADE           			PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2707 	1418 					AU7151		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE FOUND ON LEADING EDGES OF THE PROPELLER BLADES.  DAMAGE	 WAS NOT REPAIRED PER HARTZELL SERVICE INSTRUCTIONS.					1	L	7	2 	3O				A19S0   		5	C	P920
1998082800213	19980828	00213	GL  	1998	8	28	CA980507010      	3	19980430	G	6111	FC7666A2R	BLADE           			PIPER 	PA44  	PA44180     	7104402	SO  						HARTZL	HCC2Y	HCC2YR2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2698 	1418 					AU7140		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECITON.  STONE DAMAGE FOUND ON THE LEADING EDGES OF THE BLADES.  THE DAMAGE W	AS NOT REPAIRED PER HARTZELL SERVICE INSTRUCTIONS.					1	L	7	2 	3O				A19S0   		5	C	P920
1998090900008	19980909	00008	EA  	1998	9	9	CA980507011      	1	19980426	G	6123		WIRE HARNESS    			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP FEATHER	WORN            	W				H				DEACTIVATE SYST/CIRCUITS				R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		TO	TAKEOFF        	1			CA								PCE42112	BU2522		(CAN) PROPELLER WENT INTO FEATHER ON TAKEOFF. CIRCUIT BREAKER PULLED ON BETA SYSTEM PER FLIGHT MANUAL.  POST-FLIGHT INSP	ECTION FOUND WIRE HARNESS RUBBING/CHAFING ON SNOW FENCE ACTUATOR, JUST BELOW THE RT EXHAUST STACK.  WIRE HARNESS REPAIRE	D AND THE AIRCRAFT RETURNED TO SERVICE.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA	6	C	P15EA
1998100900211	19981009	00211	CE  	1998	10	9	CA980507012      	1	19980501	G	5620	50420013471	WINDOW RETAINER 			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					CABIN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			14337					PCE50021			(CAN) WINDOW RETAINERS OF WINDOWS 2 AND 3 IN THE PASSENGER COMPARTMENT WERE FOUND TO BE CORRODED.  THE CORROSION IS DIFF	ICULT TO SEE WHEN THE WINDOW SHADE ASSEMBLY IS INSTALLED BUT OBVIOUS WHEN SHADES ARE REMOVED.  SUBMITTER STATED LEAKING 	SEALS OF THE WINDOW RETAINERS COULD CONTRIBUTE TO SERIOUS FUSELAGE CORROSION.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900212	19981009	00212	SW  	1998	10	9	CA980512002      	1	19980504	G	6510	204040623005	BEARING         		212040600009	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					SEAL FACE	OVERHEATED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1    			A2007687		LEO7194X			(CAN) AFTER 1.2 HOURS TSN, BEARING HOTTER THAN NORMAL.  BEARING ASSY REMOVED.  TEARDOWN REVEALED THE SEAL FACE HAD START	ED TO TURN BLUE.  BEARING ITSELF WAS SMOOTH AND HAD NO ROUGH SPOTS.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1998082800216	19980828	00216	NM  	1998	8	28	CA980512006      	1	19980416	G	2612		WARNING BOX     			BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					FIRE DETECTION	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			CR	CRUISE         	1			CA								653499			(CAN) IN-FLIGHT FIRE BELL SOUNDED, BUT NO FIRE DETECT LIGHTS ILLUMINATED.  CHECK OF ALL THREE ENGINE FIRE DETECTION SYST	EMS FOUND ALL SYSTEMS FAILED THE TEST.  FIREWALL LIGHTS WORKED NORMALLY, APU FIRE TEST INOPERATIVE.  ENGINE FIRE TEST CA	RRIED OUT SERVICEABLE AT LOWER ALTITUDE.  FIRE BELL AURIAL WARNING BOX REMOVED AND CLEANED AND THE FIRE LEADS WERE CHECK	ED SERVICEABLE.  FUNCTION TEST OF THE SYSTEM CARRIED OUT SERVICEABLE.			2	L	7	3 	4F	4	F		A3WE    	E2EA
1998082800217	19980828	00217		1998	8	28	CA980512007      	1	19980420	G	3020	652673833	DUCT            								PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	RUPTURED        	W				A	E	F		UNSCHED LANDING         	ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      		M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA								76235			(CAN) NR 2 ENGINE FIRE LIGHT ILLUMINATED AND FIRE BELL RANG IN-FLIGHT.  THE ENGINE WAS SHUTDOWN AND THE FIRE EXTINGUISHE	R HANDLES PULLED.  POST-FLIGHT INSPECTION FOUND THE 13TH STAGE ANTI-ICE EJECTOR DUCT BLOWN.										4	F			E2EA
1998090900009	19980909	00009	GL  	1998	9	9	CA980512008      	3	19980504	G	6111	A1635112	SCREW           													MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				385  					758037		(CAN) PROPELLER RECEIVED FOR FIVE-YEAR CORROSION INSPECTION.  INSPECTION FOUND THE COUNTERWEIGHT ATTACHMENT SCREWS CORRO	DED.  THE SCREWS WERE REPLACED.															5	C	P45GL
1998082800218	19980828	00218	GL  	1998	8	28	CA980512009      	3	19980506	G	6111	S90AT8	BLADE           			CESSNA	206   	U206F       	2073333	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								247671R	841783		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE LEADING EDGE OF THE PROPELLER BLADES.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA
1998120400018	19981204	00018	EU  	1998	12	4	CA980512010      	1	19980506	G	3230	AN327	BOLT            			PILATS	PC12  	PC12        	7090550	EU  										LT MLG	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA			650  								(CAN) PILOT REPORTED AIR/GROUND ANNUNCIATOR LIGHT.  FOUND BOLT SHEARED THAT HOLDS AXIS PIN FOR TRAILING LINK.  THIS BOLT	 PREVENTS PIN DRIFT AND SECURES AXIS TO ROTATE WITH TRAILING LINK.  TARGET FOR W.O.W. PROXIMITY SWITCH IS MOUNTED ON AXI	S.  SHEARED BOLT ALLOWED TO ROTATE IN TRAILING LINK.  PROXIMITY SWITCH TARGET DID NOT CLEAR SWITCH WHEN GEAR WAS WEIGHT 	OFF WHEELS.  DISAGREEMENT BETWEEN RIGHT AND LEFT SWITCHES TURNS ON ANNUNCIATOR.  PART TC:  489.			1	L	7	1 	3T			RT	A78EU
1998100900213	19981009	00213	CE  	1998	10	9	CA980512011      	1	19980508	G	2720	A11702	BUSHING         		50524402607 	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					RT PEDAL	SEIZED          	W				K				NONE                    				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA				11   				PCE50228			(CAN) AIRCRAFT STEERING FOUND TO BE STIFF AND JERKY.  MAINTENANCE FOUND RT RUDDER PEDAL BUSHING SEIZED TO SHAFT P/N 50-5	24402-7, IPC 27-23-01, PG 4, FIG. 23-01, ITEM 25.  RUDDER PEDAL ASSEMBLY REPLACED WITH OVERHAULED SET.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1998082800219	19980828	00219	SO  	1998	8	28	CA980512012      	1	19980103	G	2910	12035193001	LINE            			EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	RT NACELLE	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10347					115667	880529		(CAN) HYDRAULIC LINES TOUCHING EACH OTHER, LOCATED AT OUTBOARD OF RIGHT HAND ENGINE NACELLE, AT ACCESS PANELS 44ZCR AND 	44ZAR.  WALL THICKNESS OF LINES UNDER LIMITS BECAUSE OF RUBBING.  PART TC:  8,875.					2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998082800227	19980828	00227	EA  	1998	8	28	CA980512022      	1	19980507	G	5740	C3W1037	FITTING         		C3W1006     	DHAV  	DHC3  	DHC3        	2800202	EA  										RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17850								(CAN) ON 400 HOUR INSPECTION, THE RIGHT HAND WING STRUT LUG FITTING STRUT TO FUSELAGE WAS FOUND CRACKED ON THE INSIDE RA	DIUS.					1	H	7	1 	3R				A815
1998120400019	19981204	00019	WP  	1998	12	4	CA980512023      	2	19980416	G	7200		ENGINE          			GULSTM	690TP 	690D        	3970405	SW  	GARRTT	TPE331	TPE3315     	01514	WP  	ROTOL	R306	R306382F7   	GL  	ENGINE BAY	NOISY           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P40493	106738		(CAN) DURING DAILY INSPECTION, MAINTENANCE FOUND A SCRAPPING SOUND IN THE ENGINE WHEN TURNING THE PROPELLER BY HAND.  SU	BMITTER SUSPECTS HOT SECTION PROBLEM.					1	H	7	2 	3T	4	T		2A4     	E4WE	6	C	P8EU
1999061800001	19990618	00001	SW  	1999	6	18	CA980512024      	1	19980501	G	5610	3600431155	WINDSHIELD      	PPG         		GULSTM	690TP 	690D        	3970405	SW  						ROTOL	R306	R306382F7   	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1247 			9612H6893			106738		(CAN) WINDSHIELD OUTER GLASS FOUND CRACKED CLOSE TO HEATING ELEMENT.						1	H	7	2 	3T				2A4     		6	C	P8EU
1998082800234	19980828	00234	NE  	1998	8	28	CA980512031      	2	19980501	G	7250	311260201	BLADE           			AEROSP	ATR42 	ATR42*      	8680900	EU  	PWA   	PW121 	PW121       	52124	NE  					TURBINE	FRACTURED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18939	2964 				120561			(CAN) THE TURBOMACHINE WAS SENT FOR INSPECTION AFTER THE OPERATOR REPORTED AN LP TURBINE BLADE FAILURE AND HIGH OIL CONS	UMPTION.  INVESTIGATION FOUND THE LP TURBINE BLADE FAILURE WAS A RESULT IN A VOID WHICH ORIGINATED IN THE BASE BLADE MAT	ERIAL. THE HIGH OIL CONSUMPTION APPEARS TO BE A RESULT OF AN OIL LEAK RELATED TO POOR OIL AND AIR SEAL CONDITIONS IN THE	 NR 5 BEARING AND HP TURBINE AREAS.   PART TC:  18,836.			2	H	7	2 	4T	4	T	RT	A53EU   	E20NE
1998100900214	19981009	00214	SO  	1998	10	9	CA980513001      	1	19980501	G	7603	455360	CABLE           			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	THROTTLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2299 					L563861A	DK1311		(CAN) THROTTLE CABLE BROKE DURING FINAL INSPECTION CHECK.  CABLE BROKE INSIDE HOUSING CLOSE TO SWAGED END UNDER CLAMP. C	ABLE FLEXED AT THAT POINT.  REPLACED.					1	L	7	1 	3O	3	O		A3SO    	E14EA	5	C	P9EA
1998100900215	19981009	00215	SW  	1998	10	9	CA980513002      	1	19980505	G	7100	5218SS1537	CLAMP           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					BASE OF T-BOLT	CRACKED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE07531			(CAN) CLAMP CRACKED AT BASE OF T-BOLT HEAD BAND.						1	G	7	1 	4U	4	U		H1SW    	E17EA
1998082800235	19980828	00235	NE  	1998	8	28	CA980513003      	2	19980505	G	7240	11502403	MOUNT           			BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					TURBINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LE07531			(CAN) DURING INSPECTION OF THE DIFFUSER, THERE WERE CRACKS FOUND IN THE STRUTS.						1	G	7	1 	4U	4	U		H1SW    	E17EA
1998082800236	19980828	00236	EA  	1998	8	28	CA980513004      	2	19980513	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28151     	7102805	SO  	LYC   	O320  	O320E3D     	41508	EA  					NR 3 CYLINDER	FRACTURED       	W				A				UNSCHED LANDING         				O			OTHER                     			LD	LANDING        	1			CA			1466 					L4560627A			(CAN) AFTER A FORCED LANDING, INSPECTION FOUND THE NR 3 CYLINDER EXHAUST VALVE BROKEN IN THE AREA OF THE FILLET.						1	L	7	1 	3O	3	O		2A13    	E274
1998082800238	19980828	00238	SO  	1998	8	28	CA980513006      	2	19980415	G	8520	70328501	CAMSHAFT        			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					NR 4 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			98   					258168R			(CAN) DURING INSPECTION, METAL PARTICLES WERE FOUND IN THE OIL.  FURTHER INVESTIGATION FOUND NR 4 CAM LOBE WORN AND PITT	ED.					1	H	7	1 	3O	3	O		3A19    	E252
1998082800239	19980828	00239	EA  	1998	8	28	CA980513007      	2	19980403	G	7414	S6LN204	DIST BLOCK      			PIPER 	PA32  	PA32260     	7103206	SO  	LYC   	O540  	O540E4B5    	41532	EA  					ENGINE MAGNETO	CRACKED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA						L679740		L679740			(CAN) AFTER MAGNETO FAILURE, THE FOLLOWING DEFECTS WERE FOUND.  THE DISTRIBUTOR BLOCK WAS CRACKED AND THERE WERE TEETH M	ISSING FROM THE DISTRIBUTOR GEAR.					1	L	7	1 	3O	3	O		A3SO    	E295
1998100900216	19981009	00216	CE  	1998	10	9	CA980513008      	1	19980425	G	2730	115610010325	TORQUE TUBE     		115610010344	BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5412 								(CAN) CRACK FOUND ON ELEVATOR TORQUE TUBE ASSEMBLY BRACKET FLANGE WHERE IT IS FASTENED TO RIB THROUGH SKIN ON LOWER SECT	ION OF RT ELEVATOR.					1	L	7	2 	4T	4	T		A14CE   	E2WE
1998090400022	19980904	00022	CE  	1998	9	4	CA980513009      	1	19980506	G	3310	S18802	RHEOSTAT        			CESSNA	172   	172H        	2072424	CE  	CONT  	O300  	O300C       	17022	SO  					CABIN	DEFECTIVE       	W				O				OTHER                   				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			203  					32444D6C			(CAN) ON ANNUAL INSPECTION, AD CHECK INDICATED THAT AD 93-24-05 OR SB SEB-92-33R1 HAD NOT BEEN CARRIED OUT, REPLACEMENT 	OF LIGHT RHEOSTAT DUE TO POSSIBLE FIRE.  REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E253
1998100900217	19981009	00217	SO  	1998	10	9	CA980513010      	1	19980507	G	3340	16381	LIGHT           			PIPER 	PA31  	PA31350     	7103110	SO  										STROBE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				L			NO TEST                   			TX	TAXI/GRND HDL  	1			CA			10958								(CAN) ANTI-COLLISION LIGHT FAILED.  PINS CORRODED AND ONE FALLING OUT.  REPAIRED.						1	L	7	2 	3O				A20SO
1998100900218	19981009	00218	CE  	1998	10	9	CA980513011      	1	19980409	G	3250		TUBE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3685 					GGMPS0054			(CAN) NOSE LANDING STEERING TUBE CHAFED NEXT TO RIVETS.  THE DAMAGE WAS AT THE FRONT AND REAR OF RIVETS THAT HOLD THE RO	D END.  CHAFED AREA WAS TO A DEPTH OF 0.015 THOUSANDS OF AN INCH.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900219	19981009	00219	CE  	1998	10	9	CA980513012      	1	19980409	G	3340	1143641373	BRACKET         		MS274321    	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4318 					GGM114452			(CAN) THE TAXI LIGHT HOUSING IS RETAINED TO A BRACKET P/N 114-364137-3 BY A RIVET.  THE RIVET HAD SHEARED AND THE LIGHT 	ASSEMBLY WAS HANGING BY THE ELECTRICAL WIRES.  SUBMITTER STATED THIS SITUATION COULD AFFECT THE OPERATION OF THE NOSE GE	AR.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998082800243	19980828	00243	SO  	1998	8	28	CA980519002      	2	19980504	G	8530		COVER           			CESSNA	206   	206CESSNA   	2073302	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	D2A34C58    	GL  	NR 5 CYLINDER	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			1252 					570943	771604		(CAN) ENGINE OIL LEAK.  INSPECTION FOUND NR 5 CYLINDER PUSH ROD COVER CRACKED AT BEAD.  PUSH ROD COVER REPLACED.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA
1998100900220	19981009	00220	SW  	1998	10	9	CA980519003      	1	19980503	G	6321	D01521	BOLT            	PRECISION   	206340301103	BELL  	407   	407         		SW  										M/R BRAKE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			138  			378380					(CAN) STEP WORN INTO BOLT FROM ROTOR BRAKE PADS AT .700 INCH AND 1.760 INCHES FROM BOLT HEAD.  WEAR APPEARS TO COME FROM	 CHATTERING OF THE PADS IN THE RETRACTED POSITION.  DUE TO ACCELERATED WEAR, BOLTS WILL BE REPLACED ON A 100 HOUR BASIS.					1	G	7	1 	3U			O	H2SW
1998082800244	19980828	00244	SW  	1998	8	28	CA980519004      	1	19980505	G	2710	2771003003	PUSHROD         			SWRNGN	SA226 	SA226AT     	8780405	SW  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6955 								(CAN) AILERON PUSH ROD AT SWAGED END FOUND CRACKED.						2	L	7	2 	4T			RT	A5SW
1998082800245	19980828	00245	SO  	1998	8	28	CA980519005      	2	19980205	G	8530		VALVE           			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  	MCAULY	3AF34C	3AF34C92    	GL  	ENGINE	BROKEN          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				891  				600100	779641		(CAN) ENGINE SHUTDOWN IN CRUISE AND THE AIRCRAFT MADE AN UNSCHEDULED LANDING, AFTER THE ENGINE EXPERIENCED ROUGH RUNNING	.  POST-FLIGHT INSPECTION FOUND AN EXHAUST VALVE WITH THE HEAD DETACHED/FRACTURED.  THE PISTON AND CYLINDER WERE DESTROY	ED AND THE OIL PAN WAS DAMAGED. THE ENGINE WAS REPLACED FORWARD OF THE FIREWALL.				1	L	7	2 	3O	3	O	 	A7CE    	E7CE	5	C	P22EA
1998082800246	19980828	00246	SO  	1998	8	28	CA980519007      	2	19980509	G	8530	653447A2	CYLINDERS       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O550  	IO550*      		SO  	MCAULY	D3A34	D3A34C401   	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			480  					5284513R	921317		(CAN) ALL ENGINE CYLINDERS WERE REPLACED DUE TO WEAR.  THE ENGINE WAS EXPERIENCING HIGH OIL CONSUMPTION.  THE SUBMITTER 	STATES THIS IS THE SECOND TIME THE CYLINDERS HAVE HAD TO BE REPLACED IN 1,025 HOURS AND SUGGESTS THAT THE USE OF 15W50, 	ALONG WITH THE SHORT DURATIONS OF FLIGHTS (5 MINUTES), AS A CONTRIBUTING FACTOR.				1	H	7	1 	3O	3	O		3A24    	E3SO	5	C	P47GL
1998100900222	19981009	00222	CE  	1998	10	9	CA980519008      	1	19980505	G	2750	55651754CR	CONTROL CABLE   			CESSNA	500   	500CESSNA   	2076602	CE  										COCKPIT	BROKEN          	W				O				OTHER                   				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			700  								(CAN) FLAP PRE-SELECT CABLE BROKE IN AREA TWO INCHES BACK FROM THE CRIMP ON BALL.  LOCATED IN THE COCKPIT AREA.  CABLE I	S CHANGED EVERY PHASE 5 INSPECTION.  PART TC:  700.					1	L	7	2 	4F			 	A22CE
1998082800247	19980828	00247	GL  	1998	8	28	CA980519010      	3	19980504	G	6111	G82PCA6	BLADE           			CESSNA	177   	177B        	2073708	CE  						MCAULY	2D34C	B2D34C211   	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2504 	971  					774931		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE LEADING EDGES OF THE PROPELLER BLADES WERE FOUND NICKED.  THE BLA	DES HAD NOT BEEN REPAIRED PER THE MCCAULEY MANUAL.					1	H	7	1 	3O				A13CE   		5	C	P7EA
1998082800248	19980828	00248	GL  	1998	8	28	CA980519011      	3	19980511	G	6114		HUB             			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	LACK OF LUBE    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1094 	807  				L1224851A	CH10658		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND THE PROPELLER HUB REAR BORE TO BE OVERSIZE.  THE CO	NTROL FORK TO BE OVERSIZE. THE PISTON TO BE UNDERSIZE.  THESE CONDITIONS ARE A RESULT OF LACK OF LUBRICATION. THE HUB HA	D NOT BEEN GREASED.				1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P920
1998082800251	19980828	00251	GL  	1998	8	28	CA980519015      	3	19980512	G	6114	C3903	RETAINER        													MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			385  						758179		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THE PROPELLER WAS DISMANTLED AND THE SPLIT RETAINER RADIUS WAS FOUND	 PITTED AND CORRODED. THE RETAINER WAS REPLACED.															5	C	P45GL
1998082800252	19980828	00252	GL  	1998	8	28	CA980519016      	3	19980512	G	6114	C3411	BEARING         													MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			385  						758179		(CAN) PROPELLER RECEIVED FOR FIVE YEAR CORROSION INSPECTION.  PROPELLER WAS DISMANTLED AND THE PROPELLER BEARING RACES W	ERE FOUND PITTED AND CORRODED.  ALL THREE BEARINGS WERE REPLACED.															5	C	P45GL
1998082800253	19980828	00253	GL  	1998	8	28	CA980519017      	3	19980512	G	6111	S90AT2	BLADE           			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C66     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1177 	99   					766378		(CAN) PROPELLER RECEIVED FOR FIVE YEAR CORROSION INSPECTION.  WHEN THE PAINT WAS REMOVED FROM THE PROPELLER BLADES THERE	 WAS VISIBLE CORROSION ON THE CAMBER FACE OF THE BLADES.  THE CORROSION WAS GROUND OUT AND THE BLADES WERE RETURNED TO S	ERVICE.				1	H	7	1 	3O			NC	5A6     		5	C	P3EA
1998082800254	19980828	00254	CE  	1998	8	28	CA980519018      	1	19980430	G	2612	24409015	FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								GGMPS0025			(CAN) DURING THE ENGINE GROUND RUN, A TEST OF THE ENGINE FIRE DETECTION SYSTEM REVEALED THE SYSTEM WAS NOT FUNCITONING. 	 INSPECTION FOUND THE FIRE DETECTION LOOP HAD BROKEN AT THE ENGINE FIREWALL.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998082800255	19980828	00255	CE  	1998	8	28	CA980519019      	1	19980505	G	2612	24409015	FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	SEVERED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			N			FALSE WARNING             			CR	CRUISE         	1			CA			4382 					GGMPS0123			(CAN) FREQUENT INTERMITTENT FIRE WARNING/INDICATION FROM RIGHT ENGINE. PRECAUTIONARY ENGINE SHUTDOWN CARRIED OUT. INVEST	IGATION FOUND THE FIRE LOOP WAS CUT TWO INCHES FROM THE FIREWALL JUST ABOVE THE IGNITION BOX.  PART TC:  4,382.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900223	19981009	00223	SO  	1998	10	9	CA980519020      	1	19980501	G	3244	6501010TT	TIRE            			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA											(CAN) RIGHT MAIN TIRE BLEW ON TAKEOFF.  REPLACED.						1	L	7	2 	3O				A20SO
1998091100455	19980911	00455	CE  	1998	9	11	CA980519021      	1	19980503	G	2810	10138901131	VALVE           		993800007   	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					FUEL SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE80138			(CAN) NACELLE FUEL CELL OVERPRESSURIZED DUE TO FAILURE OF CHECK VALVE CAUSING STRUCTURAL DAMAGE TO THE WHEEL WELL.  CHEC	K VALVE REPLACED AND A/C FLOWN FOR 60 HOURS WITH NO SIGNS OF FURTHER DAMAGE.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998082800256	19980828	00256	SO  	1998	8	28	CA980519022      	1	19980506	G	7120	3512220	MOUNT           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					ENGINE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L4104327A			(CAN) DURING INSPECTION THE EXHAUST TAIL PIPE SUPPORT BRACKET WAS FOUND CHAFING INTO THE LOWER RIGHT HORIZONTAL ENGINE M	OUNT SUPPORT WEARING A HOLE IN STRUCTURE.					1	L	7	1 	3O	3	O		2A13    	E274
1998100900224	19981009	00224	SO  	1998	10	9	CA980519023      	1	19980506	G	2434	P2C	TERMINAL        			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ALTERNATOR	BROKEN          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA								L2847827A			(CAN) DURING FLIGHT, THE TRANSPONDER AND THE RADIO BECAME WEAK.  AMP TERMINAL AT THE ALTERNATOR STUD BROKEN.  REPLACED.						1	L	7	1 	3O	3	O		2A13    	E274
1998100900226	19981009	00226	CE  	1998	10	9	CA980521002      	1	19980304	G	3040	662591	SOCKET          	AMP         	662591      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					WINDSHIELD	FAILED          	W				K				NONE                    				L			NO TEST                   			CR	CRUISE         	1			CA			8030 					PCE81547			(CAN) PILOT HEAT REPORTED AS INTERMITTENT.  MAINTENANCE CHECK CONFIRMED WHEN WINDSHIELD HEAT SELECTED TO NORMAL OR HIGH,	 VOLTAGE DROPPED OFF TO ZERO VOLTS.  FURTHER INVESTIGATION REVEALED THAT CONTACT SOCKET P/N 66259-1, 1C, IN J195 DC.  PO	WER CONNECTOR WAS OVERHEATED AND LOST CONTACT ON MATING PIN.  REPLACEMENT SOCKET HAS A DIFFERENT P/N (66741-8) AND HAS A	 SPRING ACROSS IT TO IMPROVE GRIP STRENGTH.  CONTACT 2C, COPILOT'S WINDSHIELD HEAT ALSO REPLACED FOR SAME REASON.  IT WA	S NOTED J195 D.C. POWER CONNECTOR IS LOCATED UNDER FLOOR NEAR COFFEE AND WATER CONTAINERS AND THERE WAS EVIDENCE OF COFF	EE SPILL.	1	L	7	2 	4T	4	T		A24CE   	E4EA
1998100900227	19981009	00227	SO  	1998	10	9	CA980521003      	1	19980320	G	2820	MIL48794	HOSE            			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYSTEM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, FOUND HOSE HAD HAD LIGHTNING STRIKE IN PAST.  EXITED AT ENDS, AND MATERIAL DAMAGED.  REPLACED.						1	L	7	2 	3O				A20SO
1998082800258	19980828	00258	NM  	1998	8	28	CA980521005      	1	19980509	G	3260	327	BULB            			BOEING	727   	72725       	1384006	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					RT MLG	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA								656107			(CAN) WHEN LANDING GEAR SELECTED DOWN, RT MLG DOWN INDICATOR FAILED TO LIGHT.  MISSED APPROACH PROCEDURE CARRIED OUT.  I	NDICATOR RELAMPED AND SYSTEM INDICATION TESTED NORMAL.  NORMAL LANDING CARRIED OUT.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1998100900228	19981009	00228	SW  	1998	10	9	CA980521006      	1	19980509	G	6320	212040054001	SUPPORT         		20504000145 	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					M/R GEARBOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				558  		B12964		LE07560A			(CAN) CRACK FOUND ON ONE OF THE EARS WHICH MOUNTS THE LIFT LINK ASSY.  CRACKED FROM BOLT HOLE TO EDGE.						1	G	7	1 	4U	4	U		H1SW    	E17EA
1998100900229	19981009	00229		1998	10	9	CA980521007      	1	19980512	G	6310	4141196P016	DRIVE SHAFT     	GE          	2CM9ABH7    															TRANSMISSION	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						V23448					(CAN) UNAPPROVED DRIVE SHAFT, REPLACED.
1998100900230	19981009	00230	SW  	1998	10	9	CA980521008      	1	19980512	G	3411	206070547001	TUBING          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					PITOT SYSTEM	MELTED          	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								CAE820721			(CAN) AIR SPEED INDICATOR SHOWING ONLY 20 KNOTS AT CRUISE.  PITOT HEAD TUBING HAD BEEN INSTALLED TOO CLOSE TO LANDING LI	GHT AND MELTED CAUSING LEAK.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998120400020	19981204	00020	GL  	1998	12	4	CA980521011      	2	19980303	G	7250		BLADE           			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			2000 					CAE830691			(CAN) TURBINE DAMAGE DUE TO CARBON ACCUMULATION ON COMBUSTION LINER NEAR NOZZLE AND IGNITER.  SUBMITTER SAYS PROBLEM CAU	SED BY COMBUSTION LINE PROBLEM WHICH IS CORRECTED BY CEB 1299.  PART TC:  2,028.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998090400023	19980904	00023	CE  	1998	9	4	CA980521012      	1	19980504	G	2731	0400107130	CONTROL CABLE   			CESSNA	150   	152         	2071835	CE  										ELEVATOR TAB	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11232								(CAN) ON INSPECTION, THE LOWER ELEVATOR TRIM CABLE FOUND BADLY CORRODED.  WHEN PULLED ON, IT BROKE.  REPLACED.						1	H	7	1 	3O			NT	3A19
1998100900231	19981009	00231	CE  	1998	10	9	CA980525001      	1	19980512	G	3213	65414281	OLEO            			CESSNA	500   	550         	2076604	CE  										MLG	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			404  								(CAN) RIGHT HAND OLEO ASSY COLLAPSED WHILE AIRCRAFT WAS IN THE HANGAR FOR MAINTENANCE.  PART TC:  562.						1	L	7	2 	4F				A22CE
1998082800260	19980828	00260	NM  	1998	8	28	CA980525002      	1	19980416	G	5344	AE2321100200	HINGE           			BOEING	727   	72782       	1384029	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					CARGO DOOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4185 					649672			(CAN) MAIN CARGO DOOR UPPER AFT HINGE BROKEN AT 7 SEGMENTS, REPLACED.  PART TC:  3,211.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1998090900010	19980909	00010	NE  	1998	9	9	CA980525003      	2	19980417	G	7397	W28600218	WIRE            			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8*        	52044	NE  					FUEL NOZZLE	MISINSTALLED    	W				J				DUMP FUEL               				W			INADEQUATE Q C            			DE	DESCENT        	1			CA											(CAN) RIGHT HAND FUEL NOZZLE INTRANSIT LIGHT ON WITH SWITCH CLOSED.  AFTER DUMPING FUEL, FOUND CLOSED POWER WIRE W286-00	2-18 CROSS CONNECTED WITH SPARE WIRE W286-005-18.  WIRE RECONNECTED PER WDM 28-31-01 NOZZLE VALVE.  CHECKED SERVICEABLE.					2	L	7	3 	4F	4	F	 	A3WE    	E2EA
1998082800261	19980828	00261	GL  	1998	8	28	CA980525004      	3	19980513	G	6111		BLADE           			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2614 				33824D5D	E3630		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  BLADE WAS FOUND WITH STONE DAMAGE.  THE BLADE WAS TRIMMED.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
1998082800262	19980828	00262	NE  	1998	8	28	CA980525005      	3	19980514	G	6114	70096	BEARING         			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	PROPELLER	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				617  				4218644	T16032		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE BEARING RACES WERE FOUND PITTED.						1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
1998082800263	19980828	00263	GL  	1998	8	28	CA980525006      	3	19980515	G	6111	76634	BLADE           													HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	MISOVERHAULED   	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									BG2140		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADES HAD BEEN REPAIRED IN THE FIELD AND THE BLADE WIDTHS	 WERE REDUCED BELOW MINIMUM WIDTHS PER HARTZELL MAINTENANCE MANUAL.															5	C	P9EA
1998082800265	19980828	00265	GL  	1998	8	28	CA980525008      	3	19980525	G	6111	G82NDB2	BLADE           													MCAULY	3A32C	3A32C406    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			239  						940109		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE NOT DRESSED OUT PROPERLY.																5	C	P21EA
1998082800266	19980828	00266	EA  	1998	8	28	CA980525009      	1	19980512	G	5744	C3TF155	HINGE           		C3TP1181    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION OF LEFT ELEVATOR OUTBOARD HINGE PIN BRACKET, A LIGHT BLACK STAIN WAS NOTED ALONG THE INBOARD EDG	E.  BORESCOPE INSPECTION OF INTERNAL STRUCTURE FOUND THAT TWO RIVETS THAT ATTACH THE FITTING TO THE REAR SPAR WERE LOOSE	.				1	H	7	1 	3R	3	R		A815    	5E2
1998100900232	19981009	00232	CE  	1998	10	9	CA980525010      	1	19980514	G	7603		CABLE           		5038901215  	BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					THROTTLE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			543  					297689R			(CAN) THROTTLE CABLE BROKEN AT ENGINE CONTROL END.  CABLE REPLACED.						1	L	7	2 	3O	3	O	RT	3A16    	3E1
1998120400021	19981204	00021	NE  	1998	12	4	CA980525011      	2	19980517	G	7310		LINE            			SNIAS 	350   	AS350BA     	8680817	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					FUEL SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1971 					4488			(CAN) SMALL AMOUNT OF FUEL FOUND ON ENGINE DECK.  FUEL LEAK CAME FROM FUEL LINE GOING TO LEFT INJECTOR.  FLARED END OF L	INE ON INJECTOR SIDE WAS CRACKED APPROXIMATELY 180 DEGREES.  CRACK COULD ONLY BE SEEN WITH MAGNIFYING GLASS.  PART TC: 2	,564.				1	G	7	1 	3U	3	U	NC	H9EU    	E19EU
1998082800267	19980828	00267	EA  	1998	8	28	CA980526001      	1	19980511	G	2720	6AO2059	CLEVIS          	WIPLINEINC  	6100        	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			360  			61285		13496			(CAN) ALL THREE FLYING WIRES ATTACHED TO CLEVIS AT THE FUSELAGE WERE FOUND CRACKED DURING INSPECTION.   CAUSE OF CRACKS 	TO BE DETERMINED.					1	H	7	1 	3R	3	R		A806    	5E1
1998100900233	19981009	00233	SO  	1998	10	9	CA980526004      	1	19980514	G	5751	6755001	SUPPORT         			PIPER 	PA28  	PA28R200    	7102811	SO  	LYC   	O360  	IO360C1C    	41514	EA  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2405 					L1992351A			(CAN) BOTH LT AND RT LOWER AILERON BELLCRANKS BADLY DAMAGED WHERE THEY ARE BOLTED TO THE RIB.  REPAIRED.						1	L	7	1 	3O	3	O		2A13    	1E10
1998120400022	19981204	00022	SW  	1998	12	4	CA980529001      	1	19980509	G	2913	206076030003	PUMP            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					HYDRAULIC SYS	NOISY           	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		NR	NOT REPORTED   	1			CA						AV1802888		CAE890139			(CAN) PILOT REPORTED A MINOR WEEP AND TICKING NOISE FROM HYDRAULIC PUMP.  WHEN HELICOPTER SHUT DOWN THE RETURN LINE FILT	ER BYPASS TELL-TAIL WAS POPPED.  IT WAS RESET AND AIRCRAFT STARTED, RAN AGAIN WITH SAME RESULT.   BRASS FOUND IN HYDRAUL	IC FLUID ORIGINATING FROM PUMP.				1	G	7	1 	3U	3	U		H2SW    	E1GL
1998082800268	19980828	00268	CE  	1998	8	28	CA980529002      	1	19980317	G	7810	515515612	EXHAUST STACK   			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					ENGINE	DAMAGED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			4907 					267167R			(CAN) EXHAUST BLEW OUT THE BOTTOM OF THE EXHAUST STACK (PIPE).						1	L	7	2 	3O	3	O		A7CE    	E7CE
1998100900234	19981009	00234	SO  	1998	10	9	CA980529003      	1	19980520	G	5280	47529032	HINGE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4818 					L47861A			(CAN) LANDING GEAR DOOR HINGE BRACKET CRACKED IN INNER RADIUS.  REPLACED.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998090400024	19980904	00024	CE  	1998	9	4	CA980529004      	1	19980225	G	3231	504500110	CRANK           			CESSNA	421   	421B        	2076014	CE  	CONT  	O520  	GTSIO520H   	17032	SO  					RT MLG	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			4907 					267167R			(CAN) RIGHT MLG DOOR WOULD NOT CLOSE - FOUND CRANK ASSY BROKEN AT WELD WHERE SHAFT MEETS ARM.  REPLACED.						1	L	7	2 	3O	3	O		A7CE    	E7CE
1998082800269	19980828	00269	EU  	1998	8	28	CA980529005      	1	19980504	G	3234		SELECTOR        			BRAERO	748   	HS7482B     	1500248	EU  										COCKPIT	STICKING        	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON GEAR DOWN, SELECTION HANDLE DID NOT GO ALL THE WAY DOWN, SELECTOR RECYCLED AND OPERATED PROPERLY.  SYSTEM CHECK	ED, LUBED, TESTED AND NO FAULT FOUND.   PROBLEM OCCURRED AGAIN.  TELEFLEX CABLE REPLACED, TESTED OK, OCCURRED AGAIN AND 	SELECTOR REPLACED SB 32-65 REFERS TO PROBLEM WITH SELECTOR VALVE SEIZING.				2	L	7	2 	3T				A24EU
1998082800270	19980828	00270	EU  	1998	8	28	CA980529006      	2	19980514	G	7260	602070001	SHAFT           			BRAERO	748   	HS7482B     	1500248	EU  	RROYCE	DART  	DART5342    		EU  					GEARBOX	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1232 				7149			(CAN) GENERATOR WOULD NOT COME ON LINE.  INSPECTION FOUND THE GENERATOR DRIVE (FEMALE) IN THE ACCESSORY GEARBOX NOT TURN	ING.  GEARBOX REMOVED FOR REPAIR.					2	L	7	2 	3T	4	T		A24EU   	A196
1998100900235	19981009	00235	CE  	1998	10	9	CA980529007      	1	19980513	G	5610	1013840258	WINDSHIELD      			BEECH 	B300  	B300        	1159232	CE  	PWA   	PT6   	PT6A60A     	52043	NE  					COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			992  								(CAN) DURING CRUISE AT ALTITUDE OF 35,000 FEET, A CRACK WAS NOTICED IN THE UPPER LEFT CORNER OF THE RIGHT HAND WINDSHIEL	D.  POH PROCEDURES CARRIED OUT, AIRCRAFT LANDED SAFELY.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998100900236	19981009	00236	CE  	1998	10	9	CA980529008      	1	19980519	G	3230	3581512543	ROD             			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					RT MLG	BENT            	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA								CS192942R			(CAN) RIGHT HAND GEAR COLLAPSED AFTER LANDING.  SUBSEQUENT MAINTENANCE CHECK REVEALED THAT THE RIGHT HAND RETRACT ROD WA	S BENT AT THE ACTUATOR END.  POSSIBLE CAUSE FOR THE BENT ROD WAS DUE TO THE RT UPLOCK FAILING TO RELEASE CAUSING THE ROD	 TO BEND AS THE RETRACT MECHANISM WAS MOVING TO THE EXTENDED POSITION.  THE UPLOCK HAD TO EVENTUALLY RELEASE AS THE GEAR	 WAS NOT FOUND IN THE UP AND LOCKED POSITION.  THE RETRACT ROD WAS REPLACED.			1	L	7	2 	3O	3	O	RT	3A16    	3E1
1998100900237	19981009	00237	CE  	1998	10	9	CA980529009      	1	19980514	G	5341		BOLT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					BS 190	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16083					PCE50047			(CAN) DURING THE HIGH CYCLE FUSELAGE INSPECTION, A SHEARED BOLT WAS FOUND INSIDE THE FUSELAGE IN THE AREA OF STA 190 RIG	HT SIDE WHERE THE FORWARD SPAR PASSES THROUGH THE FUSELAGE.  SUBMITTER STATED AS THIS ITEM IS IMPORTANT TO THE STRUCTURA	L INTEGRITY OF THE AIRCRAFT, BEECH WAS REQUESTED TO REPLACE THE BOLT.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998082800271	19980828	00271	EU  	1998	8	28	CA980529010      	2	19980514	G	7322	2075000200	SUPPORT         								ROTAX 	912   	ROTAX912    	55555	EU  					CARBURETOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4412707			(CAN) BOTH AIRBOX SUPPORTS FOR THE CARBURETOR FUEL PAN CATCHERS WERE FOUND CRACKED.											3	I			EXPE3I
1998090400025	19980904	00025		1998	9	4	CA980529011      	1	19980522	G	7120	785000	MOUNT           								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	DETERIORATED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4412608			(CAN) ENGINE MOUNT DRIED OUT AND CRACKED DUE TO HEAT FROM EXHAUST.  REPLACED.											3	I			EXPE3I
1998090400026	19980904	00026	CE  	1998	9	4	CA980529012      	1	19980408	G	2424	C611010102R	REGULATOR       			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	AC SYSTEM	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			672  						727629		(CAN) ELECTRICAL FAILURE.  REPLACED.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998082800273	19980828	00273	EA  	1998	8	28	CA980529014      	1	19980525	G	2824	13216250	VALVE           		C6PF1001    	DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					NR 4 FUEL CELL	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			22960			2605		PCE41110			(CAN) LEVEL-CONTROL VALVE FOUND LYING IN THE BOTTOM OF THE NR FOUR FUEL CELL.  THERE WAS A LOT OF PHYSICAL DAMAGE INDICA	TING THAT VALVE HAD BEEN LOOSE FOR SOME TIME.					1	H	7	2 	3T	4	T		A9EA    	E4EA
1998091100456	19980911	00456	CE  	1998	9	11	CA980529015      	1	19980519	G	3230	1153800025	MOTOR           			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	INTERMITTENT    	W				O				OTHER                   				J			WARNING INDICATION        			DE	DESCENT        	1			CA				3712 				PCE51811	BU4989		(CAN) LANDING GEAR FAILED TO EXTEND ON SELECTION.  GEAR EXTENDED MANUALLY AND SAFELANDING CARRIED OUT.  TEST OF LANDING 	GEAR SYSTEM INDICATED SLOW LDG MOTOR OPERATION.  FURTHER CHECKS ON MOTOR INDICATED NORMAL WEAR ON BRUSHES AND ARMATURE A	ND HALF LIFE REMAINING.  MOTOR REPLACED.   PART TC:  8,060.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
1998082800274	19980828	00274	SW  	1998	8	28	CA980529016      	1	19980518	G	2730	2744062005	CONTROL CABLE   		2744046053  	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P44424C	DRG57282		(CAN) DURING INSPECTION, A BROKEN STRAND OF WIRE WAS FOUND ON THE ELEVATOR DOWNSPRING CABLE.  WHEN CABLE WAS REMOVED, OT	HER AREAS WERE FOUND BROKEN.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
1998091100457	19980911	00457	CE  	1998	9	11	CA980529017      	1	19980511	G	3230	5082022116	CAM             		5082017928  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					NLG	BROKEN          	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								PCE80138			(CAN) WHILE CARRYING OUT LANDING GEAR RETRACTION TESTS WITH THE NOSE GEAR DOORS  DISCONNECTED AS PER THE MAINTENANCE MAN	UAL, THE CLEVIS FOR THE GEAR DOORS WAS ACCIDENTALLY ROTATED TO THE HORIZONTAL POSITION. WHEN THE LANDI NG GEAR WAS RETRA	CTED IT CAUGHT THE CLE,VIS CAUSING THE CAM TO BREAK.				1	L	7	2 	4T	4	T		A24CE   	E4EA
1998082800275	19980828	00275	EA  	1998	8	28	CA980529018      	1	19980511	G	2797	6A02056001	WIRE            	WIPLINEINC  	6100        	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			360  			61285		13496			(CAN) ALL THREE FLYING WIRES ATTACHED TO CLEVIS AT THE FUSELAGE WERE FOUND CRACKED DURING INSPECTION.  CAUSE TO BE DETER	MINED.					1	H	7	1 	3R	3	R	 	A806    	5E1
1998082800276	19980828	00276	EA  	1998	8	28	CA980529019      	1	19980511	G	2797	6A02056003	WIRE            	WIPLINEINC  	6100        	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			360  			61285		13496			(CAN) ALL THREE FLYING WIRES ATTACHED TO  CLEVIS AT THE FUSELAGE WERE FOUND CRACKED.  CAUSE TO BE DETERMINED.						1	H	7	1 	3R	3	R	 	A806    	5E1
1998120400023	19981204	00023	CE  	1998	12	4	CA980602013      	1	19980512	G	7920	035A470105	LINE            			MTSBSI	MU2   	MU2B35      	5780411	CE  	GARRTT	TPE331	TPE3316     	01514	WP  					OIL SYSTEM	CRACKED         	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			AP	APPROACH       	1			CA								P27223C			(CAN) ON SHORT FINAL, WHILE DOING PRE-LANDING CHECK, THE CREW NOTICED OIL ON THE RIGHT ENGINE COWL.  NORMAL LANDING CARR	IED OUT.  INVESTIGATION REVEALED A CRACKED FLARE ON THE OIL SCAVENGE TUBE AT THE VERNATHERM VALVE.					1	H	7	2 	3T	4	T	RT	A10SW   	E4WE
1998082800284	19980828	00284	EA  	1998	8	28	CA980602014      	2	19980523	G	8520	68865	CRANKSHAFT      			PIPER 	PA28  	PA28160     	7102806	SO  	LYC   	O320  	O320D2A     	41508	EA  	SNSNCH	74DM	M74DM       	EA  	ENGINE	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1957 					L600639A	K7270		(CAN) WHILE COMPLYING WITH AD 98-02-08 INSPECTION, PITS WERE FOUND IN THE CRANKSHAFT BORE.						1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
1998082800294	19980828	00294	EA  	1998	8	28	CA980602028      	2	19980514	G	8530	SL11626	GUIDE           		C12A1R      	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  					NR 3 CYLINDER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1977 					L2248915			(CAN) DURING 100 HOUR INSPECITON, THE COMPRESSION ON #3 CYLINDER WAS FOUND LOW. TROUBLESHOOTING FOUND THE EXHAUST VALVE 	LOOSE WITHIN THE GUIDE. A CIRCULAR PIECE OF METAL WAS FOUND IN THE OIL RETURN GALLEY. IT WAS NOT READILY EVIDENT WHERE T	HE METAL ORIGINATED, SO THE CYLINDER WAS REMOVED FOR INSPECTION. THE EXHAUST VALVE WAS FOUND SO BADLY WORN IN THE GUIDE 	THAT THE GUIDE HAD FRACTURED AND WAS AT THE POINT OF COMPLETE FAILURE. THE #3 CYLINDER WAS REPLACED.			1	H	7	1 	3O	3	O	NT	3A19    	E223
1998120400025	19981204	00025	NE  	1998	12	4	CA980602029      	1	19980525	G	6310	7636109103104	OUTPUT FLANGE   			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE890255S			(CAN) OUTPUT FLANGE REMOVED TO CHANGE OUTPUT SHAFT SEALS.  FOUND THAT THE OUTPUT FLANGE SHAFT WAS SHEARED OFF BEHIND THE	 SECURING NUT.					1	G	7	2 	3U	3	U		H1NE    	E1GL
1998082800295	19980828	00295	NE  	1998	8	28	CA980602030      	2	19980529	G	7210	130008203	BEARING         		10600814    	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					GEARBOX	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				2697 				LE07611			(CAN) CHIP DETECTOR WARNING LIGHT ILLUMINATED IN FLIGHT. AFTER LANDING INSPECTION OF THE CHIP DETECTOR SHOWED EXCESSIVE 	METAL CONTAMINATION. A MORE DETAILED INSPECTION FOUND THE NR 21 BEARING HAD A BROKEN BEARING CAGE.  NO OTHER DAMAGE WAS 	FOUND.				1	G	7	1 	4U	4	U		H1SW    	E17EA
1998100900239	19981009	00239	SW  	1998	10	9	CA980602031      	1	19980529	G	6520	212040451001	BEVEL GEAR      		212040004005	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL ROTOR	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA			10199	277  		AHT50505		LEO7655			(CAN) ON FIRE FIGHTING MISSION, 90 DEGREE CHIP LIGHT ON.  AFTER LANDING, CHIP PLUG WAS HEAVILY CONTAMINATED. INPUT GEAR 	212-040-450-001 S/N A13-02363 HAD BROKEN TEETH, BEVEL GEAR 212-040-451-001 S/N A13-03609 HAD BROKEN TEETH, G/B HOUSING 2	12-040-468-001 S/N A13-04440 INTERNAL DAMAGE FROM GEAR PARTS AND ROLLER BEARING 212-040-455-001 S/N 4360 ALSO.				1	G	7	1 	4U	4	U		H1SW    	E17EA
1998090400030	19980904	00030	EA  	1998	9	4	CA980602056      	1	19980520	G	2510	MDA1624B014	RIVET           			DHAV  	DHC6  	DHC6300     		EA  	PWA   	PT6   	PT6A27      	52043	EA  					SEATBELT	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			56   								(CAN) PROBLEMS REPORTED ON NEW SEAT BELTS INSTALLED IN A COUPLE OF OPERATORS AIRCRAFT.  PILOTS REPORTED THAT THEY DO NOT	 SEEM TO LATCH PROPERLY UNTIL GIVEN A SHARP TAP.  INSPECTION COULD NOT FIND PROBLEM INITIALLY.  A CLOSER MORE RECENT LOO	K FOUND THAT THE BELT FELL APART. THE SPLINED RIVET THAT HOLDS THE ASSEMBLY TOGETHER HAD FALLEN OUT.				1	H	7	2 	3T	4	T		A9EA    	E4EA
1998090400031	19980904	00031	CE  	1998	9	4	CA980602057      	1	19980515	G	5710	14225507	WING            			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	BS 204-222	BIRD STRIKE     	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			C	Y		F.O.D.                    	ENGINE STOPPAGE           		CR	CRUISE         	1			CA			2134 					352505	764417		(CAN) IN CRUISE, PILOT CAUGHT A FLASH OF MOTION AND HEARD A BIRD IMPACT WITH HIS LEFT WING.  DAMAGE WAS VISIBLE FROM THE	 COCKPIT. WIRES WERE VISIBLE SO ENGINE WAS SHUT DOWN AND AIRCRAFT RETURNED TO BASE.  DAMAGE WAS FOUND TO EXTEND FROM STN	 204 TO 222.  LEADING EDGE PUSHED BACK AND TWO RIBS DAMAGED.  REPAIRED.				1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
1998100900242	19981009	00242	CE  	1998	10	9	CA980602058      	1	19980417	G	3230	583800901	MOTOR           		9581001713  	BEECH 	95    	E95         	1153410	CE  	LYC   	O360  	IO360B1B    	41514	EA  					MLG	FAILED          	W				L				ABORTED APPROACH        				O			OTHER                     			AP	APPROACH       	1			CA				59   		AGB1541		L496351A			(CAN) LANDING GEAR FAILED TO EXTEND USING THE NORMAL ELECTRICAL EXTENSION SYSTEM.  THE LANDING GEAR WAS EXTENDED MANUALL	Y AND AIRCRAFT LANDED WITHOUT INCIDENT AFTER CONFIRMATION GEAR DOWN AND LOCKED.  SUBSEQUENT INVESTIGATION REVEALED THE L	ANDING GEAR ELECTRICAL MOTOR WAS INTERMITTENT AND WOULD NOT BRAKE DYNAMICALLY AND THE GEAR ACTUATOR WAS STIFF NEAR THE E	ND OF ITS TRAVEL. LANDING GEAR MOTOR AND LANDING GEAR ACTUATOR REPLACED.			1	L	7	2 	3O	3	O		3A16    	1E10
1998100900243	19981009	00243	SO  	1998	10	9	CA980602061      	1	19980413	G	3213	AN17642	BOLT            			PIPER 	PA31  	PA31350     	7103110	SO  										TORQUE LINK	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA											(CAN) AIRCRAFT PULLS LEFT ON LANDING.  UPPER TORQUE LINK BROKEN.  REPLACED.						1	L	7	2 	3O				A20SO
1998090400036	19980904	00036	EA  	1998	9	4	CA980602076      	1	19980413	G	5512		SKIN            		C3TP1181    	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	PT6   	PT6A135     	52043	NE  					HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								35094			(CAN) TWO CRACKS NOTED ON THE HORIZONTAL STABILIZER LOWER SKIN AT THE OUTBOARD HINGE. THE HINGE BRACKET WAS FOUND LOOSE.	 TWO RIVETS THAT SECURE THE HINGE TO THE REAR SPAR WERE LOOSE AND HOLES IN THE SPAR ELONGATED.  THE HORIZONTAL STABILIZE	R END RIB WAS ALSO CRACKED.				1	H	7	1 	3R	4	T		A815    	E4EA
1998090400039	19980904	00039	CE  	1998	9	4	CA980602082      	1	19980415	G	7603		POWER LEVER     			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 1 ENGINE	LOOSE           	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								PCEP0165			(CAN) FLIGHT CREW NOTICED NO RESPONSE TO VARIOUS POWER LEVER INPUTS ON THE NR 1 ENGINE DURING TAXI.  MAINTENANCE FOUND T	HE INPUT LEVER ON THE CAM CLUSTER WAS LESS THAN SECURE DUE TO THE DESIGN OF THE LEVER, WHICH IS A SPLIT/SLIP SERRATED TY	PE.  THE SERRATIONS WERE SLIPPING INTERMITTENTLY DURING INPUT FROM THE COCKPIT.  THE MECHANICAL ADVANTAGE ALLOWED FOR TH	E CONDITION AS PHYSICALLY GRASPING THE LEVER BY HAND DOES NOT INDICATE AN EXCESSIVE LOOSE CONDITION.  THE LEVER WAS SECU	RED AND THE AIRCRAFT WAS RELEASED FOR SERVICE. THE SUBMITTER STATES THAT A FLEET CAMPAIGN HAS BEEN INITIATED TO INSPECT 	THE REMAINDER OF THE FLEET.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998090400040	19980904	00040	NE  	1998	9	4	CA980602085      	2	19980428	G	8520		ROD             			DOUG  	DC3   	DC3CS1C3G   	3021458	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 7 CYLINDER	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA				268  				489267			(CAN) LARGE END OF NR 7 CYLINDER CONNECTING ROD FAILED.						2	L	7	2 	4R	4	R		A669    	5E4
1998090400043	19980904	00043	GL  	1998	9	4	CA980602088      	3	19980526	G	6111	V84337	BLADE           													HARTZL	HCA2V	HCA2VK2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			331  	193  					J1464		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADES FOUND WITH STONE DAMAGE.  PROPELLER BLADES REPAIRED	.															5	C	P24EA
1998092200001	19980922	00001	GL  	1998	9	22	CA980602090      	3	19980527	G	6111	S90AT	BLADE           													MCAULY	2AF34C	D2AF34C59   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				649  					703411		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADES FOUND CORRODED.  PROPELLER BLADES REPAIRED,  ANODIZ	ED AND PAINTED.															5	C	P5EA
1998090400044	19980904	00044	EA  	1998	9	4	CA980602091      	3	19980529	G	6111		BLADE           			PIPER 	J3    	J3F65       	7100536	SO  	CONT  	C85   	C8512F      	17008	SO  	SNSNCH	76A	76AK        	EA  	PROPLELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			259  					23082612	23828		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CORROSION REMOVED.						1	H	7	1 	3O	3	O		A692    	E233	5	N	1P210
1998090400045	19980904	00045	CE  	1998	9	4	CA980602092      	1	19980525	G	5521	07346013	SPAR            		0732000159  	CESSNA	180   	180C        	2072608	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								2025818R	762169		(CAN) ELEVATOR SPAR CRACKED AT THE OUTBOARD SECTION OF THE OUTER HINGE.  LEFT ELEVATOR.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1998090400046	19980904	00046	GL  	1998	9	4	CA980602093      	3	19980602	G	6111	82PCAC	BLADE           			CESSNA	177   	177B        	2073708	CE  						MCAULY	2D34C	B2D34C211   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			646  	276  					750588		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADE FOUND DAMAGED.  BLADE REPAIRED AND BLADE ANODIZED.						1	H	7	1 	3O				A13CE   		5	C	P7EA
1998090400047	19980904	00047	NM  	1998	9	4	CA980602094      	1	19980602	G	3230	60221341	SWITCH          			BOEING	727   	727260      		NM  										LT MLG	LOOSE           	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA				239  							(CAN) LEFT MLG DID NOT SHOW DOWN AND LOCKED AFTER TWO CYCLES AND MANUAL EXTENSION ATTEMPTS.  BOTH FORWARD PANEL AND SECO	NDARY INDICATORS ON S/O PANEL.  DOWNLOCK SWITCHES MECHANICAL LINKAGE FOUND ADRIFT DUE TO MISSING NUT AT DOWNLOCK SWITCH.	  ALSO NOTED BOLT AT SWITCH END OF LINKAGE APPEARED BACKED OFF, ONLY ONE THREAD SHOWING THROUGH NUT.  REPAIRED.  PART TC	:  187.			2	L	7	3 	4F			RT	A3WE
1998100900245	19981009	00245	GL  	1998	10	9	CA980602095      	2	19980525	G	7321	23070254	ECU             		23070254    						ALLSN 	250C  	250C47B     		GL  					FADEC	FAILED          	W				B				EMER. DESCENT           				J	R		WARNING INDICATION        	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CA			288  			JG7ALK0385		CAE847021			(CAN) ON SHORT FINAL APPROACH, FADEC FAIL WARNING LIGHT AND POWER LOSS.  PILOT FORCED TO COMPLETE LANDING UNDER LOW POWE	R AND LOW ROTOR RPM RESULTING IN A HARD LANDING.  ATTEMPTS TO DOWNLOAD FADEC ECU DATA TO MAINTENANCE TERMINAL UNSUCCESSF	UL WITH NO ECU IS AVAILABLE ERROR.  EXCHANGE OF THE ECU WITH A SERVICEABLE ONE FROM ANOTHER AC PROVED THE FAULT IS IN TH	E ECU.  ECU HAS BEEN SHIPPED TO CHANDLER EVANS FOR INVESTIGATION.								3	U			E1GL
1998100900246	19981009	00246	CE  	1998	10	9	CA980603002      	1	19980512	G	5210	551123515	HINGE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CABIN DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE70683			(CAN) CABIN DOOR WOULD NOT CLOSE.  INSPECTION REVEALED A CRACK DUE TO CORROSION ON THE UPPER ATTACHMENT LUG ARM.  SUBMIT	TER SUSPECTS DISSIMILAR METAL CORROSION DUE TO PREVIOUS REPLACMENT OF WRONG TYPE OF RIVETS.					1	L	7	2 	4F	4	F		A22CE   	E1NE
1998090400048	19980904	00048	EA  	1998	9	4	CA980603003      	2	19980521	G	8520	5015	BOLT            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					NR 1 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA				1705 				L681961A			(CAN) LOSS OF POWER ON NR 1 ENGINE FOLLOWED BY OIL LOSS.  ENGINE WAS SHUTDOWN.  INSPECTION FOUND THE STUDS AND THRU BOLT	 ON THE ENGINE CASING BROKEN.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998090400049	19980904	00049	EA  	1998	9	4	CA980603004      	2	19980521	G	7314	RG908034A	PUMP            	ROMEC       		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					FUEL SYSTEM	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CR	CRUISE         	1			CA			640  	385  		C1056		L163261			(CAN) DURING FLIGHT, THE PILOT NOTICED THE NR 2 ENGINE FUEL GAUGE DROPPING RAPIDLY WITH A CORRESPONDING DROP IN FUEL PRE	SSURE. THE EMERGENCY FUEL PUMP WAS SELECTED ON AND THE FUEL LOSS INCREASED. THE ENGINE COUGHED AND THE FUEL CROSS FEED W	AS SELECTED, STILL FUEL WAS LOST. THE AIRCRAFT LANDED AND POST FLIGHT INSPECITON FOUND THE FUEL PUMP SEAL OR THE PUMP IN	TERNAL DIAPHRAGM HAD FAILED. THE FUEL PUMP WAS REPLACED.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1998090400050	19980904	00050	WP  	1998	9	4	CA980603006      	1	19980525	G	3240	240315062312	TORQUE TUBE     			CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					LT MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								501261			(CAN) DURING A ROUTINE COCKPIT UNDER FLOOR INSPECTION, IT WAS FOUND THERE WAS EXCESSIVE WEAR ON THE LEFT POWER BRAKE VAL	VE TORQUE TUBE.  THE WEAR WAS DIFFICULT TO DETECT AS IT WAS HIDDEN BY A PHENOLIC GUIDE BLOCK HOLDING THE LOWER PORTION O	F THE TUBE STEADY.  THE WEAR AFFECTS 50 PERCENT OF THE CIRCUMFERENCE AND 80 PERCENT OF THE TUBE THICKNESS.  FAILURE OF T	HE PART COULD CAUSE A SERIOUS BRAKE PROBLEM.			2	L	7	2 	4R	4	T		6A6     	E282
1998120400033	19981204	00033	EU  	1998	12	4	CA980603014      	1	19980523	G	2435	97375	COMMUTATOR      	LUCAS       	23085014    	PILATS	PC12  	PC12        	7090550	EU  										START/GEN	BROKEN          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA			208  			97375					(CAN) PILOT REPORTED NR 1 GENERATOR FAILED IN FLIGHT, TRIED RESET, NO GOOD.  STARTER/GENERATOR COMMUTATOR HAD PIECE MISS	ING.   ALL BRUSHES DESTROYED.  PART TC:  174.					1	L	7	1 	3T			RT	A78EU
1998090400056	19980904	00056	EA  	1998	9	4	CA980603015      	2	19980525	G	7322	10367832	CARBURETOR      			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA				4    				4686027A			(CAN) DURING CLIMB, THE ENGINE BEGAN TO RUN ROUGH.  LEANING THE MIXTURE CONTROL HAD NO EFFECT.  POST-FLIGHT, THE CARBURE	TOR WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.					1	L	7	1 	3O	3	O		2A13    	E274
1998101700014	19981017	00014	SO  	1998	10	17	CA980603016      	1	19980525	G	3231	6709202	DOOR            			PIPER 	PA34  	PA34200     	7103405	SO  	CONT  	O360  	IO360C      	17025	SO  					MLG	STIFF           	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								L923051A			(CAN) WHEN GEAR SELECTED UP A GEAR UNSAFE LIGHT ILLUMINATED.  RIGHT GEAR DOOR FOUND TIGHT INTERFERRING WITH UP TRAVEL. D	OOR RE-RIGGED.					1	L	7	2 	3O	3	O		A7SO    	E1CE
1998090400057	19980904	00057	EA  	1998	9	4	CA980608001      	1	19980515	G	3246	5859242	STRUT           			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT FLOAT	BENT            	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA								11517			(CAN) ON TAKEOFF IN HEAVY SWELL CONDITION, THE LEFT FLOAT REAR STRUT BENT OVER, 1 FOOT FROM TOP.  THE UPPER REAR FITTING	 SNAPPED FROM THE LOAD AND THE LOWER LEFT REAR FITTING STAYED INTACT.  FRONT TWO STRUTS REMAINED UNDAMAGED WITH UPPER AT	TACH FITTINGS STAYING INTACT. THE LEFT TELESCOPING TUBE PUNCHED A HOLE THRU DECK OF FLOAT.  INSP FOUND A LOWER FITTING B	ROKE AND SHOWING A STRESS CRACK ON ONE END.  PARTS TO TSB LAB FOR ANALYSIS.			1	H	7	1 	3R	3	R		A806    	5E1
1998101700015	19981017	00015	SO  	1998	10	17	CA980608002      	1	19980522	G	7600	3174700	JOINT           			PIPER 	PA34  	PA34200     	7103405	SO  	CONT  	O360  	IO360C      	17025	SO  					CONTROL ARM	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CA			4658 					RL1202551A			(CAN) DURING FLIGHT, THE THROTTLE CONTROL BECAME DETACHED FROM THE THROTTLE CONTROL ARM CAUSING THE ENGINE TO DEVELOP FU	LL POWER.  ENGINE SHUT DOWN.  SINGLE ENGINE LANDING CARRIED OUT.  BALL SPRING JOINT FAILED DUE TO EXCESSIVE WEAR ALLOWIN	G THE BALL TO SLIP OUT OF THE ASSEMBLY.  REPLACED.				1	L	7	2 	3O	3	O		A7SO    	E1CE
1998090400058	19980904	00058	SW  	1998	9	4	CA980608004      	1	19980503	G	3210	1103776	U-BOLT          			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360C2E     	41514	EA  					RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				295  				L2119336A			(CAN) DURING POST-FLIGHT INSPECTION, PILOT NOTICED RIGHT LANDING GEAR U-BOLT BROKEN.  REPLACED.						1	H	7	1 	3O	3	O		A21CE   	E286
1998090400059	19980904	00059		1998	9	4	CA980608005      	1	19980524	G	7112	2075000204	BRACKET         								ROTAX 	912   	ROTAX912    	55555	EU  					AIR BOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								4412608			(CAN) BOTH LEFT AND RIGHT CATCH PAN ASSY SUPPORT BRACKETS CRACKED ACROSS THE SUPPORTING SCREW HOLES.  IN ONE CASE, THE S	UPPORTING SCREW HOLE NO LONGER ATTACHED TO THE AIR BOX ASSY.										3	I			EXPE3I
1998090400060	19980904	00060	GL  	1998	9	4	CA980608007      	3	19980526	G	6111	F84774	BLADE           			PIPER 	PA32  	PA32RT300T  	7103216	SO  	LYC   	O540  	TIO540S1AD  	41532	EA  	HARTZL	HCE2Y	HCE2YR1BF   	GL  	PROPELLER	DAMAGE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			428  	112  				L587261A	DK1785A		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. STONE DAMAGE WAS FOUND ON THE BLADE. THE BLADE WAS REPAIRED AND ANODI	ZED.					1	L	7	1 	3O	3	O		A3SO    	E14EA	5	C	P9EA
1998090400061	19980904	00061	NM  	1998	9	4	CA980608008      	1	19980527	G	3230	BACHH06NNO	LINE            			BOEING	727   	727260      		NM  										HYDRAULIC SYSTEM	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA											(CAN) LOSS OF 'A' SYSTEM HYDRAULIC FLUID IN-FLIGHT.  NOSE GEAR DOWN LINE LEAKING.						2	L	7	3 	4F			RT	A3WE
1998090400063	19980904	00063	NE  	1998	9	4	CA980608010      	3	19980601	G	6111	AG1002	BLADE           			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	PROPELLER	DAMAGE          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2114 	612  				P327965	74161		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADE FOUND WITH STONE DAMAGE AND THE CYLINDER WAS FOUND C	ORRODED.  THE PROP BLADE WAS TRIMMED AND A NEW CYLINDER LINER WAS INSTALLED.					1	Q	7	1 	3R	3	R		1A16    	5E2	5	C	P257
1998090400064	19980904	00064	WP  	1998	9	4	CA980608011      	1	19980522	G	5552	AN174	BOLTS           	CONVUL      	9015004101  	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								500964			(CAN) DURING THE 750 HR FLIGHT CONTROL INSPECTION, IT WAS DISCOVERED THAT 3 OUT OF 6 HINGE BOLTS HOLDING LEFT ELEVATOR T	AB IN PLACE WERE SEVERELY WORN. THE ELEVATOR TAB WAS REMOVED AND INSPECTED.  HARDWARE WAS REPLACED AS REQUIRED.  FURTHER	 INVESTIGATION IS IN PROGRESS TO DETERMINE CAUSE OF EARLY DETERIORATION OF WORN PARTS.				2	L	7	2 	4R	4	T		6A6     	E282
1998090400084	19980904	00084	EA  	1998	9	4	CA980610002      	1	19980610	G	2701	C2CF2281A	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  										CONTROL COLUMN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN CF-84-01 WAS CARRIED OUT, CRACKS WERE FOUND IN THE WELD AREA.  THE TORQUE TUBE WAS REPAIRED IAW SB 2/28.  CRA	CK WAS .6250 INCH LONG AT THE JUNCTION OF THE VERTICAL AND HORIZONTAL TUBES.					1	H	7	1 	3R				A806
1998090400086	19980904	00086	CE  	1998	9	4	CA980610004      	1	19980602	G	3246	16550	SPREADER BAR    	EDO         	6282960     	CESSNA	180   	180J        	2072622	CE  	CONT  	O470  	O470S       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	FLOAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								269275R	860760		(CAN) SPREADER BAR CORRODED ON BOTTOM SURFACE.  NO CORROSION INTERNALLY.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1998071400067	19980714	00067	EA  	1998	7	14	CA980610005      	2	19980601	G	7210	3013132	CARRIER         								PWA   	PT6   	PT6A28      		EA  					NR 5 BEARING	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						30B566		41733100			(CAN) AFTER OVERHAUL INSPECTION OF THE 2ND STAGE CARRIER, THE NR 5 BEARING JOURNAL SLEEVE WAS FOUND OUT OF POSITION FROM	 AN ADJACENT SHOULDER USED AS A DATUM FOR INSTALLATION.  THIS SLEEVE IS PART OF THE NR 5 BEARING JOURNAL REPAIR.  THE SL	EEVE HAS MOVED O.058 INCH FROM THE SHOULDER.  THE COMPONENT OPERATED SATISFACTORILY IN THIS CONDITION.									4	T			E4EA
1998090400087	19980904	00087	CE  	1998	9	4	CA980610007      	1	19980602	G	2510	081273578	SEAT ARMS       			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520N    	17040	SO  	MCAULY	3AF32C	3AF32C93    	GL  	COCKPIT SEATS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6635 								(CAN) PILOTS AND COPILOTS SEAT ARMS INSPECTED AND FOUND CEACKED.  HAD BEEN WELDED AND DID NOT HOLD.  NEW ARMS INSTALLED.	  MSB 89-3.					1	L	7	2 	3O	3	O	RT	A7CE    	E8CE	5	C	P22EA
1998090400092	19980904	00092	NE  	1998	9	4	CA980610012      	3	19980603	G	6111	G101A12	BLADE           			SCWZER	G164  	G164A       	3952704	EA  	PWA   	R1340 	R1340AN1    	52016	NE  	HAMSTD	12D	12D40       	NE  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				206  				22858	5614CPL		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  CORROSION FOUND BORES WERE POLISHED, FILLETS MACHINED, LEADING EDGE 	FILED, THRUST WASHED GROUND AND BLADE ANODIZED.  A COUNTERWEIGHT BRACKET AND THE COUNTERWEIGHT BEARINGS WERE FOUND WORN 	AND THEY WERE REPLACED.				1	Q	7	1 	3R	3	R		1A16    	5E2	5	C	P257
1998120400034	19981204	00034	WP  	1998	12	4	CA980610013      	2	19980602	G	7261	8965971	LINE            			SWRNGN	SA226 	SA226T      	8780122	SW  	GARRTT	TPE331	TPE3313U    	01514	WP  					ENGINE OIL	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4675 					P3272			(CAN) DURING INSPECTION OF BOTTOM IGNITOR, IT WAS NOTED THAT THE COOLING AIR HOSE TO IGNITOR HOUSING WAS RUBBING AGAINST	 REAR TURBINE BEARING OIL LINE.  OIL LINE WAS CUT WELL BEYOND LIMITS.   CUT CAUSED BY THE REINFORCING WIRE IN THE LINE. 	 PART TC:  4,060.				2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
1998090400093	19980904	00093	EA  	1998	9	4	CA980610014      	2	19980529	G	7324	75278	DIAPHRAGM       			BBAVIA	8     	8KCAB       	2110612	CE  	LYC   	O320  	AEIO320E1B  	41508	EA  					FUEL DIVIDER	FAILED          	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			CA			94   					L567655A			(CAN) DURING THE ENGINE RUN-UP PREPARATORY TO THE ANNUAL INSPECTION, THE ENGINE WAS RUNNING VERY ROUGH WITH BLADE SMOKE 	COMING FROM THE EXHAUST.  INSPECTION REVEALED THE RUBBER DIAPHRAGM IN THE FUEL FLOW DIVIDER HAD DRIED OUT, DISINTEGRATED	 AND PLUGGED THE FUEL INJECTOR LINES. THE ENGINE HAD BEEN OVERHAULED IN SEPTEMBER OF 1995, BUT HAD NEVER FLOWN.  THE ENT	IRE FUEL SYSTEM INCLUDING SERVO FUEL INJECTOR AND FUEL NOZZLES WERE SENT FOR REPAIR.			1	H	7	1 	3O	3	O		A21CE   	1E12
1998091100458	19980911	00458	EA  	1998	9	11	CA980610015      	1	19980603	G	5521	C2TE103AND	RIB             			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								JP210777			(CAN) WHILE CARRYING OUT AD CF-97-06 THE TIP RIB OF THE LEFT ELEVATOR WAS FOUND SEVERELY CORRODED.						1	H	7	1 	3R	3	R		A806    	5E1
1998091100459	19980911	00459	EA  	1998	9	11	CA980610016      	2	19980604	G	8520		CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1383 				L582576T			(CAN) FOUND CORROSION IN THE AREA (INNER BORE) OF THE CRANKSHAFT, AS SPECIFIED IN FAA AD 98-02-08, NO CRACKS FOUND.  REP	ETITIVE INSPECTION REQUIRED.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998091100460	19980911	00460	EA  	1998	9	11	CA980610017      	2	19980604	G	8520		CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				807  				L79376	81645		(CAN) FOUND CORROSION IN THE AREA (INNER BORE) OF THE CRANKSHAFT, AS SPECIFIED IN FAA AD 98-02-08, NO CRACKS FOUND.  REP	ETITIVE INSPECTION IS REQUIRED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998100900250	19981009	00250	SO  	1998	10	9	CA980610019      	1	19980527	G	3244	301027420	TIRE            	CLEVELAND   	40140       	PIPER 	PA31  	PA31350     	7103110	SO  										NLG	BULGED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING INSPECTION, A BULGE WAS FOUND IN THE SIDEWALL OF THE NOSE TIRE.  REPLACED.						1	L	7	2 	3O				A20SO
1998091100461	19980911	00461	SW  	1998	9	11	CA980610020      	1	19980525	G	5210	H29497	LATCH           			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					PASSENGER DOOR	OUT OF ADJUST   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								P03001C			(CAN) CABIN DOOR WARNING LIGHT ON IN-FLIGHT.  UPPER AFT CABIN DOOR LATCH ASSEMBLY WAS ADJUSTED.						2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998091100462	19980911	00462	SO  	1998	9	11	CA980615001      	1	19980606	G	2435	P1	GENERATOR       	WESTINGHOUSE		CURTIS	C46   	C46FAIRLIFT 		SO  	PWA   	R2800 	R280051     	52026	NE  	HAMSTD	23E	23E50       	NE  	NR 1 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				304  		AF4497859		4138160	FE1178		(CAN) DURING START, THE NR 1 GENERATOR WOULD NOT COME ON-LINE, THE AIRCRAFT WAS DISPATCHED, IN COMPLIANCE WITH THE MMEL,	 TO GO WITH ONE GENERATOR.  THE NR 1 GENERATOR WAS REPLACED AT THE AIRCRAFT'S ARRIVAL POINT.					2	L	7	2 	4R	4	R		3A2     	5E8	6	C	P603
1998091100463	19980911	00463	EA  	1998	9	11	CA980615002      	2	19980601	G	8520	74648	CRANKSHAFT      			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1499 				L3887827A			(CAN) CRANKSHAFT INSPECTED AS PRE FAA AD 98-02-08.  NUMEROUS CORROSION PITTING FOUND EXCEEDING THE MAXIMUM INTERNAL DIME	NSIONAL LIMITS.  CRANKSHAFT SCRAPPED.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998100900251	19981009	00251	CE  	1998	10	9	CA980615003      	1	19980604	G	2770	656527555	CONTROL CABLE   			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					CONTROL LOCKS	KINKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2922 					71747			(CAN) AFTER AIRCRAFT HAD BEEN PARKED OUTSIDE ON RAMP FOR AFTERNOON WITH CONTROL LOCKS ON, CONTROL LOCKS COULD NOT BE SEL	ECTED OFF.  IT WAS DISCOVERED THAT THE INNER CABLE HAD BULGED OUT OF ITS CASING AND JAMMED.  PART TC:  3,035.					1	L	7	2 	4F	4	F	 	A22CE   	E1NE
1998100900252	19981009	00252	SO  	1998	10	9	CA980615005      	1	19980601	G	3242	3068	BRAKE           			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					MLG	LOCKED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7607 					L163261			(CAN) INSPECTION REVEALED FLAT SPOT ON LT WHEEL.  BRAKE GRINDING WHEN TOWED, DISCS WARPED.  BRAKES AND WHEELS REPLACED.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900253	19981009	00253	SO  	1998	10	9	CA980615006      	1	19980605	G	3310	2699500	SWITCH          			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					COCKPIT	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								L104448			(CAN) IN-FLIGHT AT NIGHT THE PILOT NOTICED SPARKS COMING FROM UNDER THE CENTER RT EDGE OF THE INSTRUMENT PANEL.  WORK HA	D BEEN DONE ON RADIOS.  SOLDER CONNECTION ON THE 1,00O HMS RESISTOR CONNECTING THE L20N WIRE FROM THE LT AND RT LIGHT SW	ITCHES TO THE SOLID STATE DIMMER WERE BARE.  REPAIRED.				1	L	7	2 	3O	3	O		1A10    	1E4
1998091100464	19980911	00464	EU  	1998	9	11	CA980615007      	1	19980605	G	2421		GENERATOR       			AIRBUS	310   	A310304     		EU  										ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, NR 1 GENERATOR FAILED, UNABLE TO RESET IN-FLIGHT.  FAULT ISOLATION PER 24-00-00 P6150 PARTS 1 TO 5 	CARRIED OUT.  GENERATOR CONTROL UNIT RESET.  ENGINE GROUND RUN-UP CARRIED OUT, ALL PARAMETERS NORMAL.  HEAVY LANDING AND	 HEAVY BRAKE INSPECTION CARRIED OUT.  AUXILIARY POWER UNIT INOPERATIVE PREVIOUSLY  PER MEL 49-1.				2	L	7	2 	4F			RT	A35EU
1998100900255	19981009	00255	SW  	1998	10	9	CA980616002      	1	19980530	G	3210	205050400053	CROSSTUBE       		205706078101	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MLG	BROKEN          	W				C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			O			OTHER                     			HO	HOVERING       	1			CA			9756 					LEO7750			(CAN) ON LIFTING 6 FUEL DRUMS ON A SHORT LANYARD, PILOT SAW IN THE SLING MIRROR THAT THE LANYARD HAD CAUGHT ON THE RT SK	ID TUBE.  ON ATTEMPT TO LAND, IT BECAME EVIDENT THAT THE REAR CROSSTUBE HAD BROKEN AND THE LANDING WAS ABORTED, THE LOAD	 RELEASED AND HELO RETURNED TO BASE WHERE A LANDING WAS MADE ON PREPARED BLOCKS.  CROSSTUBE BROKE AT THE RT MOUNTING POI	NT FROM A PRE-EXISTING CRACK UNDER THE CLAMP.			1	G	7	1 	4U	4	U		H1SW    	E17EA
1998100900256	19981009	00256	SW  	1998	10	9	CA980616003      	1	19980608	G	6420	212010730001	ROD             		212010712001	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					TAIL ROTOR	BROKEN          	W				A				UNSCHED LANDING         				E	D		VIBRATION/BUFFET          	INFLIGHT SEPARATION       		CR	CRUISE         	1			CA								LE07641			(CAN) ROD END OUTER RACE FRACTURED LOSING 1/3 OF CIRCUMFERENCE AND RELEASING THE BALL.  LOSS OF CONTROL OF ONE BLADE AND	 TAIL ROTOR AUTHORITY.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1998091100466	19980911	00466		1998	9	11	CA980616005      	4	19980127	G	3420	7003360VAR	AHRS            	SPERRYFLT   	AH600       	DHAV  	DHC8  	DHC8103     	1386005	NM  	PWA   	120   	PW120       		NE  					COCKPIT	FAILED          	W				L	A			ABORTED APPROACH        	UNSCHED LANDING         			I	J		FLT. ATTITUDE INST.       	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) COMPASS SYSTEMS MISMATCHED.  NR 1 INDICATED 020 DEGREES, NR 2 INDICATED 008 DEGREES, C14 INDICATED 040 DEGREES, AN	D THE STANDBY INDICATED 50 DEGREES.  AFTER UNEVENTFUL LANDING ALL COMPASSES INDICATED WITHIN + OR - 1 DEGREE.  THIS IS A	 KNOWN PROBLEM AND A NEW AHRS IS IN DEVELOPMENT TO REPLACE THE AH600 FOR OPS ABOVE 79 DEGREES MAGNETIC DIP ANGLE.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998091100467	19980911	00467	CE  	1998	9	11	CA980616006      	1	19980425	G	7120	04511201	MOUNT           		94511291    	CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								242717R			(CAN) ENGINE MOUNT CRACKED ON LT LOWER ARM FROM FIREWALL TO NOSE GEAR AT WELD.  REPAIRED.						1	H	7	1 	3O	3	O		3A19    	E252
1998091100468	19980911	00468	CE  	1998	9	11	CA980616007      	1	19980527	G	2422	PC250	INVERTER        			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				G	H		MULTIPLE FAILURE          	ELECT. POWER LOSS-50 PC   		CR	CRUISE         	1			CA								PCE32180			(CAN) DURING FLIGHT, NR 1 INVERTER DROPPED OFF-LINE. T HE NR 2 INVERTER WAS SELECTED AND IT ALSO DROPPED OFF-LINE.   AFT	ER APPROXIMATELY 1/2 HOUR INTO FLIGHT, THE INVERTERS CAME ON-LINE.  MAINTENANCE INVESTIGATION REVEALED MOISTURE WAS PRES	ENT AROUND THE INVERTERS AND CONNECTORS.  THE CONNECTORS WERE CLEANED AND TREATED WITH CPC.  FUNCTIONAL CHECK CARRIED OU	T SERVICEABLE.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998091100469	19980911	00469	EA  	1998	9	11	CA980616008      	1	19980527	G	7160	055211313	SEAL            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	AIRBOX	BROKE           	W				O				OTHER                   				C			F.O.D.                    			NR	NOT REPORTED   	1			CA			2000 					L39519027A	725261		(CAN) SEAL ON THE AIR BOX ASSEMBLY BROKE OFF AND WAS INGESTED INTO THE CARBURETOR.  THE ENGINE WOULD NOT RUN ABOVE IDLE.						1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998091100472	19980911	00472	SO  	1998	9	11	CA980616011      	2	19980608	G	7322	628371	SPRING          		631415AG    	BEECH 	33    	F33A        	1151425	CE  	CONT  	O520  	IO520BB     	17032	SO  	MCAULY	3A32C	3A32C406    	GL  	CARBURETOR	BROKEN          	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TX	TAXI/GRND HDL  	1			CA			50   					813799R	921313		(CAN) THE AIRCRAFT ENGINE RAN ROUGH ON RUN-UPS. INVESTIGATION FOUND THE SPRING BETWEEN THE MIXTURE AND THROTTLE CONTROL 	ARM WAS BROKEN/DISLODGED.  THE SPRING WAS REPLACED, BUT SHORTLY AFTER BECAME DISLODGED.  THE CONTINENTAL TECH REP WAS CO	NTACTED AND HE ADIVSED THAT THE HOLE WHERE THE SPRING FITS INTO BE CHAMFERED.  A SLIGHT CHAMFER WAS MADE AND THE SPRING 	WAS SECURED.			1	L	7	1 	3O	3	O		3A15    	E5CE	5	C	P21EA
1998100900257	19981009	00257	EU  	1998	10	9	CA980616015      	1	19980527	G	6420	350A33212900	SPIDER          		350A33200405	SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	FRETTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2325 			MA0259					(CAN) 331 HOURS AFTER INCORPORATION OF SB 65.00.35, BEARING RETAINING NUT 350A33-2149-21 LOST TORQUE ALLOWING BEARING TO	 SPIN ON ROTATING SPIDER SHAFT.  OTHER THAN LOSS OF TORQUE ON THE RETAINING NUT, THE ONLY OTHER INDICATION WAS A SLIGHT 	AXIAL PLAY IN THE NON-ROTATING SPIDER.				1	G	7	1 	3U				H9EU
1998120400036	19981204	00036	WP  	1998	12	4	CA980616016      	2	19980218	G	7250	30725433	BLADE           								GARRTT	TFE731	TFE7313R    	01518	WP  					NR 1 ENGINE	SEPARATED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			T	E	D	ENGINE CASE PENETRATION   	VIBRATION/BUFFET          	INFLIGHT SEPARATION       	CL	CLIMB          	1			CA			6576 					84400			(CAN) AFTER TAKEOFF DURING CLIMB THRU 4000 FEET, A LOUD BANG HEARD, FOLLOWED BY VIBRATION AND NR 1 ENGINE SPOOLING DOWN.	  ENG SHUT DOWN.  NR 1 ENG SUFFERED CATASTROPHIC FAILURE.  TEARDOWN SHOWED 10 LPT3 BLADES WERE SEPARATED.  ONE BLADE SEP	ARATED ABOVE PLATFORM AND IS CONSIDERED PRIMARY FAILURE.  REMAINDER OF BLADES SHOWED OVERLOAD FAILURES AND CONSIDERED SE	CONDARY FAILURES.  IMBALANCE OF LPT3 ROTOR CAUSED SEVERE RUBS OF HIGH AND LOW PRESS COMPRESSOR AND TURBINE ROTATING GROU	PS.  HP SHAFT SEPARATED.  LPT3 BLADE SEPARATED AS A RESULT OF HIGH CYCLE FATIGUE.  STRESS RUPTURE OF HPT SHAFT DUE TO EX	CESSIVE HEAT FROM HEAVY ID RUB BETWEEN LP HALF-SHAFTS AND HP SHAFT.  SB TFE731-72-3482 INCORPORATES AN IMPROVED BLADE.						4	F			E6WE
1998100900258	19981009	00258	SW  	1998	10	9	CA980622005      	1	19980529	G	3213	206050119007	CROSS TUBE      		206050118055	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA								CAE822157			(CAN) AFTER SHUT DOWN, A SNAP WAS HEARD BY CREW AND HELO SAGGED IN THE BACK.  AFT CROSSTUBE BROKEN AT THE FUSELAGE MOUNT	ING POINT.  CROSSTUBE HAD BEEN STRIPPED, INSPECTED PER CF-95-17 AND REPAINTED 40 HOURS PREVIOUS.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998100900259	19981009	00259	CE  	1998	10	9	CA980622007      	1	19980609	G	3242	15903500	DISK            	CLEVELAND   	03018902    	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					BRAKE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			450  					70204			(CAN) BOTH SETS OF BRAKE ROTATOR DISC ASSEMBLIES FOUND BROKEN.  BOTH WERE IN VERY POOR SHAPE WITH SEVERE WEAR.						1	L	7	2 	4F	4	F		A22CE   	E1NE
1998100900260	19981009	00260	CE  	1998	10	9	CA980622018      	1	19980609	G	3230	MS24665355	COTTER PIN      		1148100007  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4624 					GGMPS0123			(CAN) DURING INSPECTION, A GAP WAS FOUND BETWEEN THE LEFT HAND (LT) OUTBOARD PIVOT BOLT AND MLG.  FURTHER INVESTIGATION 	REVEALED THE PIVOT BOLT COTTER PIN WAS SHEARED AND THE NUT HAD LOOSENED.  PART TC:  5,481.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900261	19981009	00261	CE  	1998	10	9	CA980622019      	1	19980610	G	3230	MS24665355	COTTER PIN      		1148100007  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					MLG	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4161 					GGM114476			(CAN) DURING OVERNIGHT INSPECTION THE COTTER PIN ON LT INBOARD PIVOT BOLT WAS FOUND SHEARED.  FURTHER CHECKING OF OTHER 	BOLTS IN THE SAME LOCATION OF THE LT LANDING GEAR AND ALSO THE RT LANDING REVEALED TORQUE OF BOLTS WAS BELOW THE RECOMME	NDED TORQUE VALUES.  PART TC:  4,925.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998100900262	19981009	00262		1998	10	9	CA980622021      	4	19980611	G	3418	450742	DETECTOR        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					STALL WARNING	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			584  					L372748			(CAN) DURING 50 HOUR INSPECTION AME HEARD BEEP FROM UNDER INSTRUMENT PANEL.  STALL WARNING ON/OFF WITH BEEP SOUND AND WH	EN STALL DETECTOR ON WING MOVED POSITIVELY BY HAND.  LIFT DETECTOR REPLACED.					1	L	7	2 	3O	3	O		1A10    	1E4
1998100900263	19981009	00263	EA  	1998	10	9	CA980622022      	2	19980611	G	8530	74295	CYLINDER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				808  				L585248			(CAN) DURING INSPECTION A DIFFERENTIAL PRESSURE CHECK ON NR 2 CYLINDER WAS 32/80.  REMOVAL AND DISASSEMBLY OF THE CYLIND	ER FOUND THE EXHAUST VALVE LEAKING, CORROSION AND EXHAUST LEAK IN THE AREA OF THE COOLING FINS.					1	L	7	2 	3O	3	O		1A10    	1E4
1998100900264	19981009	00264	EA  	1998	10	9	CA980622023      	2	19980612	G	7314	LW15473	PUMP            			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1490 				L127748			(CAN) OIL LEAK UNDER ENGINE TRACED TO FUEL PUMP DRAIN.  INSPECTION FOUND BOTTOM DIAPHRAGM OF THE THREE DRAIN CLUSTER, CU	T AND LEAKING.					1	L	7	2 	3O	3	O		1A10    	1E4
1998100900266	19981009	00266	GL  	1998	10	9	CA980623001      	3	19980602	G	6111	S82NC2	BLADE           													MCAULY	3A32C	D3A32C90    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			565  	158  					721417		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ALL OVER THE PROPELLER BLADES AIRFOIL.  THE B	LADES WERE NOT ANODIZED.  THE PROPELLER WAS RETURNED TO THE CUSTOMER AS IS.															5	C	P21EA
1998100900267	19981009	00267	GL  	1998	10	9	CA980623002      	3	19980603	G	6111		BLADE           			CESSNA	180   	180         	2072602	CE  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1423 	134  					T660N		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADES WERE FOUND TOO SHORT. THE HUB WAS EXTERNALLY CORROD	ED (P/N C0840-51); BEARINGS WERE CORRODED (P/N A14B); THE BLADE CLAMPS WERE CORRODED (P/N C0838-2). THE PROPELLER WAS RE	TURNED TO THE CUSTOMER.				1	H	7	1 	3O			NC	5A6     		5	C	P23EA
1998100900268	19981009	00268	GL  	1998	10	9	CA980623003      	3	19980605	G	6111	V84337	BLADE           			PIPER 	PA24  	PA24250     	7102404	SO  	LYC   	O540  	O540A1D5    	41532	EA  	HARTZL	HCA2V	HCA2V*      	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2620 	308  				L698340	H441		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION AND COMPLIANCE WITH AD 97-18-02.  INSPECTION FOUND ONE BLADE; ONE CLAM	P AND TWO BLADE BEARINGS WERE ALL UNSERVICEABLE.					1	L	7	1 	3O	3	O		1A15    	E295	5	C	P24EA
1998100900269	19981009	00269	GL  	1998	10	9	CA980623004      	3	19980603	G	6111	G80VHA35	BLADE           			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2975936A	841879		(CAN) PROPELLER RECEIVED FOR CORROSION REPAIR.  INSPECTION FOUND STONE DAMAGE TO THE BLADES.  THE DAMAGE WAS REPAIRED.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
1998100900270	19981009	00270	GL  	1998	10	9	CA980623005      	3	19980604	G	6111	76634	BLADE           			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	OUT OF TOLERANCE	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L118255	BG1460		(CAN) PROPELLER WAS RECEIVED FOR CORROSION INSPECTION.  SUBMITTER STATED INSPECTION FOUND THE PROPELLER BLADES SHOULD HA	VE BEEN RETIRED FROM SERVICE AS PER SERVICE BULLETIN 61-69A.  THE BLADES WERE RE-INSTALLED AT THE CUSTOMER'S REQUEST.					1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA
1998100900271	19981009	00271	GL  	1998	10	9	CA980623006      	3	19980604	G	6111	76634	BLADE           			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  	HARTZL	HCE2Y	HCE2YL2     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L118255	BG4206		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THERE WERE MACHINING MARKS FOUND ON THE BEARING BORES.  THE BEARING 	BORES WERE POLISHED.					1	L	7	2 	3O	3	O		A1EA    	1E12	5	C	P9EA
1998101700016	19981017	00016	GL  	1998	10	17	CA980623007      	3	19980608	G	6114	B18032	CYLINDER        			DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER HUB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5826 	1100 				PCE20893	BU6103		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THE CYLINDER WAS FOUND WORN.  THE CYLINDER WAS REPLACED.						1	H	7	1 	3T	3	T		A806    	E4EA	6	C	P15EA
1998100900272	19981009	00272	GL  	1998	10	9	CA980623008      	3	19980605	G	6111		BLADE           			CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				7240 					735155		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE FOUND ON THE LEADING EDGES OF THE BLADES.  SUBMITTER ST	ATED THE BLADES WERE FOUND TO BE BELOW THE MINIMUM WIDTH, THE PROPELLER WAS RETURNED TO THE CUSTOMER AS IS.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1998100900273	19981009	00273	EA  	1998	10	9	CA980623009      	3	19980609	G	6111		BLADE           			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E2A     	41508	EA  	SNSNCH	74D	74DM        	EA  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5267 	618  				L2473427A	K27024		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE LEADING EDGES AND THE FACES OF THE PRO	PELLER BLADES.  THE DAMAGE WAS REPAIRED.					1	L	7	1 	3O	3	O		2A13    	E274	5	N	P88614
1998100900274	19981009	00274	GL  	1998	10	9	CA980623010      	3	19980611	G	6111		BLADE           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4748 					901030OH	G15598		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND.  SUBMITTER STATES THE PROPELLER WAS NOT MAIN	TAINED PER THE MCCAULEY MAINTENANCE INSTRUCTIONS.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998100900275	19981009	00275	GL  	1998	10	9	CA980623011      	3	19980611	G	6111		BLADE           													MCAULY	1C160	1C160DTM    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2810 					727860		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND TO THE LEADING EDGES AND THE FACE OF THE PROP	ELLER BLADES.  DAMAGE WAS REPAIRED.															5	N	P910
1998100900276	19981009	00276	GL  	1998	10	9	CA980623012      	3	19980616	G	6114	57C0840126	HUB             			CESSNA	180   	180         	2072602	CE  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1424 	134  					T660N		(CAN) PROPELLER WAS RECEIVED FOR 5 YEARS CORROSION INSPECTION.  PROPELLER DISMANTLED AND WATER WAS FOUND IN THE BLADE CL	AMPS AND THE HUB ARMS.  CORROSION PITTING WAS ALSO FOUND ON THE HUB ARMS.  THE PROPELLER HUB WAS REPLACED.					1	H	7	1 	3O			NC	5A6     		5	C	P23EA
1998100900277	19981009	00277	GL  	1998	10	9	CA980623013      	3	19980616	G	6114	57A00148	BEARING         			CESSNA	180   	180         	2072602	CE  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1424 	134  					T660N		(CAN) PROPELLER RECEIVED FOR FIVE YEAR CORROSION INSPECTION.  PROPELLER WAS DISMANTLED AND WATER WAS FOUND IN THE PROPEL	LER BLADE CLAMPS WHERE THE BEARINGS ARE LOCATED.  THE BEARINGS WERE REPLACED.					1	H	7	1 	3O			NC	5A6     		5	C	P23EA
1998100900278	19981009	00278	GL  	1998	10	9	CA980623014      	3	19980616	G	6111	57C08382	CLAMP           			CESSNA	180   	180         	2072602	CE  						HARTZL	HC82V	HC82V*      	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1424 	134  					T660N		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER WAS DISMANTLED AND WATER WAS FOUND IN THE BLADE CLAMPS, CO	RROSION AND PITTING ON THE INNER RADIUS OF THE CLAMP WAS BEYOND REPAIR.  NEW CLAMPS WERE INSTALLED.					1	H	7	1 	3O			NC	5A6     		5	C	P23EA
1998100900279	19981009	00279	EA  	1998	10	9	CA980623015      	2	19980521	G	8530	5015	STUD            			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				262  				L175668A			(CAN) DURING INSPECTION THE BOTTOM FORWARD STUD ON NR 2 CYLINDER, AT THE BASE OF THE CYLINDER FLANGE, WAS FOUND BROKEN. 	 THE REPORTER SUGGESTS THAT THE STUD WAS NOT COMPLETELY THREADED INTO THE CASE, WHICH CAUSED THE NUT TO BECOME THREAD BO	UND WHICH STRESSED THE STUD AND LED TO THE FRACTURE.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900282	19981009	00282	EA  	1998	10	9	CA980623018      	2	19980612	G	7260	3020289	IMPELLER        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					GEARBOX	WORN            	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			15699	12169				PCE50411			(CAN) ENGINE WAS CONSUMING OIL, IT APPEARED TO BE COMING FROM THE BREATHER.  THE ACCESSORY GEARBOX WAS SPLIT TO REPLACE 	THE CARBON SEAL.  EROSION PITTING WAS FOUND ON THE LEADING EDGE OF THE IMPELLER VANES.  THE IMPELLER AND GEARSHAFT ASSEM	BLY WERE CHANGED AS A UNIT.  PART TC:  18,055.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900283	19981009	00283	EA  	1998	10	9	CA980623019      	2	19980612	G	7260	3029567	SHAFT           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					GEARBOX	WORN            	W				K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA			15699	12169				PCE50411			(CAN) ENGINE WAS CONSUMING OIL WHICH WAS EXITING FROM THE BREATHER.  ACCESSORY GEARBOX WAS REMOVED AND SPLIT TO REPLACE 	THE CARBON SEAL.  FURTHER INSPECTION OF THE GEARSHAFT ASSEMBLY SHOWED WEAR ON THE SPLINE SHAFT AND CRACKS ON THE CARBON 	SEAL FACE.  THE STARTER/GENERATOR DRIVE AND IMPELLER WERE REMOVED AND REPLACED AS A UNIT.  PART TC:  18,055.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900284	19981009	00284	EU  	1998	10	9	CA980623020      	2	19980609	G	8520	996583	CRANKSHAFT      								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			151  	1200 				4412687			(CAN) A HEAVY ENGINE VIBRATION, DURING GROUND OPERATIONS, WAS REPORTED.  INSPECTION REVEALED THE CRANKSHAFT WAS OVER TOL	ERANCE PER THE MANUFACTURER'S OVERHAUL MANUAL.										3	I			EXPE3I
1998100900285	19981009	00285	SO  	1998	10	9	CA980623021      	2	19980615	G	8530	646657	CYLINDER        			CESSNA	206   	P206B       	2073309	CE  	CONT  	O520  	IO520A      	17032	SO  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA								1116936A			(CAN) NR 5 CYLINDER WAS FOUND TO HAVE A CYLINDER SEPARATION.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998100900286	19981009	00286	GL  	1998	10	9	CA980623022      	3	19980610	G	6114	57B1938	AIR VALVE       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  	HARTZL	HCE2Y	HCE2YR2     	GL  	PROPELLER	LEAKING         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CA				789  				RL1016848	BP5470		(CAN) RIGHT HAND PROPELLER HARD TO CONTROL, ENGINE SHUTDOWN, AND AIRCRAFT RETURNED TO BASE.  PRESSURE CHECK CARRIED OUT 	ON PROPELLER AND THERE WAS NO NITROGEN PRESSURE IN THE CYLINDER.  IT IS SUSPECTED THE VALVE WAS LEAKING.  THE VALVE WAS 	REPLACED, THE CYLINDER CHARGED WITH NITROGEN AND THE ASSEMBLY WAS CHECKED SERVICEABLE.				1	L	7	2 	3O	3	O		1A10    	1E4	5	C	P9EA
1998100900287	19981009	00287		1998	10	9	CA980623023      	4	19980615	G	2211		COMPUTER        			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					AFCS	CONTAMINATED    	W				H				DEACTIVATE SYST/CIRCUITS				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA								674277			(CAN) FLT INSTRUMENT ACCY, YAW DAMPER COUPLER, A/P ACCESSORY UNIT, A/P SWITCHING UNIT, INSTRUMENT AMPLIFIER, COMPASS RAC	K, STEERING COMPUTER WERE REPLACED DUE TO INGRESS OF WATER IN AVIONIC BAY.  DURING CRUISE, AUTOPILOT ALTITUDE HOLD TRIPP	ED OFF FOLLOWED BY RAPID PITCH OSCILLATIONS.  AUTOPILOT WAS DISENGAGED AND A/C FLOW MANUALLY AT FL 330.  LATER, A SMALL 	DUTCH ROLL DEVELOPED IN SMOOTH AIR, CREW SUSPECTED YAW DAMPER BUT DUTCH ROLL SOON SUBSIDED AND FLT CONTINUED NORMALLY. L	ATER, ABOUT ONE HOUR FROM DESTINATION, A/C EXPERIENCED UNCOMMANDED YAW/ROLL WHICH CAME ON FAIRLY VIOLENTLY AND INCREASED	 IN AMPLITUDE TO BEYOND 30 DEGREE ANGLE OF BANK.  BOTH A & B FLT SWITCHES TURNED OFF TO REMOVE HYD POWER.	2	L	7	2 	4F	4	F		A16WE   	E2EA
1998120400037	19981204	00037	GL  	1998	12	4	CA980629001      	2	19980611	G	7321	23033917	FCU             			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20J     	03013	GL  					ENGINE	FAILED          	W				O				OTHER                   				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA				1311 				CAE270116			(CAN) DURING START SEQUENCE, THE TEMPERATURE EXCEEDED LIMITS OF 944 CELSIUS.  HOT START INSPECTION CARRIED OUT, NO PROBL	EMS.   SUBMITTER STATED FCU FOUND TO BE CAUSE OF HOT START.  PART TC:  1,350.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998100900288	19981009	00288	SW  	1998	10	9	CA980629002      	1	19980614	G	3213	205050400053	CROSS TUBE      		205706078101	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					CLAMP MOUNT	BROKEN          	W				D				RETURN TO BLOCK         				O			OTHER                     			LD	LANDING        	1			CA			13935					LE07605			(CAN) WHILE DISEMBARKING PASSENGER AFTER LANDING WITH THE ROTOR STILL TURNING, A LOUD SNAP WAS HEARD ACCOMPANIED WITH A 	SUDDEN ROLLING OF THE HELO TO THE RIGHT.  PILOT PREVENTED ANY FURTHER ROLL BY APPLYING CYCLIC AND AC FLOWN BACK TO BASE 	WHERE IT WAS SAFELY SUPPORTED BEFORE SHUTDOWN.  CROSSTUBE FAILED FROM CRACK UNDER THE CLAMP MOUNTING TO THE RT REAR FUSE	LAGE.			1	G	7	1 	4U	4	U		H1SW    	E17EA
1998100900289	19981009	00289	SW  	1998	10	9	CA980629003      	1	19980629	G	2742	DL5040M5	ACTUATOR        			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  					HORIZ STAB	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA				1018 		G0612		P03450			(CAN) BOTH PILOT AND COPILOT ELECTRIC TRIM FAILED AT THE SAME TIME.  SUBMITTER SUGGESTED HAVING TWO INDEPENDENT SYSTEMS.	  AWAITING TEAR DOWN REPORT.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998073100394	19980731	00394		1998	7	31	CA980629005      	4	19980606	G	2562	AK450	ELT             	AMERIKING   	AK450       															CABIN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						354180					(CAN) AT ANNUAL INSPECTION, THE ELT HAD NO OUTPUT POWER.  THE RED LED SHOWS THE USER THAT THE ELT IS OKAY.  THE 'G' SWIT	CH STILL TRIGGERS THE LED ON.  SUBMITTER SAYS THAT HE HAS SEEN 12 UNITS LIKE THIS WITH THE SAME PROBLEM.
1998100900290	19981009	00290	CE  	1998	10	9	CA980629006      	1	19980616	G	5347	CR3243	SEAT TRACK      		051124011   	CESSNA	172   	172L        	2072432	CE  						MCAULY	1C160	1C160CTM    	GL  	COCKPIT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			316  						720123		(CAN) PILOTS SEAT RAILS HAD BEEN RE-INSTALLED USING WRONG RIVETS.  PROPER RIVETS INSTALLED.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998100900291	19981009	00291	NE  	1998	10	9	CA980629007      	2	19980608	G	8530		CYLINDER        			DOUG  	A26   	A26CSHIELDS 	3020506	WP  	PWA   	R2800 	R280079     	52026	NE  					ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA			364  					FP024912			(CAN) WHILE RETURNING TO BASE AFTER FIRE BOMBING OPERATION, THE NR 2 ENGINE BEGAN TO BACKFIRE MILDLY.  A PRECAUTIONARY E	NGINE SHUTDOWN WAS CARRIED OUT.  POST-FLIGHT INSPECTION FOUND NR 3 CYLINDER SPARK PLUG PEENED OVER.  THE DAMAGED NR 3 CY	LINDER WAS REMOVED AND A CRACKED PISTON RING GLAND WAS DISCOVERED.  THE CYLINDER ASSEMBLY WAS REPLACED.  THE ENGINE GROU	ND RUN SERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE.			2	M	7	2 	4R	4	R		L34     	5E8
1998100900292	19981009	00292	NE  	1998	10	9	CA980629008      	2	19980612	G	8530		CYLINDER        			DOUG  	A26   	A26BSHIELDS 	3020504	WP  	PWA   	R2800 	R280051     	52026	NE  					ENGINE	SEPARATED       	W				E				ENGINE SHUTDOWN         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			439  					FPO4182			(CAN) UPON COMPLETION OF FIRE BOMBING RUN, SMOKE WAS NOTICED TRAILING FROM NR 2 ENGINE. PRECAUTIONARY SHUTDOWN WAS CARRI	ED OUT.  POST-FLIGHT INSPECTION FOUND THE NR 3 CYLINDER HAD FAILED.  THE CYLINDER WAS REPLACED.  THE ENGINE GROUND RUN S	ERVICEABLE AND THE AIRCRAFT RETURNED TO SERVICE.				2	M	7	2 	4R	4	R		L34     	5E8
1998100900293	19981009	00293	CE  	1998	10	9	CA980629009      	1	19980612	G	3397		WIRE            			CESSNA	208   	208B        	2073701	CE  										WING	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WHILE REPAIRING THE WING INSPECTION LIGHT,  IT WAS FOUND THAT THE LIVE WIRE TO THE LIGHT HAD BROKEN AND ARCED THRO	UGH THE STATIC LINE.  REPAIRED.					1	H	7	1 	3T			 	A37CE
1998100900294	19981009	00294		1998	10	9	CA980629010      	4	19980614	G	2210		CONTROL CABLE   			CESSNA	208   	208B        	2073701	CE  										YAW DAMPER	DAMAGED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) YAW DAMPENER CABLES UNWOUND AND CAME OFF OF THE ACTUATOR.  CABLE GUARD HAD TOO MUCH CLEARANCE.  REPAIRED.						1	H	7	1 	3T			 	A37CE
1998100900295	19981009	00295	EA  	1998	10	9	CA980629011      	1	19980617	G	2720	C2CF1811A3	SUPPORT         		C2CF1981AND 	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					RUDDER PEDAL	BROKEN          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			14963					16088			(CAN) PILOT REPORTED NO LEFT RUDDER CONTROL.  A BREAK WAS FOUND IN THE RUDDER PEDAL SUPPORT LEFT HAND.  SOME CORROSION W	AS FOUND IN THE AREA OF THE BREAK.					1	H	7	1 	3R	3	R		A806    	5E1
1998100900297	19981009	00297		1998	10	9	CA980629013      	1	19980622	G	7820	L24266710000	SILENCER        								LYC   	O360  	AEIO360A1B6 	41514	EA  					EXHAUST SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2196 					L2652551A			(CAN) DURING PRE-FLIGHT, THE PILOT NOTICED A PIECE OF METAL HANGING FROM THE NR 2 EXHAUST SILENCER.  THE NR 2 SILENCER W	AS REMOVED AND NO DEFECTS WERE FOUND.  THE NR 1 EXHAUST SILENCER WAS REMOVED AND INSPECTION FOUND A LARGE PIECE OF THE I	NTERNAL BAFFLE HAD BROKEN AWAY.  THE NR 1 EXHAUST SILENCER WAS REPLACED.									3	O			1E10
1998100900298	19981009	00298	CE  	1998	10	9	CA980629014      	1	19980617	G	5522	50610000295	SKIN            			BEECH 	90    	B90         	1152912	CE  	PWA   	PT6   	PT6A20      	52043	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11244					PCE20890			(CAN) DURING INSPECTION BEECH SI-0423-133, A 1 INCH CRACK DISCOVERED ON LT ELEVATOR LOWER SKIN AT EDGE OF OVERLAP WITH O	UTBOARD SKIN.  DURING REPAIR WHEN THE SKIN WAS REMOVED THE CRACK RAN 6 INCHES LONG UNDER THE OVERLAP.  REPAIRED.  PART T	C:  14,763.				1	L	7	2 	3T	3	T		3A20    	E4EA
1998100900308	19981009	00308	EA  	1998	10	9	CA980706001      	2	19980622	G	7310	3011849	LINE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					FUEL BYPASS	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1449 				PCE50448			(CAN) FUEL LINE WAS LEAKING AT THE FITTING WELD.						1	L	7	2 	3T	4	T		A14CE   	E4EA
1998100900309	19981009	00309	EA  	1998	10	9	CA980706002      	2	19980620	G	7322	78A110	LOCK TAB        	MARVELSCHEB 	MA4SPA      	CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					CARBURETOR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1008 					L3441127A			(CAN) PILOT WAS UNABLE TO SHUT DOWN THE ENGINE.  INSPECTION OF THE CARBURETOR FOUND THE LONG LOK TAB WASHERS ON THE SAFE	TY SCREWS, THAT SECURE THE FLOAT BOWL TO THE CARBURETOR BODY, HAD FAILED ALLOWING THE MIXTURE VALVE TO SEPARATE FROM ITS	 RECEPTACLE.  SUBMITTER STATED CANADIAN AIRWORTHINESS DIRECTIVE (AD) CF-63-9, WHICH MANDATES MARVEL SCHIEBLER SERVICE BU	LLETIN A5-63, WAS NOT COMPLIED WITH.  AD CF-63-9  REQUIRED THE SAFETY SCREWS TO BE LOCKWIRED.			1	H	7	1 	3O	3	O	NT	3A12    	E274
1998100900310	19981009	00310	WP  	1998	10	9	CA980706003      	2	19980615	G	7313	MS950004	BOLT            			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE3313UW   	01514	WP  					FUEL NOZZLE	WRONG PART      	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA								P03351			(CAN) RIGHT ENGINE FIRE WARNING CAME ON AFTER TAKEOFF.  PRIMARY FUEL NOZZLE GASKET HAD BLOWN OUT CAUSING FIRE DETECTOR T	O ILLUMINATE FIRE WARNING LIGHT.  IT WAS FOUND THAT THE BOLT SECURING THE FUEL NOZZLE WAS TOO LONG AND HAD BOTTOMED OUT 	AT LAST INSTALLATION. THESE BOLTS HAVE BEEN IN SERVICE FOR SOME TIME AND HAVE NEVER HAD A PROBLEM BEFORE STATES THE SUBM	ITTER.  FOLLOW-UP REPORT STATED THAT FIRE LIGHT CAME ON AGAIN, AND THIS TIME IT WAS DISCOVERED THAT BLEED DUST BELLOWS (	P/N 27-62030-039) HAD CRACKED.		2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
1998100900311	19981009	00311	SO  	1998	10	9	CA980706004      	2	19980610	G	8520		CASE            			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520E    	17040	SO  					ENGINE	FRACTURED       	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	B	A	VIBRATION/BUFFET          	SMOKE/FUMES/ODORS/SPARKS  	FLAME/FIRE                	CR	CRUISE         	1			CA				1185 				182891H			(CAN) AFTER TAKEOFF WITH CRUISE POWER SELECTED, THERE WAS SEVERE VIBRATION FROM THE LEFT HAND ENGINE.  SMOKE, FLAMES, AN	D OIL WERE SEEN COMING FROM THE ENGINE COWLING.  THE ENGINE WAS SHUT DOWN.  POST-FLIGHT INSPECTION FOUND THERE WERE TWO 	HOLES IN THE UPPER ENGINE CASE, ONE BETWEEN NR 5 AND NR 6 CYLINDERS, THE OTHER BETWEEN NR 1 AND NR 2 CYLINDERS.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1998100900314	19981009	00314	CE  	1998	10	9	CA980706007      	1	19980619	G	2720	03101965	SPRING          			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2G     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	RUDDER	MISMANUFACTURED 	W				O				OTHER                   				W	F		INADEQUATE Q C            	FLT CONT AFFECTED         		CL	CLIMB          	1			CA								L1725139A	728858		(CAN) NEW RUDDER SPRINGS INSTALLED AND ON FIRST FLIGHT PILOT COMPLAINED THAT IT TOOK MORE RIGHT RUDDER PEDAL PRESSURE TO	 KEEP A/C IN STRAIGHT FLIGHT.  TENSION CHECK OF NEW SPRING REVEALED THAT THE LEFT SPRING TOOK 3.5 POUNDS TO STRETCH ONE 	INCH PER MANUFACTURERS SPECS AND THE RIGHT TOOK EIGHT POUNDS TO STRETCH ONE INCH.  SUBMITTER STATED MANUFACTURER INDICAT	ES A STOCK PROBLEM EXISTED.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998100900316	19981009	00316		1998	10	9	CA980706010      	4	19980617	G	3452	RT359A	TRANSPONDER     			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ATC	FAILED          	W				H	A			DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         			B	J		SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        		CR	CRUISE         	1			CA								L475376	734303		(CAN) DURING VFR FLIGHT A BURNING SMELL WAS NOTED FOLLOWED BY SMOKE COMING FROM TRANSPONDER.  MASTER SWITCH TURNED OFF A	ND AFTER TRANSPONDER TURNED OFF THE MASTER SWITCH TURNED ON WITH NO FURTHER PROBLEM.  REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998090400095	19980904	00095	EA  	1998	9	4	CA980706011      	2	19980619	G	7200		GAS GENERATOR   			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					NR 1 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			DE	DESCENT        	1			CA								PCE32553			(CAN) ON DESCENT, THE NR 1 ENGINE SPOOLED DOWN, THE AIRCRAFT LANDED WITHOUT INCIDENT.  POST-FLIGHT INSPECTION, FOUND THE	 GAS GENERATOR MODULE SEIZED AND WOULD NOT ROTATE.  THE ENGINE WAS REPLACED.  AFTER TEARDOWN, ADDITIONAL DETAILED INFORM	ATION WILL BE SUBMITTED.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998100900317	19981009	00317	EA  	1998	10	9	CA980706012      	2	19980622	G	7310	LW120980100	INJECTOR LINE   			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 4 CYLINDER	BROKEN          	W				E				ENGINE SHUTDOWN         				R	J	Y	PARTIAL RPM/PWR LOSS      	WARNING INDICATION        	ENGINE STOPPAGE           	CR	CRUISE         	1			CA								L646461A			(CAN) LEFT HAND ENGINE SUDDENLY LOST POWER, DURING CRUISE, WITH MANIFOLD PRESSURE, RPM AND CYLINDER HEAD TEMPERATURE ALL	 DROPPING.  THE ENGINE WAS SHUT DOWN.  POST-FLIGHT INVESTIGATION FOUND THE NR 4 CYLINDER FUEL INJECTOR LINE BROKEN.  THE	 BREAK WAS AT THE END OF THE FERRULE AT THE MANIFOLD.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900318	19981009	00318	EA  	1998	10	9	CA980706013      	2	19980601	G	8520	LW15944	CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3144 	1079 				L656376	79798		(CAN) A VISUAL INSPECTION OF THE INNER DIAMETER OF THE CRANKSHAFT SHOWED VISIBLE CORROSION PITTING (AD 98-02-08 REFERS).	  AN ON-WING FLUORESCENT PENETRANT INSPECTION (FPI), CARRIED OUT BY A SUITABLY RATED AMO, FOUND NO CRACKS.  FURTHER MEAS	URING OF THE INNER DIAMETER SHOWED THE INSIDE DIAMETER TO BE WITHIN THE MAXIMUM AS STATED IN LYCOMING SERVICE BULLETIN 5	05B.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998100900319	19981009	00319	EU  	1998	10	9	CA980706014      	2	19980615	G	8520	996583	CRANKSHAFT      								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	BENT            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			536  					4412622			(CAN) UPON DISASSEMBLY OF THE ENGINE,THE CRANKSHAFT WAS FOUND TO HAVE SLIPPED ABOUT 10-15 DEGREES ON ITS AXIS.  THE CRAN	KSHAFT IS PRESS FIT TOGETHER.										3	I			EXPE3I
1998100900320	19981009	00320	EU  	1998	10	9	CA980706015      	2	19980615	G	8520	996583	CRANKSHAFT      								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	BENT            	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			724  					4412604			(CAN) UPON DISASSEMBLY OF THE ENGINE, THE CRANKSHAFT WAS FOUND TO HAVE SLIPPED ABOUT 15-20 DEGREES ON ITS AXIS.  THE CRA	NKSHAFT IS PRESS FIT TOGETHER.										3	I			EXPE3I
1998100900322	19981009	00322	EA  	1998	10	9	CA980706018      	1	19980619	G	5741	680	FITTING         		C2W1103A    	DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					LT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11088			680		2000977			(CAN) STRUT REMOVED TO REPLACE NEW UPPER BUSHINGS.  STRUT END SHOWED INDICATION OF SKIN MOVEMENT AT UPPER RIVETS THEN A 	SCRATCH FOUND ACROSS FACE OF UPPER STRUT END SB 2/41.  INSPECTION CARRIED OUT AND A SMALL CRACK WAS FOUND.					1	H	7	1 	3R	3	R		A806    	5E1
1998100900323	19981009	00323	SW  	1998	10	9	CA980706019      	1	19980615	G	6320	206040151013	TOP CASE        		206040002025	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					TRANSMISSION	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						BKW10105		822880			(CAN) ON SCHEDULED INSPECTION, FOUND GEAR TOOTH BROKEN INSIDE OF TOP CASE.  GEAR IS PART OF TOP CASE CASTING.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998100900324	19981009	00324	SO  	1998	10	9	CA980706021      	1	19980617	G	3221	20169	CONNECTING PIN  	ERAM        	1973000002  	EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	TORQUE ARM	BROKEN          	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			10923			23		115667	880529		(CAN) WHILE TOWING AIRCRAFT, WITHOUT EXCEEDING THE TURN LIMITS, THE NOSE GEAR TORQUE ARM CONNECTING PIN BROKE.  SUBMITTE	R STATED THAT THE PIN WAS CRACKED FOR SOME TIME.  THIS PIN HAS A LIMITED SERVICE LIFE OF 90,000 CYCLES AND IS INSPECTED 	AT EACH LANDING GEAR OVERHAUL.  BROKEN PARTS RETURNED TO EMBRAER FOR ANALYSIS.  PART TC:  9,361.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998100900325	19981009	00325	SO  	1998	10	9	CA980706022      	1	19980620	G	3340	MA011027002931	BEACON          	WHELEN      	HRCFA1428   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					STROBE	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA			188  			11113		L163261			(CAN) STROBE BEACON FAILED AFTER 98 HOUR, THEN 3 HOURS, THEN TRIPPED CIRCUIT BREAKER AFTER 61 HOURS AND THEN AT 25 HOURS	.  UNIT RETURNED. REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900326	19981009	00326	SO  	1998	10	9	CA980706023      	1	19980624	G	5610	189715	SEAL            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					COCKPIT	LEAKING         	W				B				EMER. DESCENT           				K			FLUID LOSS                			CR	CRUISE         	1			CA								L163261			(CAN) PILOT SIDE WINDOW SEAL LEAKING PERMITTING WATER TO ENTER CIRCUIT BREAKER PANEL DIRECTLY BELOW WINDOW.  PANEL FULL 	OF WATER. BAD RADIO COMMUNICATION, INSTRUMENTS LIGHTS FLUCTUATING, WARNING LIGHTS AND LANDING GEAR LIGHTS GOING OUT.  RE	PAIRED.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900327	19981009	00327	EU  	1998	10	9	CA980706024      	1	19980619	G	2910	HTE400005	VALVE           			BAG   	JETSTM	JETSTM3212  	1500217	EU  						MCAULY	4HFR34	4HFR34C652  	NE  	HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA			11949						910207		(CAN) ON APPROACH AND FLAPS SELECTED TO 10 DEGREES.  CREW SELECTED GEAR DOWN, BUT THERE WAS NO RESPONSE, AND NO HYD PRES	SURE.  EMERGENGY LANDING CARRIED OUT AFTER GEAR PUMPED DOWN.  AIRCRAFT LANDED OK.  HYDRAULIC FLUID NOTED COMING FROM BEL	LY OF AIRCRAFT.  FURTHER INVESTIGATION FOUND A CRACKED NON-RETURN CHECK VALVE IN THE LEFT HAND HYDRAULIC PUMP DELIVERY L	INE.  THE THREADED AREA RADIUS WAS FOUND CRACKED ON THE CHECK VALVE.  PART TC:  15,045.			2	L	7	2 	4T			RT	BA15CAA 		6	C	3PNE
1998101700017	19981017	00017	WP  	1998	10	17	CA980706031      	1	19980618	G	4920		COMPRESSOR      	GARRTT      	GTCP8590F   	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					APU	FAILED          	W				O				OTHER                   				T			ENGINE CASE PENETRATION   			TX	TAXI/GRND HDL  	1			CA				7893 		35201		501379			(CAN) DURING APU OPERATION, A LOUD NOISE WAS HEARD BY THE MAINTENANCE CREW.  THE MECHANIC RIDING THE BRAKES REALIZED THE	 NOISE WAS CAUSED BY THE SUDDEN STOPPAGE OF THE APU.  AFTER A PRELIMINARY INSPECTION, IT WAS CONFIRMED A COMPRESSOR FAIL	URE OCCURRED.  THERE WAS NO FURTHER DAMAGE TO THE A/C AS MOST OF THE FRAGMENTS REMAINED IN THE APU INTAKE AREA.  APU REP	LACED.			2	L	7	2 	4R	4	T		6A6     	E282
1998101700018	19981017	00018	SW  	1998	10	17	CA980706032      	1	19980612	G	2435	230721327	NUT             	LEARSIEGLER 	230790001   	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NR 2 STARTER	LOOSE           	W				E				ENGINE SHUTDOWN         				O			OTHER                     			IN	INSP/MAINT     	1			CA						5722		P03001C			(CAN) DURING ENGINE START, THE NR 2 STOP AND FEATHER CONTROL POPPED OUT 1/4 AT 10 PERCENT RPM.  START ABORTED.  THE NUT 	ON THE V-BAND OF THE NR 2 STARTER/GENERATOR HAD BACKED OFF ALLOWING THE STARTER/GENERATOR TO ROTATE STRIKING THE ENGINE 	CONTROLS.  V-BAND HAD BEEN LOCKWIRED.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998100900334	19981009	00334	CE  	1998	10	9	CA980706033      	1	19980611	G	3260	41EN496	SWITCH          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT MLG	FAILED          	W				B	I			EMER. DESCENT           	CABIN DEPRESSURIZATION  			O			OTHER                     			CR	CRUISE         	1			CA								71769			(CAN) IN DESCENT THROUGH APPROX FL 320, CABIN ALTITUDE CLIMBED UP TO 6,000 FPM THEN REDUCED.  CABIN ALTITUDE HELD AT 13,	000 FEET DESCENDING THROUGH 13,000 FEET, CABIN DESCENDED AT SAME RATE AS AIRCRAFT.  AFTER LANDING, AIRCRAFT WAS INSPECTE	D AND FOUND THAT THE LT SQUAT SWITCH (P/N 41EN49-6) WAS INTERMITTENT.  SWITCH WAS REPLACED AND THE AIRCRAFT WAS TEST FLO	WN SERVICEABLE.			1	L	7	2 	4F	4	F		A22CE   	E1NE
1998100900339	19981009	00339	EA  	1998	10	9	CA980707015      	2	19980602	G	8520	SL134441	PIN             			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 1 CYLINDER	FRACTURED       	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			K	J	Y	FLUID LOSS                	WARNING INDICATION        	ENGINE STOPPAGE           	CL	CLIMB          	1			CA			1706 					L617761A			(CAN) SHORTLY AFTER TAKEOFF, THE CREW NOTICED A POWER FLUCTUATION ON NR 1 ENG AND SELECTED THE BOOSTER PUMP ON TO STABIL	ZE ENGINE, WITH NO IMPROVEMENT.  ENG STARTED TO SURGE, LOSS OF MANIFOLD AND OIL PRESSURE.  A SUBSTANTIAL AMOUNT OF OIL W	AS COMING FROM THE ENG COWLING, SO THE ENG WAS SHUT DOWN AND THE A/C RETURNED TO BASE.  DISASSY OF THE ENG FOUND NR 1 CY	L PISTON PIN HAD BEEN BROKEN IN THE MIDDLE OF THE CONNECTING ROD BUSHING FOR SOME TIME UNTIL THE PISTON SKIRT AND BEARIN	G BOSS HAD BROKEN AWAY DUE TO UNEVEN LOADING. THE BROKEN PARTS WERE TOSSED AROUND INSIDE THE ENG AND GOT TRAPPED UNDER T	HE LIFTER BODY TOP HATS WHICH BROKE HOLES IN THE CRANKCASE IN TWO PLACES CAUSING OIL LOSS AND LED TO ENGINE SHUT-DOWN.	1	L	7	2 	3O	3	O		A20SO   	E14EA
1998100900352	19981009	00352	CE  	1998	10	9	CA980707029      	1	19980621	G	3230	1CH1066	SWITCH          			CESSNA	425   	425         	2076018	CE  	PWA   	PT6   	PT6A112     	52043	NE  					MLG	OUT OF RIG      	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			AP	APPROACH       	1			CA								PCE12392			(CAN) ON APPROACH, PILOT SELECTED GEAR DOWN AND HAD NO NOSE GEAR INDICATION.  RECYCLED GEAR AND RECEIVED ALL GREEN LIGHT	S, BUT ALSO HAD A GEAR INTRANSIT AND HYDRAULIC PRESSURE ON LIGHT.  PULLED ALTERNATE GEAR EXTENSION WHICH PUTS 2,000 PSI 	ON DOWN SIDE AND LANDED OK.  FOUND DOWNLOCK MICROSWITCH OUT OF RIG.  ADJUSTED AIRCRAFT SERVICEABLE.				1	L	7	2 	3T	3	T	RT	A7CE    	E4EA
1998100900353	19981009	00353	EA  	1998	10	9	CA980707030      	2	19980606	G	7230		BLADE           			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COMPRESSOR	SHIFTED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			7156 	678  				PCE81521			(CAN) STARTER WOULD ENGAGE ON START, BUT ENGINE WOULD NOT ROTATE.  STARTER WAS REMOVED AND IT WAS FOUND THE NG WOULD NOT	 ROTATE.  ENGINE WAS SPLIT AT THE C-FLANGE AND THE N1 WHEEL WOULD NOT ROTATE AND A LOUD GRINDING SOUND WAS HEARD COMING 	FROM THE COMPRESSOR SECTION.  THE ENGINE WAS RETURNED TO PRATT FOR INVESTIGATION.  IT IS BELIEVED THE 3RD STAGE COMPRESS	OR BLADES HAD SHIFTED CAUSING THE COMPRESSOR TO LOCK-UP.  PART TC:  583.			1	L	7	2 	4T	4	T		A24CE   	E4EA
1998073100395	19980731	00395	EU  	1998	7	31	CA980707031      	1	19980703	G	2497		WIRE            			ZLIN  	242   	Z242L       	9970204	EU  										AC SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) SAMPLES OF ELECTRICAL WIRING TAKEN FROM THE AIRCRAFT APPEAR TO BE OF AN INFERIOR QUALITY AND ARE CURRENTLY BEING I	NVESTIGATED					1	L	7	1 	3O			0	A76EU
1999031200246	19990312	00246	EA  	1999	3	12	CA980707058      	1	19980610	G	5341	C3FS145	TIE BAR         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					WING ATTACH	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P325395			(CAN) INSPECTION PER CF82-26R1 CORROSION WAS FOUND ON END FITTINGS BEYOND .040 INCH.  TIE BAR REPLACED IAW WITH SB 3/37.						1	H	7	1 	3R	3	R		A815    	E142
1999031200247	19990312	00247	EA  	1999	3	12	CA980707059      	1	19980610	G	5720	S3FS876	BRACKET         			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					WING SPAR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P325395			(CAN) THE RIGHT HAND FORWARD REAR SPAR CARRY THROUGH BRACKET FOUND CRACKED 1.50 INCHES AND LEFT BRACKET CRACKED .50 INCH	.  RIGHT HAND BRACKET REPLACED, AND LEFT BRACKET REINFORCED.					1	H	7	1 	3R	3	R		A815    	E142
1999031200248	19990312	00248	EA  	1999	3	12	CA980707060      	1	19980610	G	2750	C3CF1027	PUSH ROD        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	S3H1G       	52016	NE  					TE FLAPS	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P325395			(CAN) THE RIGHT HAND OUTBOARD FLAP PUSH ROD END DID NOT ROTATE PROPERLY INDICATING LOOSE RIVETS OR ENLARGED HOLES.  RIVE	TS REPLACED.					1	H	7	1 	3R	3	R		A815    	E142
1999031200249	19990312	00249	EA  	1999	3	12	CA980707061      	1	19980623	G	3246	8A0206701	FITTING         	WIPLINEINC  	8000        	DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					FLOAT	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			400  	400  		80074					(CAN) FLOAT BRACE WIRES AT THE FRONT WERE LOOSENED OFF DURING INSPECTION.  THE BOLT SECURING THE FITTING FOUND LOOSE.						1	H	7	1 	3R	3	R		A815    	5E2
1999021200157	19990212	00157	GL  	1999	2	12	CA980707066      	2	19980621	G	7530	24096200C	GASKET          			CVAC  	440   	440         	2422902	WP  	ALLSN 	501D  	501D13      	03004	GL  					NR 2 ENGINE	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA								501289			(CAN) DURING CLIMB AT 7,000 FEET, TWO ENGINE FIRE WARNING SYSTEMS ACTIVATED ZONE TWO.  ENGINE FIRE BOTTLES BLOWN AND SHU	T DOWN IAW EMERGENCY PROCEDURES, AIRCRAFT LANDED OK.  BLOWN GASKET DOWNSTREAM OF THE UPPER 14TH STAGE BLEED AIR CHECK VA	LVE.  GASKET AND CLAMP REPLACED, AIRCRAFT GROUND RUN OK.				2	L	7	2 	4R	4	T		6A6     	E282
1998120400041	19981204	00041	SW  	1998	12	4	CA980713010      	1	19980626	G	6320	212040054013	CASE ASSY       			BELL  	212   	212         	1181420	SW  										TRANSMISSION	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						A1202631					(CAN) MAIN TRANSMISSION SUPPORT CASE RECEIVED FROM SUPPLIER IS BELIEVED TO BE UNAPPROVED MILITARY PART.  BELL ADVISED TH	EY HAVE NO RECORD OF THAT S/N PART.					1	G	7	1 	4U				H4SW
1998073100396	19980731	00396	EU  	1998	7	31	CA980713012      	1	19980619	G	2910	HTE400005	VALVE           			BAG   	JETSTM	JETSTM3212  	1500217	EU  										HYDRAULIC SYS	CRACKED         	W		A		L				ABORTED APPROACH        				K	J		FLUID LOSS                	WARNING INDICATION        		AP	APPROACH       	1			CA											(CAN) ON APPROACH WHEN FLAPS SELECTED, THEY DID NOT GO DOWN.  GEAR SELECTED DOWN AND ONLY THE NOSE GEAR EXTENDED AND IND	ICATED DOWN AND LOCKED.  TOWER INFORMED.  EMERGENCY EXTENSION CARRIED OUT AND AIRCRAFT LANDED OK.  CHECK VALVE IN MAIN H	YDRAULIC SYSTEM HAD CRACKED ALLOWING FLUID TO LEAK. VALVE HAD A RADIAL CRACK RUNNING AROUND THE BODY ABOUT ONE INCH LONG	.  VALVE LOCATED ON THE MAIN PRESSURE LINE FROM THE LEFT HYDRAULIC PUMP.  MOST FLUID HAD PUMPED OVERBOARD.  EMERGENCY SY	STEM WAS OK.		2	L	7	2 	4T			RT	BA15CAA
1999043000075	19990430	00075		1999	4	30	CA980713015      	4	19980618	G	3425		FLIGHT DIRECTOR 			DHAV  	DHC8  	DHC8311     	1386006	EA  										E/E BAY	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				N			FALSE WARNING             			AP	APPROACH       	1			CA											(CAN) PILOT REPORTED THAT FLIGHT DIRECTOR WOULD NOT DISENGAGE AT 250 QFE ON APPROACH DESPITE SEVERAL ATTEMPTS.  AT APPRO	XIMATELY 150 QFE, YAW DAMPER SWITCHED LEFT TO RIGHT AND AT 80 QFE, AUTOPILOT WAS REPORTED TO ENGAGE UNCOMMANDED.  FIRST 	OFFICER DISENGAGED AUTOPILOT ON CONTROL PANEL AND AIRCRAFT LANDED OK.				2	H	7	2 	4T			RT	A13NM
1999032600127	19990326	00127		1999	3	26	CA980713016      	4	19980622	G	3414	211401150	INDICATOR       			DHAV  	DHC8  	DHC8311     	1386006	EA  										AIRSPEED	FLUCTUATING     	W				O				OTHER                   				G			MULTIPLE FAILURE          			CR	CRUISE         	1			CA											(CAN) JUST AFTER DESCENT, NR 1 ASI READINGS BECAME UNRELIABLE, FLUCTUATING BETWEEN ZERO-220 KNOTS, FLIGHT DIRECTOR AND Y	AW DAMPER DISCONNECTED.  FLUCTUATION STOPPED AFTER 2 OR 3 MINUTES.					2	H	7	2 	4T			RT	A13NM
1999012900198	19990129	00198	WP  	1999	1	29	CA980713030      	2	19980626	G	7297	730222	WIRE            		31039711    	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					CHIP DETECTOR	CHAFED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								P54266			(CAN) SHORTLY AFTER TAKEOFF, THE LEFT CHIP DETECTOR ANNUNCIATOR LIGHT CAME ON.  AIRCRAFT RETURNED TO BASE.  CHIP DETECTO	R WIRE FOUND RUBBING AGAINST THE ENGINE NEAR THE RIGHT HAND MOUNT.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999012900200	19990129	00200	NM  	1999	1	29	CA980714019      	1	19980709	G	3320	7702501	CONNECTOR       		641300      	DHAV  	DHC8  	DHC8301     		NM  										COCKPIT	FAILED          	W				O				OTHER                   				M	B	J	OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  	WARNING INDICATION        	IN	INSP/MAINT     	1			CA											(CAN) AFTER COMPLETING SB A8-33-39, THE OPERATOR REPORTED THEY FOUND 3 BURNT OVERHEAD BIN CONNECTORS, PINS 3 AND 12, AND	 ALSO REPORTED SMOKE IN THE CABIN.  FOLLOW-UP INFORMATION INDICATED THAT SOME PINS HAD BEEN INCORRECTLY CRIMPED.   NEW P	INS AND SOCKETS WERE INSTALLED.				2	H	7	2 	4T			RT	A13NM
1999021200898	19990212	00898	EA  	1999	2	12	CA980714021      	1	19980623	G	5610	601R330334	WINDOW          			CNDAIR	CL600 	CL6002B19   		EA  										COCKPIT	SHATTERED       	W				A				UNSCHED LANDING         				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			4    								(CAN) AT FLT LEVEL 300, AND 220 KNOTS, INDICATED THE COPILOT SIDE WINDOW SHATTERED.  AIRCRAFT LANDED OK.						2	L	7	2 	4F			RT	A21EA
1999012900201	19990129	00201	SW  	1999	1	29	CA980714031      	1	19980707	G	2701	KF16B	BEARING         		2771050013  	SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	CONTROL COLUMN	STIFF           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									DRG457785		(CAN) CONTROL COLUMN FELT STIFF DURING AILERON MOVEMENT.  BOTH BEARINGS FOUND STIFF IN COPILOT'S WHEEL.						2	L	7	2 	4T			RT	A8SW    		6	C	P61GL
1999012900202	19990129	00202	SW  	1999	1	29	CA980720011      	1	19980707	G	3297	602EN6026	WIRE            		2751000065  	SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					RT MLG	BROKEN          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								P54151			(CAN) AFTER GEAR SELECTION, RT GEAR HAD UP POSITION SNAG.  GEAR EXTENDED OK AND RETURNED TO BASE.  WIRES FOUND BROKEN ON	 GEAR-UP LIMIT SWITCH.  ALSO FOUND A BROKEN WIRE ON THE UP POSITION SWITCH.  WIRES SEPARATED FROM SWITCH DUE TO AGE ACCO	RDING TO SUBMITTER.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999031200259	19990312	00259	EU  	1999	3	12	CA980724020      	1	19980709	G	3230	1379305A155	FLEX HOSE       			BAG   	JETSTM	JETSTM3212  	1500217	EU  						ROTOL	R333	R333482F12  	GL  	LT MLG	CRACKED         	W				L				ABORTED APPROACH        				K			FLUID LOSS                			AP	APPROACH       	1			CA			11201						DRG32883		(CAN) THE LEFT GEAR RETRACT FLEX HOSE CRACKED AND BURST AT THE FIXED END CAUSING FLUID LOSS FROM THE MAIN SYSTEM.   EMER	GENCY SYSTEM USED TO EXTEND GEAR.  PART TC: 11,725.					2	L	7	2 	4T			RT	BA15CAA 		6	C	P61GL
1998120400044	19981204	00044	WP  	1998	12	4	CA980804009      	1	19980716	G	2435	230321481	FAN             	LEARSIEGLER 	23032010    	HUGHES	369   	369HS       	4470728	WP  	ALLSN 	250C  	250C18      	03011	GL  					START/GEN	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						14874		CAE802285B			(CAN) IN SHOP FOR REPAIR, LEAR SIEGLER STARTER/GENERATOR HAD AN APC FAN P/N 1503G1107 INSTEAD OF THE LEAR SIEGLER FAN P/	N 23032-1481.					1	G	7	1 	3U	3	U		H3WE    	E4CE
1998120400045	19981204	00045	SW  	1998	12	4	CA980804010      	1	19980716	G	2435	13654	BEARING         	LEARSIEGLER 	23032018    	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					START/GEN	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						13654		822444			(CAN) STARTER/GENERATOR IN SHOP FOR OVERHAUL DUE TO 'WORN BEARINGS' ON DISASSEMBLY, UNAPPROVED BEARINGS FOR THIS UNIT WE	RE FOUND WORN AND DRY.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998120400046	19981204	00046		1998	12	4	CA980804011      	4	19980715	G	2562	C4000	ELT             		C4000       															CABIN	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						402417					(CAN) ON ANNUAL TEST, ELT WOULD NOT TRANSMIT.   RETURNED TO POINTER FOR REPAIR.
1998111300594	19981113	00594	CE  	1998	11	13	CA980804025      	1	19980717	G	2110	23801555	HOUSING         		23801555    	LEAR  	25    	25B         	5170511	CE  										COMPRESSOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						538					(CAN) DURING TROUBLESHOOTING FOR A LOW COOLING, UNIT FAILED WITH A BANG.  INSPECTION SHOWED A HOLE IN THE HOUSING SIDE. 	 SUBMITTER SUSPECTS THAT THE UNIT WAS LOW ON OIL FOR A WHILE AND OVERHEATED.					2	L	7	2 	4J				A10CE
1998082800297	19980828	00297	EA  	1998	8	28	CA980804028      	2	19980722	G	8510		GEARBOX         			PIPER 	PA31  	PA31P       	7103120	SO  	LYC   	O541  	TIGO541E1A  	41539	EA  					NOSE	SEPARATED       	W		A		A	B			UNSCHED LANDING         	EMER. DESCENT           			D	K	Y	INFLIGHT SEPARATION       	FLUID LOSS                	ENGINE STOPPAGE           	CR	CRUISE         	1			CA			1247 					RL51262			(CAN) NOSE GEAR BOX ASSEMBLY AND PROPELLER BROKE FREE OF THE ENGINE IN FLIGHT AND FELL AWAY. NO FURTHER AIRCRAFT DAMAGE,	 THE AIRCRAFT LANDED SAFELY ON THE REMAINING ENGINE.					1	L	7	2 	3O	3	O		A8EA    	E19EA
1998111300595	19981113	00595	SW  	1998	11	13	CA980804033      	1	19980721	G	5610	3600438	WINDSCREEN      			GULSTM	690TP 	690A        	0141722	SW  	GARRTT	TPE331	TPE3315     	01514	WP  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			695  					P06353			(CAN) 30 TO 40 SECONDS AFTER WINDSHIELD HEAT WAS TURNED ON TO LOW POSITION WITH AIRCRAFT CLIMBING THROUGH 18,000 FEET, T	HE WINDSHIELD DEVELOPED SEVERAL CRACKS ALL COMING FROM THE AREA OF THE HEAT STRIP ON LOWER SECTION OF SCREEN.  WINDSHIEL	D INSTALLED IN MARCH OF '96, AND HAD ONLY 695 HOURS ON IT.				1	H	7	2 	3T	4	T		2A4     	E4WE
1998111300597	19981113	00597	CE  	1998	11	13	CA980810002      	1	19980721	G	3213	508103327	BRACE ASSY      			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA				6150 				P50876			(CAN) OLEO WENT FLAT AFTER CROSS WIND LANDING.  CREW NOTICED HYDRAULIC FLUID LEAKING FROM OLEO STRUT.  CLOSER INSPECTION	 REVEALED CRACKED HOUSING.  PART TC:  4,824.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1999031200261	19990312	00261	NM  	1999	3	12	CA980810004      	1	19980729	G	2420	RWR81S1R00FS	RESISTOR        		51539008D   	DHAV  	DHC8  	DHC8*       		NM  										GCU	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						7153					(CAN) GCU RESISTOR FOR THE RESET CIRCUIT WAS FOUND TO BE UNAPPROVED.						2	H	7	2 	4T			RT	A13NM
1998082800298	19980828	00298	EA  	1998	8	28	CA980810007      	2	19980730	G	8520		TAPPET          								LYC   	O320  	O320D2A     	41508	EA  					NR 4 CYLINDER	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L1754639A			(CAN) PILOT REPORTED A ROUGH RUNNING ENGINE.  INITIAL INVESTIGATION FOUND THE HYDRAULIC TAPPET BODY AND SYSTEM HAD FAILE	D ON THE NR 4 CYLINDER INTAKE SIDE. THE ENGINE IS BEING SENT FOR TEARDOWN AND INVESTIGATION.  FURTHER REPORT TO FOLLOW.										3	O			E274
1998100900364	19981009	00364		1998	10	9	CA980810008      	4	19980728	G	2563	SB533	DRAG CHUTE      			CESSNA	500   	500CESSNA   	2076602	CE  										FUSELAGE	SEVERED         	W				C				ABORTED TAKEOFF         				D			INFLIGHT SEPARATION       			TO	TAKEOFF        	1			CA			933  								(CAN) DURING AN ABORTED TAKEOFF, THE DRAG CHUTE WAS DEPLOYED AND STARTED TO AGGRESSIVELY SLOW THE AIRCRAFT.  THEN THE RI	SOR CORD FAILED APPROXIMATELY 12 INCHES FROM WHERE IT ATTACHES THE AIRCRAFT RESULTING IN THE DESTRUCTION OF THE AIRCRAFT	.				1	L	7	2 	4F				A22CE
1998111300598	19981113	00598	NM  	1998	11	13	CA980810011      	1	19980730	G	2910	659603	VALVE           	VICKERS     	659603      	DHAV  	DHC8  	DHC8102     	2809003	NM  										SPOILER	FAILED          	W				O				OTHER                   				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			4769 			1212					(CAN) PILOT REPORTED LOSS OF OUTBOARD SPOILERS, FOLLOWED SHORTLY AFTER BY INBOARD SPOILERS.   ALSO, LOW PRESSURE CAUTION	 LIGHT ON FOR OUTBOARD SPOILERS.  PILOT NOTED FULL MOVEMENT ON CONTROL WHEEL WITH NO BINDING.  FLIGHT SPOILER VALVES IN 	BOTH NR 1 AND NR 2 SYSTEMS REPLACED.  VALVES BEING RETURNED TO MANUFACTURER FOR INVESTIGATION.				2	H	7	2 	4T			RT	A13NM
1998111300601	19981113	00601	SO  	1998	11	13	CA980811004      	1	19980729	G	2910	2057010122	LATCH           			CURTIS	C46   	C46FAIRLIFT 		SO  	PWA   	R2800 	R280051     	52026	NE  	HAMSTD	23E	23E50       	NE  	HYDRAULIC SYS	DAMAGED         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA								4138160	FE1178		(CAN) DURING CLIMB, PILOT NOTICED THAT BOTH HYDRAULIC PUMPS WERE CYCLING MORE THAN NORMAL, BUT ALSO NOTICED THAT THE HYD	RAULIC FLUID WAS MAINTAINING ITS LEVEL.  AIRCRAFT LANDED AND PILOT NOTICED FLUID BY THE TAIL WHEEL WITH NO REAL SIGNIFIC	ANT LOSS OF FLUID.  O-RING ON UPLOCK HAD BLOWN.  UPLOCK REPLACED.				2	L	7	2 	4R	4	R		3A2     	5E8	6	C	P603
1998111300602	19981113	00602	EU  	1998	11	13	CA980811005      	3	19980717	G	6111	C18818A	BLADE           													MUHBR	MTV	MTV3BC      	EU  	PROPELLER	DELAMINATED     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1945 			LC4939			94277		(CAN) FIBERGLASS DELAMINATED ON THE PROPELLER BLADE AT THE BLADE ROOT. THE PROPELLER BLADE WAS REPAIRED PER THE MAINTENA	NCE MANUAL.															5	C	USSR
1998111300603	19981113	00603	GL  	1998	11	13	CA980811006      	3	19980731	G	6111		BLADE           			CESSNA	172   	172K        	2072430	CE  						MCAULY	1C172	1C172MTM    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									E14315		(CAN) PROPELLER CORRODED.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998111300604	19981113	00604	GL  	1998	11	13	CA980811007      	3	19980716	G	6111		BLADE           			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1272 						MC013		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND.						1	H	7	1 	3O			NT	3A12    		5	N	P910
1998111300605	19981113	00605	GL  	1998	11	13	CA980811008      	3	19980730	G	6111	57A2202	BEARING         			CESSNA	172   	172K        	2072430	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YR1     	GL  	PROP BLADE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1187 	936  				L112636	CH17349		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADE BEARING WAS FOUND BROKEN.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P920
1998111300606	19981113	00606	CE  	1998	11	13	CA980811009      	1	19980717	G	3213	112230561	FITTING         		567850A     	BEECH 	18    	3N          	1151042	CE  	PWA   	R985  	R985AN14B   	52008	NE  					LT STRUT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2000 					JP206571			(CAN) LEFT HAND FRONT STRUT FOUND TO HAVE BROKEN FITTING AT TOP INBOARD FITTING.  ALSO OUTBOARD FITTING FOUND CRACKED.						1	L	7	2 	3R	3	R		A765    	5E1
1998111300607	19981113	00607	SO  	1998	11	13	CA980811010      	2	19980724	G	8530		CYLINDER        			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4000 	1361 				11535D6A			(CAN) LOW COMPRESSION ON NR 2 CYLINDER.  INSPECTION FOUND A STICKING EXHAUST VALVE AND THE CYLINDER CRACKED SLIGHTLY FRO	M THE EXHAUST SEAT TO THE SPARK PLUG.  THE CYLINDER WAS REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E253
1998111300609	19981113	00609	CE  	1998	11	13	CA980811013      	1	19980624	G	3222	A300792	BEARING         		5042000230  	CESSNA	402   	402B        	207590P	CE  										NLG	SEIZED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA											(CAN) WHILE TAXIING, THE PILOT FELT THAT THE A/C WANTED TO TURN RIGHT, HE STOPPED AND FOUND THE NOSE WHEEL FORK BROKEN D	UE TO OVERHEAT AND WEAR CAUSED BY THE AXLE SPINNING INSTEAD OF THE BEARING TURNING.  REPLACED.					1	L	7	2 	3O				A7CE
1998111300611	19981113	00611	SO  	1998	11	13	CA980811015      	2	19980731	G	8530	641370A8	CYLINDER        			CESSNA	337   	P337H       	2075731	CE  	CONT  	O360  	TSIO360CB   	17025	SO  	MCAULY	2AF34C	D2AF34C305  	GL  	ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				218  				230693R	870004		(CAN) DURING FLIGHT, THE PILOT HEARD A LOUD NOISE, COMING FROM THE REAR ENGINE, FOLLOWED BY A DROP IN MANIFOLD PRESSURE 	AND ON LANDING A REDUCTION IN OIL PRESSURE.  THE ENGINE SHUTDOWN ON THE RUNWAY.  INSPECTION FOUND THE NR 4 CYLINDER SPLI	T AT THE BARREL.				1	H	7	2 	3O	3	O		A6CE    	E9CE	5	C	P5EA
1998111300613	19981113	00613	EA  	1998	11	13	CA980814002      	2	19980722	G	8520	SL13792	SEAL            			ROBSIN	R22   	R22         	7640102	WP  	LYC   	O320  	O320B2C     	41508	EA  					CRANKSHAFT	LEAKING         	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA			278  					L1794639A			(CAN) THE SUBMITTER REPORTS AN INCREASE IN OIL LEAKS, IN CRANKSHAFT OUTPUT SEALS, IN RECENTLY OVERHAULED ENGINES.  IN A 	PREVIOUS CASE, THE SEAL WAS FOUND LEAKING AND IN THIS CASE, THE SEAL WAS FOUND UNSEATED (HANGING LOOSE ON THE OUTPUT SHA	FT).  IN BOTH CASES, THE SEALS WERE LACKING THE SEALANT THAT SHOULD BE USED DURING INSTALLATION.				1	G	7	1 	3O	3	O		H10WE   	E274
1998111300614	19981113	00614	NE  	1998	11	13	CA980814003      	2	19980719	G	8520	7627DG	CAM             			CNDAIR	CL215 	CL2151A10   		EA  	PWA   	R2800 	R2800*      	52026	NE  					ENGINE	WORN            	W				E				ENGINE SHUTDOWN         				E	Y		VIBRATION/BUFFET          	ENGINE STOPPAGE           		AP	APPROACH       	1			CA				424  				P35970			(CAN) NR 2 AND  NR 4 CYLINDER VALVES WERE NOT OPERATING, INVESTIGATION FOUND THE FRONT CAM LOBES WERE MISSING.  THE CAM 	WAS REPLACED AND SO WERE THE NR 2 AND NR 4 CYLINDERS.  THE ENGINE WAS RETURNED TO SERVICE.  AFTER 77 HOURS OF OPERATION,	 THE REAR CAM LOBES WERE WORN AWAY.  THE ENGINE WAS REPLACED AND SENT FOR OVERHAUL.				2	H	7	2 	4R	4	R		A14EA   	5E8
1998111300615	19981113	00615	CE  	1998	11	13	CA980814004      	1	19980730	G	3250	24670036	BUNGEE          		24670036    	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	NLG STEERING	FAILED          	W		A		K				NONE                    				F			FLT CONT AFFECTED         			TO	TAKEOFF        	1			CA			5100 					L2457636A	797859		(CAN) AFTER TAKEOFF, THE RUDDER PEDALS JAMMED IN THE FULL LEFT POSITION.  CONTINUED CLIMB TO ALTITUDE AND WAS ABLE TO UN	JAM THE PEDALS.  CARRIED OUT NORMAL LANDING.  ON GROUND AND STOPPED PEDALS JAMMED IN FULL LEFT POSITION.  THE STEERING B	UNGEE SHAFT BROKEN AND PULLED APART.  REPLACED.				1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
1998111300617	19981113	00617	NE  	1998	11	13	CA980814006      	2	19980805	G	8520	3592	ROD             			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA				794  				19356			(CAN) AIRCRAFT LANDED DUE TO LOSS OF ENGINE POWER. INSPECTION FOUND THE NR 3 CYLINDER CONNECTING ROD WAS BROKEN.  PILOT 	REPORTED A HYDRAULIC LOCK 14-19 HOURS EARLIER, AFTER THE FUEL PRIMER SYSTEM WAS WORKED ON.  REMOVAL OF NR 3 CYLINDER REV	EALED THE CENTER PRIMER INSERT MISSING.  SUBMITTER STATED THIS POSSIBLY ALLOWED ALL PRIME TO BE DIRECTED TO THIS CYLINDE	R.  MAINTENANCE CREW REPORTED THEY PULLED THE PROP THROUGH SEVERAL TIMES AFTER THE PRIME WAS WORKED ON.  THE ENGINE WAS 	REPLACED.		1	H	7	1 	3R	3	R		A806    	5E1
1998111300618	19981113	00618	EA  	1998	11	13	CA980814007      	2	19980806	G	8530		EXHAUST VALVE   			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  					ENGINE	FAILED          	W				A				UNSCHED LANDING         				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CR	CRUISE         	1			CA								L2284036A			(CAN) ENGINE STARTED RUNNING ROUGH AND LOSING POWER, SO AIRCRAFT LANDED.  POST-FLIGHT INSPECTION FOUND THE NR 2 CYLINDER	 EXHAUST VALVE BROKEN AT THE STEM.  COMPRESSION CHECK OF ALL CYLINDERS WAS LOW.  ALL CYLINDERS WERE REMOVED.  NR 1, NR 3	, AND NR 4 CYLINDERS WERE CRACKED.  METAL WAS FOUND IN THE OIL FILTER. THE ENGINE WAS REMOVED AND WILL BE EITHER REPAIRE	D OR REPLACED.			1	L	7	1 	3O	3	O		2A13    	E286
1998111300619	19981113	00619	CE  	1998	11	13	CA980814008      	1	19980806	G	3411	5032426913	LINE            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					PITOT SYSTEM	LEAKING         	W				K				NONE                    				L	K		NO TEST                   	FLUID LOSS                		IN	INSP/MAINT     	1			CA								PCE50201			(CAN) AFTER FUSELAGE STRINGER REPAIR, A LEAK CHECK OF THE PITOT STATIC SYSTEM WAS CARRIED OUT AND WAS FOUND TO HAVE AN E	XCESSIVE LEAK RATE.  A FURTHER CHECK REVEALED THAT THE CAUSE WAS DUE TO PIN HOLES IN EACH AFT STATIC LINE.  THE PIN HOLE	S WERE ATTRIBUTED TO CORROSION CAUSED BY WATER FROM A LEAKING WINDOW SEAL.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998111300620	19981113	00620		1998	11	13	CA980814010      	4	19980728	G	6122	A210786	GOVERNOR        													HOFMAN	HOV352	HOV352F     	NE  	PROPELLER	LEAKING         	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA				680  					H195		(CAN) SUBMITTER REPORTS OIL LEAKING FROM PROP GOVERNOR MOUNTING GASKET.  SUBMITTER STATES THE OIL LEAK IS CAUSED BY THE 	MOUNTING BOLTS NOT ALLOWING THE GASKET TO FIT FLAT TO THE MOUNTING PAD; THUS, ALLOWING THE GASKET TO LIFT AND THE OIL TO	 ESCAPE.														5	C	TP5BO
1998111300630	19981113	00630	GL  	1998	11	13	CA980818012      	2	19980807	G	7323	23070106	GOVERNOR        	BENDIX      		BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				33   		23992		CAE890139			(CAN) THE GOVERNOR WAS OPERATING OK, PRIOR TO SHUTDOWN WITH THE N2 RANGE FROM 97 PERCENT TO 100 PERCENT RPM.  SHORTLY AF	TER ON RESTART, THE N2 OPERATING RANGE HAD GONE TO 100 PERCENT TO 103 PERCENT RPM AND THE PILOT COULD NOT BEEP THE ENGIN	E BELOW 102 PERCENT.  THE CAUSE OF THE GOVERNOR FAILURE IS UNKNOWN.				1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400099	19980904	00099	SO  	1998	9	4	CA980818013      	2	19980810	G	8520	627307A10	CRANKCASE       			CESSNA	150   	A150M       	2071831	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			IN	INSP/MAINT     	1			CA				280  				252018	K18431		(CAN) NO ENGINE OIL PRESSURE INDICATION ON STARTUP.  ENGINE WAS SHUTDOWN.  REAR CASE REMOVED AND INSPECTION FOUND WHAT A	PPEARED TO BE A CRACK ON THE REAR LOWER LEFT OF THE CRANKCASE.  THE PART WAS SENT FOR EVALUATION.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998111300639	19981113	00639	EA  	1998	11	13	CA980818023      	2	19980807	G	8530	17F21186	ROCKER ARM      		W12966      	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				966  				L715916A			(CAN) WHILE CHANGING AN INTAKE PUSH ROD TO COMPLY WITH LYCOMING 400 HOUR VALVE TRAIN INSPECTION (TAPPET CLEARANCE), THE 	PUSH ROD WAS FOUND TO HAVE A O.020 INCH DEEP SCORE AROUND THE CIRCUMFERENCE, A HALF INCH FROM THE TOP.  CLOSER INSPECTIO	N FOUND THE SCORING CAUSED BY AN EXHAUST ROCKER INSTALLED IN THE INTAKE POSITION.  THE INTAKE ROCKER PART NUMBER HAD BEE	N ETCHED ON IT.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1998111300640	19981113	00640		1998	11	13	CA980818025      	1	19980804	G	5520		BRACKET         		115610010325															ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PERFORMED SB 2145 AND FOUND A CRACK AT ELEVATOR SUPPORT BRACKET TAPER PIN  HOLE.
1998111300641	19981113	00641	CE  	1998	11	13	CA980818026      	1	19980810	G	2612		FIRE LOOP       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NR 2 ENGINE	LOOSE           	W				K				NONE                    				J			WARNING INDICATION        			CL	CLIMB          	1			CA								PCEPS0191			(CAN) DURING CLIMB, THE FLIGHT CREW NOTICED A MOMENTARY ILLUMINATION OF THE NR 2 ENGINE FIRE ANNUNICATOR.  MAINTENANCE F	OUND TWO CLAMPS UNSECURED ALLOWING THE FIRE LOOP TO GROUND OUT DEPENDING ON THE AIRCRAFT FLIGHT ATTITUDE.  THE CLAMPS WE	RE RE-SECURED AND THE FIRE LOOP TESTED SERVICEABLE.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998111300642	19981113	00642	CE  	1998	11	13	CA980818027      	1	19980810	G	3010		TUBE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					DEICE SYSTEM	MELTED          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA								PCEPS0191			(CAN) CREW REPORTED AIRFOIL LIGHT ILLUMINATED DURING TAIL CYCLE.  MAINTENANCE FOUND THAT THE DEICE TUBING FOR THE TAILET	S HAD MELTED DUE TO THE ROUTING BY THE LOGO LIGHTS. TUBING REPLACED AND RE-ROUTED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999031200263	19990312	00263	EA  	1999	3	12	CA980818028      	1	19980729	G	5320	C2FS3871	BOLT            		C2FS3231A   	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUSELAGE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								15290			(CAN) RIGHT HAND LOWER POST BOLT FOUND VERY LOOSE AND BADLY WORN.  UNIT THAT BOLT ATTACHES TO ALSO WORN.  SAME ON LEFT S	IDE.					1	H	7	1 	3R	3	R		A806    	5E1
1999031200264	19990312	00264	NM  	1999	3	12	CA980818029      	1	19980805	G	2133	9503124D0100	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  										OUTFLOW VALVE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8035 								(CAN) FOUND THE NR 4 DUMP LINE FOR THE SAFETY OUTFLOW VALVE CRACKED DUE TO AGE.   PART TC:  6,370.						2	H	7	2 	4T			RT	A13NM
1998111300643	19981113	00643	CE  	1998	11	13	CA980818031      	1	19980811	G	5610	1143840202	WINDSHIELD      			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			21698					PCE32139			(CAN) DURING FLIGHT, A LOUD NOISE WAS HEARD.  A VISUAL CHECK REVEALED COPILOT'S WINDOW HAD CRACKED.  AIRCRAFT RETURNED T	O DEPARTURE BASE. MAINTENANCE CHECK REVEALED ONLY OUTER PLY OF WINDOW HAD CRACKED.  AIRCRAFT FERRIED BACK TO MAINTENANCE	 BASE PER MEL AND WINDOW WAS CHANGED.  PART TC: 31,570.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998090400101	19980904	00101	EA  	1998	9	4	CA980819001      	2	19980702	G	7250	3006146	BEARING         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 1 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E	J	Y	VIBRATION/BUFFET          	WARNING INDICATION        	ENGINE STOPPAGE           	CR	CRUISE         	1			CA								CPPS61812			(CAN) CHIP DETECTOR LIGHT ILLUMINATED FOLLOWED BY ENGINE VIBRATION, ON NR 1 ENGINE.  ENGINE WAS SECURED.  POST-FLIGHT IN	SPECTION FOUND THE NR 3 BEARING HAD FAILED CAUSING METAL CONTAMINATION TO THE C-BOX.  THE BEARING WAS PREVIOUSLY A RE-MA	NUFACTURED BII BEARING.  THE BEARING HAD BEEN INSTALLED 2000 HOURS PREVIOUSLY.  THE BEARING HAS BEEN SENT FOR FURTHER EV	ALUATION.  PRATT & WHITNEY CANADA HAS NO RECORD OF THE BEARING (SERIAL NUMBER X984) AND CONCLUDED EITHER THE BEARING IS 	A VERY OLD PRATT & WHITNEY CANADA (ORIGINALLY) BEARING OR IS A BOGUS PART.		1	G	7	1 	4U	4	U		H4SW    	E22EA
1998111300646	19981113	00646	EA  	1998	11	13	CA980819002      	2	19980416	G	8520		CRANKSHAFT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	PITTING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1668 				L1124439A	MI042		(CAN) PITTING CORROSION FOUND DURING INSPECTION IN ACCORDANCE WITH AD 98-02-08.  LIQUID PENETRANT INSPECTION CARRIED OUT	.  NO CRACKS EVIDENT.  CRANKSHAFT IS ON 100 HOUR RE-INSPECTION CYCLE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998111300647	19981113	00647	EA  	1998	11	13	CA980819003      	2	19980319	G	8520		CRANKSHAFT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	PITTING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1348 				L1227939A	83736		(CAN) PITTING CORROSION FOUND DURING INSPECTION IN ACCORDANCE WITH AD 98-02-08.  LIQUID PENETRANT INSPECTION CARRIED OUT	.  NO CRACKS EVIDENT.  CRANKSHAFT IS ON 100 HOUR RE-INSPECTION CYCLE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998111300648	19981113	00648	EA  	1998	11	13	CA980819004      	2	19980420	G	8520		CRANKSHAFT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	PITTING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1041 				L958839A	BB080		(CAN) PITTING CORROSION FOUND DURING INSPECTION IN ACCORDANCE WITH AD 98-02-08.  LIQUID PENETRANT INSPECTION CARRIED OUT	.  NO CRACKS EVIDENT.  CRANKSHAFT IS ON 100 HOUR RE-INSPECTION CYCLE.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998111300649	19981113	00649	EA  	1998	11	13	CA980819005      	2	19980731	G	7530	909700443	SENSE LINE      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					RT ENGINE	CRACKED         	W				E	H	A		ENGINE SHUTDOWN         	DEACTIVATE SYST/CIRCUITS	UNSCHED LANDING         		J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CL	CLIMB          	1			CA								PCE50944			(CAN) ON MEDIVAC DEPARTURE, RIGHT HAND BLEED AIR FAILURE LIGHT CAME ON SHORTLY AFTER TAKE-OFF.  RIGHT ENGINE SHUT DOWN. 	 AIRCRAFT RETURNED TO BASE.  MAINTENANCE CHECK REVEALED RIGHT BLEED AIR PRESSURE ANNUNCIATOR SENSE LINE CRACKED UNDER FL	OOR AT BLEED AIR MANIFOLD.  LINE REPAIRED AND SYSTEM CHECKED SERVICEABLE.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998111300650	19981113	00650	CE  	1998	11	13	CA980819006      	1	19980807	G	3230	1153800025	MOTOR           		1153800025  	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA				478  		1247		PCE50045			(CAN) LANDING GEAR (LDG) WOULD NOT RETRACT ON TAKEOFF.  LANDING GEAR MANUALLY EXTENDED AND AIRCRAFT LANDED SAFELY.  MAIN	TENANCE CHECK REVEALED LANDING GEAR RETRACT MOTOR HAD FAILED.  PART TC:  415.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1998090400102	19980904	00102	EA  	1998	9	4	CA980819009      	2	19980807	G	7200		ENGINE          			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 1 ENGINE	ROLLED BACK     	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA								PCE86031	234882		(CAN) AS AIRCRAFT ROTATED, NR 1 ENGINE POWER ROLLED BACK AND T5 PEGGED ON GAUGE. T5 STABILIZED AT 900C DURING THE 30-60 	SECONDS FOR AIRCRAFT TO REACH 400 FEET ALTITUDE.  AT 400 FEET, ENGINE WAS SHUTDOWN.  AIRCRAFT RETURNED TO BASE.  ENGINE 	TROUBLESHOOTING IS IN PROGRESS,  FURTHER REPORT TO FOLLOW.				2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
1998111300651	19981113	00651	CE  	1998	11	13	CA980819011      	1	19980811	G	2612	473275	FIRE DETECTOR   			BEECH 	200   	B200C       	1152924	CE  	PWA   	PT6   	PT6A42      	52043	NE  					ENGINE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		CR	CRUISE         	1			CA								PCE94677			(CAN) DURING FLIGHT, MASTER CAUTION AND RIGHT FIRE LIGHT ILLUMINATED.  ENGINE SHUT DOWN AND AIRCRAFT RETURNED TO BASE. M	AINTENANCE CHECK FOUND FAULTY FIRE DETECTOR SENSOR AND THERE WAS NO EVIDENCE OF FIRE.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998111300652	19981113	00652	CE  	1998	11	13	CA980819012      	1	19980805	G	3610	13823E4M0240	BLEED AIR LINE  			BEECH 	1900  	1900C       	1154161	CE  										ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) RIGHT HAND BLEED AIR LIGHT AND MASTER CAUTION LIGHTS ILLUMINATED SHORTLY AFTER TAKEOFF.  AIRCRAFT SAFELY RETURNED 	TO DEPARTURE BASE.  MAINTENANCE CHECK FOUND A BLEED AIR LINE HAD DEVELOPED A SMALL PIN HOLE WHICH ALLOWED AIR TO ESCAPE 	REDUCING PRESSURE IN THE SYSTEM CAUSING WARNING LIGHTS TO COME ON.  DEFECTIVE LINE REPLACED AND SYSTEM CHECKED SERVICEAB	LE.			2	L	7	2 	4T			RT	A24CE
1998111300653	19981113	00653	EU  	1998	11	13	CA980819013      	2	19980813	G	7322	261705	VALVE           		887261      						ROTAX 	912   	ROTAX912    	55555	EU  					CARBURETOR	WORN            	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA			917  					4412619			(CAN) AIRCRAFT ENGINE LOST POWER DURING CRUISE.  CARBURETOR REMOVED FOR INSPECTION.  THE FLOAT NEEDLE VALVE WAS FOUND WO	RN AT THE BEADED EDGE.  ROTAX TECHNICAL BULLETIN NR 912-05R2 HAS ILLUSTRATED PICTURES OF A FAILED FLOAT NEEDLE VALVE.										3	I			EXPE3I
1998111300654	19981113	00654	SO  	1998	11	13	CA980825001      	1	19980731	G	2910		LINE            			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					HYDRAULIC SYS	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA								PCE52339			(CAN) ON APPROACH WHEN LANDING GEAR SELECTED DOWN, ALL HYDRAULIC FLUID LOST.  ON GROUND, FOUND HOLE IN HYDRAULIC LINE. H	YDRAULIC LINE CHAFED ON ELECTRICAL WIRE AND MAY HAVE ARCED CAUSING HOLE.   REPAIRED.					1	L	7	2 	3T	4	T		A8EA    	E4EA
1999021200160	19990212	00160		1999	2	12	CA980825004      	1	19980818	G	8011	230321402	BEARING         	LUCAS       	23032018    															STARTER	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						8909					(CAN) BEARING SEIZED IN PREVIOUSLY RE-SLEEVED DRIVE END BELL.  END BELL CRACKED, BEARING LINER SEPARATED FROM END BELL. 	 FAILURE CAUSING DAMAGE TO ARMATURE.  SUSPECT UNAPPROVED PARTS.
1998111300656	19981113	00656	NE  	1998	11	13	CA980825005      	2	19980804	G	8530	23521CA1	CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			822  					7215			(CAN) ENGINE WAS RUNNING ROUGH WITH LOSS OF OIL AND POWER.  INSPECTION FOUND THE NR 5 CYLINDER WAS CRACKED AT THE EXHAUS	T VALVE EAR AND HAD SEPARATED.					1	H	7	1 	3R	3	R		A815    	5E2
1998111300657	19981113	00657	CE  	1998	11	13	CA980825006      	1	19980813	G	7120	04511201	MOUNT           			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10808					6760R			(CAN) DURING INSPECTION THE ENGINE MOUNT WHICH RUNS FROM THE LOWER RIGHT HAND FIREWALL PICKUP TO THE NOSE GEAR COLLAR WA	S FOUND CRACKED AT THE WELD.  THE SUBMITTER REPORTS THAT 1337.9 HOURS EARLIER, A SIMILAR CRACK WAS FOUND AND REPAIRED ON	 THE LEFT HAND SIDE OF THE COLLAR.				1	H	7	1 	3O	3	O		3A19    	E252
1998111300658	19981113	00658	GL  	1998	11	13	CA980825007      	3	19980821	G	6111	90DCA14	BLADE           			CESSNA	172   	R172K       	2072431	CE  	CONT  	O360  	IO360K      	17025	SO  	MCAULY	2A34C	2A34C203    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1978 	412  				355206	752700		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PAINT WAS REMOVED FROM THE BLADES AND CORROSION WAS FOUND ON THE CAM	BER AND THE THRUST FACE OF THE PROPELLER BLADES.  THE CORROSION WAS REMOVED BY GRINDING IN ACCORDANCE WITH MCCAULEY SERV	ICE MANUAL 780630 AND THE BLADES WERE RETURNED TO SERVICE.				1	H	7	1 	3O	3	O		3A17    	E1CE	5	C	P3EA
1999031200266	19990312	00266	SO  	1999	3	12	CA980825009      	1	19980810	G	2750	159AMM101034	BELLCRANK       			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					TE FLAPS	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20721					16062			(CAN) DEFLECTION CRANK FOUND CRACKED USING NDT TECHNIQUE.    PART TC:  19,718.						2	L	7	2 	4T	4	T		1A17    	E297
1998111300659	19981113	00659	GL  	1998	11	13	CA980825011      	1	19980817	G	2720	2027222600	PEDAL           			DIAMON	DA20A1	DA20A1      	05626UX	GL  										RUDDER CONTROL	CRACKED         	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			990  								(CAN) LEFT BRAKE PEDAL CRACKED JAMMING THE MASTER BRAKE CYLINDER IN THE ON POSITION.  REPAIRED.						1	L	7	1 	3O			NT	TA4CH
1998111300660	19981113	00660	CE  	1998	11	13	CA980825012      	1	19980812	G	2730	804187504	TORQUE ARM      			BEECH 	18    	D18S        	1151004	CE  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						9Y132		8266	176520		(CAN) WHILE CARRYING OUT NDT PER FAA AD 77-19-07, CRACKS WERE FOUND IN THE ELEVATOR CONTROL ARM.  THE CRACKS ALL STARTED	 AT ATTACHMENT HOLES.  SEVEN HOLES IN ALL FROM .250 INCH TO .500 INCH IN LENGTH.  REPLACED.					1	L	7	2 	3R	3	R		A765    	5E1	5	C	P736
1998111300661	19981113	00661	SO  	1998	11	13	CA980825013      	1	19980812	G	3710	441CC7	DRY AIR PUMP    			PIPER 	PA31  	PA31350     	7103110	SO  										VACUUM SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				308  		62062					(CAN) PILOT REPORTED INEFFECTIVITY OF LEFT VACUUM PUMP.  INTERNAL DAMAGE.  SUBMITTER STATED SHAFT DID NOT SHEAR AS HAPPE	NS NORMALLY.  REPLACED.					1	L	7	2 	3O				A20SO
1998111300662	19981113	00662	SO  	1998	11	13	CA980825014      	1	19980815	G	3710	441CC7	DRY AIR PUMP    			PIPER 	PA31  	PA31350     	7103110	SO  										VACUUM SYS	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1    		088802					(CAN) NEW PUMP INSTALLED AND FAILED ON FIRST FLIGHT.  SUBMITTER SUSPECTED HEAT FROM EXHAUST AND TURBO.  REPLACED.						1	L	7	2 	3O				A20SO
1998111300666	19981113	00666	CE  	1998	11	13	CA980825021      	1	19980814	G	7120	05510171	MOUNT           			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4773 					L1996227A			(CAN) DURING INSPECTION, A CRACK WAS FOUND ON THE ENGINE MOUNT WELD AT THE LEFT INBOARD SIDE OF THE LOWER CROSS BRACE.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1998111300667	19981113	00667	WP  	1998	11	13	CA980825022      	2	19980818	G	7310	39423041	VALVE           			SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	NR 1 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA				5331 				P44393	DRG457785		(CAN) NR 1 ENGINE WOULD NOT SHUT OFF WITH THE STOP BUTTON.  THE FUEL SHUTOFF VALVE WAS REPLACED AND THE AIRCRAFT RETURNE	D TO SERVICE.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
1998111300669	19981113	00669	EA  	1998	11	13	CA980827006      	2	19980724	G	7250	MS971406	BOLT            		3017860     	DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	COMPRESSOR	CRACKED         	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				138  				PCE22037	BU240		(CAN) SHORTLY AFTER TAKEOFF, PILOT NOTICED THE ENGINE WOULD NOT PRODUCE PROPER POWER (30 POUND TORQUE AT 700 T5).  THE A	IRCRAFT CONTINUED TO DESTINATION.  POST-FLIGHT INSPECTION RUN-UP INDICATED RUBBING SOUND FROM COMPRESSOR TURBINE AREA. T	HE ENGINE WAS SPLIT AT THE C FLANGE AND THE CT WHEEL WAS REMOVED.  INSPECTION OF THE CT VANE ASSEMBLY REVEALED 2 BOLTS H	AD BACKED OUT OF THE CT TURBINE VANE SUPPORT AND HAD CAME IN CONTACT WITH THE CT WHEEL AND THE CT BLADES CAUSING DAMAGE.	  PART TC:  276.		1	H	7	1 	3T	3	T		A806    	E4EA	6	C	P15EA
1998111300670	19981113	00670	SO  	1998	11	13	CA980827007      	1	19980820	G	5280	4199400	HINGE           		4205900     	PIPER 	PA31  	PA31        	7103102	SO  						HARTZL	HCC4Y	HCC4YR2     	GL  	MLG DOOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8535 						FH271		(CAN) RIGHT OUTBOARD GEAR DOOR APPEARED LOOSE.  FORWARD HINGE BROKEN.  A CRACK HAD ORIGINATED IN THE INNER RADIUS OF THE	 ELBOW SECTION.  CRACK APPEARED TO HAVE RUN 3/4 WAY THROUGH BEFORE IT FAILED.					1	L	7	2 	3O				A20SO   		5	C	P52GL
1998111300673	19981113	00673	EA  	1998	11	13	CA980827010      	2	19980819	G	7532	310082903	BLEED VALVE     			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					COMPRESSOR	STICKING        	W				E				ENGINE SHUTDOWN         				J	Y		WARNING INDICATION        	ENGINE STOPPAGE           		AP	APPROACH       	1			CA				1022 				PCE57237			(CAN) PILOT REPORTED NR 2 ENGINE PARAMETERS BEGAN TO FLUCTUATE DURING SHORT FINAL.  POST-FLIGHT INSPECTION FOUND THE COM	PRESSOR BLEED VALVE STICKING.  THE VALVE WAS REPLACED AND THE ENGINE WAS GROUND RUN SERVICEABLE.					1	L	7	2 	4T	4	T		A21SO   	E4EA
1998111300674	19981113	00674	SO  	1998	11	13	CA980827012      	1	19980819	G	7160	554094	CONTROL CABLE   			PIPER 	PA28  	PA28140     	7102802	SO  	LYC   	O320  	O320E3D     	41508	EA  					CARBURETOR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								L2068527AC			(CAN) ON START, CARBURETOR HEAT WOULD NOT FUNCTION.  INSPECTION FOUND THE CARBURETOR HEAT CABLE BROKEN.  IT IS THOUGHT T	HAT THE CONNECTOR WHERE THE CABLE ATTACHES TO THE VALVE ARM ON THE AIR BOX WAS OVERTORQUED CAUSING THE CABLE TO FLEX AND	 BREAK.				1	L	7	1 	3O	3	O	 	2A13    	E274
1998111300675	19981113	00675	EU  	1998	11	13	CA980827013      	1	19980821	G	5610	115C260042	PLATE           			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  					CANOPY	JAMMED          	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			629  	629  				L1838739A			(CAN) LATCH JAMMED ON CANOPY PLATE.  CANOPY COULD NOT BE MOVED AFT AS IT WAS HOOKING ON THE PLATE.  LATCH/LOCK IN THE OP	EN POSITION.  THIS WOULD STOP CANOPY EMERGENCY DEPLOYMENT.					1	L	7	1 	3O	3	O	NT	A57EU   	E274
1998111300676	19981113	00676	CE  	1998	11	13	CA980827014      	1	19980814	G	3610	1149700401	BLEED AIR LINE  			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					ENGINE	CRACKED         	W				H				DEACTIVATE SYST/CIRCUITS				J	M		WARNING INDICATION        	OVER TEMP                 		NR	NOT REPORTED   	1			CA			20530								(CAN) THE BLEED AIR LINE BLEW OUT A TRIANGULAR PIECE OF MATERIAL APPROXIMATELY .25 INCH IN SIZE AT THE OUTSIDE OF THE BE	ND RADIUS JUST BEYOND THE THRESHOLD OF THE NACELLE.  ABRASION MARKS WERE VISIBLE DIRECTLY OVER THE CRACKED AREA AND BLOW	N BACK AREA.  THIS CAUSED A HIGH TEMP AIR LEAK, WHICH, IN TURN, MELTED THE EVA TUBING GIVING THE RIGHT BLEED WARNING IND	ICATION.  TUBING REPLACED.  PART TC:  29,007.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998111300681	19981113	00681		1998	11	13	CA980908002      	1	19980819	G	7810	2078000107	EXHAUST PIPE    	ROTAX       	913435      						ROTAX 	912   	ROTAX912    	55555	EU  					NR 3 CYLINDER	BROKEN          	W				O				OTHER                   				E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		CL	CLIMB          	1			CA			1196 					4412514			(CAN) DURING PRACTICE LANDINGS, A LOUD ENGINE NOISE WAS HEARD, FOLLOWED BY A LOSS OF POWER, WHEN CLIMB POWER WAS APPLIED	.  AIRCRAFT RETURNED TO BASE.  POST-FLIGHT INSPECTION FOUND THE NR 3 CYLINDER EXHAUST PIPE HAD BROKEN.  THE PLASTIC COOL	ANT RESERVOIR HAD MELTED IN SEVERAL PLACES; THE UPPER IGNITION LEAD HAD BURNT AND THE SPARK PLUG HAD BLOWN OFF.									3	I			EXPE3I
1998111300683	19981113	00683	CE  	1998	11	13	CA980908004      	1	19980818	G	3246	3000E	SPREADER BAR    	CAP         	3000E       	CESSNA	180   	180K        	2072624	CE  						MCAULY	2A34C	C2A34C204   	GL  	FLOAT	CORRODED        	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA						1194			765699		(CAN) SPREADER BARS AT THE FLOAT WERE SPLIT ON THE RIGHT HAND SIDE IN OUTSIDE TUBING.  CONDITION COULD NOT BE DETECTED W	ITHOUT DISMANTLING THE FAIRING IN BETWEEN THE FLOATS.  THE INSIDE SLEEVE IN THE ATTACHMENT AREA COVERS THE INSIDE OF THE	 SPREADER BAR TUBING, AND COVERED THE CORRODED AREA.  CONDITION FOUND BY THE PILOT.  INVESTIGATION REVEALED A SEVERELY W	EAKENED STRUCTURE DUE TO A SPLIT IN BOTH SPREADER BARS.			1	H	7	1 	3O				5A6     		5	C	P3EA
1998111300684	19981113	00684	NE  	1998	11	13	CA980908005      	2	19980812	G	8520	3508	CRANKCASE       			GRUMAV	G21   	G21A        	3951204	SO  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1210 				JP7309			(CAN) REMOVAL OF NR 5 CYLINDER, DUE TO LOW COMPRESSION, REVEALED A CIRCUMFERENTIAL CRACK IN THE FORWARD FACE OF THE FORW	ARD CRANKCASE HALF.  NUMEROUS CRYSTALLINE STRUCTURED CHIPS WERE FOUND IN THE MAIN OIL SCREEN. THE AMOUNT OF MATERIAL WAS	 NOT UNUSUAL, BUT THE TYPE OF MATERIAL WAS.  THE ENGINE HAD DEVELOPED AN OIL LEAK THAT WAS TRACED TO THE CRACK IN THE FO	RWARD CASE. THE CRACK WAS EXTENSIVE ENOUGH TO CONSIDER ENGINE FAILURE IMMINENT.			1	H	7	2 	3R	3	R		TC654   	5E1
1998111300685	19981113	00685	EA  	1998	11	13	CA980908006      	2	19980609	G	7421	SR88	SPARK PLUG      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 4 CYLINDER	CRACKED         	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			E	R		VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      		LD	LANDING        	1			CA								L1067239A			(CAN) WHILE DOING CIRCUITS, THE ENGINE BEGAN TO RUN ROUGH WITH PARTIAL POWER LOSS.  THE AIRCRAFT LANDED AND POST-FLIGHT 	INSPECTION FOUND NR 3 CYLINDER HAD 2 DEAD SPARK PLUGS AND NR 4 CYLINDER HAD A SPARK PLUG WITH BROKEN CERAMIC.  ALL THE E	NGINE SPARK PLUGS WERE REPLACED AND THE ENGINE WAS GROUND RUN SERVICEABLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998111300687	19981113	00687	EU  	1998	11	13	CA980908008      	2	19980827	G	8550	EP3000E02E03E017	HOSE            								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE OIL	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA			467  					4412584			(CAN) THE OIL SUCTION HOSES COLLAPSED DURING OPERATION IN HIGH AMBIENT TEMPERATURES, AT HIGH POWER SETTINGS.  NEW HOSES 	WERE INSTALLED AND PROBLEM REPEATED ITSELF AFTER A SHORT TIME.  SUBMITTER STATED PROBLEM IS THAT HOSE MATERIAL IS QUITE 	FLEXIBLE AND SOFTENS WHEN HOT.									3	I			EXPE3I
1998111300688	19981113	00688	SW  	1998	11	13	CA980908009      	1	19980822	G	2432	15580	BATTERY         	SAFT        		BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5313B      	41549	NE  					BATTERY BAY	THERMAL RUNAWAY 	W				C				ABORTED TAKEOFF         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			CA						27033		LE07531			(CAN) BATTERY 'HOT' INDICATOR CAME 'ON'.  BATTERY THERMAL RUNAWAY.						1	G	7	1 	4U	4	U		H1SW    	E17EA
1998111300689	19981113	00689	NE  	1998	11	13	CA980908010      	2	19980824	G	7323	11608523	GOVERNOR        			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA				635  				LE07560A			(CAN) ROTOR RPM DROPS AND OVERSPEEDS WITH COLLECTIVE LEVER MOVEMENT.  ADJUSTMENT OF DROOP COMPENSATOR TO MAXIMUM DID NOT	 SOLVE THE PROBLEM.  GOVERNOR WAS REPLACED AND PROBLEM SOLVED.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1998111300690	19981113	00690	NE  	1998	11	13	CA980908011      	2	19980824	G	8530		CYLINDER        			DOUG  	B26   	B26C        	3200524	WP  	PWA   	R2800 	R280079     	52026	NE  					NR 2 ENGINE	CRACKED         	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA				536  				FPO43289			(CAN) AFTER FIRE BOMBING CARRIED OUT, PILOT WAS ADVISED THAT THE NR 2 ENGINE WAS SMOKING, PRECAUTIONARY SHUTDOWN WAS CAR	RIED OUT.  POST-FLIGHT INSPECTION FOUND THE NR 5 CYLINDER WAS CRACKED AND LEAKING OIL. THE CYLINDER WAS REPLACED AND THE	 ENGINE TEST FLOWN SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.				2	M	7	2 	4R	4	R		L34     	5E8
1998100900366	19981009	00366		1998	10	9	CA980908012      	1	19980825	G	2436	RWR81S1ROOFS	RESISTOR        	LUCAS       	51509002R   															DC SYSTEM	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						3110B					(CAN) RESISTOR INSTALLED NOT AS REQUIRED BY MANUFACTURER.
1998100900367	19981009	00367	EU  	1998	10	9	CA980908016      	2	19980818	G	7520		COOLANT         								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE	EMPTY           	W				A				UNSCHED LANDING         				B	E	M	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	OVER TEMP                 	TO	TAKEOFF        	1			CA			984  					4412707			(CAN) PILOT REPORTED ELECTRICAL AND OIL SMELL IN THE COCKPIT AFTER TAKEOFF, WITH THE ENGINE STARTING TO RUN ROUGH.  PREC	AUTIONARY LANDING CARRIED OUT.  POST-FLIGHT INSPECTION REVEALED NO COOLING IN THE ENGINE. THE OVERFLOW VESSEL FULL AND T	HE TEMPERATURE TRANSMITTER BLOWN APART.									3	I			EXPE3I
1998111300692	19981113	00692	NE  	1998	11	13	CA980908017      	2	19980820	G	8500		ENGINE          			CVAC  	PBY5  	PBY5A       	2421208	WP  	PWA   	R1830 	R183092     	52020	NE  					NR 1 NACELLE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA								25007			(CAN) DUE TO DECREASING OIL PRESSURE AND INCREASING OIL TEMPERATURE, THE NR 1 ENGINE WAS FEATHERED IN-FLIGHT.  POST-FLIG	HT INSPECTION FOUND THE MAIN OIL FILTER CONTAINED METAL PARTICLES. THE ENGINE WAS REMOVED FOR INTERNAL INSPECTION.					2	H	7	2 	4R	4	R		2548    	5E4
1998111300693	19981113	00693	EU  	1998	11	13	CA980908018      	1	19980512	G	6320	4638302023	BEARING         	ZAHNRAD FABR	4638001001  	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					R/H INPUT	DAMAGED         	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1116 			1130		CAE835698			(CAN) RIGHT INPUT BEARING PEELING.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998111300694	19981113	00694	SO  	1998	11	13	CA980908019      	1	19980825	G	5510	MS21069L4	NUT             		5302050501  	GULSTM	AA5   	AA5A        	3960106	SO  	LYC   	O320  	O320E2G     	41508	EA  					HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1439 					L4319027A			(CAN) AIRCRAFT DAMAGED IN LANDING ACCIDENT.  WHEN HORIZONTAL STABILIZER WAS BEING REINSTALLED AFTER REPAIR, A BOLT WOULD	 NOT REACH PROPER TORQUE.  HORIZONTAL STABILIZER WAS REMOVED AND IT WAS FOUND THAT 4 OF THE 8 FRONT SPAR ANCHOR NUTS WER	E CRACKED.				1	L	7	1 	3O	3	O		A16EA   	E274
1998111300695	19981113	00695	GL  	1998	11	13	CA980908020      	3	19980820	G	6110		PROPELLER       													MCAULY	1A170	1A170DM     	GL  	FORWARD	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1072 					52291		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PREVIOUS INSTALLATION/REMOVAL IN JULY 1965.  THIS INSTALLATION ENTRY	 AT 269 HOURS.  NO LOG BOOK ENTRIES OF REPAIRS.															5	N	P857
1998111300696	19981113	00696	EU  	1998	11	13	CA980908021      	1	19980821	G	5510	SC7095399	FITTING         			STBROS	SC7   	SC73        	8100512	EU  										HORIZ STAB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			18500								(CAN) WORN BUSHINGS AND FITTINGS FOUND AT TAILPLANE ATTACHMENT TO FUSELAGE.  A CRACKED GUSSET BETWEEN VERTICAL AND HORIZ	ONTAL STABILIZER FOUND.  FURTHER INVESTIGATION DETERMINED THAT THE CAUSE OF THE CRACK WAS THAT THE AFT ATTACHMENT OF THE	 TAIL PLANE WAS LOOSE CAUSING A TWISTING MOMENT IN THE HORIZONTAL STABILIZER.  SHORTS CONTACTED AND OVERSIZE BUSHINGS IN	STALLED.			1	H	7	2 	3T				A15EU
1998111300697	19981113	00697	NM  	1998	11	13	CA980908023      	1	19980702	G	2612	92296735	RELAY           			BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					INTERNAL	FAILED          	W				O				OTHER                   				L			NO TEST                   			NR	NOT REPORTED   	1			CA								P689955			(CAN) APU FIRE TEST NO BELL OR HORN.  FOUND APU AURAL WARNING CUT-OUT RELAY R195 FAULTY.  REPLACED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998111300698	19981113	00698	NM  	1998	11	13	CA980908025      	1	19980709	G	2750	DAT6278A14	BEARING         		652661458   	BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					TE FLAP	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1222 		293		P689955			(CAN) INBOARD FLAP WOULD NOT EXTEND.  FOUND RIGHT INBOARD SCREW JACK FAIRING FORWARD BEARING SEIZED.  REPAIRED.  PART TC	:  931.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998111300699	19981113	00699	NM  	1998	11	13	CA980908026      	1	19980812	G	3411		STATIC VALVE    			BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					PITOT SYSTEM	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P689955			(CAN) ON 24 MONTH INSPECTION, FOUND CAPTAIN'S ALT STATIC SOURCE VALVE LEAKING, REPLACED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998111300700	19981113	00700	NM  	1998	11	13	CA980908027      	1	19980725	G	5753	69228961	WEB             		652163391   	BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								P689955			(CAN) LEFT OUTBOARD MID-FLAP OUTBOARD CLOSURE RIB/WEB CRACKED AT END OF FLAP AFT SPAR AND FAIRING AFT MOUNT BROKEN.  SCR	EW JACK HARD CHAFING INSIDE FAIRING OUTSIDE, RESULTING IN CYCLIC SIDELOAD PRESSURE AGAINST ADJACENT SUPPORT STRUCTURE ON	 FLAP.  REPAIRED.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998111300701	19981113	00701	NM  	1998	11	13	CA980908028      	1	19980815	G	3246	102201	RIM             	BFGOODRICH  	313061      	BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					NR 4 WHEEL	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				168  		7052		695337			(CAN) FOUND NR 4 MAIN WHEEL RIM MISSING OUTER RIM 90 PERCENT OF CIRCUMFERENCE. TIRE STILL HOLDING PRESSURE.  PIECE FOUND	 ON RUNWAY.  REPLACED.  PART TC:  182.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998111300702	19981113	00702	SW  	1998	11	13	CA980908029      	1	19980817	G	5320	206033110239	STIFFENER       		206033002005	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20      	03013	GL  					FUSELAGE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8600 			AOJH0009		CAE295298			(CAN) VERTICAL CONTROL TUNNEL AFT RIGHT STIFFENER CRACKED.  BELL TB 206L-79-41 HAD NOT BEEN ACCOMPLISHED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998111300703	19981113	00703	EA  	1998	11	13	CA980908030      	1	19980817	G	2430	MS3126E1210S	CONNECTOR       			CNDAIR	CL600 	CL6002B19   		EA  										DC SYSTEM	FAILED          	W				C				ABORTED TAKEOFF         				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA											(CAN) CONNECTOR P18PA TO THE MAIN BATTERY POWER CONTROLLER (K12PA) FOUND BURNED AND COMPLETELY DETACHED FROM THE CONTROL	LER.  ADJACENT AREA WIRING WITHIN JUNCTION BOX WAS HEAT DAMAGED.					2	L	7	2 	4F			RT	A21EA
1998111300704	19981113	00704	EA  	1998	11	13	CA980908031      	2	19980824	G	7414	S6LN200	MAGNETO         	BENDIX      							LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						A79182		L585248			(CAN) ENGINE RECEIVED ON TRANSPORT FROM OVERHAULER.  PRE-INSTALLATION INSPECTION FOUND THE TOP AND BOTTOM MAGNETO LUGS C	RACKED.  IT APPEARS THE CARGO STRAPS WERE PASSED OVER THE MAGNETO WHEN THE ENGINE WAS SECURED FOR TRANSPORT.  SUBMITTER 	STATED IMPROPER POSITIONING AND/OR STRESS CAUSED THE STRAPS TO EXERT SUFFICIENT PRESSURE TO FRACTURE THE LUGS.									3	O			1E4
1998111300705	19981113	00705	EA  	1998	11	13	CA980908032      	2	19980820	G	8520	LW11750	ROD             			BEECH 	23    	C23         	1151242	CE  	LYC   	O360  	O360A4K     	41514	EA  					NR 1&3 CYLINDER	DISCONNECTED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3338 	1351 				L2133036A			(CAN) NR 1 AND NR 3 CONNECTING RODS WERE FOUND DISCONNECTED FROM THE CRANKSHAFT.  ENGINE IS BEING SENT FOR INVESTIGATION	.					1	L	7	1 	3O	3	O		A1CE    	E286
1998111300712	19981113	00712	SW  	1998	11	13	CA980908042      	1	19980708	G	3212	1200211	VALVE           		2060673     	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20B     	03013	GL  					FLOAT	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						0207		CAE830970			(CAN) ON TEST, SLOW INFLATION OF EMERGENCY FLOAT.  DISASSEMBLY OF VALVE SHOWED 2 SUPPORT HEADS AND 2 TEFLON DISCS ON BOT	TOM OF VALVE.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998111300713	19981113	00713	EA  	1998	11	13	CA980908043      	2	19980818	G	8500		ENGINE          			GRUMAV	TBM   	TBM3AIRTRD  	3950308	EA  	WRIGHT	R2600 	R260020     	67050	EA  	HAMSTD	23E	23E50       	NE  	ENGINE BAY	FAILED          	W				B	E			EMER. DESCENT           	ENGINE SHUTDOWN         			B	E	R	SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          	PARTIAL RPM/PWR LOSS      	CR	CRUISE         	1			CA								W446997	P87361		(CAN) ON A ROUTINE FLIGHT AT 1,500 FEET, THE ENGINE BACKFIRED TWICE, FOLLOWED BY SMOKE AND FLAME FROM THE LEFT SIDE OF T	HE ENGINE.  THIS WAS IMMEDIATELY FOLLOWED BY A COMPLETE POWER LOSS OF THE ENGINE.  THE PILOT CARRIED OUT A FORCED LANDIN	G IN A WOODED AREA.  THE ENGINE HAS BEEN REMOVED FROM THE AIRCRAFT.  A MORE DETAILED REPORT WILL FOLLOW THE INVESTIGATIO	N.			1	L	7	1 	4R	4	R		L82     	TC176	6	C	P603
1998111300714	19981113	00714	EU  	1998	11	13	CA980908045      	1	19980825	G	7160	75027C1	VALVE           			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					AIR BOX	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2477 					L2370951A			(CAN) INSPECTION FOUND CRACKS AROUND THE INTAKE HOLE ON ENGINE AIR BOX VALVE ASSEMBLY.						1	H	7	2 	3O	3	O		A31EU   	1E10
1999061800002	19990618	00002	SW  	1999	6	18	CA980908046      	1	19980822	G	5610	3600431255	WINDSHIELD      			GULSTM	690TP 	690D        	3970405	SW  						ROTOL	R306	R306382F7   	GL  	COCKPIT	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			415  			97289H7849			106738		(CAN) WINDSHIELD OUTER GLASS CRACKED IN THE TOP RIGHT HAND CORNER.						1	H	7	2 	3T				2A4     		6	C	P8EU
1998111300715	19981113	00715	CE  	1998	11	13	CA980909002      	1	19980831	G	3340	A35541	LIGHT           		3005511     	CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					FUSELAGE	INOPERATIVE     	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3129 								(CAN) NAVIGATION LIGHT CIRCUIT BREAKER TRIPPED IN-FLIGHT.  FOUND TAIL POSITION LIGHT ASSY GROUNDED INTERNALLY.  CONTACTS	 MELTED AND BULB SOLDER PLUG MELTED CAUSING A SHORT.					1	L	7	2 	4F	4	F		A22CE   	E1NE
1998111300716	19981113	00716	SO  	1998	11	13	CA980909003      	2	19980317	G	8520		LIFTERS         								CONT  	O520  	TSIO520M    	17040	SO  					ENGINE	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				4    				511652			(CAN) NEW VALVE LIFTERS INSTALLED DUE TO SPALLING.											3	O			E8CE
1998111300717	19981113	00717	SO  	1998	11	13	CA980909004      	1	19980209	G	3230	SA72682012	UPLOCK CABLE    			PIPER 	PA31  	PA31350     	7103110	SO  										MLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIGHT MLG UPLOCK CABLE WORN BY CONTACT WITH MLG FORWARD LINK ASSY.  REPLACED.						1	L	7	2 	3O			 	A20SO
1998111300718	19981113	00718	SO  	1998	11	13	CA980909005      	1	19980820	G	5280	4752932	HINGE           		4752931     	PIPER 	PA31  	PA31350     	7103110	SO  										MLG DOOR	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) RIGHT MLG FAILED TO EXTEND WHEN SELECTED DOWN.  EMERGENCY HAND PUMP FAILED TO LOWER GEAR.  EMERGENCY BOTTLE WAS DI	SCHARGED AND GEAR LOWERED, AIRCRAFT LANDED OK.  FOUND FORWARD DOOR HINGE BROKEN AND JAMMED AGAINST SKIN PREVENTING THE G	EAR FROM PASSING BY THE DOOR.  REPLACED.				1	L	7	2 	3O				A20SO
1998111300720	19981113	00720	EA  	1998	11	13	CA980909008      	1	19980901	G	2610	896431	LOOP            			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	NR 1 ENGINE	FAILED          	W				E	F			ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      			J			WARNING INDICATION        			CL	CLIMB          	1			CA								PCE86031	234882		(CAN) ON CLIMB OUT, THE NR 1 ENGINE FIRE WARNING ILLUMINATED.  THE ENGINE WAS SHUTDOWN AND BOTH FIRE BOTTLES WERE DISCHA	RGED. THE AIRCRAFT DIVERTED.  POST-FLIGHT INSPECTION FOUND NO ACTUAL FIRE.  FIRE DETECTION SYSTEM BEING CHECKED FOR FAUL	T.  INSPECTION FOUND THE FIRE LOOPS WERE CROSSED ON INSTALLATION.				2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
1998111300722	19981113	00722	EA  	1998	11	13	CA980909010      	1	19980819	G	5320		STOP            			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A      	30015	NE  					PASSENGER DOOR	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA			6997 					807295			(CAN) PASSENGER DOOR NOISY AND LEAKING AIR DURING FLIGHT.  AIRCRAFT RETURNED TO BASE.  DOOR STRIKER FOUND CRACKED ON FRA	ME.  DOOR FRAME WEB SPLICED PER ENGINEERING ORDER DRAWING NUMBER 600-31535.  PART TC:  5,964.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
1999021200910	19990212	00910	EA  	1999	2	12	CA980909020      	1	19980810	G	2435		DRIVESHAFT      	AIRPTS      	215T5091018 	CNDAIR	CL215 	CL2156B11415		EA  										START/GEN	SHEARED         	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			245  								(CAN) DURING CRUISE, THE LEFT GENERATOR LIGHT CAME ON.  RESETS FAILED.  DRIVESHAFT FRACTURED PROBABLY DUE TO BEARING FAI	LURE LEADING TO EXCESSIVE RUBBING AND SEIZURE.					2	H	7	2 	4T			RT	A14EA
1999021200911	19990212	00911		1999	2	12	CA980909021      	4	19980822	G	3160	215T5096510	CONTROLLER      			CNDAIR	CL215 	CL2156B11415		EA  										COCKPIT	FAILED          	W				A				UNSCHED LANDING         				P			NO WARNING INDICATION     			FF	FIRE FIGHTING  	1			CA				12   							(CAN) AIRCRAFT ON FIREFIGHTING.  AFTER FIRST DROP, THE PANEL INDICATED AN ERROR CODE.  RESTART IN CONSIDERATION ALTHOUGH	 NOT RECOMMENDED BECAUSE OF IMPORTANCE OF FIRE.  ON 46TH DROP, THE CREW HEARD THE SOUND OF THE DOOR OPENING, BUT ALL LIG	HTS DID NOT CHANGE AND NO ERROR CODE.  IN SPITE OF CREW ATTEMPTS, THEY COULD NOT CHANGE INDICATIONS.  EMERGENCY PROCEDUR	ES CARRIED OUT.  MISSION ABORTED.  COULD NOT DUPLICATE.  PART REPLACED.			2	H	7	2 	4T			RT	A14EA
1998111300729	19981113	00729	EU  	1998	11	13	CA980909022      	1	19980827	G	2913	3508807	PUMP            	VICKERS     	3508807     	AIRBUS	310   	A310304     		EU  										HYDRAULIC SYS	LEAKING         	W				H				DEACTIVATE SYST/CIRCUITS				K			FLUID LOSS                			CR	CRUISE         	1			CA			42221	1634 		MX366024					(CAN) TWO HOURS INTO FLIGHT, LOST ALL BLUE SYSTEM HYDRAULIC FLUID, APPROXIMATELY 45 MINUTES LATER, THE BLUE SYSTEM HYDRA	ULIC RESERVOIR OVERHEAT LIGHT CAME ON AND REMAINED ON FOR DURATION OF THE FLIGHT.  MAINTENANCE FOUND BLUE SYSTEM  ENGINE	 HYDRAULIC PUMP CASING LEAKING.  PUMP REPLACED AND SYSTEM CHECKED SERVICEABLE.				2	L	7	2 	4F			RT	A35EU
1998111300732	19981113	00732	SO  	1998	11	13	CA980909026      	1	19980831	G	2730	81262109	LINK            		DWG41963    	PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELEVATOR CONTROL LINK SPRING ATTACHMENT HOLE ELONGATED.  REPLACED.  AD 98-08-18 SB 626C.						1	L	7	2 	3O				A20SO
1998111300733	19981113	00733	EA  	1998	11	13	CA980909027      	2	19980901	G	8550	77527	EXTENSION       			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					OIL FILLER	IMPROPER PART   	W				K				NONE                    				K	W		FLUID LOSS                	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA			5571 					L585248			(CAN) AFTER ENGINE INSTALLATION, AN OIL LEAK WAS FOUND ON RUN-UP.  INVESTIGATION FOUND THE WRONG OIL FILLER EXTENSION IN	STALLED, RESULTING IN THE ENGINE BEING OVER SERVICED WITH OIL, THIS LEAD TO THE OIL LEAK. THE PROPER PART (P/N 74313) WA	S INSTALLED.				1	L	7	2 	3O	3	O		1A10    	1E4
1998111300734	19981113	00734	SW  	1998	11	13	CA980915001      	1	19980903	G	3213	204050227001	CAP             			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					SKID TUBE	DEBONDED        	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								LE07560A			(CAN) CAPS COMING OFF ON BOTH LT AND RT SKID TUBES.  ADHESIVE PEELING OFF FROM CAP AND ADHESIVE WAS APPLIED OVER THE PAI	NTED TUBE.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1998111300735	19981113	00735	NE  	1998	11	13	CA980915003      	2	19980905	G	8520		RING            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134053     	52016	NE  					CAM	DAMAGED         	W				K				NONE                    				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA								P326170			(CAN) AFTER LANDING, THE PILOT NOTICED THE ENGINE WAS RUNNING ROUGH AND POPPING AT IDLE.  INVESTIGATION  FOUND THE CAM R	ING WAS DAMAGED.  THE ENGINE WAS REMOVED AND SENT FOR REPAIR.					1	H	7	1 	3R	3	R		A815    	5E2
1998111300740	19981113	00740	EA  	1998	11	13	CA980915009      	2	19980902	G	8530		PUSH ROD        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					ENGINE	IMPROPER PART   	W				K				NONE                    				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								L1053348			(CAN) PILOT REPORTED THE ENGINE RUNNING ROUGH DURING TEST FLIGHT, AFTER CYLINDER CHANGE.  POST-FLIGHT COMPRESSION TEST F	OUND DIFFERENTIAL PRESSURE 0/80, WITH THE INTAKE VALVE OPEN.  INSPECTION FOUND THE INTAKE PUSH ROD TO BE THE WRONG LENGT	H, SHORTER PUSH ROD INSTALLED AND THE COMPRESSION CHECK INDICATED 75/80.  THE SUBMITTER SUGGESTS THAT INTAKE AND EXHAUST	 PUSH RODS, WHICH ARE DIFFERENT LENGTHS, ARE SOME TIMES INSTALLED INCORRECTLY.			1	L	7	2 	3O	3	O		1A10    	1E4
1998120400052	19981204	00052		1998	12	4	CA980915010      	4	19980903	G	3442	IN1202B	INDICATOR       			STBROS	SD3   	SD330       	8100602	EU  	PWA   	PT6   	PT6A45R     	52043	EA  					COCKPIT	MALFUNCTIONED   	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			AP	APPROACH       	1			CA						1452		PCE84133			(CAN) CREW WAS ON APPROACH WHEN THEY TURNED THE RADAR OFF AND THEN ON AGAIN.  SMOKE WAS OBSERVED COMING FROM THE RADAR I	NDICATOR.  THE CREW TURNED THE RADAR OFF AND COMPLETED AN EMERGENCY LANDING WITHOUT INCIDENT.  TROUBLESHOOTING THE RADAR	 SYSTEM INDICATED THAT THE RADAR INDICATOR WAS AT FAULT.  AFTER REMOVAL OF THE INDICATOR, IT WAS NOTICED THAT THE HOLES 	IN THE INDICATOR FOR COOLING WERE FILLED WITH DUST AND FOREIGN MATTER.  UNIT REPLACED AND NO FURTHER PROBLEMS REPORTED.			2	H	7	2 	4T	4	T		A41EU   	E4EA
1998120400053	19981204	00053	CE  	1998	12	4	CA980915011      	1	19980822	G	5610	051323027	WINDSHIELD      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  					COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9886 					RL836176T			(CAN) ON LANDING, WINDSHIELD CRACKED 3.5 INCHES ON LEFT UPPER SIDE.  CRACK STOP DRILLED, AND AIRCRAFT FLOWN TO BASE.  WI	NDSHIELD REPLACED.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998120400054	19981204	00054	SO  	1998	12	4	CA980915012      	1	19980819	G	3230	487862	SWITCH          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					MLG	LOOSE           	W				K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			CA			4218 					L81561C			(CAN) NO GREEN LIGHT INDICATION FOR DOWN AND LOCKED LANDING GEAR.  MAINTENANCE FOUND MICROSWITCH ON RIGHT LANDING GEAR L	OOSE.  MICROSWITCH ADJUSTED AND SECURED.  RETRACTION TESTS CHECKS SERVICEABLE.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998120400055	19981204	00055	GL  	1998	12	4	CA980915013      	1	19980902	G	6510	28010413	FLEX COUPLING   		28135255R   	ENSTRM	F28   	F28C        	3300407	GL  	LYC   	O360  	HIO360E1AD  	41514	EA  					BS 317	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			272  			00508776H		L1837051A			(CAN) ONE CRACKED PLATE IN FLEX PACK ON 100 HR INSPECTION.						1	G	7	1 	3O	3	O		H1CE    	1E10
1998120400056	19981204	00056	CE  	1998	12	4	CA980915014      	1	19980902	G	3246		NOSE GEAR       	EDO         	3500        	CESSNA	185   	A185F       	2072821	CE  										NLG	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) LEFT FLOAT MAIN GEAR WOULD NOT LOCK UP ALL THE TIME.  MAIN SLIDE FITTING IN UP POSITION, BUT NOT LOCKED.  PUMP WOU	LD CONTINUE TO OPERATE TO FORCE GEAR TO LOCK.  NEITHER CABLE ADJUST, NOR TENSION CYLINDER O-RING REPLACEMENT DID ANY GOO	D.  LEFT NOSE STRUT FOUND LOW ABOUT 2 INCHES.  IT WAS NOT NOTICED AT FIRST BECAUSE THE RT NOSE WOULD SUPPORT THE WEIGHT 	OF BOTH FLOATS.  WHEN GEAR SELECTED UP, THE NOSE GEAR WOULD SOMETIMES BE COMPRESSED BY 2 INCHES AND THE FORK WOULD REST 	AGAINST THE UPPER FORWARD BULKHEAD, NOT ALLOWING THE MAIN SLIDE FITTING TO LOCK.  PROPER SERVICING OF OLEO REQUIRED TO A	LLOW PROPER GEAR OPERATION.	1	H	7	1 	3O				3A24
1998120400057	19981204	00057	NE  	1998	12	4	CA980915015      	2	19980903	G	8530		CYLINDER        			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134053     	52016	NE  					ENGINE	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								8884			(CAN) NR 2 CYLINDER FAILED IN-FLIGHT AND A POWERLESS LANDING CARRIED OUT.  INSPECTION FOUND THE EXHAUST VALVE BROKE AND 	THE HEAD SPLIT.  THE CYLINDER WAS REPLACED.  TWENTY MINUTES INTO TEST FLIGHT, THE ENGINE EXPERIENCED A POWER LOSS.  AIRC	RAFT LANDED SAFELY.  POST-FLIGHT COMPRESSION TEST FOUND THE NR 7 CYLINDER WITH A DIFFERENTIAL PRESSURE OF 0/80.  INSPECT	ION FOUND THE CYLINDER HEAD AND VALVE SEAT DAMAGED DUE TO FOD AND THE OIL SCREEN FULL OF ALUMINUM PARTICLES.  WHEN NR 2 	CYLINDER FAILED, THE EXHAUST VALVE BROKE AND DAMAGED THE INTAKE VALVE.  PARTS FROM THE INTAKE VALVE WENT INTO THE MANIFO	LD AND SUPERCHARGER SECTION, THEN TO THE NR 7 CYLINDER CAUSING THE FAILURE.  THE ENGINE WAS REMOVED FROM SERVICE.	1	H	7	1 	3R	3	R		A815    	5E2
1998120400058	19981204	00058	SO  	1998	12	4	CA980915018      	1	19980901	G	3297		WIRE            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					RT MLG	BROKEN          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA								RL301061A			(CAN) ON APPROACH, DURING LANDING GEAR LOWERING, NO LIGHT INDICATION OR FLAG FOR THE RIGHT MAIN LANDING GEAR.  EMERGENCY	 DECLARED AND AIRCRAFT LANDED SAFELY.  MAINTENANCE INVESTIGATION FOUND A BROKEN WIRE.					1	L	7	2 	3O	3	O	 	A20SO   	E14EA
1998120400059	19981204	00059	NM  	1998	12	4	CA980915019      	1	19980903	G	2820	82820083003	LINE            			DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					FUEL SYSTEM	CHAFED          	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			19091					120387			(CAN) AS THE PILOT WAS DOING A WALK-AROUND CHECK, HE NOTICED A SMALL FUEL LEAK FROM A DRAIN HOLE UNDER THE RIGHT HAND WI	NG.  FURTHER INVESTIGATION REVEALED THAT THIS LEAK WAS DUE TO CHAFING ON THE TUBE AGAINST THE SPLIT RING INSIDE THE SPLI	T CONNECTOR.  TUBE PART NUMBER 82820083-003, AND SPLIT WASHER PART NUMBER 3659-6-9.  PART TC:  24,481.				2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1998121700008	19981217	00008	SO  	1998	12	17	CA980915022      	1	19980908	G	5210	43515000	PIN             		41420002    	PIPER 	PA31  	PA31310     	7103103	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					PAX DOOR HINGE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			579  					L161761			(CAN) PASSENGER DOOR HINGE FOUND LOOSE.  NEW HINGE HARDWARE OBTAINED FROM PIPER DEALER RECENTLY INSTALLED.  THE HINGE PI	N WAS FOUND TO HAVE A DIAMETER OF .089 INCH.  A HINGE PIN WITH A DIAMETER OF .091 INCH WAS INSTALLED WHICH ELIMINATED AN	Y LOOSENESS OR PLAY.  A LOOSE HINGE PIN COULD CONTRIBUTE TO THE DOOR OPENING IN-FLIGHT.				1	L	7	1 	3O	3	O	RT	A20SO   	E14EA
1998100900371	19981009	00371	EA  	1998	10	9	CA980915023      	2	19980908	G	8520		CRANKSHAFT      			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					NR 2 ENGINE	DISCONNECTED    	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA								RL18968A			(CAN) NR 2 ENGINE SUDDENLY STOPPED DURING FLIGHT. POST-FLIGHT INSPECTION FOUND THE CAMSHAFT AND THE ACCESSORY GEARBOX WE	RE NO LONGER DRIVEN BY THE CRANKSHAFT.  A FOLLOW-UP REPORT WILL BE SUBMITTED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998120400072	19981204	00072	EA  	1998	12	4	CA980916016      	2	19980811	G	8530	ECLW13448CP	HEAD            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540*     	41532	EA  					NR 3 CYLINDER	CRACKED         	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E	K		VIBRATION/BUFFET          	FLUID LOSS                		CL	CLIMB          	1			CA								L803061A			(CAN) DURING CLIMB-OUT, THE NR 1 ENGINE BEGAN TO RUN ROUGH.   A SHORT TIME LATER, OIL STARTED TO APPEAR ON THE ENGINE CO	WLING.  THE CREW DID A PRECAUTIONARY SHUTDOWN AND RETURNED TO THE POINT OF DEPARTURE.  POST-FLIGHT INSPECTION FOUND THE 	NR 3 CYLINDER WITH A CRACKED HEAD, MOVEMENT OF THE HEAD ALLOWED THE PUSHROD SEALS TO UNSEAT RESULTING IN THE OIL LEAK. T	HE NR 3 CYLINDER WAS REPLACED AND GROUND RUN SERVICEABLE.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1998120400084	19981204	00084	EA  	1998	12	4	CA980916029      	2	19980909	G	8520	1937	BOLT            		67514       	PIPER 	PA32  	PA32300     	7103212	SO  	LYC   	O540  	IO540K1G5   	41532	EA  					CRANKSHAFT	SHEARED         	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA				1200 				L1751348A			(CAN) PILOT EXPERIENCED TOTAL ENGINE FAILURE.  AFTER A SUCCESSFUL FORCED LANDING, INVESTIGATION REVEALED CAMSHAFT WAS NO	T TURNING WITH PROP ROTATION.  THE REMOVAL REAR CASE SHOWED CRANKSHAFT GEAR ATTACHMENT BOLT AND DOWEL WERE SHEARED.  THE	 GEAR WAS OUT OF MESH WITH REMAINING GEAR TRAIN.  THE WRENCH FLATS ON BOLT HEAD WERE ROUNDED OFF INDICATING GEAR HAD BEE	N RUNNING LOOSE FOR SOME TIME.  LT MAGNETO HAD A CRACKED CASE, ONE IMPULSE COUPLING STOP PIN WAS SEVERELY WORN AND FLYWE	IGHTS WERE LOOSE DUE TO WORN RIVETS.  THE SUBMITTER SUGGESTS THAT FAILURE WAS CAUSED BY 2 FAULTS:  THE GEAR WAS LOOSE, A	ND, MAGNETO STOPPED DUE TO EXCESSIVE WEAR IN IMPULSE COUPLING WHICH FORCED GEAR TO SHEAR.	1	L	7	1 	3O	3	O		A3SO    	1E4
1998120400094	19981204	00094	NM  	1998	12	4	CA980916042      	1	19980831	G	5700	57085	FLYING WIRE     			CHRIS 	HUSKY 	A1          	221020X	NM  										WING	BROKEN          	W				A				UNSCHED LANDING         				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			1833 								(CAN) IN CRUISE, AIRCRAFT ON FLOATS, IN CALM AIR, THE PILOT FELT A THUMP IN THE CONTROL STICK AND A SUBSEQUENT VIBRATION	.  FLIGHT CONTINUED TO AN UNEVENTFUL LANDING.  THE UPPER LEFT FLYING WIRE WAS FOUND TO HAVE SEPARATED 6 INCHES FROM THE 	LOWER END.  NO CORROSION EVIDENT.  PART TC:  2,386.				1	H	7	1 	3O			NC	A22NM
1998120400095	19981204	00095	CE  	1998	12	4	CA980916044      	1	19980827	G	7110	H296K1136	COWL            		50910275267 	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  					NACELLE	UNLATCHED       	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA								PCE40209			(CAN) A TAKEOFF WAS ATTEMPTED WITH THE ENGINE COWL RIGHT FORWARD UPPER UNLATCHED COWL OPENED AND PUNCTURED THE NACELLE. 	 COWL STAYED WITH THE AIRCRAFT AND TAKEOFF ABORTED.  NO FURTHER PROBLEMS.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1998121700009	19981217	00009	CE  	1998	12	17	CA980916045      	1	19980914	G	6123	5038912119	SWITCH          			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN2     	GL  	RT ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								PCE40813	BU8250		(CAN) AFTER TAKEOFF, LEFT AUTOFEATHER LIGHT WOULD NOT ARM.  AIRCRAFT RETURNED TO BASE.  MAINTENANCE CHANGED THE HIGH PRE	SSURE SWITCH ON RIGHT ENGINE.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
1998120400096	19981204	00096	CE  	1998	12	4	CA980916046      	1	19980902	G	2820	A29002	LINE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			224  					PCEPS0209			(CAN) DURING ROUTINE MAINTENANCE, THE RIGHT HAND ENGINE MAIN FUEL PUMP HOSE ASSY WAS FOUND TO BE LEAKING.  HOSE ASSY REP	LACED.  LEAKING OF HOSE WAS DUE TO INTERNAL FAILURE OF HOSE LINING.  PART TC:  293.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998120400097	19981204	00097	CE  	1998	12	4	CA980916047      	1	19980914	G	3260	11438004113	SWITCH          			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					LT MLG	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			LD	LANDING        	1			CA			661  					PCEPSO197			(CAN) ON GEAR DOWN SELECTION, THE LEFT HAND MAIN INDICATOR WOULD OCCASIONALLY DELAY SLIGHTLY BEFORE ILLUMINATING.  MAINT	ENANCE FOUND THE INTERNAL DOWN POSTION MICROSWITCH IS SOMEWHAT INTERMITTENT.  ACTUATOR REPLACED.  PART TC:  774.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999043000081	19990430	00081	EA  	1999	4	30	CA980916048      	1	19980826	G	2432	MA300H	BATTERY         			DHAV  	DHC6  	DHC6200     		EA  	PWA   	PT6   	PT6A20      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	E/E BAY	FAILED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TX	TAXI/GRND HDL  	1			CA				30   		9601563		PCE20443	BU8721		(CAN) DURING RAMP TAXI FLIGHT, CREW AND PASSENGER NOTED SMOKE IN AFT CABIN.  GENERATOR AND ELECTRICAL SYSTEMS SHUT DOWN.	  PASSENGER DEPLANED.  BAGGAGE COMPARTMENT OPENED AND AUXILIARY BATTERY FOUND SMOKING.  IT HAD HAD A THERMAL RUNAWAY AND	 WAS MELTED.  NO OTHER DAMAGE.				1	H	7	2 	3T	3	T		A9EA    	E4EA	6	C	P15E
1999031200270	19990312	00270	EA  	1999	3	12	CA980916049      	1	19980826	G	5523	C2TE44A	TAB             		C2TE2A      	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								8730			(CAN) DURING INSPECTION, THE ELEVATOR TRIM TAB WAS FOUND CRACKED BOTH TOP AND BOTTOM AT THE PUSH ROD END.  RACK APPROXIM	ATELY 2 INCHES LONG CAUSING SUBSTANTIAL LOSS IN STRENGTH.					1	H	7	1 	3R	3	R		A806    	5E1
1999031200271	19990312	00271	EA  	1999	3	12	CA980916050      	1	19980903	G	5751	C3WA122	SKIN            			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						FW214		P325615			(CAN) TRAILING EDGE OF RIGHT HAND AILERON FOUND CRACKED IN 4 DIFFERENT LOCATIONS ON SAME SKIN.						1	H	7	1 	3R	3	R		A815    	5E2
1998120400098	19981204	00098	EU  	1998	12	4	CA980916051      	2	19980908	G	7240	RK45001	FLAME TUBE      	RROYCE      	RK49163A    	BRAERO	748   	HS7482A     	4231001	EU  	RROYCE	DART  	DART5342    		EU  					EXHAUST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2189 		A171		19295			(CAN) DURING A REGULAR SCHEDULED FUEL BURNER WIPE ON THE NR 5 COMBUSTION CAN, THE BURNER TOOL BRUSH WOULD NOT CONTACT TH	E FUEL NOZZLE.  THE CAN WAS REMOVED AND THE FLAME TUBE DOME END, WHERE THE SWIRL VANE IS LOCATED, WAS FOUND CRACKED APAR	T WAY AROUND THE CIRCUMFERENCE AND COMPLETELY DETACHED FROM THE WELDS.  THIS CAUSED THE SWIRL VANE CAP TO LODGE IN THE T	UBE AT ABOUT A 5 DEGREE ANGLE.  THE FLAME TUBE WAS ALSO CRACKED ON THE WELD JOINT, JUST FORWARD OF THE LINER.  THE COMBU	STION LINER WAS REPLACED.  PART TC:  3,213.		2	L	7	2 	3T	4	T		A24EU   	A196
1998120400099	19981204	00099		1998	12	4	CA980916052      	4	19980806	G	6122	11967614	GOVERNOR        	WOODWARD    	8210403A    	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	FAILED          	W				K				NONE                    				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA			703  			11967614					(CAN) ON TAKEOFF ROLL, PROP RPM DROPPED FROM GOVERNING SPEED OF 1700 RPM TO 1500 RPM.  UPON ROTATION ,THE PROP RPM GRADU	ALLY RETURNED AND STABILIZED AT 1700 RPM ONCE AIRBORNE AT 20 FEET.  MAINTENANCE REPLACED THE PROP GOVERNOR WITH A NEW ST	YLE GOVERNOR P/N 8210-410 AS PER PRATT & WHITNEY S/B 14260R1.  THE NEW STYLE PROP GOVERNOR HAS A RE-DESIGNED OIL PUMP TO	 INCREASE DURABILITY.  PART TC:  1,445.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
1998120400102	19981204	00102	CE  	1998	12	4	CA980916059      	1	19980909	G	2820	120040618	LINE            			CESSNA	206   	TU206B      	2073324	CE  	CONT  	O520  	TSIO520C    	17040	SO  	MCAULY	3A32C	D3A32C90    	GL  	FUEL SYSTEM	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2093 					1404397C	681591		(CAN) RIGHT AILERON CABLE RUNNING VERTICALLY UP THE RIGHT WINDOW POST RUBBING AND WEARING INTO THE FUEL LINE WHICH IS RU	NNING UP THE SAME POST.					1	H	7	1 	3O	3	O		A4CE    	E8CE	5	C	P21EA
1999012900210	19990129	00210	SO  	1999	1	29	CA980916061      	1	19980825	G	3246	MS2125005016	BOLT            	BFGOODRICH  	314461      	EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	RT MLG WHEEL	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1960 			1874		115667	880529		(CAN) PILOT FOUND A BROKEN BOLT DURING WALK-AROUND ON THE RIGHT HAND INBOARD MAIN WHEEL ASSY.  BOLT HAD BEEN INSPECTED P	ER SB 3-1446-32-4, WHICH RECOMMENDS THAT BOLTS, IF FOUND OK ON EXAM, CAN BE USED UP TO FIVE TIRE CHANGES.  THIS DEFECTIV	E BOLT WAS MAGNETIC PARTICLE INSPECTED 4 TIMES PRIOR TO FAILURE.  SUBMITTER RESOLVES TO INSTALL NEW BOLTS AT EVERY TIRE 	CHANGE.   PART TC:  1,685.			2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1998120400106	19981204	00106	EA  	1998	12	4	CA980916065      	1	19980910	G	7810	3503	GASKET          			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					EXHAUST	FAILED          	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			50   					JP20781			(CAN) DURING INSPECTION, THE EXHAUST GASKETS WERE FOUND BURNED IN THE CENTER AREA.  THE SUBMITTER REPORTS THAT PREVIOUSL	Y GASKETS WERE MADE FROM ASBESTOS MATERIAL, WHICH WAS NOT SUSCEPTIBLE TO BURNING.					1	H	7	1 	3R	3	R		A806    	5E1
1998120400107	19981204	00107	NE  	1998	12	4	CA980916066      	2	19980903	G	7230	UL19820	LINE            			BOEING	757   	757236      		NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					NR 1 ENGINE	BROKEN          	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								30841			(CAN) AT FL 350, THE FLIGHT CREW HAD INDICATION OF SMOKE IN THE FLIGHT DECK.  NO SMOKE WAS REPORTED IN THE CABIN AND ALL	 ENGINE PARAMETERS WERE NORMAL.  THE FLIGHT WAS DIVERTED.  AT 10,000 FEET, THE NR 1 ENGINE OIL QUANTITY WAS READING 8, O	IL TEMPERATURE 135, OIL PRESSURE 57 PSI AND THE OIL FILTER ECAS MESSAGE CAME ON.  THE NR 1 ENGINE POWER WAS REDUCED TO I	DLE AND THE SMOKE DISSIPATED.  NORMAL LANDING WAS CARRIED OUT.  POST-FLIGHT INSPECTION OF THE NR 1 ENGINE FOUND THE INTE	RCONNECTING OIL TUBE BROKEN INSIDE THE NR 3 MODULE.  THE ENGINE WAS REPLACED.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
1999031200273	19990312	00273	EA  	1999	3	12	CA980922001      	1	19980813	G	3297	5801	WIRE            			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					NLG	CUT             	W				A	L			UNSCHED LANDING         	ABORTED APPROACH        			J			WARNING INDICATION        			AP	APPROACH       	1			CA			530  					13496			(CAN) NO RIGHT NOSE GEAR DOWN AND LOCK LIGHT.   WIRE FOUND BROKEN AT PROXIMITY SWITCH.						1	H	7	1 	3R	3	R	 	A806    	5E1
1998100900373	19981009	00373	NE  	1998	10	9	CA980922002      	2	19980912	G	7260		CHIP DETECTOR   			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	ILLUMINATED     	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			J			WARNING INDICATION        			CR	CRUISE         	1			CA								LEO7611			(CAN) DURING FIREFIGHTING OPERATIONS, THE CHIP LIGHT ILLUMINATED.  AFTER INSPECTION, THE AIRCRAFT WAS RETURNED TO SERVIC	E.  ONE HOUR INTO OPERATIONS, THE CHIP LIGHT AGAIN ILLUMINATED AND THE AIRCRAFT WAS REMOVED FROM SERVICE.  A FURTHER REP	ORT WILL BE SUBMITTED WHEN THE ENGINE HAS BEEN DISASSEMBLED.				1	G	7	1 	4U	4	U		H1SW    	E17EA
1998120400113	19981204	00113	CE  	1998	12	4	CA980922003      	1	19980915	G	2820	S23591	VALVE           		042601923   	CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	LT WING	LEAKING         	W				O				OTHER                   				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			8748 						KD023		(CAN) ON TAXI FROM RAMP, EXCESSIVE FUEL WAS NOTICED COMING FROM THE LEFT WING VENT.  VENT VALVE FOUND LEAKING.						1	H	7	1 	3O			NT	3A19    		5	N	P50GL
1998120400116	19981204	00116	SO  	1998	12	4	CA980922006      	2	19980811	G	7414	103493504R	MAGNETO         			CESSNA	210   	210R        	2073458	CE  	CONT  	O520  	IO520L      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				40   				270490R	842114		(CAN) AFTER LANDING A MAGNETO CHECK FOUND THE LEFT HAND MAGNETO DEAD. THE MAGNETO WAS REPLACED. THE CAUSE OF THE FAULT W	AS NOT DETERMINED.					1	H	7	1 	3O	3	O	RT	3A21    	E5CE	5	C	P47GL
1998120400117	19981204	00117	GL  	1998	12	4	CA980922007      	3	19980909	G	6114	D32612	HUB             													HARTZL	HCE3Y	HCE3YR2     	GL  	PROPELLER	SCORED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									DJ8255A		(CAN) INSPECTION FOUND THE REAR OF THE PROPELLER HUB MARKED AND CRACKED WAS CAUSED BY THE STUDS USED TO INSTALL THE PROP	ELLER TO THE ENGINE FLANGE.															5	C	P33EA
1998120400118	19981204	00118	NE  	1998	12	4	CA980922008      	3	19980911	G	6114		HUB             			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	PROPELLER	CRACKED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				1442 				4224511	WPL88001		(CAN) PILOT REPORTED THE PROPELLER WAS SLOW TO RESPOND DURING PROPELLER CYCLING.  INSPECTION FOUND THE REAR BARREL CRACK	ED.  DISASSEMBLY OF THE BARREL REVEALED THE INTERIOR RADIUS WAS CRACKED 3/4 OF THE RADIUS.   AS THIS BARREL HOLDS THE PR	OP BLADE IN THE SPIDER, THE SUBMITTER STATES THAT FAILURE OF THE BARREL WAS IMMINENT.				1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
1998120400119	19981204	00119	SW  	1998	12	4	CA980922009      	1	19980910	G	6210	204011250001	BLADE           			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					MAIN ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			749  			A11749		LE07158X			(CAN) DURING A FUEL STOP, ENGINEER FOUND CRACK IN BLADE.  NO ABNORMAL FLIGHT CHARACTERISTICS. CRACK RUNS FROM THE INBOAR	D CORNER OF THE TRIM TAB, FORWARD TO THE SPAR AND THEN INBOARD ALONG THE SPAR FOR 6 INCHES.  BELL ASB 205-96-67 IS BEING	 DONE DAILY, BUT THIS CRACK IS NOT IN THE AREA COVERED BY THE ASB.				1	G	7	1 	4U	4	U		H1SW    	E17EA
1999012900211	19990129	00211	EA  	1999	1	29	CA980922010      	1	19980914	G	5740	21531033800	ANGLE           			CNDAIR	CL215 	CL2151A10   		EA  										RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2750 								(CAN) WHILE DOING AD CF-97-07 OF WING-TO-FUSELAGE FITTINGS, A CRACK WAS FOUND ON THE RIGHT HAND FORWARD OUTBOARD ANGLE A	T THE LOWER 3 FASTENER HOLE LOCATION.  THE CRACK WAS VISIBLE TO THE NAKED EYE.  CRACK EXTENDED FROM THE CENTER OF FASTEN	ER HOLE TO WITHIN .50 INCH FROM THE ANGLE EDGE, AND .1250 INCH THROUGH THE OTHER SIDE OF FASTENER HOLE.  AIRCRAFT HAD 37	5 HOURS SINCE LAST INSPECTION OF THIS AD.			2	H	7	2 	4R				A14EA
1998120400120	19981204	00120	SO  	1998	12	4	CA980922011      	1	19980910	G	2730	81948002	TUBE            			PIPER 	PA31T 	PA31T2      	7103127	SO  	PWA   	PT6   	PT6A135     	52043	NE  					ELEVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			858  					PCE92516			(CAN) AIRCRAFT ELEVATOR PULL-UP CABLE DAMPENER TUBE WAS FOUND DAMAGED IN THE MID-SECTION.  SPRING RETAINING WASHER RUBBE	D THROUGH THE TUBE, HALF ITS CIRCUMFERENCE.					1	L	7	2 	3T	4	T	RT	A8EA    	E4EA
1998120400121	19981204	00121	SO  	1998	12	4	CA980922012      	2	19980914	G	8530	SA10200A20P	PISTON RING     	SUPAIRPART  		CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A102	1A102OCM    	GL  	NR 1 CYLINDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1693 					2047929AS0	G14848		(CAN) DURING INSPECTION, METAL PARTICLES WERE FOUND IN THE OIL SCREEN AND FILTER.  A COMPRESSION CHECK REVEALED LOW COMP	RESSION ON NR 1 CYLINDER.  FURTHER INVESTIGATION FOUND A CRACKED PISTON RING, DAMAGED PISTON AND A SCORED CYLINDER WALL.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1998120400122	19981204	00122	CE  	1998	12	4	CA980922015      	1	19980915	G	5713	262200063	STRINGER        			CESSNA	208   	208B        	2073701	CE  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) STRINGER FOUND CRACKED.  STRINGER IS RIVETED TO BOTTOM SURFACE OF TOP WING SKIN WITH MOST INBOARD RIVET PICKING UP	 ON THE INNERMOST FLAP TRACK.  AREA SEEN BY LOWERING FLAPS AND REMOVING PANEL IN FLAP BAY JUST OUTBOARD OF INBOARD FLAP 	TRACK.  BOTH WINGS IN SAME CONDITION.  PART TC:  1,483.				1	H	7	1 	3T				A37CE
1998100900374	19981009	00374	NE  	1998	10	9	CA980922018      	2	19980909	G	7200		ENGINE          			BOEING	727   	727217      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J	Y	VIBRATION/BUFFET          	WARNING INDICATION        	ENGINE STOPPAGE           	CL	CLIMB          	1			CA								695336			(CAN) EXTREME ENGINE AND AIRFRAME VIBRATION WAS FELT ON CLIMB-OUT AFTER TAKEOFF.  NR 2 ENGINE FAIL LIGHT ILLUMINATED.  A	LL ENGINE PARAMETERS DECAYED TO IDLE. PRECAUTIONARY ENGINE SHUTDOWN WAS CARRIED OUT AND THE AIRCRAFT RETURNED TO ITS POI	NT OF DEPARTURE.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998120400123	19981204	00123	SW  	1998	12	4	CA980922019      	1	19980910	G	2840	222366684103	PROBE           			BELL  	430   	430         	1182150	SW  										FUEL SYSTEM	MISINSTALLED    	W				D				RETURN TO BLOCK         				N	X	W	FALSE WARNING             	ENGINE FLAMEOUT           	INADEQUATE Q C            	TX	TAXI/GRND HDL  	1			CA			3    								(CAN) DURING FLIGHT TEST PROGRAM AT BHTC, LOW FUEL INDICATION ILLUMINATED ON BOTH ENGINES AT THE 300 POUND LEVEL WHILE T	HE NORMAL IS ABOUT 100 POUNDS.  AIRCRAFT RETURNED TO BASE AND LANDED WITH 270 POUNDS REMAINING.  DURING THE 2 MINUTE COO	L DOWN, BOTH ENGINES STARTED TO SPUTTER AND FUEL PRESSURE LIGHT ILLUMINATED, BOTH ENGINES WERE SHUT DOWN BEFORE FLAME-OU	T.  LOWER FUEL PROBES HAD BEEN INSTALLED INCORRECTLY UPSIDE DOWN.			1	G	7	2 	3U			RT	H9SW
1998120400124	19981204	00124	SO  	1998	12	4	CA980922020      	1	19980910	G	5530	4046308	SKIN            			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					VERTICAL STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			7721 					L161761			(CAN) BEACON CIRCUIT BREAKER TRIPPED.  WATER INFILTRATING THE FRONT TOP END OF THE VERTICAL STABILIZER, AND RUNNING INTO	 POWER PACK IN THE BEACON.  THE BEACON IS MOUNTED ON THE FIN TIP. THIS WAS ORIGINALLY USED FOR AN ADF ANTENNA INSTALLATI	ON ALSO BUT WAS NO LONGER USED.  THE ATTACH FITTINGS WERE MOUNTED WITH POP RIVETS INSTEAD OF FULL HEAD RIVETS.  IN TIME,	 WATER WAS FORCED INTO THE RIVET HOLES ALLOWING THE RIVETS TO CORRODE, THE FITTINGS TO LOOSEN, AND EVENTUALLY, CRACK THE	 FIN TIP.		1	L	7	2 	3O	3	O		A20SO   	E14EA
1998120400125	19981204	00125		1998	12	4	CA980922021      	4	19980910	G	3422	40002028501	CORRECTOR       	BENDIX      		PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					HSI	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2527		L104448			(CAN) HSI NOT WORKING CORRECTLY.  FOUND COMPASS CORRECTOR NOT CONNECTED AND THE NORTH-SOUTH ADJUSTING POLE DAMAGED.						1	L	7	2 	3O	3	O		1A10    	1E4
1998120400127	19981204	00127	CE  	1998	12	4	CA980922024      	1	19980902	G	5554	MS289135C	BEARING         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					RUDDER	STIFF           	W				K				NONE                    				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA								PCE32017			(CAN) CREW REPORTED STEERING AS BEING STIFF ACCOMPANIED WITH A GRINDING NOISE.  UPON INVESTIGATION, THE LOWER RUDDER BEA	RING WAS FOUND TO BE STIFF TO MOVE. THE CENTER ATTACHMENT BOLT WAS SEIZED TO THE BEARING AND HAD TO BE DRILLED OFF THE B	ELLCRANK.  NEW BEARING INSTALLED AND RUDDER TRAVEL CHECKED OK.				2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1998120400128	19981204	00128	EA  	1998	12	4	CA980928001      	2	19980805	G	8520	13B37020	CRANKSHAFT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1179 				L1057839A			(CAN) TO COMPLY WITH AD 98-02-08, IN ACCORDANCE WITH LYCOMING SERVICE BULLETIN 505B, PITTING WAS NOTED ON THE INTERNAL B	ORE OF THE CRANKSHAFT.  FPI CARRIED OUT, NO CRACKS WERE FOUND.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998120400129	19981204	00129	EA  	1998	12	4	CA980928002      	2	19980807	G	8520	13B37026	CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1783 				L415576	733708		(CAN) TO COMPLY WITH AD 98-02-08, IN ACCORDANCE WITH LYCOMING SERVICE BULLETIN 505B, PITTING WAS NOTED ON THE INTERNAL B	ORE OF THE CRANKSHAFT.  FPI CARRIED OUT, NO CRACKS WERE FOUND.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998120400130	19981204	00130	EA  	1998	12	4	CA980928003      	2	19980910	G	8520	13B37020	CRANKSHAFT      			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					ENGINE	PITTED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1249 				L1028239A			(CAN) TO COMPLY WITH AD 98-02-08, IN ACCORDANCE WITH LYCOMING SERVICE BULLETIN 505B, PITTING WAS NOTED ON THE INTERNAL B	ORE OF THE CRANKSHAFT. FPI CARRIED OUT, NO CRACKS WERE FOUND.					1	H	7	1 	3O	3	O	NT	3A12    	E274
1998120400131	19981204	00131	EU  	1998	12	4	CA980928004      	2	19980915	G	8500	2072000002	RADIATOR PIPE   								ROTAX 	912   	ROTAX912    	55555	EU  					ENGINE COOLING	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1341 					4412518			(CAN) ON 100-HOUR INSPECTION, THE INBOARD EXHAUST RETAINER SPRING BETWEEN NR 3 CYLINDER EXHAUST STACK AND THE MUFFLER HA	D WORN 3 DEEP GROOVES IN THE SOLID COOLANT RETURN PIPE THAT IS ROUTED BESIDE IT.  AIRCRAFT MANUFACTURER INFORMED.										3	I			EXPE3I
1998120400133	19981204	00133	CE  	1998	12	4	CA980928006      	1	19980820	G	3250	12438116	COLLAR          		1243610221  	CESSNA	206   	U206G       	2073356	CE  	CONT  	O520  	IO520F      	17032	SO  	MCAULY	D3A34	D3A34C404   	GL  	NLG	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			TO	TAKEOFF        	1			CA								195892RA	960119		(CAN) ON TAKEOFF, THE STEERING COLLAR BROKE.   AIRCRAFT LANDED OK.  NEW PART APPEARS TO BE OF A HEAVIER MATERIAL.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P47GL
1998120400137	19981204	00137	CE  	1998	12	4	CA980928010      	1	19980911	G	5541	073100049	RIB             			CESSNA	180   	180         	2072602	CE  						MCAULY	2A34C	2A34C66     	GL  	RUDDER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									720750		(CAN) WHILE INVESTIGATING MINOR SKIN DIAMAGE, IT WAS NOTED THAT RIBS 073100-49 AND -50 WERE MISSING.  ALL OF THE RIVET H	OLES WERE PLUGGED WITH RIVETS.					1	H	7	1 	3O			NC	5A6     		5	C	P3EA
1998120400139	19981204	00139	SO  	1998	12	4	CA980928012      	1	19980916	G	5280	466522	HINGE           		4752932     	PIPER 	PA31  	PA31350     	7103110	SO  										MLG DOOR	CRACKED         	W				O				OTHER                   				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, GEAR INTRANSIT LIGHT WOULD NOT GO OUT.  GEAR CYCLED DOWN, BUT UNABLE TO GET 3 GREENS.  GEAR MANUALL	Y LOWERED, AND THEN 3 GREENS.  THE LEFT GEAR INNER DOOR, FORWARD HINGE WAS FOUND BROKEN IN HALF.  HINGE WAS OF THE IMPRO	VED TYPE CALLED FOR IN SB 682 AND AD 80-26-05.  THESE RELIEVED THE RECURRENT INSPECTION REQUIREMENT.				1	L	7	2 	3O				A20SO
1998100900375	19981009	00375	CE  	1998	10	9	CA980928015      	1	19980916	G	3233	EA16141	ACTUATOR        			CESSNA	210   	210C        	2073412	CE  	CONT  	O470  	IO470S      	17026	SO  	MCAULY	2A34C	D2A34C49    	GL  	LT MLG	SNAPPED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			AP	APPROACH       	1			CA						246		1022672S1	756150		(CAN) LEFT GEAR WOULD NOT EXTEND TO LOCK.  AIRCRAFT MANEUVERING MANAGED TO PUT GEAR INTO LOCK. THE LEFT GEAR ACTUATOR FO	UND WITH A SNAPPED SECTOR GEAR SHAFT.  REASON UNKNOWN.  PART FORWARDED TO TSB.  THE LEFT BRAKE ALSO HAD FAILED ON LANDIN	G.				1	H	7	1 	3O	3	O		3A21    	3E1	5	C	P3EA
1998120400142	19981204	00142	SO  	1998	12	4	CA980928016      	2	19980917	G	7310	63432611A4	MANIFOLD        			CESSNA	401   	401A        	207590D	CE  	CONT  	O520  	TSIO520VB   	17040	SO  					FUEL SYS	DAMAGED         	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA								516376			(CAN) NR 1 ENGINE RAN ROUGH IN CRUISE.  INSPECTION FOUND ONE FUEL INJECTOR WAS PARTIALLY BLOCKED.  THE FUEL MANIFOLD WAS	 DISASSEMBLED AND THE SCREEN WITHIN THE MANIFOLD WAS FOUND DISTORTED.  THE FUEL MANIFOLD WAS REPLACED.  THE ENGINE WAS G	ROUND RUN SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.				1	L	7	2 	3O	3	O		A7CE    	E8CE
1998120400144	19981204	00144	CE  	1998	12	4	CA980928018      	1	19980923	G	5713	9912001212	STRINGER        			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10183					PCE50224			(CAN) DURING THE INVESTIGATION OF DAMAGE TO THE LOWER SKIN OF THE CENTER SECTION, THE AUXILIARY FUEL CELL LINER WAS REMO	VED, FOUND THE T-EXTRUSION WHICH TIES TOGETHER THE LOWER SKIN WITH THE NACELLE KEEL STRUCTURE CRACKED AT THE AFT END.  P	ART TC:  11,414.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998120400145	19981204	00145	WP  	1998	12	4	CA980928019      	2	19980911	G	7250	8675697	CARBON SEAL     			MTSBSI	MU2   	MU2B36      	5780412	CE  	GARRTT	TPE331	TPE3316251M 	01514	WP  					1ST STAGE	FAILED          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			CR	CRUISE         	1			CA			664  					P20079C			(CAN) THE PILOT OBSERVED FLUCTUATIONS IN TORQUE AND OIL PRESSURE, AS WELL AS VISIBLE OIL VENTING FROM THE ENGINE. THE EN	GINE WAS SHUT DOWN AND THE AIRCRAFT LANDED.   POST-FLIGHT INSPECTION FOUND A MISSING SECTION OF THE 1ST STAGE TURBINE WH	EEL CREATED AN IMBALANCE WHICH LED TO THE VIBRATION THAT CAUSED THE FAILURE OF THE COMPRESSOR INLET CARBON SEAL.  THIS A	LLOWED HIGH PRESSURE P2 AIR TO PRESSURIZE THE GEARBOX AN OIL TANK, RESULTING IN THE VENTING OF OIL OVERBOARD.  PART TC: 	 770.		1	H	7	2 	3T	4	T	RT	A10SW   	E2WE
1998120400146	19981204	00146		1998	12	4	CA980928020      	4	19980918	G	3197		WIRE            	COLLINS     	FD108Y      	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					COCKPIT	CHAFED          	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			TO	TAKEOFF        	1			CA			7640 					PCE81498			(CAN) OVER A SHORT PERIOD OF TIME, CREW REPORTED A PECULIAR ODOR DURING TAKEOFF IN PERFORMING MAINTENANCE BEHIND PILOTS 	INSTRUMENT PANEL, SOOT TRAILS AND ELECTRICAL ARC MARKS WERE FOUND ON LOWER INBOARD EDGE OF WINDSHIELD WIPER MOTOR MOUNTI	NG PLATE.  IT APPEARED TO BE FROM A SMALL WIRE BUNDLE LEADING TO FLIGHT DIRECTOR ANNUNCIATOR ASSY WHICH HAD BEEN ROUTED 	BETWEEN WIPER MOTOR MOUNTING BRACKET AND LARGE WIRE BUNDLE.  THIS BRACKET CAUSED THE CHAFING.  WIRING WAS REPAIRED AND W	IRE HARNESS REROUTED.  NO FURTHER ODOR REPORTS SINCE THE REPAIR.		1	L	7	2 	4T	4	T	 	A24CE   	E4EA
1998120400151	19981204	00151	CE  	1998	12	4	CA980928029      	1	19980910	G	7120	NAS335CP23	BOLT            		265103113   	LEAR  	35    	35A         	5170602	CE  	GARRTT	TFE731	TFE73122B   	01518	WP  					ENGINE MOUNT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4156 					P89710			(CAN) TWO BOLTS FOUND CRACKED AT ENGINE REMOVAL USING NDT METHOD.  THESE BOLTS ARE NOT ON A MAINTENANCE SCHEDULE REQUIRI	NG INSPECTION.  PART TC:  3,492.					2	L	7	2 	4F	4	F		A10CE   	E6WE
1998120400152	19981204	00152	NE  	1998	12	4	CA980928030      	2	19980817	G	7200		ENGINE          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					NR 1 NACELLE	MALFUNCTIONED   	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			N			FALSE WARNING             			CL	CLIMB          	1			CA			1672 					872133			(CAN) SHORTLY AFTER TAKEOFF, THE NR 1 ENGINE LOW OIL PRESSURE WARNING MESSAGE CAME ON.  ALL ENGINE PARAMETERS WERE NORMA	L.  PILOT ELECTED TO DO A PRECAUTIONARY ENGINE SHUT DOWN.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  PART TC:  1,790	.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
1998120400153	19981204	00153	NE  	1998	12	4	CA980928031      	2	19980919	G	7320	9378M87P06	SENSOR          								GE    	CF6   	CF680C2B2   	30025	NE  					HMU	FAULTY          	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			DE	DESCENT        	1			CA						MYG57773		705110			(CAN) DURING DESCENT, THE POWER WAS INCREASED TO MAINTAIN AIRSPEED TARGET.  NR 1 ENGINE PARAMETERS DID NOT CHANGE, BUT R	EMAINED INDICATING LOWER THAN NORMAL IDLE.  PRECAUTIONARY ENGINE SHUTDOWN CARRIED OUT.  POST-FLIGHT, THE N1 HYDROMECHANI	CAL SENSOR WAS CHANGED AND TESTED SERVICEABLE.									4	F			E13NE
1998120400154	19981204	00154	EU  	1998	12	4	CA980928032      	1	19980914	G	5246	A2151041500300	FUEL DOOR       			AIRBUS	310   	A310304     		EU  										WING	MISSING         	W				K				NONE                    				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) DURING INSPECTION, REFUEL DOOR MISSING.  REPLACED.						2	L	7	2 	4F			RT	A35EU
1998120400155	19981204	00155	CE  	1998	12	4	CA980928034      	1	19980922	G	7603	MS27039108	SCREW           		1005241777  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					POWER LEVER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5448 					GGM114452			(CAN) THE PILOT NOTICED SOME LOOSENESS IN THE RIGHT CONDITION LEVER DURING PRE-START CHECK LIST.  MAINTENANCE DETERMINED	 THE LOOSENESS WAS DUE TO A LOOSE SCREW SECURING THE LEVER TO THE SHAFT.  SCREW TIGHTENED.  PART TC:  6,347.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998120400156	19981204	00156	CE  	1998	12	4	CA980928035      	1	19980922	G	3250	1148200305	TUBE            		1148200303  	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NW STEERING	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5356 					GGM114476			(CAN) DURING MAINTENANCE INSPECTION, THE TUBE (P/N 114-820030-3) WAS FOUND CHAFED BY THE BOOT (P/N 50-820125) THAT IS HE	LD TIGHT ON THE TUBE BY A TIE WRAP.  PART TC:  6,383.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998120400157	19981204	00157	GL  	1998	12	4	CA980928036      	3	19980916	G	6112	4E11883	DEICER BOOT     			PIPER 	PA31  	PA31350     	7103110	SO  						HARTZL	HCE3Y	HCE3YR2A    	GL  	NR 2 BLADE	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA			3751 	1862 		E48541			DJ9380A		(CAN) NR 2 PROPELLER BLADE ON THE NR 1 ENGINE LOST ITS DEICER BOOT DURING FLIGHT.  THE MISSING DEICER BOOT WAS NOTICED A	FTER A 1.5 HOUR FLIGHT.  OTHER THAN A MOMENTARY DECREASE IN ENGINE RPM DURING THE FLIGHT, THE PILOT DID NOT NOTICE ANY V	IBRATION AND WAS UNAWARE THAT THE DEICER BOOT HAD SEPARATED.  THE BOOT HAD BEEN INSTALLED LOCALLY AND AN INSPECTION 9.9 	HOURS PREVIOUSLY DID NOT SHOW ANY PEELING OF THE BOOT.  PART TC:  400.			1	L	7	2 	3O				A20SO   		5	C	P33EA
1998120400160	19981204	00160	CE  	1998	12	4	CA980930004      	1	19980921	G	2710	06601055	CONTROL CABLE   			CESSNA	305   	305A        	2074002	CE  	CONT  	O470  	O47011      	17026	SO  					AILERON	CHAFED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			93   					104163			(CAN) AILERON CABLE FOUND WITH BROKEN STRANDS.  ON REMOVAL, NUMEROUS STRANDS WERE FOUND WORN AND BROKEN.						1	H	7	1 	3O	3	O	 	5A5     	E269
1998120400161	19981204	00161	CE  	1998	12	4	CA980930005      	1	19980608	G	2110	1005540375	PULLEY          		R20648820662	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      	 	EA  					AC BAY	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA								PCE50944			(CAN) AIR CONDITIONER COMPRESSOR PULLEY FAILURE.  BOLT STARTED TO BACK OFF CAUSING THE PULLEY TO MIGRATE OFF SHAFT AND M	OVE.  STEEL WOODRUFF KEY BEGAN TO CHEW UP THE PULLEY.  DUE TO THE LOOSENESS, PULLEY FAILED.  THERE IS NO LOCKING DEVICES	 ON THE END BOLT TO PREVENT ITS TURNING.				1	L	7	2 	3T	4	T	 	A14CE   	E4EA
1998120400162	19981204	00162	NE  	1998	12	4	CA980930006      	2	19980918	G	7230	130058402	BEARING         			BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			394  					LE07253X			(CAN) DURING INSPECTION, A COUPLE OF PIECES OF METAL WERE FOUND IN THE ENGINE EXTERNAL OIL FILTER.  THE ENGINE WAS OPENE	D AND INSPECTION FOUND THE NR 2 BEARING CAGE WAS BROKEN.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1998120400165	19981204	00165	SO  	1998	12	4	CA980930010      	1	19980914	G	5210	4663300	SOLENOID        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					DOOR SEAL	FAILED          	W				I				CABIN DEPRESSURIZATION  				O			OTHER                     			CL	CLIMB          	1			CA				1233 				P50701			(CAN) DURING CLIMB THROUGH 13,000 FEET THE AIRCRAFT LOST CABIN PRESSURIZTION.  INSPECTION FOUND THAT THE PRESSURE CONTRO	L CIRCUIT BREAKER HAD TRIPPED.  FAULT TRACED TO THE DOOR SEAL SOLENOID WHICH HAD EXCESSIVE CURRENT DRAW.					1	L	7	2 	3T	4	T		A8EA    	E4EA
1998120400166	19981204	00166	SO  	1998	12	4	CA980930011      	1	19980818	G	2810	6901545	LINE            			PIPER 	PA44  	PA44180     	7104402	SO  										FUEL VENT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5199 								(CAN) DURING 100 HOUR INSPECTION, FUEL FUMES WERE NOTED IN THE WINGS.  FUEL VENT HOSE FOUND CRACKED WHERE IT GOES THROUG	H A WING RIB.					1	L	7	2 	3O				A19S0
1998120400167	19981204	00167	EA  	1998	12	4	CA980930012      	2	19980922	G	8520	74970	CRANKSHAFT      								LYC   	O360  	O360A3A     	41514	EA  					ENGINE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA				50   				L486736			(CAN) REPORT OF PROBLEMS WITH CRANKSHAFT BALANCING R & O SHOP LED OWNER TO GROUND HIS AIRCRAFT AND REMOVE THE CRANKSHAFT	 FOR MPI INSPECTION.  CRACKS WERE FOUND AROUND 80 PERCENT OF THE NR 4 CRANKPIN RADIUS.  SIGNS OF OVERHEATING WERE ALSO P	RESENT ON THE SURFACE OF THE MAIN JOURNAL.  THE CRANKSHAFT WAS REPLACED.									3	O			E286
1998120400168	19981204	00168	EA  	1998	12	4	CA980930013      	2	19980922	G	8520	74709	CRANKSHAFT      								LYC   	O360  	IO360A1A    	41514	EA  					ENGINE	CRACKED         	W				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA				60   				L47451			(CAN) REPORT OF PROBLEMS WITH CRANKSHAFT BALANCING R & O SHOP LED OWNER TO GROUND HIS AIRCRAFT AND REMOVE THE CRANKSHAFT	 FOR MPI INSPECTION.  CRACKS WERE FOUND AROUND CRANKPIN RADIUS.  THE CRANKSHAFT WAS REPLACED.										3	O			1E10
1998120400169	19981204	00169	CE  	1998	12	4	CA980930014      	1	19980918	G	5711		SCREW           			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A34      	52043	EA  					SPAR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE40241			(CAN) DURING THE 13,000 CYCLE FUSELAGE INSPECTION, THREE SCREWS ON THE FORWARD SPAR CAP WERE FOUND CORRODED AND SHEARED 	OFF.  FURTHER INVESTIGATION REVEALED THE PRC AROUND THE UPPER SPAR CAP AND FUSELAGE SKIN HAD WORKED LOOSE AND MAY BE THE	 SOURCE FOR THE CORROSION.  THE PRC WAS REPLACED, NEW SCREWS INSTALLED WITH LPS 3 RUST INHIBITOR, AND ALL CORROSION REMO	VED.  NO FURTHER EVIDENCE OF CORROSION SINCE REPAIR CARRIED OUT.			1	L	7	2 	3T	4	T		A14CE   	E4EA
1999021200912	19990212	00912	SW  	1999	2	12	CA980930015      	1	19980902	G	2400		ELECTRICAL SYS  			SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	DC SYSTEM	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			DE	DESCENT        	1			CA									DRG233581		(CAN) IN DESCENT BETWEEN 8 TO 6,000 FEET, THE AIRCRAFT WAS STRUCK BY LIGHTNING WHICH RESULTED IN A COMPLETE ELECTRICAL F	AILURE.  SYSTEM RESET AND POWER WAS RESTORED.  POST-LANDING INSPECTION FOUND ARCING ON THE NR 1 PROPELLER, LEFT AILERON 	AND THERE WAS A HOLE IN THE TAILCONE.  NR 1 ENGINE ALSO REMOVED FOR INSPECTION.				2	L	7	2 	4T			RT	A8SW    		6	C	P61GL
1999012900213	19990129	00213	SW  	1999	1	29	CA980930017      	1	19980904	G	3242	21203	BRAKE           			SWRNGN	SA227 	SA227AC     	8780603	SW  						ROTOL	R321	R321482F8   	GL  	MLG	OVERHEATED      	W				O				OTHER                   				M			OVER TEMP                 			TX	TAXI/GRND HDL  	1			CA									DRIDRG143781		(CAN) DURING ROLL-OUT AFTER TOUCH AND GO, THE AIRCRAFT CAME TO AN UNASSISTED STOP.  IT WAS DETERMINED THAT NR 3 AND NR 4	 BRAKE ASSEMBLIES HAD BECOME OVERHEATED.  BRAKES WERE DISMANTLED AND NO ANOMALIES WERE DISCOVERED.					2	L	7	2 	4T			RT	A8SW    		6	C	P61GL
1999021200913	19990212	00913	SW  	1999	2	12	CA980930019      	1	19980921	G	2400		ELECTRICAL SYS  			SWRNGN	SA227 	SA227AC     	8780603	SW  						MCAULY	4HFR34	4HFR34C652  	NE  	DC SYSTEM	FAILED          	W				A				UNSCHED LANDING         				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA									880868		(CAN) IN CRUISE AT 14,000 FEET, THE AIRCRAFT WAS STRUCK BY LIGHTNING AND ALL ELECTRICAL POWER WAS LOST.  SYSTEMS RESET O	K AND AIRCRAFT LANDED ALRIGHT.  INSPECTION FOUND NR 1 COM UNSERVICEABLE, A BURN ON THE LEFT AND RIGHT WING TIP FAIRING A	ND THE LEFT OUTBOARD WING TIP RIB.  PROPS AND ENGINES NOT AFFECTED.				2	L	7	2 	4T			RT	A8SW    		6	C	3PNE
1998120400170	19981204	00170	CE  	1998	12	4	CA980930020      	1	19980917	G	2731		CABLES          			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ELEVATOR	CROSSED         	W				K				NONE                    				W			INADEQUATE Q C            			NR	NOT REPORTED   	1			CA								PCE70200			(CAN) ON TEST FLIGHT AFTER PHASE V INSPECTION, PILOT NOTICED THAT NOSE DOWN TRIM CORRECTION RESULTED IN NOSE PITCHING UP	.  INSPECTION FOUND CROSSED ELEVATOR TRIM CABLES.					1	L	7	2 	4F	4	F		A22CE   	E1NE
1998120400173	19981204	00173		1998	12	4	CA980930024      	4	19980917	G	2562	4530150REVK3	ELT             	ARTEX       	1104        	BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						57781		PCEPS0103			(CAN) DURING AIRCRAFT TOW OUT, IT WAS NOTICED THE ELT TRANSMIT LIGHT WAS ON.  RESETTING THE REMOTE SWITCH HAD NO EFFECT 	AND RESETTING THE ELT ON/OFF SWITCH HAD NO EFFECT.  THE ELT BATTERY HAD TO BE DISCONNECTED FOR THE ELT TO STOP TRANSMITT	ING.  THE CASE OF THE ELT WAS CRACKED ON TOP AND BOTTOM ALLOWING MOISTURE TO INGRESS AND POSSIBLY CAUSING A SHORT.  THE 	ELT WAS REPLACED.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999032600139	19990326	00139	SO  	1999	3	26	CA981001002      	1	19980911	G	2121	C180559A1	BLOWER          			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					AIR DISTRIBUTION	SHORTED         	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA								PCE56742			(CAN) CREW REPORTED SMOKE IN THE CABIN AND CREW SHED UNNECESSARY ELECTRICAL LOADS.  SMOKE DISSIPATED.  AIRCRAFT LANDED O	K.  BLOWER MOTOR FOUND SHORTED.					1	L	7	2 	4T	4	T		A21SO   	E4EA
1998120400174	19981204	00174	SW  	1998	12	4	CA981001003      	1	19980817	G	5320	206033110183	WEB             		206033002005	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8600 			AOJH0009		CAE295298			(CAN) VERTICAL CONTROL ROD TUNNEL RT VERTICAL WEB CRACKED AT THE SECOND RIVET LEVEL BELOW THE MAIN BOX BEAM.  BELL TB 20	6L-79-41 HAD NOT BEEN ACCOMPLISHED.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998120400175	19981204	00175	SW  	1998	12	4	CA981001004      	1	19980817	G	5320	206033210001	BEAM            		206033002005	BELL  	206   	206L        	1181522	SW  	ALLSN 	250C  	250C20      	03013	GL  					TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8600 			AOJH0009		CAE295298			(CAN) ROOF ASSY MAIN BOX BEAM CRACKED AT THE RT CORNER ATTACHMENT OF THE VERTICAL CONTROL ROD TUNNEL.  BELL T.B. 206L-79	-41 HAD NOT BEEN CARRIED OUT.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800373	19981218	00373	CE  	1998	12	18	CA981001005      	1	19980922	G	5412	05530313	FIREWALL        			CESSNA	172   	172R        	2072401	CE  										COWL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			489  								(CAN) CRACKS FOUND ON THE LOWER FIREWALL NEAR THE COWL MOUNT BRACKETS.  AIRCRAFT HAS LESS THAN ONE YEAR IN SERVICE.						1	H	7	1 	3O			NT	3A12
1998121800374	19981218	00374	SO  	1998	12	18	CA981001006      	2	19980925	G	8530	637837	SPRING          		65496A2     	CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	NR 2 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1219 					290468R	881972		(CAN) WHILE CARRYING OUT SERVICE BULLETIN CSB98-1B, THE OUTER VALVE SPRINGS ON NR 2 CYLINDER INTAKE AND EXHAUST, AS WELL	 AS ON NR 1 CYLINDER INTAKE VALVE WERE FOUND BROKEN.  THE SPRINGS WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE	.				1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1999021200917	19990212	00917	EA  	1999	2	12	CA981001015      	1	19980918	G	2430		WIRE            		601R577961PC	CNDAIR	CL600 	CL6002B19   	       	EA  										DC GENERATOR	CHAFED          	W				H				DEACTIVATE SYST/CIRCUITS				H			ELECT. POWER LOSS-50 PC   			CR	CRUISE         	1			CA			16   								(CAN) DUE TO A WIRE CHAFING ON THE FIREWALL IN THE RIGHT HAND PYLON, A SHORT CIRCUIT OCCURRED DURING TEST FLIGHT.  GENER	ATOR REMAINED OFF-LINE.					2	L	7	2 	4F			RT	A21EA
1998121800378	19981218	00378	EA  	1998	12	18	CA981006002      	2	19980925	G	8520	LW10646	ROD             			PIPER 	PA60  	PA60601     	7106010	NM  	LYC   	O540  	IO540K1J5   	41532	EA  					NR 1 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CL	CLIMB          	1			CA				961  				RL1961748A			(CAN) DURING CRUISE, THE PILOT NOTED THE NR 1 ENGINE WAS RUNNING ROUGH.  THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT RETUR	NED TO BASE.  POST-FLIGHT INSPECTION REVEALED A HOLE IN THE ENGINE CASE, IT WAS ALSO NOTED THAT A CONNECTING ROD HAD FAI	LED.  THE ENGINE WAS REPLACED.				1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998121800380	19981218	00380	CE  	1998	12	18	CA981006005      	1	19980915	G	7120	045100336	MOUNT           			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	ENGINE	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7324 					L1432015	772234		(CAN) LOWER OLEO COLLAR FOUND BROKEN WHERE THE MOUNT LEG IS WELDED TO THE COLLAR.  SOME OTHER IRREGULARITIES WERE FOUND 	USING NDT.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
1998121800381	19981218	00381	SO  	1998	12	18	CA981006006      	2	19980829	G	8530	CNF61A1	CYLINDER        			CESSNA	206   	U206C       	2073332	CE  	CONT  	O520  	IO520F      	17032	SO  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1092 				247554R			(CAN) CYLINDERS NR 3 AND NR 6 FOUND CRACKED ON INSPECTION.						1	H	7	1 	3O	3	O		A4CE    	E5CE
1998121800383	19981218	00383	SO  	1998	12	18	CA981006008      	1	19980710	G	8120	4066109020R	TURBOCHARGER    	GARRETTLTD  		PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	LEAKING         	W				C				ABORTED TAKEOFF         				B	R		SMOKE/FUMES/ODORS/SPARKS  	PARTIAL RPM/PWR LOSS      		TO	TAKEOFF        	1			CA				1181 		1154		L37161			(CAN) ON TAKEOFF ROLL, THE TURBO CHARGER OIL SEAL FAILED CAUSING A LOSS OF POWER (MANIFOLD PRESSURE) AND SMOKE FROM THE 	EXHAUST.  TAKEOFF WAS ABORTED AND THE AIRCRAFT RETURNED TO THE RAMP.  TURBOCHARGER WAS REPLACED.  NO OTHER FAULTS WERE F	OUND.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1998121800384	19981218	00384		1998	12	18	CA981006009      	1	19980928	G	6120	50001	SHAFT           													HAMSTD	12D	12D40       	NE  	PROPELLER	BROKEN          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				500  					75179		(CAN) THE PROPELLER WAS RECEIVED WITH A BROKEN COUNTERWEIGHT SHAFT.  THE SHAFT BROKE BETWEEN THE THREADED SECTION AND TH	E GRIP (POINT OF TRANSITION).															5	C	P257
1998121800385	19981218	00385	NE  	1998	12	18	CA981006010      	3	19980824	G	6111	R6507A	BLADE           			GRUMAV	TBM   	TBM3EAIRTRD 	3950310	EA  	WRIGHT	R2600 	R260020     	67050	EA  	HAMSTD	23E	23E50       	NE  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				432  				447247	P55111		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADES WERE FOUND CORRODED ON THE BLADE FLANGES AND THE TA	PER BORE.  DISASSEMBLY REVEALED THE BLADE FLANGES WERE BELOW MINIMUM THICKNESS.					1	L	7	1 	4R	4	R		L82     	TC176	6	C	P603
1998121800386	19981218	00386	GL  	1998	12	18	CA981006011      	3	19980828	G	6111	G90DFA10	BLADE           			CESSNA	210   	T210M       	2073451	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2248 	551  				517834	793025		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND ALL THREE BLADES HAD BEEN FIELD MODIFIED BELOW MINI	MUM WIDTH.					1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL
1998121800387	19981218	00387	GL  	1998	12	18	CA981006012      	3	19980914	G	6114		HUB             													MCAULY	2A31C	2A31C21     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									810424		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND THE WRONG SPINNER SCREWS WERE USED ON A PREVIOUS IN	STALLATION.  THE SCREWS WERE TOO LONG AND THEY DAMAGED THE PROPELLER HUB.  THE SUBMITTER REPORTED THAT A CONCESSION HAD 	TO BE OBTAINED FROM MCCAULEY FOR AUTHORITY TO REPAIR.														5	C	P919
1998121800388	19981218	00388	GL  	1998	12	18	CA981006013      	3	19980901	G	6114	2964	NUT             			CESSNA	175   	175B        	2072506	CE  	FRNKLN	6AV335	6A335B      	27020	EA  	MCAULY	2A31C	2A31C21     	GL  	PROPELLER HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			696  	63   				55013	687151		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND A PROPELLER RETAINING NUT CRACKED.						1	H	7	1 	3O	3	O		3A17    	E244	5	C	P919
1998121800389	19981218	00389	EA  	1998	12	18	CA981006014      	3	19980828	G	6111	28719K	BLADE           			CESSNA	172   	172N        	2072434	CE  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1481 			28719K		L3361036A	28719K		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.   INSPECTION FOUND STONE DAMAGE TO THE LEADING EDGES AND THE FACE OF 	THE PROPELLER BLADES.					1	H	7	1 	3O	3	O	NT	3A12    	E286	5	N	P4EA
1998121800390	19981218	00390	GL  	1998	12	18	CA981006015      	3	19980915	G	6114		HUB             			CONAER	LA4   	LA4200      	5110310	NE  	LYC   	O360  	IO360A1B    	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				478  				L2098751A	CH24561		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND THE HUB CORRODED.  THE SUBMITTER STATES THAT THE LA	ST CORROSION INSPECTION, WHICH WAS IN 1988, REQUIRED REWORK TO THE MAXIMUM LIMITS DUE TO THE LACK OF INSPECTION AT THE S	CHEDULED TIME.				1	H	7	1 	3O	3	O		1A13    	1E10	5	C	P920
1998121800391	19981218	00391		1998	12	18	CA981006016      	1	19980810	G	7830	65378315	VALVE           								PWA   	JT8   	JT8D17      	52049	NE  					NR 3 ENGINE	STICKING        	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA								689960			(CAN) NR 3 ENGINE WOULD NOT GO INTO REVERSE.  THRUST REVERSER DIRECTIONAL VALVE FOUND STICKING AND LEAKING.											4	F			E2EA
1999010800002	19990108	00002	NM  	1999	1	8	CA981006017      	1	19980909	G	3234	560252	VALVE           			BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					MLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								689961			(CAN) LANDING GEAR SELECTOR LEAKING FROM BODY CASTING.  REPLACED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998121800392	19981218	00392	NM  	1998	12	18	CA981006022      	1	19980921	G	2912	65903059	FILTER          			BOEING	727   	727         	1384001	NM  										HYD SYSTEM	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON RECEIPT, THE FILTER HAD CORROSION MOLD ON FILTER ELEMENT.  ELEMENT VERY BRITTLE.						2	L	7	3 	4F				A3WE
1999021200918	19990212	00918	EA  	1999	2	12	CA981006023      	1	19980924	G	3260	601R575111	UPLOCK          			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					LT MLG	OUT OF ADJUST   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) DURING TAKEOFF, UNSCHEDULED LANDING CARRIED OUT BECAUSE OF GEAR DISAGREE MESSAGE. UPLOCK TARGET ON LEFT MAIN LANDI	NG GEAR HAD TO BE ADJUSTED.					2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
1998121800393	19981218	00393	NM  	1998	12	18	CA981006024      	1	19980924	G	2751	10607916	INDICATOR       			BOEING	727   	727217      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA						363		688128			(CAN) INBOARD FLAPS LOCKED OUT AT 15 DEGREES AFTER TAKEOFF. DUMPED FUEL AND LANDED USING ALTERNATE FLAP EXTENSION.  REPL	ACED FLAP INDICATOR.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998121800394	19981218	00394	NM  	1998	12	18	CA981006025      	1	19980924	G	2751	2061131	INDICATOR       			BOEING	727   	727212      	138407G	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA						363		688149			(CAN) INBOARD FLAPS LOCKED OUT AT 5 DEGREES AFTER TAKEOFF.  AIRCRAFT RETURNED TO BLOCKS.  INDICATION ADJUSTED AND FLAP I	NDICATOR REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1998121800395	19981218	00395	EU  	1998	12	18	CA981006026      	1	19980926	G	5240	A215103800300	DOOR            			AIRBUS	310   	A310304     		EU  										FUSELAGE	SEPARATED       	W				O				OTHER                   				D			INFLIGHT SEPARATION       			NR	NOT REPORTED   	1			CA											(CAN) AIR GROUND DOOR MISSING AND ADJACENT FAIRING PARTIALLY RIPPED OFF.  REPAIRED AND DOOR REPLACED.  SB 310-52-2030 TO	 BE CARRIED OUT WHEN PARTS RECEIVED.					2	L	7	2 	4F			RT	A35EU
1998121800397	19981218	00397	SO  	1998	12	18	CA981006028      	2	19980922	G	8530	SA530830	PIN             			CESSNA	170   	170B        	2072306	CE  	CONT  	C145  	C1452       	17012	SO  					NR 4 CYLINDER	WORN            	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			270  					6910D22			(CAN) DURING MAINT TO CORRECT A ROUGH RUNNING ENGINE, OIL SCREEN CHECK INDICATED METAL CONTAMINATION.  OIL CHANGE INITIA	TED, METAL CONTAMINATION CONFIRMED.  INVEST FOUND CONTAMINATION CAME FROM COMPLETE FAILURE OF 2 PISTON PIN PLUGS AND EXC	ESSIVE WEAR OF REMAINING PLUGS.   SUBMITTER SUGGESTED ROUGH RUNNING CAUSED BY SCORING IN NR 4 CYL BARREL WHICH WAS CAUSE	D BY PISTON PIN RUBBING DIRECTLY ON BARREL DUE TO FAILED PIN PLUG.  CRANKSHAFT DISMANTLED, CLEANED, INSPECTED, AND SENT 	FOR ULTRANSONIC INSP.  CRANKSHAFT JOURNALS AND RUNOUTS, CONNECTING RODS INSP FOR ALIGNMENT AND TWIST, ROD BUSHINGS FOUND	 WITHIN LIMITS.  DUE TO EXTENT OF CONTAMINATION, PISTONS, BEARINGS, PISTON PINS, AND ONE CYL WERE REPLACED.	1	H	7	1 	3O	3	O		A799    	E253
1998121800398	19981218	00398	EA  	1998	12	18	CA981006029      	2	19980925	G	8530	LW10076	SEAT            		OSK21119    	CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ALL CYLINDERS	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				636  		OS891AT		L67276	729271		(CAN) CYLINDER REMOVED DUE TO ROUGH RUNNING ENGINE.  INSPECTION FOUND THE UPPER EXHAUST SEAT CRACKED AND BROKEN AND THE 	EXHAUST VALVE WAS DESTROYED.  THE PART NUMBER FOUND ON THE EXHAUST SEAT WAS LW-10076, WHICH, ACCORDING TO SB NR 435 AND 	AD 80-14-07, SHOULD HAVE BEEN REPLACED BY PART NR 16475-KLI.  IT APPEARS THAT ON OVERHAUL, THE SB AND THE AD WERE NOT CO	MPLIED WITH.			1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998121800399	19981218	00399	EU  	1998	12	18	CA981006030      	1	19980925	G	2742	9787314202	ACTUATOR        			PILATS	PC12  	PC12        	7090550	EU  										HORIZ STAB	CONTAMINATED    	W				O				OTHER                   				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA			680  			086					(CAN) POOR PITCH RESPONSE IN-FLIGHT.  GROUND TEST OK.  LAST LEG OF FLIGHT TRIM FAILED AT ATTITUDE.  LANDED OK.  REPLACED	 ACTUATOR.  INVESTIGATION INDICATED THAT MOISTURE IN UNIT FROZE AT ALTITUDE DEPENDING ON OAT.  PART TC:  412.					1	L	7	1 	3T			RT	A78EU
1998121800400	19981218	00400	CE  	1998	12	18	CA981007001      	1	19980928	G	3110		FITTING         			CESSNA	180   	180         	2072602	CE  										INSTRUMENT PANEL	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			NR	NOT REPORTED   	1			CA			3486 								(CAN) PILOT NOTED A DRASTIC LOSS OF ELEVATOR CONTROL.  THE RADIO STACK IN THE CENTER OF THE INSTRUMENT PANEL HAD BROKEN 	AT THE TOP FITTING AND THE STACK FELL INTO THE PANEL.  THE ELEVATOR CONTROL THEN GOT STUCK, AS THE TRANSPONDER TRAY WAS 	RESTRICTING UP TRAVEL.  NEW BRACKETS WERE INSTALLED.				1	H	7	1 	3O			NC	5A6
1998121800401	19981218	00401	CE  	1998	12	18	CA981007002      	1	19980928	G	2720	0733102	BELLCRANK       			CESSNA	180   	180         	2072602	CE  										RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3486 								(CAN) RIGHT HAND CABLE ATTACH POINT FOR THE RUDDER BELLCRANK BROKE DUE TO SEVERE CORROSION WHILE AIRCRAFT WAS DOCKING. A	LL RUDDER CONTROL LOST.  AIRCRAFT OPERATED IN SALT WATER ENVIRONMENT AND THE FITTING WAS STEEL BUSHING IN AN ALUMINUM PI	ECE.				1	H	7	1 	3O			NC	5A6
1998121800403	19981218	00403	CE  	1998	12	18	CA981007004      	1	19980911	G	5510	07321014	CHANNEL         		12320008    	CESSNA	185   	A185F       	2072821	CE  						MCAULY	2A34C	D2A34C58    	GL  	HORIZ STAB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5166 						891358		(CAN) ON 100-HOUR INSPECTION, THE LEFT REAR REINFORCEMENT BOX ON THE HORIZONTAL STABILIZER WAS FOUND CRACKED FROM THE BO	LT HOLE.  THE SPAR REINFORCEMENT CHANNEL WAS ALSO FOUND CRACKED.  CRACK ABOUT 2 INCHES LONG.  P/N OF CHANNEL 0732603.					1	H	7	1 	3O				3A24    		5	C	P3EA
1998121800404	19981218	00404	EA  	1998	12	18	CA981007005      	1	19980930	G	5751	21515065	BALANCE ARM     			CNDAIR	CL215 	CL2151A10   		EA  										AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2750 								(CAN) THE RUDDER AILERON INTERCONNECT TAB MASS BALANCE ARM WAS FOUND CRACKED CLOSE TO THE MOUNTING BASE. THIS IS THE THI	RD TIME THIS OPERATOR HAS FOUND THESE ARMS CRACKED ON OTHER AIRCRAFT.  THESE CRACKS WERE FOUND DURING ROUTINE WINTER INS	PECTIONS.  (CANADAIR 'B' CHECKS)				2	H	7	2 	4R				A14EA
1998121800406	19981218	00406	SO  	1998	12	18	CA981007007      	1	19981001	G	2751	487927	SWITCH          		4941506     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A1A   	41532	EA  					TE FLAP	CORRODED        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			4231 					L81561C			(CAN) WHEN FLAPS SELECTED TO 15 DEGREES, THEY STUCK.  AIRCRAFT LANDED OK.  INVESTGATION FOUND CORROSION ON THE UPPER LIM	IT SWITCH.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998121800407	19981218	00407	SO  	1998	12	18	CA981007008      	1	19980916	G	7810		EXHAUST STACK   		LW12425     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					NR 2 CYLINDER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1556 				L127748			(CAN) COWLING REMOVED FOR STARTER CHANGE.  INSPECTION FOUND THE EXHAUST STACK ON NR 2 CYLINDER BROKEN.  THE OUTBOARD STU	D AND THE HELICOIL WERE PULLED FROM THE CYLINDER.  NUMBERS ON CYLINDERS AND ACCESSORIES DO NOT MATCH LOG BOOK NUMBERS.					1	L	7	2 	3O	3	O		1A10    	1E4
1998121800412	19981218	00412	CE  	1998	12	18	CA981013001      	1	19980914	G	3260		WARNING SYSTEM  			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					MLG	FAILED          	W				O				OTHER                   				P			NO WARNING INDICATION     			NR	NOT REPORTED   	1			CA								PCE40547			(CAN) ON AUGUST 14, 1998, AIRCRAFT MADE A WHEELS UP LANDING.  PRIMARY CAUSE WAS PILOT DID NOT SELECT GEAR DOWN.  SINCE T	HEN, PILOTS HAVE REPORTED WARNING HORN DOES NOT GIVE WARNING UNTIL POWER IS REDUCED WELL BELOW TOUCH-DOWN POWER.  BEECH 	CALLS FOR WARNING HORN TO ACTIVATE WHEN ENGINE COMPRESSOR SPEED IS (N1)  AT OR BELOW 79 PERCENT.  IT IS RECOMMENDED THAT	 ALL OPERATORS OF THESE AIRCRAFT FLIGHT CHECK THE WARNING SYSTEM AND VERIFY THE AUDIBLE WARNING IS ADJUSTED TO A LEVEL T	HAT WOULD WARN THE PILOTS PRIOR TO TOUCH DOWN.		1	L	7	2 	3T	4	T		A14CE   	E4EA
1998121800413	19981218	00413	CE  	1998	12	18	CA981013002      	1	19980930	G	5710	11412002823	STRUCTURE       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					WING LE	DAMAGED         	W				O				OTHER                   				C			F.O.D.                    			LD	LANDING        	1			CA			3844 					PS0050			(CAN) ON LANDING ROLL OUT, AIRCRAFT STRUCK A DEER AND DAMAGED THE INBOARD LEADING EDGE AND LEFT INBOARD FLAP.  THE FLAP 	WAS REMOVED AND INSPECTED FOR INTERNAL DAMAGE ALONG WITH THE LEADING EDGE.  THE FLAP WAS INSTALLED AND SECURED IN THE RA	ISED POSITION.  A LINE BEHIND THE LEADING EDGE WAS REPAIRED.  THE AIRCRAFT WAS DECLARED SERVICEABLE FOR FERRY FLIGHT TO 	HOME BASE.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998121800414	19981218	00414	CE  	1998	12	18	CA981013003      	1	19980928	G	7820	5000127B3	MUFFLER         			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			542  			73474		L4570027A			(CAN) DURING OIL CHANGE, THE OVERBOARD PIPE ON THE MUFFLER WAS FOUND LOOSE.  A CRACK WAS FOUND IN THE EXHAUST PIPE BRACE	 AND COLLECTOR CAN JOINT RUNNING HALF WAY ROUND THE CIRCUMFERENCE, TOTALLING ABOUT 4 INCHES IN LENGTH.  SUBMITTER SAYS T	HESE UNITS LAST ABOUT 1,000 TO 1,200 HOURS BEFORE PROBLEMS OCCUR.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1998121800419	19981218	00419	EA  	1998	12	18	CA981013008      	1	19980906	G	2731	82700550001	CHAIN           			DHAV  	DHC8  	DHC8311     	1386006	EA  										ELEVATOR TRIM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS FOUND IN THE ELEVATOR TRIM CHAIN.  PART TC:  8,750.						2	H	7	2 	4T			RT	A13NM
1998121800420	19981218	00420	EA  	1998	12	18	CA981013009      	1	19980911	G	2731	82700550001	CHAIN           			DHAV  	DHC8  	DHC8311     	1386006	EA  										ELEVATOR TRIM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) CRACKS FOUND IN ELEVATOR TRIM CHAIN.  PART TC:  8,750.						2	H	7	2 	4T			RT	A13NM
1998121800421	19981218	00421	NE  	1998	12	18	CA981013010      	2	19980919	G	7230	BACC10DU450	CLAMP           		10614261    	BOEING	727   	727217      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					NR 2 ENGINE	LEAKING         	W				A	J			UNSCHED LANDING         	DUMP FUEL               			M			OVER TEMP                 			CR	CRUISE         	1			CA											(CAN) NR 2 ENGINE STRUT OVERHEAT LIGHT ILLUMINATED IN-FLIGHT.  POST-FLIGHT INSPECTION FOUND NR 2 ENGINE RIGHT HAND PRECO	OLER CLAMPS LEAKING.  ALSO NR 3 ENGINE LEFT HAND 13TH STAGE CROSSOVER DUCT MANIFOLD GASKET LEAKING.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998121800422	19981218	00422	NM  	1998	12	18	CA981013013      	1	19980728	G	3210	400083501	BRACE           			PIPER 	PA60  	PA60601P    	7106012	NM  	LYC   	O540  	IO540S1A5   	41532	EA  					LT MLG	CRACKED         	W				O				OTHER                   				J			WARNING INDICATION        			LD	LANDING        	1			CA			1504 					L1196448			(CAN) ON LANDING ROLL-OUT AT ABOUT 40 KNOTS, THE WARNING HORN SOUNDED AND THE LEFT WING STARTED TO DROP.   LEFT ENGINE S	HUTDOWN, A/C STAYED ON RUNWAY.  LEFT GEAR COLLAPSED DAMAGING WING, AND GEAR DOOR.  SUBMITTER STATED CAUSED BY FAILURE OF	 LEFT LOWER SIDE BRACE UPPER BOLT HOLE.  PIPER SL SL600-60 FOR CRACKING OF DOOR BELLCRANK ADDED A BUMPER TO STOP THE DOO	RS FROM BEING TORN OFF ON LANDING.  ALSO, A SNUBBER FITTING IN MAIN GEAR ACTUATOR SLOWING GEAR OPERATION ON UP-SWING.  S	UBMITTER SAYS THIS WOULD BE NICE ON DOWN SELECTION AS WELL.  PART TC:  906.		1	M	7	2 	3O	3	O	RT	A17WE   	1E4
1998122400362	19981224	00362	EA  	1998	12	24	CA981013014      	2	19980914	G	7261		PUMP            			CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	OIL SYSTEM	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			DE	DESCENT        	1			CA			1785 					L3955927A	730784		(CAN) ON DESCENT, REDUCTION OF 300-500 RPM WAS FOLLOWED 20 SECONDS LATER BY THE ENGINE SEIZING.  AIRCRAFT LANDED SAFELY.	  POST-FLIGHT INSPECTION FOUND THE OIL PUMP HAD FAILED.  THE ENGINE WAS A WRITE OFF;  BROKEN AND SEIZED RODS, BROKEN CRA	NKCASE, ETC.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998121800424	19981218	00424	CE  	1998	12	18	CA981013016      	1	19980927	G	3213	508103237	TORQUE KNEE     		115810000606	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE51811	BU4989		(CAN) DURING A 100-HOUR INSPECTION, A CRACK WAS FOUND ON THE RADIUS OF THE TORQUE KNEE ATTACHMENT POINT.  AREA IS TO BE 	DYE PENETRANT INSPECTED PER 100-HOUR INSPECTION ITEM B NR 6.  PART TC:  57,207.					1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
1998121800425	19981218	00425	NM  	1998	12	18	CA981014001      	1	19980928	G	6310	A0511	SHEAVE          		A0511       	ROBSIN	R22   	R22BETA     		NM  	LYC   	O320  	O320B2C     	41508	EA  					ACTUATOR	OUT OF ADJUST   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						0966		L1792439A			(CAN) ON WALK-AROUND, DRIVE BELT TENSIONNER ACTUATOR MOTOR RUBBING ON FRAME.  SHEAVE ALIGNMENT OUT OF ADJUSTMENT.  CORRE	CTED.					1	G	7	1 	3O	3	O		H10WE   	E274
1999043000082	19990430	00082	EU  	1999	4	30	CA981014002      	1	19980630	G	2750	S2911002300100	BRACKET         			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	TE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16486					PCE120934	MFG890534		(CAN) ON 'C' CHECK, THE MOUNTING BRACKET FOR THE FLAP VALVE BLOCK WAS FOUND CRACKED.  A COMPLETE FAILURE OF THE BRACKET 	WOULD CAUSE BROKEN HYDRAULIC LINES WITH LOSS OF FLUID. THE BRACKET WAS REPLACED WITH A NEW IMPROVED TYPE,-140.  THIS IS 	SECOND AIRCRAFT THIS SHOP HAS FOUND WITH THE PROBLEM.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE
1999032600140	19990326	00140	EU  	1999	3	26	CA981014003      	1	19980802	G	5320		FRAME           			AEROSP	ATR42 	ATR42300    	8680920	EU  										WINDSCREEN	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			16486								(CAN) ON 'C' CHECK WHEN WINDSCREEN RETAINER WAS REMOVED FOR INSPECTION, WATER WAS FOUND IN THE LOWER CHANNEL AREA.  LIGH	T CORROSION IN CHANNELS.  SEVERAL LOWER WINDSCREEN ATTACH BARREL NUTS WERE REPLACED.  MOISTURE THE RESULT OF IMPROPER SE	AL AND IMPROPER SEALANT.  AIRCRAFT HAD ALSO BEEN STORED OUTSIDE FOR 10 MONTHS.				2	H	7	2 	4T			RT	A53EU
1998121800426	19981218	00426	SO  	1998	12	18	CA981014004      	1	19980507	G	2810	5277800	FUEL CELL       	GOODYEAR    	BTC67       	PIPER 	PA31  	PA31350     	7103110	SO  										LT WING	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10660			7461718					(CAN) FUEL STAINS NOTED ON LEFT WING ROOT.  FUEL LEAKAGE TRACED TO LEFT MAIN FUEL CELL.  CELL HAD PIN HOLES.						1	L	7	2 	3O				A20SO
1998121800427	19981218	00427	NE  	1998	12	18	CA981014005      	2	19980528	G	8530	CN90ER	CYLINDER        			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				287  				2823			(CAN) THE ENGINE WAS RUNNING ROUGH DURING RUN-UP.  THE ENGINE WAS SHUTDOWN AND INSPECTION FOUND THE NR 9 CYLINDER CRACKE	D AND SEPARATED BETWEEN THE HEAD AND THE BARREL.  THE CYLINDER WAS REPLACED AND THE ENGINE RAN SMOOTHLY.					1	H	7	1 	3R	3	R		A806    	5E1
1998121800428	19981218	00428	SO  	1998	12	18	CA981014006      	1	19980814	G	2822	2B664	PUMP            	AIRBORNE    		PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYSTEM	FAILED          	W				K				NONE                    				J			WARNING INDICATION        			CR	CRUISE         	1			CA						1F23					(CAN) IN-FLIGHT, WARNING INDICATION SHOWED FAILURE OF LEFT FUEL BOOST PUMP.						1	L	7	2 	3O				A20SO
1998121800429	19981218	00429	EA  	1998	12	18	CA981014007      	2	19980818	G	7314	RG9080J7A	PUMP            	ROMEC       		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					LT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2312 		C3658		L739061A			(CAN) DURING TAXI, PILOT REPORTED FLUCTUATING FUEL PRESSURE AND LOW PRESSURE INDICATIONS AT LOWER RPM SETTINGS.  PRESSUR	E NORMAL AT HIGHER SETTINGS.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1998121800430	19981218	00430	SO  	1998	12	18	CA981014008      	1	19980818	G	2822	421136	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										FUEL SYSTEM	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA						10946					(CAN) DURING MAINTENANCE AND PRESSURE TESTING OF FUEL SYSTEM, THE EMERGENCY BOOST PUMP FAILED.						1	L	7	2 	3O				A20SO
1998121800431	19981218	00431	SO  	1998	12	18	CA981014009      	1	19980929	G	2140	A96040035	TUBE            	JANITROL    	FR10E214EL  	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					HEATER	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			482  			A96040035		PCE51061			(CAN) HEATER RUNNING RICHER AND LEAVING A HEAVIER THAN NORMAL EXHAUST DEPOSIT ON THE FUSELAGE IN-FLIGHT.  ON GROUND, IT 	WOULD BLOW OUT CARBON DEPOSIT FROM THE EXHAUST STACK AND EXHAUST DARKER THAN NORMAL DECAY TEST CARRIED OUT.  HEATER WAS 	FACTORY REMANUFACTURED WITH EXTENDED LIFE COMBUSTION TUBE.				1	L	7	2 	3T	4	T		A8EA    	E4EA
1998121800432	19981218	00432		1998	12	18	CA981014010      	4	19981002	G	6122	8210003R	GOVERNOR        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB3T	HCB3TN3     	GL  	NR 2 PROP	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA				2669 		1435468		PCE50216	BUA19890		(CAN) DURING CLIMB, NR 2 PROPELLER SPEED WOULD FLUCTUATE BETWEEN 2000-1800 RPM AND OCCASIONALLY AS LOW AS 1200 RPM.  ENG	 POWER REDUCED TO MAINTAIN TORQUE LIMIT.  CONTROL INPUT TO INCREASE PROP SPEED WAS INEFFECTIVE, BUT PROP SPEED COULD BE 	FURTHER REDUCED OR FEATHERED ON COMMAND.  AIRCRAFT RETURNED TO POINT OF DEPARTURE.  SNAG COULD BE DUPLICATED ON GROUND R	UN AND IT WAS DETERMINED THAT NORMAL PROP CONTROL WAS RETURNED WHEN ELEC POWER WAS REMOVED FROM THE GOV PITCH LOCK SOLEN	OID.  PROP RIGGING, ELECTRICAL WIRING AND SWITCHES WERE CHECKED AND WERE WITHIN LIMITS.  PROP GOVERNOR REPLACED AND RIGG	ED IAW WITH MAINTENANCE MANUAL.   GROUND RUNS WERE CARRIED OUT SERVICEABLE AND AIRCRAFT WAS RETURNED TO SERVICE.	1	L	7	2 	3T	4	T		A8EA    	E4EA	6	C	P15EA
1998121800433	19981218	00433	EA  	1998	12	18	CA981014011      	2	19980718	G	7310	24382000	LINE            			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					FUEL SYSTEM	CLOGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8789 					RL181966C			(CAN) DURING A ROUTINE MAINTENANCE ENGINE START-UP, NO FUEL WAS OBSERVED COMING FROM THE INTAKE DRAIN AFTER A HEAVY PRIM	E.  THE ENGINE COWLINGS WERE REMOVED AND THE ENGINE WAS AGAIN PRIMED FOR SEVERAL MINUTES, FUEL WAS NOW OBSERVED COMING F	ROM THE ALTERNATE AIR BOX.  THE HOSE WAS PULLED OFF AN INTAKE DRAIN VALVE AND ABOUT ONE QUART OF FUEL DRAINED OFF.  CLOS	ER INSPECTION FOUND THE FUEL DRAIN LINES TEED INTO ONE AND THIS TEE WAS PLUGGED.  WHEN EXAMINING THE MATERIAL IN THE TEE	, IT APPEARS THAT OVER THE YEARS, FUEL DYE HAD COAGULATED AND PLUGGED THE LINE.		1	L	7	2 	3O	3	O		A1EA    	1E12
1998121800434	19981218	00434	EA  	1998	12	18	CA981014012      	2	19980731	G	8520	LW15944	CRANKSHAFT      			CESSNA	172   	172N        	2072434	CE  	LYC   	O320  	O320H2AD    	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3248 	1184 				L656376	79798		(CAN) AN ON-WING F.P.I. COMPLETED ON THE CRANKSHAFT BY A SUITABLY RATED AMO FOUND NO CRACKING.  THE INNER DIAMETER WAS C	LEANED OF CORROSION PER LYCOMING MSB 505B.  THE INNER DIAMETER WAS MEASURED WITHIN LIMITS.  THE INNER DIAMETER WAS STAMP	ED PER THE LYCOMING MSB 530.				1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1998121800435	19981218	00435	CE  	1998	12	18	CA981014013      	1	19980901	G	3242	215286	BRAKE           			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					LT & RT	OVERHEATED      	W				C				ABORTED TAKEOFF         				A			FLAME/FIRE                			TO	TAKEOFF        	1			CA								PCE70683			(CAN) FOLLOWING A REJECTED TAKEOFF, THE PILOT THOUGHT HIS TIRES WERE FLAT.  IT WAS CONFIRMED THAT BOTH SIDES WERE FLAT A	ND THE BRAKES WERE BURNING.  FIRE EXTINGUISHED.  INSPECTION FOUND BOTH BRAKES AND WHEEL ASSEMBLIES WERE OVERHEATED CAUSI	NG THE TIRES TO DEFLATE.  DISCUSSION INDICATED THAT THE REJECTED TAKEOFF LED TO THE OVERHEATED BRAKES.  THE TAKEOFF WAS 	REJECTED BECAUSE OF BIRDS ON THE RUNWAY.			1	L	7	2 	4F	4	F		A22CE   	E1NE
1998121800436	19981218	00436	EA  	1998	12	18	CA981014014      	2	19980929	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	LTIO540J2BD 	41533	EA  					NR 2 ENGINE	CRACKED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			NR	NOT REPORTED   	1			CA			1091 					L159368A			(CAN) ON FIRST START, ENG MIS-STARTED AND BACKFIRED.  REMOVAL OF ENG COWLINGS AND INSP SHOWED NO DEFECTS.  ACFT CARRIED 	ON WITH MISSION.  ON RETURN AFTER 3.5 HRS OF FLT, PILOT REPORTED AN ENG VIBRATION, BUT UNSURE OF WHICH ENG.   RUN-UP DET	ERMINED IT WAS NR 2 ENG DUE TO 200 RPM MAG DROP, WITH LT MAG OFF.  ON SHUTDOWN, NR 5 CYL WAS COLD TO TOUCH.  BOTH SPARK 	PLUGS WERE FOUND FOULED AND WERE REPLACED.  FUEL NOZZLES CLEANED AND VALVES, ROCKERS, AND INTAKE DUCTS CHECKED SERVICEAB	LE.  NO MAG DROP, BUT MANIFOLD PRESSURE ACTING UP.  ON SHUTDOWN, REMOVAL AND INSP OF NR 5 CYL FOUND PISTON TOP HEAD DISI	NTEGRATED WITH NO SIGN OF METAL REMANENTS.  THERE WAS A HAIRLINE CRACK BETWEEN INTAKE PORT FLANGE AND CYL FINS.	1	L	7	2 	3O	3	O		A20SO   	E14EA
1998121800437	19981218	00437	SO  	1998	12	18	CA981014015      	1	19981003	G	5297	151325	WIRE            		3313600     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					DOOR	BROKEN          	W				O				OTHER                   				D			INFLIGHT SEPARATION       			CR	CRUISE         	1			CA								L104448			(CAN) PASSENGER NOTED DAYLIGHT ON TOP OF DOOR.  A ONE-HALF TO THREE-QUARTER INCH GAP.  PART NUMBER WIRE FOUND BROKEN INS	IDE CASING.  SB 338 COVERS SPECIAL MEASURES TO BE TAKEN IN ADJUSTING TOP REAR PIN TO PREVENT IT FROM BOTTOMING AND CAUSI	NG BACK PRESSURE ON ACTUATING WIRE.  PART TC:  7,267.				1	L	7	2 	3O	3	O	 	1A10    	1E4
1998121800438	19981218	00438	CE  	1998	12	18	CA981014016      	1	19981001	G	3213	444EN496	SWITCH          			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					MLG	MALFUNCTIONED   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			TO	TAKEOFF        	1			CA								PCE32052			(CAN) DURING A NORMAL BUSHING CHANGE ON THE MAIN LANDING GEAR TORQUE LINK, THE LANDING GEAR SAFETY SWITCH WAS REMOVED. O	N REINSTALLATION AND RIGGING, THE LANDING GEAR WAS NOT COMPLETELY COMPRESSED AND LANDING GEAR WOULD NOT RETRACT.  THEREF	ORE, RIGGING OF THE SWITCH WAS NOT CORRECT.  ON RIGGING MAIN LANDING GEAR SAFETY SWITCH, FULL COMPRESSION OF OLEO MAY AL	TER INITIAL ADJUSTMENT.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1999012900928	19990129	00928	EA  	1999	1	29	CA981014017      	1	19981002	G	2720	MS165623	PIN             			CNDAIR	CL215 	CL2156B11415		EA  										RUDDER	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			544  								(CAN) AT 500-HOUR INSPECTION, THE RUDDER SHOWED SIGNS OF UPWARD PLAY.  REMOVAL OF THE RUDDER WAS NECESSARY TO SEE THAT T	HE SLOTTED PIN WAS FOUND SHEARED AND ALLOWED THE COLLAR OF BEARING TO LOOSEN MORE THAN HALF A TURN.  PART TC:  348.					2	H	7	2 	4T			RT	A14EA
1998121800439	19981218	00439	SO  	1998	12	18	CA981019001      	1	19981001	G	2913	1213HBG310	PUMP            			PIPER 	PA31  	PA31350     	7103110	SO  										HYDRAULIC	FAILED          	W				O				OTHER                   				J			WARNING INDICATION        			CL	CLIMB          	1			CA				916  							(CAN) ON DEPARTURE, GEAR WOULD NOT INDICATE UP AND LOCKED.  RE-SELECTED GEAR DOWN, SLOW TO EXTEND, BUT DID LOCK DOWN.  R	ETURNED TO BASE.  FOUND LEFT HYDRAULIC PUMP HAD FAILED.					1	L	7	2 	3O				A20SO
1998121800441	19981218	00441	CE  	1998	12	18	CA981019008      	1	19980819	G	3230	105932B	POWER PACK      			BEECH 	76    	76          	1153005	CE  										MLG	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			LD	LANDING        	1			CA											(CAN) LANDING GEAR FAILED TO EXTEND USING NORMAL EXTENSION SYSTEM.  PILOT USED EMERGENCY GEAR EXTENSION AND LANDED WITHO	UT INCIDENT.  INVESTIGATION REVEALED WORN GEAR MOTOR BRUSHES AND COMMUTATOR.  HYDRAULIC POWER PACK REPLACED.					1	L	7	2 	3O				A29CE
1999032600141	19990326	00141	EA  	1999	3	26	CA981019009      	1	19981019	G	2610	72610008	DETECTOR        			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	FIRE PROTECTION	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) NUMEROUS FALSE FIRE WARNINGS UNCOVERED THE POSSIBILITY OF CROSSING THE CONNECTIONS OF THE FIRE LOOPS.  IT IS POSSI	BLE BECAUSE THERE IS A MALE AND FEMALE CONNECTOR ON EACH CONNECTION.  THE PART THAT MAKES UP THE CONNECTION CAN WORK LOO	SE AND STAY WITH THE OPPOSITE CONNECTOR ALLOWING THE CROSS CONNECTION.  THE SUBMITTER NOTES THAT CROSS CONNECTIONS WILL 	TEST ACCURATELY IN THE COCKPIT.			2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
1998120400176	19981204	00176	NE  	1998	12	4	CA981019010      	2	19980912	G	7261	51R062	VALVE           								PWA   	4168  	PW4168      		NE  					OIL SYSTEM	FAILED          	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		CL	CLIMB          	1			CA			12148					733335			(CAN) THE AIRCRAFT WAS ON A TRANSIT STOP AND THE ENGINES WERE SERVICED WITH OIL.  ON CLIMB OUT, THE NR 2 ENGINE OIL PRES	SURE INDICATION FLUCTUATED AND THEN WENT TO AMBER XX INDICATION, INDICATING LOSS OF DATA.  THE OIL PRESSURE INDICATION R	ETURNED INTERMITTENTLY AND INDICATED LOWER BUT SERVICEABLE OIL PRESSURE.  THE CREW PATCHED MAINTENANCE AND IT WAS CONCLU	DED THAT THE SNAG WAS AN INDICATION PROBLEM, SO THE AIRCRAFT COMPLETED THE FLIGHT.  POST-FLIGHT INSPECTION OF THE OIL TA	NK FILLER NECK FOUND THE O-RING FOR THE CHECK VALVE SEAT WAS NOT IN ITS GROOVE AND THIS PREVENTED THE CHECK VALVE FROM S	EATING PROPERLY.  PRATT & WHITNEY ARE INVESTIGATING THE PROBLEM.  PART TC:  3,640.						4	F			E36NE
1998120400177	19981204	00177	EA  	1998	12	4	CA981019012      	2	19981003	G	7261	3030359	DETECTOR        			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					GEARBOX	SHEARED         	W				O				OTHER                   				K			FLUID LOSS                			AP	APPROACH       	1			CA								81923			(CAN) ON APPROACH, THE RIGHT HAND ENGINE EXPERIENCED TORQUE FLUCTUATIONS.  POWER WAS REDUCED AND THE AIRCRAFT LANDED WIT	HOUT INCIDENT.  ON SHUTDOWN, OIL WAS OBSERVED LEAKING FROM THE RIGHT HAND ENGINE.  ON INVESTIGATION, IT WAS FOUND THAT T	HE MAGNETIC CHIP DETECTOR, ON THE REDUCTION GEARBOX, WAS SHEARED OFF CAUSING THE OIL LEAK.  SUBMITTER STATED IT APPEARS 	THE MAGNETIC CHIP DETECTOR WAS OVERTORQUED ON INSTALLATION.			1	L	7	2 	4T	4	T		A24CE   	E4EA
1998121800442	19981218	00442	SW  	1998	12	18	CA981019013      	1	19980922	G	2844	7G547	SWITCH          			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					BOOST PUMP	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE800419BA			(CAN) PRESSURE SWITCH LEAKING BETWEEN CONNECTING BOLT AND OUTER CASING.  WHEN WORKING ON THE SWITCH,  LIGHT CAME 'ON' AN	D STAYED 'ON'.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998121800443	19981218	00443	GL  	1998	12	18	CA981019014      	2	19980908	G	7313	6890917	NOZZLE          			HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			242  					CAE830691			(CAN) FUEL NOZZLE WAS SENT FOR CLEANING AND FLOW CHECK.  THE FUEL NOZZLE WAS RETURNED SERVICEABLE.  AFTER 66 HOURS OF SE	RVICE THE ENGINE BROKE DOWN AND THE CAUSE WAS ATTRIBUTED TO THE COMBUSTION LINER. THE FUEL NOZZLE WAS REINSTALLED AND AF	TER 75 HOURS OF SERVICE, WHEN THE TURBINE WAS REMOVED A LARGE DEPOSIT OF CARBON WAS PRESENT IN THE COMBUSTION LINER.  TH	E FUEL NOZZLE WAS AGAIN SENT FOR CLEANING AND THIS TIME THE NOZZLE WAS FOUND UNSERVICEABLE.			1	G	7	1 	3U	3	U		H3WE    	E4CE
1998121800460	19981218	00460	CE  	1998	12	18	CA981022005      	1	19981010	G	5540	053101814	BRACKET         			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	RUDDER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1107 						E18117		(CAN) HORIZONTAL MOVEMENT OF RUDDER WAS POSSIBLE WITH LIGHT PRESSURE.  MOST NOTABLE AT LOWER HINGE.  HINGE BRACKETS UPPE	R AND LOWER AT CENTER AND LOWER POSITIONS HAD ELONGATED BOLT HOLES.  CAUSE NOT DETERMINED.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1998121800461	19981218	00461	SW  	1998	12	18	CA981022006      	1	19981010	G	3210	604025011	SUPPORT         		212321103   	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					CROSSTUBE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						361		LE07253X			(CAN) SUPPORT SLIP TO THE RIGHT ON BOTH FRONT AND REAR CROSSTUBE.  ADHESIVE (PRC) PEELING OFF SUPPORT.  P/N ARE STC-AERO	NAUTICAL ACCESSORIES INC.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1998121800462	19981218	00462	CE  	1998	12	18	CA981022007      	1	19981014	G	2823	NAS561C29	PIN             		2416001     	CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	FUEL SELECTOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5250 					L2457636A	797859		(CAN) FUEL SELECTOR GEAR ASSY AND U-JOINT SHAFT WAS REMOVED TO REPAIR EXCESS PLAY.  ONE GEAR WAS LOOSE ON ITS SHAFT.  WH	EN ROLL PIN WAS REMOVED IT WAS FOUND TO BE BROKEN IN 3 PIECES.  ROLL PIN HOLDS GEAR ON SHAFT.					1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
1999012900930	19990129	00930	SW  	1999	1	29	CA981022009      	1	19981015	G	2910	2781006021	LINE            			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					HYDRAULIC SYSTEM	CRACKED         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA			13701					P54142C			(CAN) AFTER TAKEOFF, ANNUNCIATOR PANEL INDICATION OF A HYDRAULIC LEAK.   AIRCRAFT RETURNED TO AIRPORT OK.  INVESTIGATION	 FOUND A CRACKED PIPE.  14,411.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
1998121800463	19981218	00463	CE  	1998	12	18	CA981022010      	1	19980923	G	3230	1003810061	SWITCH          		1018100021  	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					LT MLG	OUT OF ADJUST   	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA								PCE80138			(CAN) WHEN LANDING GEAR SELECTED UP, THE GEAR UNSAFE LIGHT REMAINED ON.  DURING MAINTENANCE RETRACTION TESTS, THE LEFT G	EAR UP SWITCH WAS FOUND TO BE OUT OF ADJUSTMENT.  SWITCH ADJUSTMENTS CARRIED OUT AND SYSTEM CHECKED OKAY.					1	L	7	2 	4T	4	T		A24CE   	E4EA
1998121800465	19981218	00465	SO  	1998	12	18	CA981022013      	2	19981014	G	7322	07501337	SEAL            			CESSNA	182   	182Q        	2072732	CE  	CONT  	O470  	O470U       	17026	SO  	MCAULY	2A34C	C2A34C204   	GL  	AIR BOX	MISSING         	W				A				UNSCHED LANDING         				Y	J		ENGINE STOPPAGE           	WARNING INDICATION        		CR	CRUISE         	1			CA			2600 					463261	771383		(CAN) DURING FLT WITH PARTIAL CARB HEAT, EGT GAUGE DROPPED STEADILY TO MINS.  ALL OTHER ENG PARAMETERS NORMAL AND UNCHAN	GED.  FULL CARB HEAT APPLIED WITH MIX RICH PER POH AND CARB ICE, IMMEDIATE LOSS OF ENG POWER WITH ROUGH RUNNING AND ENG 	STOPPED DUE TO OVERRICH MIX WHICH LEANED TO REGAIN POWER.  ENG RAN SMOOTHLY WITH A SLIGHT DROP IN MANIFOLD PRESSURE.  AC	FT IN WOODED TERRAIN AND POOR LOCATION FOR FORCED LDNG.  ACFT RETURNED TO BASE WITH UNEVENTFUL LDNG.  INSP FND CARB VENT	URI PARTIALLY BLOCKED BY A PIECE OF CARB HEAT DOOR BAFFLE MAT'L (APPROX 4 INCHES BY 1 INCH) WHICH SEPARATED FROM BACK OF	 CARB HEAT DOOR.  REPLACED AND SNAG RECTIFIED.  SUBMITTER SUGGESTS ALL CESSNA WITH SIMILAR INST CHK CARB HEAT DOOR.	1	H	7	1 	3O	3	O	NT	3A13    	E273	5	C	P3EA
1998121800466	19981218	00466	CE  	1998	12	18	CA981027001      	1	19980902	G	5740		FITTING         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C201    	GL  	RT WING	WORN            	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA			6014 					4930273KR	753840		(CAN) RIGHT HAND WING FOUND MOVING EXCESSIVELY AT ALL ATTACH POINTS.  FITTINGS FOUND WORN TO .016 INCH PLAY.  FITTINGS B	USHED IAW CESSNA INSTRUCTIONS AND NAS CLOSE TOLERANCE BOLTS INSTALLED.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1998121800467	19981218	00467		1998	12	18	CA981027002      	1	19981019	G	2841	1124	INDICATOR       	SIMMONDS    	393004061   															COCKPIT	MISMARKED       	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1124					(CAN) FUEL QUANTITY INDICATOR RECEIVED WITH WRONG IDENTIFICATION PLATE ATTACHED.
1998121800469	19981218	00469	SO  	1998	12	18	CA981027004      	1	19980925	G	2912	AN6227B22	O-RING          			PIPER 	PA31  	PA31350     	7103110	SO  										HYD FILTER	DISPLACED       	W				O				OTHER                   				K	J		FLUID LOSS                	WARNING INDICATION        		LD	LANDING        	1			CA			11389								(CAN) ON APPROACH, LANDING GEAR WOULD NOT EXTEND.  EMERGENCY SYSTEM USED AND GEAR EXTENDED OK.  LANDING OK.  RIGHT HAND 	LANDING GEAR HYDRAULIC FILTER HOUSING O-RING FOUND DISPLACED CAUSING FLUID LEAK.					1	L	7	2 	3O				A20SO
1998121800470	19981218	00470	SO  	1998	12	18	CA981027005      	2	19981027	G	8530	C66AIR	CYLINDER        			CESSNA	337   	337D        	2075717	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C302  	GL  	NR 2	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			O			OTHER                     			CR	CRUISE         	1			CA								900352OH	7911029		(CAN) DURING CRUISE, THE FRONT ENGINE HAD A CYLINDER FAILURE.  THE CYLINDER WAS REPLACED AFTER LANDING.						1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
1998121800471	19981218	00471	SO  	1998	12	18	CA981027006      	2	19980920	G	7322	AN3	BOLT            			CESSNA	207   	207         	2073602	CE  	CONT  	O520  	IO520F      	17032	SO  					THROTTLE BODY	DAMAGED         	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			TO	TAKEOFF        	1			CA				337  				279878R			(CAN) AFTER TAKEOFF, THE ENGINE LOST POWER.  POST-FLIGHT INSPECTION FOUND THE BOLT THAT SECURES THE THROTTLE CABLE TO TH	E THROTTLE BODY ARM HAD WORN DUE TO LACK OF TIGHTNESS.  THE COTTER PIN WAS WORN AND SUBSEQUENTLY FELL APART.  THE SECURI	NG NUT WAS ALSO STRIPPED OF THREADS.  THIS BOLT WAS INSTALLED ON AN OVERHAULED ENGINE 336.9 HOURS AGO AND THE SUBMITTER 	SUGGESTS THAT IT WAS UNLIKELY EITHER THE NUT OR BOLT WERE NEW.			1	H	7	1 	3O	3	O		A16CE   	E5CE
1998121800472	19981218	00472	SW  	1998	12	18	CA981027007      	1	19981016	G	2435	230322843	SHAFT           	AIRPRTSCORP 	150SG117Q   	BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20B     	03013	GL  					START/GEN	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				715  		5350					(CAN) ON DISASSEMBLY AT OVERHAUL FACILITY, THE APC STARTER/GENERATOR WAS FOUND TO CONTAIN A LUCAS SHAFT AND A LUCAS DAMP	ENER IN PLACE OF THE APC SHAFT, P/N 150SG1103-2.  THE ASSEMBLY ALSO HAD A SECOND DAMPENER DEVICE AT THE ANTI-DRIVE END. 	  SUBMITTER STATED NO APPARENT DAMAGE DUE TO THIS INCORRECT INSTALLATION.				1	G	7	1 	3U	3	U		H2SW    	E4CE
1999012200269	19990122	00269	EA  	1999	1	22	CA981027008      	1	19981015	G	5711	2151003268	SPAR            			CNDAIR	CL215 	CL2151A10   		EA  										LT & RT WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3013 								(CAN) WHILE COMPLYING WITH AD CF-92-26, REF SB 215-A454, BOTH LEFT AND RIGHT REAR SPAR CAPS WERE FOUND CRACKED USING VIS	UAL METHOD.  ON DISASSEMBLY, FOUND THE LEFT SPAR CAP WAS COMPLETELY CRACKED THROUGH, WHILE THE RIGHT HAND ONE WAS CRACKE	D ABOUT HALF WAY THROUGH.				2	H	7	2 	4R				A14EA
1998121800473	19981218	00473	CE  	1998	12	18	CA981027009      	1	19981008	G	5343	071349561	BRACKET         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470S       	17026	SO  					RT/LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1278 					269215R			(CAN) DURING CHANGE OVER FROM FLOATS TO WHEEL GEAR, BOTH THE LEFT AND RIGHT MLG OUTBOARD SUPPORT BRACKETS WERE FOUND CRA	CKED.  LEFT P/N 0713495-61 AND RIGHT HAND P/N 0713495-62.					1	H	7	1 	3O	3	O		5A6     	E273
1998121800474	19981218	00474	CE  	1998	12	18	CA981027010      	1	19981016	G	5343	071349561	BRACKET         			CESSNA	180   	180H        	2072618	CE  	CONT  	O470  	O470R       	17026	SO  	MCAULY	2A34C	2A34C66     	GL  	LT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			344  					832841R	805321		(CAN) DURING CHANGE OVER FROM FLOATS TO WHEEL GEAR, THE LEFT MAIN LANDING GEAR OUTBOARD SUPPORT BRACKET FOUND CRACKED.						1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1998121800476	19981218	00476	CE  	1998	12	18	CA981027013      	1	19981020	G	5415	50980002122	ANGLE           			BEECH 	99    	99A         	1154003	CE  	PWA   	PT6   	PT6A28      		EA  					RT NACELLE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24922					PCE51145			(CAN) DURING 100 HOUR ANNUAL INSPECTION, THE RIGHT INBOARD UPPER NACELLE AREA REVEALED SMOKING RIVETS ATTACHING STIFFENE	R ANGLE TO ENGINE MOUNT ATTACHMENT ASSY P/N 50-980089.  CLOSER INSPECTION REVEALED APPROXIMATELY A 2 INCH CRACKING STIFF	ENER ANGLE.  DURING THE REPAIR PROCESS, THE UPPER STIFFENER ANGLE WAS ALSO FOUND CRACKED.  THESE CRACKS WERE NOT VISIBLE	 UNTIL AN ACCESS HOLE WAS CUT TO REPAIR LOWER STIFFENER ANGLE.  PART TC:  35,143.			1	L	7	2 	3T	4	T		A14CE   	E4EA
1999040200120	19990402	00120	NM  	1999	4	2	CA981027018      	1	19981019	G	5610	94069H3427	TERMINAL        	PPG         	NP15790112  	DHAV  	DHC8  	DHC8103     	1386005	NM  										RT WINDSHIELD	OVERHEATED      	W				A				UNSCHED LANDING         				M	B		OVER TEMP                 	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA						94069H3427					(CAN) SMOKE DEVELOPED IN COCKPIT.  INSPECTION FOUND THE RIGHT HAND FORWARD WINDSHIELD ELECTRICAL CONNECTION TERMINAL STR	IP L2 OVERHEATED AND THE INSULATION ON THE TERMINAL LUG HAD MELTED.   HEAT BUILD-UP WAS BETWEEN THE TERMINAL STRIP AND T	HE HEATER BUS IN THE WINDSHIELD.  TERMINAL LUG WAS FOUND PROPERLY TIGHTENED TO THE STRIP.				2	H	7	2 	4T			RT	A13NM
1998121800478	19981218	00478	NM  	1998	12	18	CA981027019      	1	19981018	G	2720	106055220	SWITCH          	BOEING      	65178661    	BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					RUDDER	CORRODED        	W				D				RETURN TO BLOCK         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA								P689955			(CAN) CREW REPORTED RUDDER SYSTEM A LOW PRESSURE LIGHT CAME ON.  CANNON PLUG ON RUDDER A SYSTEM LOW PRESSURE SWITCH WAS 	FULL OF RUST.  SWITCH AND CANNON CONNECTOR CLEANED AND RESECURED.  SYSTEM SERVICEABLE.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998121800479	19981218	00479	NE  	1998	12	18	CA981027020      	2	19981019	G	7230	12355813	VALVE           								PWA   	JT8   	JT8D17      	52049	NE  					NR 1 ENGINE	LEAKING         	W				A				UNSCHED LANDING         				M			OVER TEMP                 			CL	CLIMB          	1			CA								P689955			(CAN) NR 1 STRUT OVERHEAT LIGHT WARNING CAME ON WHILE CLIMBING THROUGH 8,000 FEET ON TAKEOFF.  POWER WAS REDUCED, LIGHT 	EXTINGUISHED AND AIRCRAFT RETURNED TO ITS POINT OF DEPARTURE.  POST-FLIGHT INSPECTION FOUND THE 8TH STAGE CHECK VALVE, O	N NR 1 ENGINE LEANING AT THE CLAMPS AND THROUGH THE VALVE PIN HOUSING.  THE 8TH STAGE CHECK VALVE WAS REPLACED AND IT CH	ECKED SERVICEABLE.								4	F			E2EA
1998121800480	19981218	00480	GL  	1998	12	18	CA981027021      	2	19980831	G	7230	6895803	SCROLL          		23005200    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE BAY	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5097 			CAE70024		CAE860375			(CAN) WHILE CONDUCTING A 600 HOUR INSPECTION, A CRACK 1 INCH BY .50 INCH WAS FOUND IN THE SCROLL ASSEMBLY.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998121800481	19981218	00481	EA  	1998	12	18	CA981027022      	2	19980923	G	7322	BA5110A	SEAL            	BRACKETT    	STCSA71GL   	CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	CARBURETOR	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			306  					L4004427A	720159		(CAN) STC SA71GL WAS INCORPORATED ON THE ENGINE.  FAA AD 96-09-06, WHICH SUPERSEDES FAA AD 95-03-02, CALL FOR THE INSPEC	TION OF THE CARBURETOR AIR INTAKE FILTER GASKET AT 100 HOUR INTERVALS.  REQUIREMENTS FOR TERMINATING ACTION OF THIS AD I	S THE REPLACEMENT OF THE AIR FILTER ASSEMBLY INSTALLED PER THE STC, WITH A REPLACEMENT AIR FILTER ASSEMBLY PER AD 96-09-	06.  AD TERMINATION ACTION WAS CARRIED OUT, WITH THE INSTALLATION OF AIR FILTER ASSEMBLY PART BA-5110 REVISION H WHICH R	EPLACED AIR FILTER ASSEMBLY PART BA-5110, PER THE REVISED AD AND STC.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1999061800003	19990618	00003	SW  	1999	6	18	CA981027023      	1	19981020	G	5610	3600431455	WINDSHIELD      	PPG         		GULSTM	690TP 	690D        	3970405	SW  						ROTOL	R306	R306382F7   	GL  	COCKPIT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			182  			98225H4291			106738		(CAN) WINDSHIELD OUTER GLASS FOUND CRACKED CLOSE TO HEATING ELEMENT.						1	H	7	2 	3T				2A4     		6	C	P8EU
1998122400365	19981224	00365	EA  	1998	12	24	CA981028007      	2	19981001	G	8530	LW12966	CYLINDER        			PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					ENGINE	SEPARATED       	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA			409  					L258961A			(CAN) DURING CLIMB, THE PILOT HEARD A LOUD BANG.  A QUICK TURN AROUND WAS EXECUTED AND THE AIRCRAFT RETURNED TO ITS POIN	T OF DEPARTURE.  POST-FLIGHT INSPECTION REVEALED ONE OF THE CYLINDERS HAD SEPARATED.  THE ENGINE WAS REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1999032600142	19990326	00142	EA  	1999	3	26	CA981028009      	1	19981022	G	3213	C3U547	JOINT           			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					STRUT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5000 					3264212			(CAN) A CRACK FOUND ON THE JOINT ASSEMBLY TOP WHICH IS INSTALLED AT THE TOP END OF THE AXLE STRUT.  AD CF-69-12 AND SB 3	/12 BOLT INSPECTION ARE RELEVANT.  ALSO SB 3/32 LANDING GEAR ATTACHMENT TORQUE LOADING.					1	H	7	1 	3R	3	R		A815    	5E2
1998122400368	19981224	00368	SO  	1998	12	24	CA981028011      	1	19981021	G	5751	1710018	SPAR            		17100       	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12129			6653		L602648			(CAN) CRACKS FOUND IN LEFT AILERON INBOARD RIB P/N 17100-13, TO WHICH IS ATTACHEDTHE HINGE LEFT INBOARD P/N 17095-00 THR	OUGH THE SPAR.  CRACKS LOCATED AT BOTTOM HOLE.					1	L	7	2 	3O	3	O		1A10    	1E4
1998122400369	19981224	00369	GL  	1998	12	24	CA981030001      	2	19980718	G	7250	6878426	NOZZLE          		6898734     						ALLSN 	250C  	250C20      	03013	GL  					2ND STAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				267  		CAT21597		CAE822213			(CAN) INSPECTION FOUND CIRCUMFERENCE CRACKS ON THE OUTER BAND OF THE NOZZLE ASSEMBLY.  NOZZLE WAS CRACKED APPROXIMATELY 	75 PERCENT OF THE OUTER CIRCUMFERENCE WHERE THE OUTER BAND WAS REPLACED DURING LAST OVERHAUL.  FAULT WAS FOUND DURING RE	PAIR OF 1ST STAGE TURBINE WHEEL.  PART TC:  466.									3	U			E4CE
1998122400379	19981224	00379	SW  	1998	12	24	CA981030018      	1	19981010	G	3210	604025001	SUPPORT         		212321104   	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					CROSSTUBE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						729		LE07253X			(CAN) SUPPORT SLIPPING TO THE RIGHT ON BOTH FRONT AND AFT CROSSTUBES.  ADHESIVE (PRC) PEELING FROM SUPPORT.						1	G	7	1 	4U	4	U		H1SW    	E17EA
1998122400381	19981224	00381	NE  	1998	12	24	CA981109002      	2	19981024	G	8530	36805	PISTON          		47157       	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					ENGINE	CRACKED         	W				O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA				356  		D185		16188			(CAN) CRACK IN NR 3 PISTON ALLOWED PRESSURE IN THE CRANKCASE TO EXIT AROUND THE CRANKCASE SEAL AND CAUSE SMOKE AND FUMES	 TO EXIT THE ENGINE COWL.  THERE WAS NO VISIBLE SIGN OF DETONATION OR PRE-IGNITION BY AN BURNING OR CHARRING.					1	H	7	1 	3R	3	R		A806    	5E1
1998122400382	19981224	00382	SO  	1998	12	24	CA981109004      	1	19981029	G	6120	2489408	CONTROL CABLE   			PIPER 	PA31  	PA31325     	7103105	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROPELLER	SHEARED         	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA								L399561A	DJ1020A		(CAN) DURING PRE-FLIGHT, PILOT NOTED PROP LEVER WAS TOO LOOSE AND THE PROP DID NOT RESPOND.   AIRCRAFT SHUT DOWN.  INSPE	CTION FOUND THE PROP CABLE AT THE CONTROL COLUMN LEVER, THE CABLE STRANDS WERE ALL BROKEN.  BREAK AT END WHERE CABLE IS 	SWAGED ON TO CABLE END.				1	L	7	2 	3O	3	O	 	A20SO   	E14EA	5	C	P33EA
1998122400383	19981224	00383		1998	12	24	CA981109005      	4	19981001	G	2561		LIFE VEST       			CESSNA	500   	560CESSNA   	2076750	CE  										CABIN	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) DURING RECURRENT TRAINING, 3 OUT OF 4 LIFE VESTS DID NOT INFLATE PROPERLY.   VESTS RETURNED TO MANUFACTURER FOR IN	VESTIGATION.					2	L	7	2 	4F			RT	A22CE
1999040200125	19990402	00125	EA  	1999	4	2	CA981109006      	1	19981026	G	2820	C6PF11471	LINE            			DHAV  	DHC6  	DHC6        	2802606	EA  										FUEL SYSTEM	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA											(CAN) WELDED TUBE ASSY IS FIVE INCHES TOO LONG.						1	H	7	2 	3T			RT	A9EA
1999012900932	19990129	00932	SW  	1999	1	29	CA981109007      	1	19981026	G	3250	2781032682	LINE            			SWRNGN	SA227 	SA227AC     	8780603	SW  										NLG WW	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC FLUID FOUND LEAKING FROM NOSE WHEELWELL AREA.  FLUID WAS COMING FROM THE STEERING FILTER HOUSING INLET L	INE.  A SMALL CRACK WAS FOUND AT THE BEND RADIUS.					2	L	7	2 	4T			RT	A8SW
1999040200126	19990402	00126	SW  	1999	4	2	CA981109008      	1	19981027	G	2400	MS3120E2221S	CONNECTOR       			SWRNGN	SA226 	SA226*      		SW  										ELECTRICAL SYS	MISLABELED      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN SB 226-24-026 WAS BEING CARRIED OUT, A NEW CONNECTOR WAS FOUND WITH THE LABELING FOR PINS FROM THE FORWARD AN	D AFT ENDS DID NOT MATCH.					2	L	7	2 	4T			RT	A56W
1998122400384	19981224	00384		1998	12	24	CA981109009      	4	19980920	G	3452	066106200	TRANSPONDER     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ATC PANEL	FAILED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA								PCE85170			(CAN) TRANSPONDER SNAGGED FOR NO LIGHTS.  FURTHER INVESTIGATION REVEALED BOARD NEAR TRANSISTOR WAS BURNT.  THIS PROBLEM 	ADDRESSED UNDER MOD NR 6 FOR THIS TRANSPONDER.  NEW TRANSPONDER INSTALLED AND IT WAS DISCOVERED THIS ONE HAD NOT BEEN MO	DIFIED.  IT ALSO WAS REMOVED AND RETURNED FOR THE MODIFICATION.				1	L	7	2 	4T	4	T		A24CE   	E4EA
1998121800485	19981218	00485	SO  	1998	12	18	CA981109010      	2	19981009	G	8520		CRANKCASE       			CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360G      	17025	SO  	MCAULY	2AF34C	D2AF34C306  	GL  	REAR ENGINE	CRACKED         	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	K	J	VIBRATION/BUFFET          	FLUID LOSS                	WARNING INDICATION        	CL	CLIMB          	1			CA				866  				352551	764417		(CAN) THE REAR ENGINE OF A 337G SKYMASTER WAS REPORTED AS RUNNING ROUGH.  INSPECTION FOUND THE SPARK PLUGS FOULED, SO TH	E PLUGS WERE REPLACED. THE ENGINE RAN SMOOTH AND IT WAS RELEASED FOR RETURN TO SERVICE.  ON THE SECOND FLIGHT WHEN POWER	 WAS REDUCED, THE ENGINE STARTED TO RUN ROUGH WITH ABNORMAL ENGINE OIL TEMPERATURE AND PRESSURE.  POWER WAS REDUCED AND 	THE OIL TEMPERATURE WENT OVER THE RED LINE SO THE ENGINE WAS SHUTDOWN.  THE AIRCRAFT RETURNED TO BASE.  POST-FLIGHT INSP	ECTION FOUND THE RIGHT SIDE OF THE REAR COWLING COVERED IN OIL.  REMOVAL OF THE COWLING REVEALED THE CRANKCASE WAS CRACK	ED IN SEVERAL PLACES.	1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
1998122400385	19981224	00385	SW  	1998	12	24	CA981109011      	1	19981027	G	2435	312281095	DAMPENER        	LUCAS       	23064001    	BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					START/GENERATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA						2919		LE08236A			(CAN) STARTER/GENERATOR IN SHOP FOR REPAIR WAS FOUND TO HAVE WRONG DAMPENER BACKPLATE INSTALLED CAUSING INSUFFICIENT SPR	ING PRELOAD WHICH RESULTED IN EXCESS WEAR ON THE SPLINED HUB, DAMPENER PLATE, AND SHAFT SPLINE.					1	G	7	1 	4U	4	U		H1SW    	E1EA
1998122400386	19981224	00386	SO  	1998	12	24	CA981109012      	1	19980825	G	3297	6741102	WIRE            			PIPER 	PA34  	PA34220T    	7103420	SO  	CONT  	O360  	TSIO360KB   	17025	SO  	MCAULY	3AF32C	3AF32C508   	GL  	LT MLG	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA								242915R	814393		(CAN) WHEN GEAR SELECTED DOWN, NO GREEN LIGHT FOR LEFT GEAR AND GEAR UNSAFE LIGHT ON.  FLY-BY OK.  AIRCRAFT LANDED SAFEL	Y.  INSPECTION FOUND A BROKEN WIRE AT THE CONNECTOR FOR THE GEAR SWITCH.					1	L	7	2 	3O	3	O	 	A7SO    	E9CE	5	C	P22EA
1998122400387	19981224	00387	GL  	1998	12	24	CA981109013      	3	19981014	G	6114	C084034	HUB             													HARTZL	HCB3R	HCB3R302    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3566 	214  					CX170		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  HUB, PISTON AND BEARINGS WERE FOUND CORRODED AND WERE REPLACED.																5	C	P28EA
1999012200588	19990122	00588	GL  	1999	1	22	CA981109014      	3	19981007	G	6111	LV9333N4	BLADE           			STOLAM	RC3   	RC3         	3080203	NM  						HARTZL	HCA3V	HCA3V203    	GL  	LEADING EDGE	FOD DAMAGE      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			115  	45   					FC43		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADE FOUND WITH FOD DAMAGE AND INTERNAL CORROSION ON THE 	BLADE.  THE PROPELLER BLADE WAS REPLACED.					1	H	7	1 	3O			RC	A769    		5	C	P6EA
1998122400388	19981224	00388	GL  	1998	12	24	CA981109015      	3	19981014	G	6111		BLADE           			CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2106 					LD008		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE BLADES LEADING EDGES AND FACES.  THE D	AMAGE WAS TRIMMED OUT.					1	H	7	1 	3O			NT	3A12    		5	N	P910
1998122400389	19981224	00389	GL  	1998	12	24	CA981109016      	3	19981022	G	6111	DM7648	BLADE           			CESSNA	172   	172         	2072402	CE  	CONT  	O300  	O300A       	17022	SO  	MCAULY	1A170	1A170*      	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								13031D7A	66332		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  INSPECTION FOUND CORROSION AND BLADE DAMAGE DUE TO STONES.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P857
1998122400390	19981224	00390	EA  	1998	12	24	CA981109017      	3	19981027	G	6111		BLADE           													SNSNCH	74DMS	M74DMS      	EA  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA									K7559		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES.																5	N	P88614
1998122400391	19981224	00391	EA  	1998	12	24	CA981109018      	3	19981020	G	6111		BLADE           			PIPER 	PA28  	PA28181     	7102807	SO  	LYC   	O360  	O360A4M     	41514	EA  	SNSNCH	76E	76EM8S5     	EA  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1272 				L2125636A	14428K		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE BLADES LEADING EDGES AND FACES.						1	L	7	1 	3O	3	O		2A13    	E286	5	N	P4EA
1998122400392	19981224	00392	GL  	1998	12	24	CA981109019      	3	19981022	G	6111		BLADE           			CESSNA	172   	172G        	2072420	CE  	CONT  	O300  	O300D       	17022	SO  	MCAULY	1C172	1C172EM     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1042 				28787D4D	79554		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE LEADING EDGES AND FACES OF THE BLADES.						1	H	7	1 	3O	3	O	NT	3A12    	E253	5	N	P910
1998122400393	19981224	00393	CE  	1998	12	24	CA981109020      	1	19981023	G	3250	24670036	BUNGEE          			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	NLG STEERING	BROKEN          	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			7552 					L3135636A	940226		(CAN) PILOT UNABLE TO STEER AIRCRAFT STRAIGHT AFTER A TIGHT TURN INTO WIND.  INSPECTION FOUND THE STEERING BUNGEE LOCATE	D ABOVE THE RUDDER TORQUE TUBES BETWEEN THE PILOT'S AND CO-PILOT'S PEDALS TO BE BROKEN AND JAMMED.  THIS IS SECOND INCID	ENT ONE OF SUBMITTERS 172 AIRCRAFT.  NO WAY TO INSPECT INTERNAL PARTS OF STEERING BUNGEE.				1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
1998122400394	19981224	00394	SO  	1998	12	24	CA981109021      	1	19981023	G	7120	LW13291	MOUNT           			PIPER 	PA44  	PA44180     	7104402	SO  	LYC   	O360  	O360E1A6    	41514	EA  					ENGINE	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				650  				L24777T			(CAN) DURING ROUTINE INSPECTION, THE LEFT LOWER ENGINE MOUNTING BRACKET WAS FOUND LOOSE.  ONE OF THE TWO SECURING BOLTS 	WAS FOUND MISSING AND THE OTHER WAS LOOSE.  SI NR 1380 RECOMMENDS CHECKING THE TORQUE ON THE BOLTS 100 HOURS AFTER INSTA	LLATION.  THERE WAS ALSO A ONE TIME AD INSPECTION REQUIRED IN 1979, BUT THE ENGINE HAS SINCE BEEN REPLACED.				1	L	7	2 	3O	3	O		A19S0   	E286
1998122400395	19981224	00395	SO  	1998	12	24	CA981109022      	2	19981002	G	8520	643202	CRANKCASE       			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  					NR 2 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1076 				514215			(CAN) PILOT REPORTED OIL LEAK ON NR 2 ENGINE.  ENGINE WAS WASHED DOWN AND RUN-UP.  INSPECTION FOUND A 1.5 INCH CRACK JUS	T BELOW THE FORWARD TOP THROUGH-BOLT AREA, NEAR THE THRUST BEARING AREA OF THE FRONT OF THE CRANKCASE.  THE ENGINE WAS R	EMOVED AND SENT FOR OVERHAUL.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE
1998122400396	19981224	00396	CE  	1998	12	24	CA981109023      	1	19981015	G	2421	01612	ALTERNATOR      			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  					AC SYSTEM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				328  				503204			(CAN) ALTERNATOR REMOVED AT SAME TIME AS ENGINE REMOVAL.  ONE ATTACHING EAR WAS FOUND CRACKED, TO THE POINT THAT THE ONL	Y THING HOLDING IT WAS THE MOUNTING FLANGE GASKET.  SUBMITTER STATED CRACK VERY HARD TO SEE AS ENGINE BAFFLING OBSCURES 	CLEAR VIEW.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE
1998122400397	19981224	00397	CE  	1998	12	24	CA981109024      	1	19981015	G	5321	04102381	FLOORBOARD      			CESSNA	150   	150M        	2071830	CE  	CONT  	O200  	O200A       	17020	SO  					CABIN	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12790					250825SO			(CAN) DURING ANNUAL INSPECTION, A CRACK WAS FOUND IN THE FLOOR PANEL UNDER THE COPILOT'S SEAT TRACK VERY AFT POSITION. C	RACK WAS PARALLEL TO THE END OF THE SEAT TRACK AND THEN RUNS FORWARD ON BOTH SIDES.  CRACK ALSO FOUND UNDER THE INBOARD 	SEAT TRACK POSITION.				1	H	7	1 	3O	3	O		3A19    	E252
1999012200270	19990122	00270	CE  	1999	1	22	CA981109025      	1	19981019	G	7120	085112120	MOUNT           			CESSNA	414   	414         	2075908	CE  	CONT  	O520  	TSIO520J    	17040	SO  					RT ENGINE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5032 					503204			(CAN) AFTER ENGINE REMOVAL FROM RIGHT HAND POSITION, AN AREA ON OUTBOARD ENGINE RT BEAM HAD A SLIGHT BUMP.  FURTHER EXAM	INATION REVEALED A PORTION OF THE Z-SECTION WHICH MAKES UP THE BEAM WAS CORRODED RIGHT THROUGH.  INBOARD BEAM ALSO CORRO	DED.  SUBMITTER SUGGESTS THAT OTHER OPERATORS SHOULD LOOK AT THIS AREA.				1	L	7	2 	3O	3	O	RT	A7CE    	E8CE
1998122400398	19981224	00398	EU  	1998	12	24	CA981109026      	1	19981015	G	3211	115C5031	BRACKET         			GROB  	G115  	G115C       	1660303	EU  	LYC   	O320  	O320D1A     	41508	EA  					LT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			733  					L1838739A			(CAN) LEFT MAIN GEAR FOUND WITH EXCESSIVE PLAY DURING INSPECTION.  LEFT MAIN GEAR UPPER BRACKET FOUND BROKEN AT THE FORW	ARD BOLT HOLE.  CRACKS WERE FOUND IN THE WELDS AND THE BOLTS CLAMPING THE MAIN LANDING GEAR LEG WERE BENT.					1	L	7	1 	3O	3	O	NT	A57EU   	E274
1999040200131	19990402	00131	EA  	1999	4	2	CA981109034      	1	19981026	G	3260	21HE23RB	SWITCH          	MENASCO     	1510015     	DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	RT MLG	BROKEN          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA			1561 			MC141		86041	237398		(CAN) LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF. THERE WERE A NUMBER OF PROBLEMS FOUND.  LOCKING PINS ON WOW SWITCHES	 THAT HOLD CONNECTORS IN PLACE, ON RIGHT SIDE OUTBOARD IT WAS BROKEN DUE TO CORROSION, ON RIGHT INBOARD PINS BROKEN, BUT	 NO CORROSION.  LEFT INBOARD WOW SWITCH PINS ALSO BROKEN, NO CORROSION.   ALSO FOUND LOOSE AND BROKEN WIRE ON RIGHT LAND	ING GEAR WOW SWITCH HARNESS.			2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
1999040200132	19990402	00132	NM  	1999	4	2	CA981109035      	1	19981011	G	3230	54C546349	VALVE           			DHAV  	DHC8  	DHC8102     	2809003	NM  										NLG	DEFECTIVE       	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA											(CAN) AFTER TAKEOFF, GEAR SELECTED UP.   NOSE GEAR RED LIGHT STAYED ON AS WELL AS LEFT AND RIGHT DOOR ADVISORY LIGHTS FO	R MAIN GEAR.  NOSE LANDING GEAR SOLENOID SEQUENCE VALVE REPLACED.					2	H	7	2 	4T			RT	A13NM
1998122400399	19981224	00399		1998	12	24	CA981109036      	1	19981021	G	6123	13777	SOLENOID        								ALLSN 	501D  	501D13      	03004	GL  	ALLSN	A6441	A6441FN606  	GL  	LT PROPELLER	FAULTY          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE500816	HC335		(CAN) DURING INSPECTION, FOUND LEFT HAND PROPELLER WOULD NOT FEATHER.  THE ELECTRICAL SOLENOID WAS FOUND AT FAULT.											4	T			E282	6	C	P898
1999012200271	19990122	00271	NM  	1999	1	22	CA981109037      	1	19980928	G	2750	694353125	CONTROL CABLE   			BOEING	737   	737210C     	1384459	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					TE FLAP	BROKEN          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA								674358			(CAN) CABLE BROKE ON AFT FLAP EXTENSION ON LANDING.  NO NOTICE OF ANY CONTROL ASYMMETRY FOUND ON PRE-FLIGHT.   REPLACED.						2	L	7	2 	4F	4	F	 	A16WE   	E2EA
1998122400400	19981224	00400	CE  	1998	12	24	CA981109038      	1	19981103	G	5540		DRAIN           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RUDDER	SEALED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1294 								(CAN) DURING INSPECTION, WATER WAS FOUND TRAPPED IN THE RUDDER 4 INCHES ABOVE THE TRIM TAB.  DRAIN HOLES WERE FOUND TO B	E SEALED.  DRAINS OPENED AND WATER RELEASED.  SUBMITTER STATED APPARENTLY HOLES WERE SEALED AT THE FACTORY, BEECH NOTIFI	ED OF THE PROBLEM.  PART TC:  2,562.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998122400401	19981224	00401	CE  	1998	12	24	CA981109039      	1	19981103	G	5510	1016200006	DRAIN           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					HORIZ STABILIZER	CLOGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1294 								(CAN) ON REMOVAL OF THE HORIZONTAL STABILIZER UPPER INSPECTION PANEL, FOUND THERE WAS WATER ACCUMULATION NEXT TO THE BUL	KHEAD PN 101-600015-9.  THIS CONDITION WAS CAUSED BY THE INCORRECT LOCATION OF A WATER DRAIN HOLE.  SUBMITER STATED IF T	HE WATER IS ALLOWED TO ACCUMULATE AND FREEZE, IT COULD CAUSE SERIOUS ELEVATOR CONTROL PROBLEMS.  BEECH TECHNICAL SUPPORT	 INFORMED OF THE PROBLEM.  PART TC:  2,562.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1998122400403	19981224	00403	SO  	1998	12	24	CA981109043      	1	19981026	G	3260	3128700	BRACKET         			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA			10054					L810948			(CAN) PILOT SELECTED GEAR DOWN AND THE LEFT GEAR LIGHT DID NOT COME ON.  MANY ATTEMPTS TRIED.  MICROSWITCH BRACKET FOUND	 BROKEN.  ALSO NOTED THAT BOLT P/N AN177-27 AT THE CENTER OF THE RETRACTION LINK WAS BROKEN.					1	L	7	2 	3O	3	O		1A10    	1E4
1998122400404	19981224	00404	EA  	1998	12	24	CA981109044      	2	19981028	G	7414	67542	BEARING         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					LEFT MAGNETO	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			576  					L2486840A			(CAN) THE ENGINE DID NOT START NORMALLY. THE LEFT MAGNETO WAS REMOVED FOR INSPECTION AND THE GEAR BALL BEARINGS FELL INT	O THE OIL SUMP.  THE SUMP WAS OPENED AND THE BALL BEARING CASE WAS FOUND SHREDDED, POSSIBLY BY THE GEAR.  IT WAS CONCLUD	ED THAT THE BEARING BROKE WHILE THE ENGINE WAS RUNNING.  THERE WAS NO OTHER DAMAGE.  THE MAGNETO WAS REPLACED.   AS A PR	ECAUTION, ALL THE GEARS WERE NDT CHECKED AND THE ENGINE WAS RETURNED TO SERVICE.			1	G	7	1 	3O	3	O		H11NM   	E295
1999021200927	19990212	00927	EA  	1999	2	12	CA981109045      	1	19981030	G	2760	270003	PCU             			CNDAIR	CL600 	CL6002B19   		EA  										RT SPOILER	FAILED          	W				H				DEACTIVATE SYST/CIRCUITS				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CR	CRUISE         	1			CA						MAL1193					(CAN) SUSPECTED UNCOMMANDED DEPLOYMENT OF RT FLIGHT SPOILER.  AT FL 290, WITH A/P ON AIRPLANE INCLINED TO RIGHT.   A/P D	ISCONNECTED, CAUTION MESSAGE 'R FLT SPLR',  FOLLOWED BY STATUS MESSAGES 'FLT SPLRS FAULT' AND 'O/B GND SPLR FAULT'.  MAI	NTENANCE FOUND RT FLIGHT SPOILER O/B PCU SOLENOID VALVE RESISTANCE +90 OHMS AND SECU NR 1 DEAD.				2	L	7	2 	4F			RT	A21EA
1999021200928	19990212	00928	EA  	1999	2	12	CA981109046      	1	19981021	G	5755		FITTING         		600106021002	CNDAIR	CL600 	CL6002B19   		EA  										RT SPOILER	CRACKED         	W				O				OTHER                   				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		AP	APPROACH       	1			CA			10355			22W					(CAN) PILOT REPORTED AN UNCOMMANDED DEPLOYMENT OF RT FLIGHT SPOILER ON APPROACH 'FLT SPLR' STATUS MSG.  DURING APPROACH 	WITH FLAPS 45 DEGREES AFTER 10 SECONDS, 'FLT SPLRS DEPLOY' MSG STRONG AILERON TO LEFT REQUIRED TO KEEP DIRECTIONAL CONTR	OL.  INSPECTION FOUND A LARGE CRACK IN THE INBOARD PCU SPOILER FITTING..  PART TC:  8,622.				2	L	7	2 	4F			RT	A21EA
1998122400405	19981224	00405	EU  	1998	12	24	CA981109047      	1	19981001	G	2550	145201	CABLE           	BREEZE      	140276      	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					CARGO HOOK	SEPARATED       	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			50   			3115		CAE835628			(CAN) INADVERTENT RELEASE OF LOAD.  SWAGED END OF MANUAL RELEASE CABLE SEPARATED CAUSING THE HOOK TO UNLATCH.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE
1999021200929	19990212	00929	SW  	1999	2	12	CA981109048      	1	19981025	G	2897	PAA5741	WIRE            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					FUEL PROBE	CHAFED          	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA								P03001C			(CAN) RIGHT HAND FUEL QUANTITY INDICATOR INTERMITTENTLY ROTATES CLOCKWISE.  FUEL PROBE REPLACED AT WS 115.9 AND WIRE REP	AIRED BETWEEN CENTER TUBE AND THE TOP TERMINAL PROBE.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1998122400406	19981224	00406	EA  	1998	12	24	CA981113003      	2	19980918	G	8530	SL73806	PUSH ROD        			PIPER 	PA38  	PA38112     	7103812	SO  	LYC   	O235  	O235L2C     	41505	EA  					NR 2 CYLINDER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1124 					L1574415			(CAN) DURING INVESTIGATION OF LEAKING VALVE ON NR 2 CYLINDER, THE PRESSED END OF A PUSH ROD WAS FOUND LOOSE.  THE ROD WA	S A SUPERIOR AIR PARTS MANUFACTURED PART.					1	L	7	1 	3O	3	O		A18SO   	E223
1998122400407	19981224	00407	CE  	1998	12	24	CA981113010      	1	19981103	G	2720	MS21251B6L	TURNBUCKLE      		975240281   	BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) DURING THE INTERIOR INSPECTON OF THE AIRCRAFTS TAIL, A TURNBUCKLE ON THE RUDDER CABLE WAS FOUND CRACKED.  THE CRAC	K RAN THE LENGTH OF THE SLOT THAT THE TURNBUCKLE SAFETY PIN FITS INTO.  THE TURNBUCKLE WAS STILL IN SAFETY AND THE CABLE	 TENSION WAS CORRECT.  TURNBUCKLE WAS REPLACED AND FLEET INSPECTION INITIATED TO INSPECT ALL TURNBUCKLES.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1998122400408	19981224	00408	CE  	1998	12	24	CA981113011      	1	19981103	G	5210	50440014415	DOOR FRAME      			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					PASSENGER DOOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) THE DOOR FRAMES PART NUMBERS SO-440014-415, SO-440020-103, AND SO-440025-173 WERE REPLACED DUE TO EXCESSIVE WEAR. 	 THE WEAR IS CAUSED BY THE DOOR SKIN AS IT MEETS THE FUSELAGE FRAME.  A THIN LAYER OF PRC IS USED TO CUSHION THE DOOR SK	IN TO FRAME CONTACT AREA.  SUBMITTER STATED THIS CONDITION OCCURRED ON ALL EIGHT KING AIR 100/A100 AIRCRAFT IN THE FLEET	.			1	L	7	2 	3T	4	T		A14CE   	E4EA
1998122400409	19981224	00409	NM  	1998	12	24	CA981113012      	1	19981007	G	2710	69667411	BEARING         		65275353    	BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					AILERON	STICKING        	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								653499			(CAN) RECURRING REPORTS OF AILERONS FAIL TO CENTER, FEEL+CENTERING MECHANISM REPLACED.  SUBMITTER STATED FOUND SB 727-27	-0154 CAPT AILERON DISCONNECT ASSEMBLY BEARING IMPROPERLY INSTALLED.  REPAIRED.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1999012200070	19990122	00070	GL  	1999	1	22	CA981113013      	3	19981102	G	6114		HUB             													MCAULY	1C235	1C235LFA    	GL  	INNER HUB	CRACKED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			360  						RD089		(CAN) INSPECTION FOUND A CRACK .75 INCH LONG AND 0.007 INCH DEEP ON THE INNER FLANGE PORTION OF THE HUB BORE.																5	N	P12EA
1998122400410	19981224	00410	NM  	1998	12	24	CA981113014      	1	19981007	G	5320		FITTING         			BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 940	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			56851					653499			(CAN) BS 940 FUSELAGE MAIN FRAME FITTING AT FLOOR BEAM ATTACH FLANGES - RIGHT FITTING LOWER FORWARD FLANGE CRACKED FROM 	EDGE TO FASTENER.  LEFT FITTING CRACKED IN WEB AREA.  REPAIRED.  AD 94-07-08, SB 727-53-0190 REFERS.  PART TC:  53,613.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1998122400418	19981224	00418		1998	12	24	CA981116002      	4	19981029	G	3422	VG203M	GYRO            			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				520  		42123		16227			(CAN) LEFT ADI TOPPLED.						2	L	7	2 	4T	4	T		1A17    	E297
1998122400419	19981224	00419		1998	12	24	CA981116003      	4	19981102	G	3422	VG203M	GYRO            			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				301  		7121258		16227			(CAN) RIGHT HAND ADI GYRO FLAGGING NUMEROUS TIMES.						2	L	7	2 	4T	4	T		1A17    	E297
1998122400420	19981224	00420		1998	12	24	CA981116004      	4	19981109	G	3460	167	WARNING SYSTEM  		1452        	BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						167		PCE81062	300783		(CAN) NO SOUND OUTPUT WITH ACTIVATION OF CABIN WARNING SIGNS.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE
1998122400421	19981224	00421	CE  	1998	12	24	CA981116005      	1	19981001	G	2710		CONTROL CABLE   			CESSNA	421   	421C        	2076016	CE  										AILERON	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) WHEN FLAPS WERE LOWERED, THE AILERON CABLES WERE FOUND FRAYED MIDWAY DOWN.  BOTH LEFT AND RIGHT SIDE.						1	L	7	2 	3O			 	A7CE
1998122400422	19981224	00422	CE  	1998	12	24	CA981116006      	1	19981015	G	2730		CONTROL CABLE   			CESSNA	310   	310         	2074202	CE  										ELEVATOR	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ELEVATOR CABLE FOUND FRAYED DOWN CENTER JUST FORWARD OF THE THE REAR SPAR AT THE PULLEY AND THE ELEVATOR TRIM CABL	E FRAYED DOWN CENTER BEHIND THE REAR SPAR, UNDER MIDDLE SLATS AT THE FAIRLEAD.					1	L	7	2 	3O			RT	3A10
1998122400423	19981224	00423	NM  	1998	12	24	CA981116007      	1	19981004	G	3211	69272951	BOLT            		65727613877 	BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					RT MLG	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				2079 				P689955			(CAN) WHILE REPLACING CLAMPS ON RIGHT MLG, TECH NOTICED DRAIN HOLE ON FORWARD TRUNNION FAIRING BLOCKED.  INVESTIGATION F	OUND RIGHT MLG TRUNNION LINK FUSE BOLT LOCKING SLEEVE, SEAL RING AND GREASE RESERVOIR ADRIFT IN BOTTOM OF FAIRING.  LEFT	 MLG FOUND FUSE BOLT BACKED OFF 50 PERCENT.   REPAIRED.  PART TC:  1,589.				2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1998122400424	19981224	00424		1998	12	24	CA981116008      	1	19981028	G	7500	BACC10DU450	CLAMP           		65222804    						PWA   	JT8   	JT8D17      	52049	NE  					BLEED AIR	LOOSE           	W				D				RETURN TO BLOCK         				M			OVER TEMP                 			TX	TAXI/GRND HDL  	1			CA								P689955			(CAN) AIRCRAFT RETURNED FROM TAXI-OUT DUE NR 1 STRUT OVERHEAT INDICATION.  FOUND LEAK AT 13TH STAGE MODULATING VALVE DOW	N STREAM CLAMP.  CLAMP SECURED.										4	F			E2EA
1998122400426	19981224	00426	NE  	1998	12	24	CA981116010      	2	19981102	G	7250	1338M51P01	BLADE           								GE    	CF6   	CF680C2A5   		NE  					ENGINE TURBINE	DAMAGED         	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA								695393			(CAN) FLIGHT CREW REPORTED POSSIBLE BIRD STRIKE DURING TAKEOFF.  ALL PARAMETERS DURING FLIGHT OK.  DURING BIRD STRIKE, C	HECK FOUND THE FOLLOWING FAN BLADES DAMAGED 32, 33, 34, 35.  DAMAGED BLADES REPLACED AND ENGINE GROUND RUN SERVICEABLE.										4	F			E13NE
1998122400427	19981224	00427	NM  	1998	12	24	CA981116011      	1	19981105	G	2612	894093	FIRE LOOP       			BOEING	737   	7372A9C     	1384495	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					NR 2 ENGINE	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								707346			(CAN) NR 2 ENGINE FIRE WARNING ILLUMINATED DURING CLIMB.  BOTH FIRE BOTTLES WERE DISCHARGED AND THE AIRCRAFT RETURNED TO	 ITS DEPARTURE POINT.  POST-FLIGHT INSPECTION FOUND THE LOWER FIRE LOOP FAULTY, THE PINS AT THE CONNECTORS WERE CORRODED	.  THE FIRE LOOP WAS REPLACED AND THE SYSTEM FUNCTIONED NORMALLY.				2	L	7	2 	4F	4	F		A16WE   	E2EA
1999021200934	19990212	00934	EA  	1999	2	12	CA981116013      	1	19981107	G	2750	860D10018	FECU            			CNDAIR	CL600 	CL6002B19   		EA  										TE FLAPS	FAILED          	W				A				UNSCHED LANDING         				F	J		FLT CONT AFFECTED         	WARNING INDICATION        		CL	CLIMB          	1			CA						538					(CAN) AFTER TAKEOFF, A 'FLAP FAIL' MESSAGE APPEARED.  AIRCRAFT RETURNED.  FLAPS LUBED FECU AND BPSU (P/N 855D100-9)  REP	LACED.					2	L	7	2 	4F			RT	A21EA
1998122400428	19981224	00428	NE  	1998	12	24	CA981123001      	1	19981101	G	2820		LINE            			SKRSKY	S76   	S76C        	8143008	NE  										FUEL SYSTEM	LEAKING         	W				E				ENGINE SHUTDOWN         				K	R		FLUID LOSS                	PARTIAL RPM/PWR LOSS      		AP	APPROACH       	1			CA			90   								(CAN) ON APPROACH, NR 1 LOW FUEL PRESSURE INDICATION FOLLOWED 10 SECONDS LATER BY ENGINE 'OUT' WARNING.  LANDED OK.  AIR	 LEAK IN FUEL FEED CONNECTION AT FUEL SUMP FOOT VALVE ALLOWING AIR TO BE INTRODUCED IN FEEDLINE WHEN FUEL LEVEL BELOW 15	0 POUNDS.  NEW AIRCRAFT ONLY HAS 90 HRS TIME.				1	G	7	2 	3U			NC	H1NE
1999043000086	19990430	00086	CE  	1999	4	30	CA981123003      	1	19981109	G	5320	04118991	STIFFENER       			CESSNA	150   	150H        	2071818	CE  	CONT  	O200  	O200A       	17020	SO  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3965 					44904A			(CAN) INTERGRANULAR CORROSION FOUND ON THE TOP LEFT AND RIGHT SIDES OF THE STIFFENER.  ONE SIDE HAD CRACKS FROM THE EXPA	NSION OF THE MATERIAL.  THIS APPEARS TO BE EXTREMELY FAST ACTING AS NO PROBLEM HAD BEEN NOTED 3 MONTHS PRIOR.  OTHER COR	ROSION ALSO FOUND ON LEFT DOOR FRAME.				1	H	7	1 	3O	3	O		3A19    	E252
1998122400431	19981224	00431	CE  	1998	12	24	CA981123005      	1	19981111	G	3260	1CH25	WIRE            			BEECH 	90    	C90         	1152913	CE  	PWA   	PT6   	PT6A21      	52043	EA  					LT MLG	BROKEN          	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA								PCE24337			(CAN) ON SELECTING LANDING GEAR DOWN, THE LEFT MAIN GEAR FAILED TO INDICATE DOWN AND LOCKED.  GEAR CYCLED SEVERAL TIMES 	WITH NO CHANGE.  A TOWER FLY-BY SHOWED GEAR APPEARED TO BE DOWN AND LOCKED.  SAFE LANDING CARRIED OUT WITH NR 1 ENGINE S	HUTDOWN.  MAINTENANCE CHECK FOUND A BROKEN WIRE ON THE GEAR DOWNLOCK SWITCH.  REPAIRS CARRIED OUT TO WIRE ALONG WITH RET	RACTION TESTS.			1	L	7	2 	3T	4	T		3A20    	E4EA
1998122400432	19981224	00432	EA  	1998	12	24	CA981123006      	1	19981112	G	2435	APC230461121	SHAFT           	LUCAS       	23048004M   	DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					START/GENERATOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				891  		3776					(CAN) DRIVE SHAFT FOUND IN THE STARTER/GENERATOR AT BLOCK 8 IS AN UNAPPROVED PART.  OTHERWISE, THE SHAFT IS SERVICEABLE 	(SUBJECT TO MPI) FOR USE IN OTHER MODELS OF THE 23048 SERIES STARTER/GENERATORS.  THE SHAFT IN QUESTION IS A PMA PART. T	HE MANUFACTURER CONCURS THAT SHAFT P/N APC 23046-1121 IS NOT EQUIVALENT OR APPROVED AS A SHAFT P/N 23046-2153.				1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
1998122400433	19981224	00433	SO  	1998	12	24	CA981123007      	1	19981031	G	3230		TORQUE LINK     			PIPER 	PA31  	PA31350     	7103110	SO  										LT MLG	BROKEN          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA											(CAN) LEFT MAIN GEAR UPPER TORQUE LINK FOUND TO BE BROKEN AT AFT ATTACHMENT.						1	L	7	2 	3O				A20SO
1998122400434	19981224	00434	SO  	1998	12	24	CA981123008      	1	19981110	G	2140	A96090016	HEATER CAN      	JANITROL    	B3500       	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					CABIN	CRACKED         	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			950  			A96090016		L27561A			(CAN) EXHAUST FUMES IN CABIN.  MAINTENANCE CHECK OF FORWARD CABIN HEATER FOUND A 1.5 INCH CRACK AT THE BOTTOM OF THE CAN	 BY THE EXHAUST STACK.  ALSO, CAN WAS BUCKLED AT CRACK AREA.  HEATER REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1999021200935	19990212	00935	EA  	1999	2	12	CA981123009      	1	19981029	G	3244	256K433	TIRE            		50090291    	CNDAIR	CL600 	CL6002B16   	1900305	EA  										RT MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			LD	LANDING        	1			CA			282  			SEPT910403					(CAN) DURING LANDING, THE TIRE TREAD SEPARATED FROM THE NR 3 MAIN AND DAMAGED THE RIGHT MLG WIRING HARNESS.  SUBMITTER I	NDICATES THAT GOODYEAR IS AWARE OF PROBLEM AND ARE ACTIVELY TRYING TO SOLVE.  REF. GOODYEARS B 98-32-001.  PART TC:  168					2	L	7	2 	4F			RT	A21EA
1998122400435	19981224	00435	WP  	1998	12	24	CA981123012      	1	19981112	G	3233	523622	STRUT           	MENASCO     	523500      	CVAC  	340   	340CVAC     	242270A	WP  	ALLSN 	501D  	501D13D     	03004	GL  					NLG	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				2003 		6030		501501			(CAN) NOSE LANDING GEAR CYLINDER FOUND CRACKED IN RETRACT FORK BOSS.  INSPECTION CARRIED OUT IN ACCORDANCE WITH GENERAL 	DYNAMICS SB 640(340D)-32-12A.  REPLACED.					2	L	7	2 	4R	4	T		6A6     	E282
1998122400436	19981224	00436	SO  	1998	12	24	CA981123013      	1	19981110	G	5540	5108400	BALANCE WEIGHT  		5109400     	PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					RUDDER	LOOSE           	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA			12405					PCE51966			(CAN) PILOT REPORTED A SLIGHT VIBRATION FROM THE RUDDER DURING FLIGHT.  MAINTENANCE CHECK FOUND THE RUDDER BALANCE WEIGH	T WAS LOOSE DUE TO A CRACKED RIB AREA WHICH ATTACHES THE ANCHOR NUT AND BOLT OF THE BALANCE WEIGHT.					1	L	7	2 	3T	4	T		A8EA    	E4EA
1998122400437	19981224	00437	CE  	1998	12	24	CA981123016      	1	19981104	G	2435	GQ6642R	BEARING         			CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	STARTER	FAILED          	W				K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			CA									804566		(CAN) STARTER CLUTCH OUTSIDE BEARING BLOWN CAUSING SEAL DAMAGE AND OIL LEAK.						1	L	7	2 	3O				A25CE   		5	C	P45GL
1999021200937	19990212	00937	EA  	1999	2	12	CA981123017      	1	19981101	G	3010		GROUND STRAP    			CNDAIR	CL600 	CL6002B19   		EA  										PICCOLO TUBE	SHORTED         	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT, THE 'WING ANTI-ICE DUCT RT' APPEARED ON SEVERAL OCCASIONS.  INVESTIGATION FOUND THE GROUNDING STRAP	 OF THE PICCOLO TUBE WAS TOUCHING THE HEAT SENSOR.  WIRE REPOSITIONED.					2	L	7	2 	4F			RT	A21EA
1999021200938	19990212	00938	EA  	1999	2	12	CA981123018      	1	19981117	G	3230	750006000	VALVE           			CNDAIR	CL600 	CL6002B19   		EA  										NLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA											(CAN) ON APPROACH CREW SELECTED GEAR DOWN.   NOSE GEAR DID NOT EXTEND.  EMERGENCY PROCEDURE PERFORMED AND NOSE GEAR EXTE	NDED.  VALVE V1GA FOUND FAILED.					2	L	7	2 	4F			RT	A21EA
1998122400438	19981224	00438	SO  	1998	12	24	CA981123019      	1	19981105	G	2721	1651500	ROD             		1619912     	PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					RUDDER TRIM	BROKEN          	W				A				UNSCHED LANDING         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA						273079		RL683348			(CAN) DURING FLIGHT WHILE TRIMMING THE RUDDER, THE PILOT EXPERIENCED A HEAVY SHAKING OF THE AIRCRAFT.  AIRCRAFT LANDED S	AFELY.  MAINTENANCE CHECK FOUND THE FORKED END OF THE AFT TRIM TAB ROD ASSEMBLY WAS BROKEN OFF.					1	L	7	2 	3O	3	O		1A10    	1E4
1998122400439	19981224	00439	SW  	1998	12	24	CA981123021      	1	19981106	G	6321	2040013763	BRAKE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			CR	CRUISE         	1			CA								CPPS60495			(CAN) PILOT REPORTED MAGNETIC BRAKE INOPERATIVE IN THE FORE AND AFT AXIS.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998122400440	19981224	00440		1998	12	24	CA981123022      	4	19981112	G	5301	145122	CABLE           	BREEZE      	140276      	BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL BOOM	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						2789		CAE836045			(CAN) THREE STRANDS OF SLING CABLE BROKEN BELOW UPPER ATTACHMENT SWAGING.						1	G	7	2 	3U	3	U	 	H3EU    	E4CE
1999040200140	19990402	00140	CE  	1999	4	2	CA981123024      	1	19981112	G	5753	052290114	SUPPORT         			CESSNA	150   	150L        	2071826	CE  	CONT  	O200  	O200A       	17020	SO  					RT TE FLAP	FAILED          	W				A	B			UNSCHED LANDING         	EMER. DESCENT           			F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA								20567570A			(CAN) RIGHT FLAP FAILED.   INSP FOUND OUTER SECTION OF INBD FLAP SUPPORT ARM P/N 0522901-14 HAD FAILED 2 INCHES AFT OF F	ORWARD BOLT HOLE.  THE INNER SECTION OF INBD FLAP SUPPORT ARM P/N 0523901-13 HAD FAILED JUST AFT OF BOLT HOLE.  METAL DI	SCOLORED.  CRACK FOUND AROUND BOLT HOLE ON OUTER BRACKET P/N 0523901-14 POSSIBLY CAUSED BY BENDING STRESS WHEN PILOT WAS	 FORCED TO RETRACT FLAPS.  RIVET MISSING FROM T/E OF WING AT INBD FLAP TRACK.  BOTH BRACKETS ATTACHING INBD FLAP TRACK T	O LOWER TRAILING EDGE SKIN WERE DESTROYED WHEN PILOT RETRACTED FLAP TO FULL UP.  SLIGHT BEND IN TRAILING EDGE  OF WING A	T INBD FLAP TRACK.  A LOT OF WEAR ON FLAP ARM CAUSED BY FLAP ROLLER BEARINGS RUBBING AGAINST INSIDE OF FLAP ARMS.	1	H	7	1 	3O	3	O		3A19    	E252
1999043000089	19990430	00089	EA  	1999	4	30	CA981125025      	1	19981110	G	3246	C2UT473	TORQUE TUBE     			DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FLOAT	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								21536			(CAN) TOTAL FAILURE OF WATER RUDDER STEERING.   TORQUE TUBE IN TAIL THAT TRANSMITS STEERING INPUT TO WATER RUDDERS FOUND	 BROKEN 10 INCHES FROM THE BOTTOM OF POST DUE TO SEVERE INTERNAL CORROSION.					1	H	7	1 	3R	3	R		A806    	5E1
1998122400441	19981224	00441	GL  	1998	12	24	CA981125026      	2	19981110	G	7510	6876333	TUBE            								ALLSN 	250C  	250C20B     	03013	GL  					ANTI ICE SYSTEM	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE835808			(CAN) DURING FLIGHT, THE PILOT SELECTED NR 1 ENGINE ANTI-ICE AND THERE WAS NO TEMPERATURE RISE ON THE NR 1 ITT TEMPERATU	RE INDICATOR.  ON RETURN TO BASE, INSPECTION FOUND THE ANTI-ICE TUBE WAS BROKEN JUST AFT OF THE FLARE.  THE ANTI-ICE TUB	E WAS REPLACED AND THE SYSTEM FUNCTIONED NORMALLY.									3	U			E4CE
1999040200149	19990402	00149	EA  	1999	4	2	CA981125027      	1	19980916	G	2435	APC250SG10641	ARMATURE        	LEARSIEGLER 	23048004    	DHAV  	DHC6  	DHC6200     		EA  	PWA   	PT6   	PT6A20      	52043	EA  					START/GENERATOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1255		PCE20421			(CAN) THE WRONG ARMATURE WAS FOUND IN THE STARTER/GENERATOR DURING OVERHAUL.  THE ARMATURE SHOULD HAVE BEEN A 23048-1031	.  THE ARMATURE USED BELONGS TO AN APC 250SG SERIES STARTER/GENERATOR AND IS NOT APPROVED FOR THE LSI LUCAS STARTER/GENE	RATOR.				1	H	7	2 	3T	3	T		A9EA    	E4EA
1998121800487	19981218	00487		1998	12	18	CA981125053      	4	19981105	G	2300	18071	COVER           			CESSNA	172   	172P        	2072436	CE  						MCAULY	1C160	1C160DTM    	GL  	NOISE FILTER	MISSING         	W				A				UNSCHED LANDING         				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA									BL042		(CAN) AIRCRAFT HAS AN RFI 70 FIRE WALL MOUNTED RADIO NOISE FILTER.  THE COVER OVER THE TERMINALS WAS MISSING.  CAR WARME	R MOUNTED ON AFT LEFT SIDE OF ENGINE MOUNT, THE CORD WAS ROUTED UP TO OIL FILLER DOOR ON TOP OF RIGHT SIDE.  THE TYE WRA	P BROKE ON THE PLUG IN CORD AND CORD WAS NOW ABLE TO GO TO FIREWALL.  PLUG MADE CONTACT WITH TERMINALS OF NOISE FILTER C	AUSING A FLUCTUATION ON VOLT GAUGE AND PILOT COULD SMELL SOMETHING.			1	H	7	1 	3O			NT	3A12    		5	N	P910
1998122400449	19981224	00449		1998	12	24	CA981125054      	1	19981125	G	2121	K271B200HG	BEARING         	DYNAMICAIR  	C175R3A1    															BLOWER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				50   		119					(CAN) BEARING FAILURE CAUSED DAMAGE TO THE ARMATURE AND END BELL OF THE BLOWER.
1998121800488	19981218	00488	SO  	1998	12	18	CA981125055      	2	19981113	G	8500		ENGINE          			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	D3A34	D3A34C403   	GL  	ENGINE BAY	FAILED          	W				A				UNSCHED LANDING         				E	Y	J	VIBRATION/BUFFET          	ENGINE STOPPAGE           	WARNING INDICATION        	CL	CLIMB          	1			CA				103  				814845P	951559		(CAN) AIRCRAFT PRE-HEATED FOR 4 HRS PRIOR TO START DUE TO -19 CELSIUS OVERNIGHT TEMP.  100 LL FUEL WAS OBTAINED FROM SEA	LED DRUMS.  ENG RUN-UP WAS GOOD.  TAKEOFF WAS GOOD WITH ENG PRODUCING FULL POWER AND RPM.  ALL ENG PARAMETERS WERE NORMA	L.  ACFT CLIMBED TO 600 FEET AND PILOT REDUCED POWER.  ABOUT 10 SECONDS LATER, PILOT HEARD A KNOCKING SOUND AND ELECTED 	TO RETURN TO DEPARTURE POINT.  A LOUD BANG WAS HEARD AND ENG STOPPED ABRUPTLY.  A SUCCESSFUL FORCED LDG, ON ICE, WAS CAR	RIED OUT.  ACFT SECURED.  IT WAS NOTED THAT TOP AND BOTTOM OF RT SIDE OF ENG COWLING WAS DENTED FROM INSIDE.  THERE WAS 	OIL DRIPPING FROM COWLING.  AS PILOT AND PASSENGERS HAD TO WALK 5 MILES BEFORE DARKNESS, NO FURTHER INSP WAS MADE.	1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P47GL
1998122400451	19981224	00451	CE  	1998	12	24	CA981125058      	1	19981021	G	5510	07321014	SUPPORT         		07326004    	CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	HORIZ STABILIZER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								477977K	901861		(CAN) HORIZONTAL STABILIZER RIGHT REAR HINGE REINFORCEMENT BOX FOUND CRACKED FROM EDGE TO BOLT HOLE.						1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P3EA
1999012200297	19990122	00297	CE  	1999	1	22	CA981125059      	1	19981021	G	5320	07122071	ANGLE           		07912005    	CESSNA	180   	180         	2072602	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C203    	GL  	BS 172-230	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7218 					477977K	901861		(CAN) THE LEFT FUSELAGE TAIL CONE REINFORCEMENT ANGLE WAS FOUND CRACKED AT THE STABILIZER REAR HINGE ATTACH HOLE. THIS A	NGLE RUNS APPROXIMATELY FROM STA 172 TO STA 230.  NEW ANGLE P/N 0712048-7 INSTALLED.					1	H	7	1 	3O	3	O	NC	5A6     	E273	5	C	P3EA
1999011500362	19990115	00362	SO  	1999	1	15	CA981125060      	1	19981104	G	3230	402377	BOLT            		4550403     	PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA			744  								(CAN) PILOT REPORTED VIBRATION AND WHEEL SHIMMY ON LANDING.  MAINTENANCE CHECK FOUNDTHE RIGHT MAIN LANDING GEAR LOWER TO	RQUE LINK BOLT WAS BROKEN.  LOWER TORQUE LINK AND BOLT REPLACED.					1	L	7	2 	3O				A20SO
1999011500363	19990115	00363	SO  	1999	1	15	CA981125061      	1	19981117	G	2730	710563D	SPRING          			PIPER 	PA31  	PA31350     	7103110	SO  										ELEVATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			302  								(CAN) NEW ELEVATOR DOWN SPRING INSTALLED IN ACCORDANCE WITH PIPER SB SB/1002.  SEVERAL MONTHS LATER ON A PRE-FLIGHT CHEC	K, IT WAS FOUND THERE WAS NO PRESSURE ON THE ELEVATOR.  FURTHER INSPECTION REVEALED A BROKEN ELEVATOR SPRING APPROXIMATE	LY .75  OF AN INCH FROM THE END.  NEW SPRING INSTALLED.				1	L	7	2 	3O				A20SO
1999011500364	19990115	00364	CE  	1999	1	15	CA981125063      	1	19981001	G	5520	115610010257	WEIGHT          		115610010338	BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  					ELEVATOR	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						9198SP5		PCE40209			(CAN) ELEVATOR WAS REMOVED FOR INSPECTION PER SB 2145 AND THE BALANCE WEIGHT WAS FOUND TO BE LOOSE.						1	L	7	2 	3T	4	T		A14CE   	E4EA
1999011500365	19990115	00365	CE  	1999	1	15	CA981125065      	1	19981023	G	3260		SWITCH          			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A28      		EA  					MLG	STUCK           	W				C				ABORTED TAKEOFF         				N			FALSE WARNING             			TO	TAKEOFF        	1			CA								PCE40813			(CAN) AIRCRAFT TAKEOFF ABORTED AT ROTATIONAL SPEED DUE TO GEAR SAFETY HOOK FLICKERING AND HORN SOUNDING.  UPON RETURN TO	 RAMP, IT WAS NOTED THE ELEVATOR STAB WAS OUT OF TRIM FOR TAKEOFF AND THE HORN STOPPED SOUNDING AS SOON AS THE POWER LEV	ERS WERE RETARDED.  PILOT CONFIRMED HE HAD THREE GREEN LIGHTS ON GEAR THE FULL TIME.  AT ROTATIONAL SPEED, THE SQUAT SWI	TCH WOULD HAVE BEEN AT ITS THRESHOLD FOR BEING MADE AND IT WOULD HAVE GONE AWAY ON SWITCH DISCONNECT.  PROBLEM ATTRIBUTE	D TO MOMENTARY STICKING OF SWITCH DURING ROLL-OUT.  SWITCH CLEANED AND SYSTEM CHECKED SERVICEABLE.		1	L	7	2 	3T	4	T		A14CE   	E4EA
1999011500366	19990115	00366	CE  	1999	1	15	CA981125066      	1	19981023	G	2720	115524067	SPRING          			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE41562			(CAN) RUDDER SPRING FOUND CRACKED ON INNER CIRCUMFERENCE.  CRACK FOLLOWED LENGTH  OF SPRING AND NOT ACROSS.						1	L	7	2 	3T	4	T		A14CE   	E4EA
1999011500367	19990115	00367	CE  	1999	1	15	CA981125070      	1	19981104	G	5540	1006000121	BELLCRANK       			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					RUDDER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCE41483			(CAN) WHEN THE RUDDER BELLCRANK ASSEMBLY WAS REMOVED FOR INSPECTION, IT WAS NOTICED THERE WAS A DEEP PITTING AROUND THE 	ATTACHMENT BOLT HOLE.  THE CORROSION RADIATED OUT FROM THE HOLE TWO INCHES.  THIS LOCATION IS UNDER THE RUDDER TORQUE TU	BE ATTACHMENT FITTING AND IS IMPOSSIBLE TO INSPECT WITH THE RUDDER ASSEMBLY INSTALLED.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1999011500368	19990115	00368	CE  	1999	1	15	CA981125071      	1	19981110	G	3411	AN9296D	CAP             			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  					PITOT SYSTEM	MISSING         	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								PCE50747			(CAN) AIRCRAFT RETURNED TO BASE AFTER LOW AIR SPEED INDICATION.  THE CAP ON PITOT STATIC DRAIN WAS FOUND MISSING.  NEW C	AP INSTALLED AND PITOT STATIC TESTS CARRIED OUT, SERVICEABLE.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1999011500369	19990115	00369	CE  	1999	1	15	CA981125074      	1	19981118	G	3250	99820027	BOLT            			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A28      		EA  					NLG STEERING	LOOSE           	W				O				OTHER                   				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				2251 				51808			(CAN) NOSE WHEEL STEERING ERRATIC DURING TAXI. AIRCRAFT RETURNED TO RAMP.  MAINTENANCE FOUND NOSE STEERING STRADDLE BOLT	S LOOSE AND WORN.  BOLTS REPLACED.  PART TC:  4,176.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1999011500370	19990115	00370	CE  	1999	1	15	CA981125076      	1	19981118	G	2421		WIRE            			BEECH 	99    	B99         	1154004	CE  	PWA   	PT6   	PT6A27      	52043	EA  					LT GENERATOR	BROKEN          	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CL	CLIMB          	1			CA								PCE51811			(CAN) AIRCRAFT RETURNED TO BASE, UNABLE TO BRING GENERATOR ON-LINE.  MAINTENANCE FOUND BROKEN WIRE ON LEFT GENERATOR FAU	LT RELAY.  WIRING REPAIRED AND CHECKED SERVICEABLE.					1	L	7	2 	3T	4	T	 	A14CE   	E4EA
1999011500371	19990115	00371	CE  	1999	1	15	CA981125078      	1	19980918	G	2750	1005240741	MOTOR           			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					TE FLAP	SEPARATED       	W				K				NONE                    				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA								PCE32053			(CAN) AFTER LANDING, FLAPS SELECTED FROM 17 DEGREES TO ZERO DEGREES.  THE FLAPS DID NOT RESPOND.  MAINTENANCE FOUND THAT	 THE TRANSMISSION/MOTOR ASSEMBLY HAD INTERNALLY SEPARATED AND THE ASYMMETRY SWITCH LOCKED OUT FURTHER MOVEMENT.  THE TRA	NSMISSION/MOTOR WAS REPLACED.  WHEN THE MANUAL OVERRIDE WAS SELECTED THE OUTER FLAPS RETURNED TO FULL UP AND THE INNER P	ANELS STAYED DEPLOYED AT 17 DEGREES.			2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1999011500372	19990115	00372	CE  	1999	1	15	CA981125079      	1	19980918	G	3233	11438004113	ACTUATOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT MLG	MALFUNCTIONED   	W				O				OTHER                   				J			WARNING INDICATION        			AP	APPROACH       	1			CA			673  					PCEPSO197			(CAN) DURING APPROACH, THE GEAR WAS SELECTED DOWN BUT THE RIGHT MAIN WAS VERY SLOW TO GREEN UP.  MAINTENANCE HAD PREVIOU	SLY REPLACED LEFT ACTUATOR FOR THE SAME PROBLEM.  HOWEVER, THE PROBLEM TRANSFERRED TO THE RIGHT SIDE.  RIGHT ACTUATOR TO	 BE REPLACED AS A PRECAUTIONARY MEASURE.  PART TC:  788.				2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999011500373	19990115	00373	EA  	1999	1	15	CA981125081      	2	19981013	G	7314	025323300	MOUNT           			STBROS	SD3   	SD330       	8100602	EU  	PWA   	PT6   	PT6A45R     	52043	EA  					FUEL PUMP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				5562 				PCE84095			(CAN) DURING INSPECTION IT WAS FOUND THAT THE FUEL PUMP MOUNTING FLANGE WAS CRACKED.  THE FUEL PUMP WAS REPLACED.						2	H	7	2 	4T	4	T		A41EU   	E4EA
1999012900937	19990129	00937	EU  	1999	1	29	CA981125082      	1	19981119	G	3010		OUTLET          			STBROS	SD3   	SD330       	8100602	EU  	PWA   	PT6   	PT6A45R     	52043	EA  					WING DEICE	PLUGGED         	W				A				UNSCHED LANDING         				W			INADEQUATE Q C            			CL	CLIMB          	1			CA								PCE84241			(CAN) ON FIRST FLIGHT AFTER INSPECTION, DEICE BOOTS SELECTED ON AND WING DE-ICE BOOTS REMAINED INFLATED.  DUE TO ICING C	ONDITIONS AIRCRAFT RETURNED TO MAINTENANCE BASE.  WING DE-ICE BOOTS OUTLET VENTS WERE FOUND PLUGGED WITH TAPE FROM MAINT	ENANCE TASK THE PREVIOUS NIGHT.				2	H	7	2 	4T	4	T		A41EU   	E4EA
1999040200150	19990402	00150	EA  	1999	4	2	CA981125083      	1	19980713	G	5310	C2FS3281A	STRUT           			DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  					FUSELAGE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11134					42113357			(CAN) WHILE CHANGING PILOT'S WINDSCREEN, THE FAIRING HOLDING WINDSCREEN WAS REMOVED.   CORROSION WAS THEN NOTICED ON BOT	H THE RIGHT AND LEFT FUSELAGE STRUT ASSEMBLIES.  OTHER P/N C2FS328A.					1	H	7	1 	3R	3	R		A806    	5E1
1999021200941	19990212	00941	SO  	1999	2	12	CA981125084      	1	19981001	G	2752	MS3440	CONNECTOR       		3203001011  	EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	ACTUATOR	CORRODED        	W				B				EMER. DESCENT           				F			FLT CONT AFFECTED         			DE	DESCENT        	1			CA			9169 			1170		115667	880529		(CAN) WHILE ON DESCENT WITH FLAPS AT 15 DEGREES, THE FLAP WARNING LIGHT CAME ON WITH A NOTICEABLE ROLL TENDENCY.  EMERGE	NCY DECLARED AND LANDING OK.  INSPECTION FOUND CORROSION ON THE RIGHT HAND, OUTBOARD FLAP ACTUATOR AND HARNESS.  ALSO, C	ONNECTOR P/N MS3476..  PART TC:  7,938.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1999012900938	19990129	00938	SO  	1999	1	29	CA981125085      	1	19981102	G	2752	12023217002	LOCKWIRE        		3203001011  	EMB   	120   	EMB120RT    		SO  	PWA   	118   	PW118       		NE  	HAMSTD	14RF	14RF9       	NE  	ACTUATOR	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			11338			1170		115667	880529		(CAN) DURING REMOVAL OF FLAP ACTUATOR FOR INVESTIGATION, WEAR FOUND ON INSIDE OF RIGHT HAND OUTBOARD FLAP ACTUATOR HOUSI	NG WHICH PROTRUDES INSIDE WING TANK, CAUSED BY LOCKWIRE ON FLAP ACTUATOR CLAMP.  WALL THICKNESS OF HOUSING IS 0.050 INCH	 AND THE LOCKWIRE CHAFED THROUGH 0.040 INCH.  IMPROPERLY INSTALLED LOCKWIRE CAUSED PROBLEM.  PART TC:  9,719.				2	L	7	2 	4T	4	T	RT	A31SO   	E20NE	6	C	P11NE
1999043000090	19990430	00090	NM  	1999	4	30	CA981130001      	1	19981118	G	3010	153212A	DIST VALVE      	BENDIX      		DHAV  	DHC8  	DHC8*       		NM  										ANTI ICE SYS	PLUGGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						RF3895					(CAN) DE-ICE DISTRIBUTION VALVE DRAIN HOLE PLUGGED WITH POTTING COMPOUND LEADING TO MOISTURE ACCUMULATION AND CAUSING DA	MAGE TO SEALING SURFACES LEADING TO MALFUNCTION.					2	H	7	2 	4T			RT	A13NM
1999021200161	19990212	00161	NM  	1999	2	12	CA981130002      	1	19981118	G	3010	153212A	VALVE           	BENDIX      		DHAV  	DHC8  	DHC8*       		NM  										ANTI ICE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						RF3890					(CAN) DRAIN HOLE PLUGGED WITH POTTING COMPOUND ALLOWING MOISTURE TO ACCUMULATE CAUSING MALFUNCTION.						2	H	7	2 	4T			RT	A13NM
1999011500375	19990115	00375	EU  	1999	1	15	CA981130003      	1	19980817	G	2435	36B510500P1	SHAFT           			AMD   	FALC20	FALCON20D5  	2730003	EU  	GE    	CF700 	CF7002D2    	30010	NE  					STARTER/GEN	SHEARED         	W				O				OTHER                   				O			OTHER                     			IN	INSP/MAINT     	1			CA			3320 	339  				304237B			(CAN) NR 2 ENGINE FAILED TO START.  INVESTIGATION FOUND THE NR 2 STARTER/GENERATOR INTERNAL SHAFT SHEARED.  UNIT WAS REP	LACED AND THE AIRCRAFT RETURNED TO SERVICE.  THE SUBMITTER STATES THAT THIS IS THE THIRD FAILURE OF THIS NATURE IN THE L	AST THREE MONTHS.  AS A RESULT, THE COMPANY HAS IMPLEMENTED A POLICY OF AN NDT INSPECTION AT EACH STARTER/GENERATOR OVER	HAUL.			2	L	7	2 	4F	4	F	RT	A7EU    	E7EA
1999012200310	19990122	00310	CE  	1999	1	22	CA981130018      	1	19981118	G	2435	23078019	GENERATOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					START/GENERATOR	SEIZED          	W				H				DEACTIVATE SYST/CIRCUITS				O			OTHER                     			CR	CRUISE         	1			CA			4019 	1173 		96102		GGMPS0025			(CAN) DURING FLIGHT, LEFT GENERATOR CAME OFF-LINE, SEVERAL ATTEMPTS TO RESET WERE UNSUCCESSFUL.  THE GENERATOR CONTROL U	NIT WAS CHANGED TO FACILITATE FURTHER TROUBLESHOOTING.  ON STARTING LEFT ENGINE, IT WAS NOTICED THERE WAS NO STARTER ROT	ATION AND AN UNUSUALLY HIGH DISCHARGE RATE ON THE LOADMETER. THE LEFT GENERATOR WAS FOUND SEIZED DUE TO INTERNAL FAILURE	.  FAILED GENERATOR REPLACED.  PART TC:  4,606.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999012200311	19990122	00311	SO  	1999	1	22	CA981130019      	1	19981110	G	8120	LW10119	SUPPORT         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					TURBOCHARGER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				292  				L161761			(CAN) ENGINE RECEIVED FROM OVERHAUL ON EXCHANGE.  INSPECTION FOUND THE BOLT HOLDING THE TOP TURBO ROD TO THE ENGINE BENT	.  THE BOLT WAS BENT DUE TO IT BEING FORCED TO MOUNT A SUPPORT PLATE WITH INCORRECT DIMENSIONS.  THE FORCING OF THE SUPP	ORT PLATE LED TO ITS CRACKING.  THIS LED TO AN OIL LEAK CAUSED BY UNDUE STRAIN ON THE TURBO INSTALLATION.  A NEW PLATE W	AS INSTALLED AND IT WAS REPORTED THAT EVRYTHING FELL INTO PLACE.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1999012200312	19990122	00312	EA  	1999	1	22	CA981130020      	2	19981111	G	7322	17500111	SHROUD          			CESSNA	172   	172L        	2072432	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160CTM    	GL  	CARBURETOR HEAT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4548 					L4428827A	710547		(CAN) CARBURETOR HEAT SHROUD FOUND SLIPPED DOWN ON EXHAUST STACK.  PART OF UPPER CLAMP P/N AN7377W56 WAS MISSING.  SHROU	D CRACKED IN FOUR PLACES.  SCREEN IN SHROUD PARTLY BURNED, LOOSE OR DISINTEGRATING.					1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1999012200313	19990122	00313	CE  	1999	1	22	CA981130021      	1	19981111	G	7603	986305320	POWER LEVER     			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	COCKPIT	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			6874 					L1864115	P773466		(CAN) NO FRICTION LOCK ON THROTTLE.  WHEN THROTTLE REMOVED, IT WAS FOUND TO BE IMPROPERLY SECURED TO CARBURETOR ARM.  TH	E BOLT WAS TOO LONG JAMMING CARBURETOR HOUSING.  SUBMITTER STATED  IMPROPER NUT USED AND NO COTTER PIN.  SPECIAL CLAMP F	OUND INSTALLED IN REVERSE.  AD 86-24-07 AND SIL SE79-6 ARE RELEVANT.				1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
1999012200314	19990122	00314	EA  	1999	1	22	CA981130022      	2	19981111	G	7322	S12309	CONTROL UNIT    			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235L2C     	41505	EA  	MCAULY	1A103	1A103TCM    	GL  	CARBURETOR HEAT	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6874 					L1864115	P773466		(CAN) CARBURETOR HEAT CONTROL WIRE FOUND WORN AT THE OUTLET OF CASING NEAR THE CARBURETOR BOX ARM.  THIS ONLY DETECTED W	ITH CARBURETOR HEAT FULLY OPENED.					1	H	7	1 	3O	3	O	NT	3A19    	E223	5	N	P50GL
1999012200315	19990122	00315	CE  	1999	1	22	CA981130023      	1	19981111	G	3242	1640400	DISC            			CESSNA	150   	152         	2071835	CE  						MCAULY	1A103	1A103TCM    	GL  	LT BRAKE	MISDRILLED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA			6874 						P773466		(CAN) BRAKE DISC FOUND WORN.  SUBMITTER STATED PART DRILLED TO RECEIVE A .3125 INCH BOLT, BUT NORMAL BOLT IS .25 INCH.						1	H	7	1 	3O			NT	3A19    		5	N	P50GL
1999012200316	19990122	00316	SW  	1999	1	22	CA981130024      	1	19981119	G	5302	206031314037	CHANNEL         		206031314119	BELL  	206   	206L4       	1182110	SW  										TAIL BOOM	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2185 								(CAN) CRACK FOUND ON THE LEFT CHANNEL OF THE SPAR AT THE SUPPORT FOR ONE OF THE ATTACHMENTS FOR THE TAIL BEAM.  PART TC:	  2,747.					1	G	7	1 	3U			NC	H2SW
1999012200317	19990122	00317	NE  	1999	1	22	CA981130025      	2	19981117	G	7250	311360201	BLADE           			DHAV  	DHC8  	DHC8*       		NM  	PWA   	120   	PW120A      		NE  					TURBINE SECTION	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			25386	20606				120179			(CAN) THE OPERATOR REPORTED HIGH ITT WITH SMOKE IN CABIN.  ENGINE SENT FOR INVESTIGATION AND REPAIR.  DISASSY FOUND ENG 	HAD SUFFERED EXTENSIVE DAMAGE FROM LP TURBINE STATOR ASSY REARWARDS AS A RESULT OF COINCIDENTAL FAILURES OF ONE OR MORE 	LP TURBINE BLADES.  SUBMITTER STATED IT IS NOT CLEAR WHETHER THIS WAS A PRIMARY FAILURE OF LP BLADES OR A BLADE FAILURE 	RESULTING FROM IMPACT DAMAGE FROM DEBRIS ARISING FROM A BURNT HP VANE OR A BURNT LP STATOR ASSY.  SECONDARY DAMAGE WAS S	UBSTANTIAL WITH NR 6 AND NR 7 BEARING HOUSING SEPARATED INTO 3 DISCRETE PARTS.  PART TC:  35,083.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999040200153	19990402	00153	SO  	1999	4	2	CA981202001      	1	19981120	G	5751	62373000	DOUBLER         		681292      	PIPER 	PA28  	PA28180     	7102808	SO  	LYC   	O360  	O360A4A     	41514	EA  					AILERON	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3185 			4916		L2002636A			(CAN) AILERON DOUBLER FOUND CRACKED AT THE OUTER END ON THE UPPER RADIUS CORNER.  THIS DOUBLER SUPPORTS THE MASS BALANCE	.  A TWISTING OF THE DOUBLER HAPPENS IN ROUGH AIR OR WITH HEAVY FLIGHT LOADS.  IN ADDITION, THE SUBMITTER SUGGESTS THAT 	THE CONTROL LOCK LOCATION MAY ENCOURAGE DOUBLER CYCLING IN WINDY CONDITIONS.				1	L	7	1 	3O	3	O		2A13    	E286
1999043000092	19990430	00092	EA  	1999	4	30	CA981202002      	1	19981125	G	5520	C6TEM10132729	BRACKET         		C6TEM102829 	DHAV  	DHC6  	DHC6200     		EA  	PWA   	PT6   	PT6A20      	52043	EA  					ELEVATOR	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20000			198					(CAN) ELEVATOR HINGE BRACKETS FOUND WITH EXFOLIATION CORROSION.  LESS THAN HALF OF THE MATERIAL REMAINING.						1	H	7	2 	3T	3	T		A9EA    	E4EA
1999040200154	19990402	00154	EA  	1999	4	2	CA981202003      	1	19981125	G	5511	C6TP10151	RIB             			DHAV  	DHC6  	DHC6100     		EA  	PWA   	PT6   	PT6A20      	52043	EA  					HORIZONTAL STAB	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			20000			86		PCE21096			(CAN) HEAVY CORROSION FOUND ON THE HORIZONTAL STABILIZER CENTER RIB.  SPOT WELDS WERE DELAMINATED THREE-QUARTERS OF THE 	LENGTH OF THE PART.					1	H	7	2 	3T	3	T		A9EA    	E4EA
1999012900214	19990129	00214	EA  	1999	1	29	CA981202004      	2	19980709	G	7322	MA4SPA	NOZZLE          	FACET       		CESSNA	172   	172M        	2072418	CE  	LYC   	O320  	O320E2D     	41508	EA  	MCAULY	1C160	1C160DTM    	GL  	CARBURETOR	SEPARATED       	W				E				ENGINE SHUTDOWN         				O			OTHER                     			CR	CRUISE         	1			CA						BL209931		40552127A	KD028		(CAN) ENGINE POWER COULD NOT BE REDUCED BELOW 2300 RPM, THE THROTTLE APPEARED TO BE STUCK.  ON THE ADVISE OF THE TOWER A	ND GROUND STAFF, THE PILOT SET UP AN APPROACH AND ONCE LANDING WAS ASSURED THE ENGINE WAS SHUT OFF BY SETTING THE MIXTUR	E TO IDLE CUTOFF. THIS WAS EXECUTED AND AN UNEVENTFUL LANDING WAS CARRIED OUT.  POST-FLIGHT INSPECTION FOUND THE CARBURE	TTOR ACCELERATOR PUMP DISCHARGE NOZZLE HAD SEPARATED FROM THE PUMP AND JAMMED THE BUTTERFLY VALVE CAUSING LOSS OF THROTT	LE CONTROL.		1	H	7	1 	3O	3	O	NT	3A12    	E274	5	N	P910
1999040200155	19990402	00155	CE  	1999	4	2	CA981202005      	1	19981117	G	3240	65171082	COUPLING        		65171024    	CESSNA	500   	560CESSNA   	2076750	CE  										BRAKE PUMP	FAILED          	W				E				ENGINE SHUTDOWN         				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			600  								(CAN) ON STARTING SECOND ENGINE, THE PILOT NOTICED THAT THE BRAKE PUMP MOTOR NOISE SOUNDED DIFFERENT THAN NORMAL.  WHEN 	ENGINE STARTED, PILOT RELEASED BRAKES TO TAXI AND RECEIVED A 'POWER BRAKE LOW PRESSURE LIGHT'.  ENGINES SHUT DOWN.  THE 	BRAKE PUMP MOTOR RAN CONTINUOUSLY, BUT DID NOT MAKE ANY PRESSURE.  FURTHER INVESTIGATION SHOWED THAT THE COUPLING HAD FA	ILIED.			2	L	7	2 	4F			RT	A22CE
1999040200156	19990402	00156	SO  	1999	4	2	CA981202006      	1	19981124	G	2140	B07D67	BLOWER          	JANITROL    	B4050       	PIPER 	PA31  	PA31350     	7103110	SO  										HEATER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2500 								(CAN) HEATER QUIT DURING IN-FLIGHT INSPECTION.  THE COMBUSTION BLOWER WAS FOUND TURNING, BUT NOT BLOWING.  ALL BLADES FR	OM SQUIRREL CAGE WERE MISSING.					1	L	7	2 	3O				A20SO
1999040200157	19990402	00157	SO  	1999	4	2	CA981202007      	1	19981119	G	3233	OAS51071	ACTUATOR        			PIPER 	PA31T 	PA31T       	7103124	SO  	PWA   	PT6   	PT6A28      		EA  					RT MLG	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						309		PCE50170			(CAN) RIGHT MAIN GEAR ACTUATOR BROKEN AT THE ATTACH AND PIVOT BOLT HOLE.  AREA DIFFICULT TO INSPECT WITH ACTUATOR INSTAL	LED.					1	L	7	2 	3T	4	T		A8EA    	E4EA
1999040200158	19990402	00158	CE  	1999	4	2	CA981202008      	1	19981120	G	3246	16204500	WHEEL           	PARKERHANFIN	40750       	CESSNA	207   	207A        	2073604	CE  										MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) 3 INCH CRACK FOUND ON THE OUTER WHEEL HALF FLANGE AND INNER RADIUS WHERE THE TIRE BEAD SEATS.						1	H	7	1 	3O				A16CE
1999040200159	19990402	00159	CE  	1999	4	2	CA981202009      	1	19981119	G	3231	08411063	LINK            			CESSNA	310   	310R        	2074245	CE  	CONT  	O520  	IO520M      	17032	SO  	MCAULY	3AF32C	3AF32C87    	GL  	MLG DOOR	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								560819	808431		(CAN) PILOT REPORTED THE GEAR DOOR WAS HANGING DOWN.  THE RETRACT LINK THAT LETS THE DOOR FOLLOW THE GEAR WAS FOUND SEVE	RED.					1	L	7	2 	3O	3	O		3A10    	E5CE	5	C	P22EA
1999012900215	19990129	00215	EU  	1999	1	29	CA981202010      	1	19981120	G	2611	CG7PD1	SMOKE DETECTOR  			AIRBUS	300   	A300B4203   	3930306	EU  										CARGO BAY	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) SMOKE WARNING INDICATION FROM MAIN CARGO DECK AREA.  AIR TURN BACK.  ISOLATED DEFECTIVE SMOKE DETECTOR.  AIRCRAFT 	RETURNED TO SERVICE PER MEL.  DEFECTIVE DETECTOR TO BE REPLACED.					2	L	7	2 	4F				A35EU
1999040200160	19990402	00160	CE  	1999	4	2	CA981202011      	1	19981021	G	3233	12416079	SUPPORT         		22110141    	CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C214   	GL  	MLG ACTUATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5431 			R18200806			922542		(CAN) WHEN LEFT ACTUATOR REMOVED TO ALLOW MOUNT BOLT REPLACEMENT, A CRACK WAS FOUND ON THE FORWARD INBOARD SIDE OF THE B	EARING SHOULDER WHERE THE PIVOT OF THE LANDING LEG RESTS.					1	H	7	1 	3O			RT	3A13    		5	C	P7EA
1999012900939	19990129	00939	EU  	1999	1	29	CA981202012      	1	19981101	G	2500	AS2224	CONTROL         			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					CARGO RELEASE	MISLOCATED      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA								4418			(CAN) WITH COLLECTIVE DOWN AND LOCKED, NOT ABLE TO FULLY ACTUATE THE EMERGENCY FUEL CUT-OFF LEVER.   THIS DUE TO INTERFE	RENCE BETWEEN THE EMERGENCY FUEL CUT-OFF LEVER AND THE MANUAL CARGO RELEASE LEVER LOCATED ON THE COLLECTIVE.  BOTH AIRCR	AFT IN FLEET WERE AFFECTED.  PROBLEM EASILY CORRECTED BY RE-POSITIONING THE CARGO RELEASE LEVER ON COLLECTIVE.				1	G	7	1 	3U	3	U		H9EU    	E19EU
1999040200161	19990402	00161	CE  	1999	4	2	CA981202013      	1	19981104	G	3233	12810193	ACTUATOR        		98820152    	CESSNA	182   	R182        	2072734	CE  						MCAULY	2D34C	B2D34C214   	GL  	LT MLG	CORRODED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA			1891 			1472			7810425		(CAN) HYDRAULIC FLUID NOTED ON THE LEFT ACTUATOR DURING RETRACTION TEST.  TWO CORRODED POINTS FOUND AND THE METAL WAS DE	LAMINATED AT THESE POINTS.  THE HOLE WHICH DEVELOPED AND THAT ALLOWED THE FLUID TO LEAK COULD ONLY BE SEEN WITH A MAGNIF	YING GLASS, AT MAXIMUM PRESSURE AND WHEELS DOWN AND LOCKED.				1	H	7	1 	3O			RT	3A13    		5	C	P7EA
1999012900216	19990129	00216	SO  	1999	1	29	CA981202014      	1	19981124	G	5510	1001	VORTEX GEN      			PIPER 	PA31  	PA31350     	7103110	SO  										HORIZ STABILIZER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11384								(CAN) FOUR VORTEX GENERATORS MISSING OR BENT FROM AIRCRAFT.  AIRCRAFT MUST THEN BE OPERATED AT LOWER GROSS WEIGHT.						1	L	7	2 	3O				A20SO
1999012900217	19990129	00217	EA  	1999	1	29	CA981202015      	2	19981125	G	7414	103493101R	MAGNETO         		CS6LN1209   	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					NR 2 ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1698 		8138005		L286061A			(CAN) PILOT REPORTED NR 2 ENGINE HARD TO START.  SPARK PLUGS WERE REPLACED AND MAINTENANCE FOUND ALL MAGNETO SWITCHES IN	 THE ON POSITION, MAGS WERE TURNED OFF.  IT IS ASSUMED THE SHUT-DOWN PROCEDURES WERE CUT SHORT.  AIR CREWS WERE CAUTIONE	D ON DANGER OF LEAVING THE MAGNETOS LIVE.  ENGINE WAS STARTED FOR ENGINE FUNCTIONAL CHECK AND WHEN THE LEFT MAG WAS SELE	CTED, THE ENGINE STOPPED.  THE LEFT MAG WAS REPLACED, THE ENGINE RAN-UP SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SER	VICE.		1	L	7	2 	3O	3	O		A20SO   	E14EA
1999012900218	19990129	00218	NE  	1999	1	29	CA981202016      	2	19981123	G	7261	MS920829	BOLT            								PWA   	PW120 	PW123       		NE  					ENG OIL PUMP	WRONG PART      	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			529  					109071			(CAN) METAL PARTICLES IN THE OIL SUMP FILTER LED TO INSPECTION OF THE OIL PUMP. THE FOUR MOUNTING BOLTS OF THE ENGINE OI	L PUMP WERE FOUND TO BE TOO LONG.  P/N MS9208-29 BOLTS HAD BEEN USED, THE PROPER BOLTS WERE P/N MS9208-26.  THE PROPER B	OLTS WERE INSTALLED AND THE WORN CASING ON THE SUMP PUMP WAS ALSO REPLACED.									4	T			E20NE
1999012900940	19990129	00940	EA  	1999	1	29	CA981202017      	2	19981022	G	7414	92050179	WOODRUFF KEY    	SLICK       	4371        	CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					LT MAGNETO	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1231 		92050179		L1088539A			(CAN) THE WOODRUFF KEY FOUND WORN CAUSING A TIMING PROBLEM WITH THE LEFT MAGNETO.						1	H	7	1 	3O	3	O	NT	3A12    	E274
1999012900941	19990129	00941	CE  	1999	1	29	CA981202018      	1	19981123	G	2435	23048018	BRUSHES         			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A27      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	START/GENERATOR	WORN            	W				E				ENGINE SHUTDOWN         				A	B		FLAME/FIRE                	SMOKE/FUMES/ODORS/SPARKS  		CR	CRUISE         	1			CA			972  			16341		PCE41111	BU4989		(CAN) CREW REPORTED AN IN-FLIGHT FIRE AND THE ENGINE WAS SHUT DOWN.  POST-FLIGHT INSPECTION OF THE STARTER/GENERATOR FOU	ND THREE SETS OF BRUSHES WORN BELOW WEAR INDICATOR MARK AND ONE SET AT 1/2 LIFE.  NO EVIDENCE OF FIRE.  PROBLEM ATTRIBUT	ED TO ELECTRICAL ARCING.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P15EA
1999012900942	19990129	00942	SO  	1999	1	29	CA981207001      	2	19981129	G	8520	642088	CRANKCASE       			BEECH 	55    	95C55       	1152708	CE  	CONT  	O520  	IO520C      	17032	SO  	MCAULY	3AF32C	3AF32C75    	GL  	ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				1041 				243689R	753494		(CAN) ENGINE LEAKING OIL.  INSPECTION FOUND TWO THROUGH BOLTS BROKEN.  THIS CAUSED NR 4 CYLINDER TO BECOME LOOSE.  THE L	OOSE CYLINDER CREATED PULL ON THE CYLINDER HOLD-DOWN STUDS AND CRACKED THE CRANKCASE, WHERE THE STUD WAS PULLED.					1	L	7	2 	3O	3	O		3A16    	E5CE	5	C	P22EA
1999012900943	19990129	00943	SO  	1999	1	29	CA981207002      	2	19981102	G	8520	642187A1	CRANKCASE       			CESSNA	185   	A185F       	2072821	CE  	CONT  	O520  	IO520D      	17032	SO  	MCAULY	3A32C	D3A32C90    	GL  	ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				750  				175164R	814323		(CAN) INSPECTION FOUND ENGINE CASE CRACKED AT A NON-CRITICAL AREA, RADIATING OUT FROM CYLINDER HOLD-DOWN STUD.						1	H	7	1 	3O	3	O		3A24    	E5CE	5	C	P21EA
1998122400452	19981224	00452	EU  	1998	12	24	CA981207005      	2	19981118	G	7200		BLADE           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					NR 2 ENGINE	BENT            	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CL	CLIMB          	1			CA								9117			(CAN) ON CLIMB-OUT, THE AIRCRAFT EXPERIENCED A SEVERE VIBRATION FOLLOWED BY A LOUD BANG.  AT THIS TIME THE PILOTS NOTICE	D THE NR 2 ENGINE STARTING TO SPOOL DOWN AND TEMP OUT.  THE CREW ELECTED TO SHUT THE NR 2 ENGINE DOWN AND RETURN TO THE 	DEPARTURE POINT.  POST-FLIGHT INSPECTION FOUND THE LOW PRESSURE TURBINE BLADES BENT AND THE LP COMPRESSOR UNABLE TO MOVE	.  THE ENGINE WAS REPLACED.  THE FAILED ENGINE HAS BEEN SENT FOR OVERHAUL, TEARDOWN REPORT TO FOLLOW.			2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1999021200162	19990212	00162	EU  	1999	2	12	CA981207006      	1	19981126	G	2130	FGFB722505250A2	LINE            			AMD   	FALC50	FALCON900   	2700160	EU  	GARRTT	TFE731	TFE7315BR   		WP  					AIR DIST	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			5093 					P97133			(CAN) CRACK RUNNING THROUGH 50 PERCENT OF THE TUBE CIRCUMFERENCE AT THE INSIDE RADIUS RESULTED IN A LOSS OF PRESSURE TO 	THE WATER SYSTEM.  REPLACED.   PART TC:  2,109.					2	L	7	3 	4F	4	F	RT	A46EU   	E6WE
1999040200162	19990402	00162	SO  	1999	4	2	CA981207007      	1	19981118	G	2460	170001200	CIRCUIT BREAKER 			PIPER 	PA42  	PA42720     	7104212	SO  	PWA   	PT6   	PT6A61      	52043	EA  					COCKPIT	OVERHEATED      	W				K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			CA			3655 					PCE99138			(CAN) DURING GROUND RUN, A HOT ODOR WAS DETECTED.  INVESTIGATION FOUND THE SOURCE TO BE THE RIGHT GENERATOR BUS TIE CIRC	UIT BREAKER IN THE LOWER CENTER PEDESTAL.  THE BOLT CONNECTING THE BREAKER TO THE BUS WAS NOT TIGHT AND THE PHENOLIC BLO	CK WAS GETTING HOT.				1	L	7	2 	4T	4	T		A23SO   	E4EA
1999012900946	19990129	00946	SW  	1999	1	29	CA981207008      	1	19981028	G	5711	2733000001	SPAR            			SWRNGN	SA227 	SA227AC     	8780603	SW  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			24062								(CAN) MAINTENANCE CARRIED OUT THE INSPECTION REQUIRED BY AIRFRAME AIRWORTHINESS LIMITATIONS MANUAL ST-UN-M001 ATA 5710, 	FIG. 10-1, REV C DATE APRIL 17,1998 - AND FOUND THE MAIN SPAR CENTER WEB CRACKED AT BOTH STRINGER NR 13 CUT-OUTS.  AIRCR	AFT FERRIED TO CALGARY AND REPAIRS CARRIED OUT.  PART TC:  34,944.				2	L	7	2 	4T			RT	A8SW
1999012900947	19990129	00947	EA  	1999	1	29	CA981207009      	1	19980519	G	7120	89110016009	MOUNT           			DHAV  	DHC8  	DHC8311     	1386006	EA  	PWA   	PW120 	PW123       		NE  					NR 1 ENGINE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						TA002		123038			(CAN) DURING A CHECK INSPECTION, THE NR 1 ENGINE INBOARD STRUT WAS FOUND BROKEN.  THE STRUT WAS REPLACED.						2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999012900948	19990129	00948	CE  	1999	1	29	CA981207010      	1	19981118	G	2820	050011874	LINE            			CESSNA	172   	172M        	2072418	CE  										FUEL SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) ON TWO OCCASIONS DURING THE PRECEDING WEEK,THIS SUBMITTER FOUND THE FUEL LINE RUNNING FROM THE RIGHT PEDESTAL TO T	HE FUEL STRAINER AT THE FIRWALL HAD BEEN CHAFED BY THE NOSE WHEEL STEERING TUBE.  THIS WAS FOUND ON TWO DIFFERENT AIRCRA	FT.				1	H	7	1 	3O			NT	3A12
1999012900949	19990129	00949	NE  	1999	1	29	CA981207011      	2	19981015	G	7414	SB9RV3	MAGNETO         	BOSCH       		DHAV  	DHC2  	DHC2*       	2800108	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	22D	22D30       	NE  	RT MAGNETO	BROKEN COIL     	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA				1042 		BB5004		207325	176434		(CAN) PILOT RETURNED TO DOCK AFTER RUN-UP INDICATED THE RIGHT HAND MAGNETO WAS DEAD.  INVESTIGATION REVEALED THE END OF 	THE ROTOR WITH CONTACT WITH THE COIL WAS BROKEN OFF AND THE COIL DAMAGED.  THE MAGNETO WAS REPLACED.					1	H	7	1 	3R	3	R		A806    	5E1	5	C	P736
1998122400453	19981224	00453	WP  	1998	12	24	CA981207013      	2	19981129	G	7250	31016031	WHEEL           			MTSBSI	MU2   	MU2B60      	5780460	CE  	GARRTT	TPE331	TPE33110    	01514	WP  					1ST STAGE	FAILED          	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			M			OVER TEMP                 			CL	CLIMB          	1			CA			6748 			90350118145		P36205C			(CAN) DURING AN OVERSHOOT, THE PILOT HEARD A LOUD BANG AND NOTED EXCESSIVE EGT, FOLLOWED BY NR 1 ENGINE FAILURE. THE ENG	INE WAS SHUTDOWN.  ENGINE DISASSEMBLY FOUND 1ST TURBINE BLADE HAD SEPARATED AT THE BLADE ROOT. THE BLADE FAILURE DOES NO	T APPEAR TO BE A RESULT OF OVER TEMPERATURE, BUT FATIGUE MAY HAVE BEEN A FACTOR.  PART TC:  8,207.				1	H	7	2 	3T	4	T	RT	A10SW   	E4WE
1999012900951	19990129	00951	CE  	1999	1	29	CA981207014      	1	19981201	G	2720	071230915	BRACKET         			CESSNA	180   	180A        	2072604	CE  	CONT  	O470  	O470K       	17026	SO  	MCAULY	2A34C	2A34C50     	GL  	RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4257 					49383R	735578		(CAN) BOTH RUDDER BELLCRANK BRACKETS REPLACED AT STA 209 ON THE REAR BULKHEAD.  PARTS WERE CRACKED THROUGH THE UPPER BOL	T HOLES WHERE THEY ARE BOLTED ONTO BULKHEAD.					1	H	7	1 	3O	3	O		5A6     	E273	5	C	P3EA
1999021200163	19990212	00163	EA  	1999	2	12	CA981207017      	1	19981105	G	5350		NOSE CONE       			CNDAIR	CL600 	CL6002B19   		EA  	GE    	CF34  	CF343A1     	30015	NE  					FUSELAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								807380			(CAN) ON APPROACH, AIRCRAFT ENCOUNTERED BIRD STRIKES.  FIVE STRIKES ON AIRCRAFT WERE NOTED, BOTH LANDING LIGHT LENSES BR	OKEN, RIGHT ENGINE NOSE COWL DENTED, BOTH LANDING GEARS NO DAMAGE, AND RIGHT FLAP TRAILING EDGE DENT.  NOSE COWL REPLACE	D, LIGHT LENSES REPLACED AND TRAILING EDGE OF FLAP REPAIRED.				2	L	7	2 	4F	4	F	RT	A21EA   	E15NE
1999021200165	19990212	00165	EA  	1999	2	12	CA981207020      	1	19981115	G	5610	NP1393222	WINDOW          			CNDAIR	CL600 	CL6002B19   		EA  										COCKPIT	SHATTERED       	W				B				EMER. DESCENT           				O			OTHER                     			CR	CRUISE         	1			CA											(CAN) AT FLIGHT LEVEL FL 350, OFFICERS SIDE WINDOW SHATTERED.  EMERGENCY DESCENT CARRIED OUT TO FL 140.  SAFE LANDING CA	RRIED OUT.					2	L	7	2 	4F			RT	A21EA
1999021200166	19990212	00166	EA  	1999	2	12	CA981207021      	1	19981123	G	5330		SKIN            			DHAV  	DHC6  	DHC6200     		EA  	PWA   	PT6   	PT6A20      	52043	EA  					FUSELAGE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			29192					PCE20421			(CAN) CRACK FOUND ON SKIN UNDER LOWER VHF BLADE ANTENNA.  SERVICE BULLETIN 6/305 IN REGARD TO THIS AREA HAD NOT BEEN CAR	RIED OUT.					1	H	7	2 	3T	3	T		A9EA    	E4EA
1999021200167	19990212	00167	SO  	1999	2	12	CA981207022      	2	19981124	G	8530	649478	CAMSHAFT        			BEECH 	95    	95B55       	1152729	CE  	CONT  	O470  	IO470L      	17026	SO  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				581  				297689R			(CAN) PRE-INSPECTION RUN-UP, FOUND THE ENGINE RUNNING ROUGH AT IDLE.  COMPRESSION CHECK FOUND NR 1 AND NR 2 WITH LOW COM	PRESSION.  THE CYLINDERS WERE REMOVED FOR INSPECTION AND THE CAMSHAFT LOBES WERE FOUND WORN. THE INTAKE LIFTER ON NR 2 C	YLINDER WAS ALSO FOUND WORN.  THE ENGINE WAS REPLACED.				1	L	7	2 	3O	3	O	RT	3A16    	3E1
1999021200168	19990212	00168	GL  	1999	2	12	CA981207023      	1	19981119	G	2900	6D47812051	HYDRAULIC TUBE  			BOMBDR	BD700 	BD7001A10   		GL  										NR 2	BROKEN          	W				O				OTHER                   				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) HYDRAULIC LINE IN REAR FUSELAGE BROKEN.  HYDRAULIC LINE P/N 478-1205-1 HAD BECOME SEPARATED AT END OF SLEEVE P/N B	0302132V04 DURING ENGINE RUN.  THIS CAUSED THE LOSS OF ALL HYDRAULIC FLUID OF NR 2 SYSTEM.					2	L	7	2 	4F			RT	T00003NY
1999021200169	19990212	00169	EA  	1999	2	12	CA981207024      	1	19981115	G	2434	MS21042L4	CONNECTOR       			CNDAIR	CL215 	CL2156B11415		EA  										ELECTRICAL SYS	LOOSE           	W				H				DEACTIVATE SYST/CIRCUITS				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			303  								(CAN) SHORTLY AFTER TAKEOFF, SMOKE EMANATED FROM THE MAIN DISTRIBUTION CENTER ACCOMPANIED WITH A BURNING SMELL.  MAINTEN	ANCE INVESTIGATION REVEALED SOURCE TO BE THE MDC AT THE ELECTRICAL CONNECTION BETWEEN THE AIR COMPRESSOR AND THE 100-AMP	 CURRENT LIMITER (2F4PD).  CONNECTION WAS LOOSE, CAUSING ARCING AND EXCESSIVE HEAT THAT BURNT THE TERMINAL PHENOLIC INSU	LATOR ON GENERATOR BOX NR 2.			2	H	7	2 	4T			RT	A14EA
1999021200170	19990212	00170	SO  	1999	2	12	CA981207026      	1	19981126	G	3710	2H2211	REGULATOR       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					PNEU SYSTEM	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7837 					L161761			(CAN) PILOTS REPORTED LEFT WING DE-ICER BOOT NOT VERY EFFICIENT WHEN NEEDED.  TESTING EVENTUALLY FOUND HOSE P/N 82371-10	6 FROM FIREWALL TO DUAL REGULATOR LEAKING IF AIRCRAFT ROCKED DURING TEST.  THE HOSE WAS HARDENED.  THE LOW PRESSURE VALV	E WAS NOT OPERATING CORRECTLY IF AIR PRESSURE APPLIED.  SUBMITTER SUSPECTS PLUNGER MISSING FROM VALVE.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1999021200171	19990212	00171	EA  	1999	2	12	CA981207027      	1	19981201	G	3020		LINE            			CNDAIR	CL215 	CL2156B11415		EA  										DEICE SYSTEM	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			529  								(CAN) DURING INSPECTION OF THE ENGINES, DISCOVERED THAT THE POWER WIRING TO THE AIR INTAKE HEATING SYSTEM RUBBED ON A RI	GID DRAIN.  IT WAS ALSO NOTEDTHAT 5 OF 6 ENGINES INSPECTED HAD A SIMILAR PROBLEM.					2	H	7	2 	4T			RT	A14EA
1999021200173	19990212	00173	NE  	1999	2	12	CA981207029      	2	19981123	G	7261	310499602	SHAFT           								PWA   	118   	PW118       		NE  					OIL PUMP	FRACTURED       	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA								115255			(CAN) ENGINE REMOVED AFTER PILOT REPORTED LOSS OF OIL PRESSURE. THE CAUSE OF THE LOSS OF OIL PRESSURE WAS THE FRACTURE O	F THE MAIN OIL PUMP DRIVE SHAFT, WHICH WAS FRACTURED AT THE LOCATION OF THE SLEEVE BUSHING IN THE MAIN OIL PRESSURE PUMP	 HOUSING.  IT IS THE OPINION OF THE SUBMITTER THAT THE PUMP DRIVE SHAFT FAILURE WAS CAUSED BY THE PUMP GEARS BEING JAMME	D, THERE WAS NO DETERMINATION AS TO THE CAUSE OF THE JAMMING.								4	T			E20NE
1999021200174	19990212	00174	NE  	1999	2	12	CA981207030      	2	19981126	G	7210	31073301	BEARING         			DHAV  	DHC8  	DHC8301     		NM  	PWA   	PW120 	PW123       		NE  					GEARBOX	SPALLED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			8940 	3106 		FC16186		123070			(CAN) THE ENGINE WAS REMOVED AFTER METAL FLAKES WERE FOUND ON THE REDUCTION GEARBOX CHIP DETECTOR AND THE RGB SCAVENGE F	ILTER.  DISASSEMBLY OF THE RGB FOUND THE SOURCE OF THE METAL CONTAMINATION WAS THE MASSIVE SPALLING OF THE NR 15 BEARING	 WITH MATERIAL LOSS FROM ALL ROLLERS AND FROM THE OUTER RACE. THE CAUSE OF THE SPALLING COULD NOT BE CONCLUSIVELY DETERM	INED, BUT IT IS CONSIDERED TO BE MOST LIKELY THE RESULT OF LOW LEVEL ELECTRICAL DISCHARGE PITTING OF THE BEARING.  LIGHT	NING STRIKE CAUSING HIGH LEVEL DISCHARGE DAMAGE TO THE BEARING IS ALSO CONSIDERED A POSSIBILITY.   PART TC:  18,264.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999021200175	19990212	00175	EA  	1999	2	12	CA981209001      	2	19981201	G	7261	M832481017	O-RING          		3004322     	EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					NR 2 ENGINE	FAILED          	W				E				ENGINE SHUTDOWN         				K			FLUID LOSS                			NR	NOT REPORTED   	1			CA								PCE56867			(CAN) PILOT SHUT DOWN NR 2 ENGINE DUE TO LOW OIL PRESSURE.  POST-FLIGHT INSPECTION FOUND OIL LEAKING FROM THE OIL PRESSU	RE TUBE AT THE C-FLANGE, WHEN THE ENGINE WAS BEING MOTORED.  THE OIL PRESSURE TUBES WERE REMOVED AND INSPECTED FOR DAMAG	E. THE TUBES WERE REINSTALLED WITH NEW O-RINGS.  THE OIL SYSTEM WAS REPLENISHED AND THE ENGINE WAS RUN-UP SERVICEABLE.				1	L	7	2 	4T	4	T		A21SO   	E4EA
1999021200176	19990212	00176	SW  	1999	2	12	CA981209002      	1	19981204	G	7810	222063307105	SEAL            		222063307141	BELL  	222   	222U        	1182140	SW  										SEAL FRAME	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7104 								(CAN) SEAL ASSEMBLY CONSISTING OF FRAME, RING AND ANGLE FOUND WITH CRACK IN SPOT WELDS ATTACHING ANGLE TO TAILPIPE BODY 	AND CRACKS IN SPOT WELDS ATTACHING RING TO FRAME.					1	G	7	2 	3U				H9SW
1999021200177	19990212	00177	NE  	1999	2	12	CA981209003      	2	19981127	G	7260	711000	BEARING         			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					GEARBOX	WORN            	W				E	J	A		ENGINE SHUTDOWN         	DUMP FUEL               	UNSCHED LANDING         		K			FLUID LOSS                			CR	CRUISE         	1			CA			37361	3416 				648824			(CAN) DURING CRUISE, 42 MINUTES AFTER TAKEOFF, THE NR 1 ENGINE OIL QUANTITY WAS READ AT 1.75 GALLONS.  THE OIL LEVEL HAD	 BEEN SERVICED TO 4.0 GALLONS PRIOR TO DEPARTURE.  DURING THE NEXT 5 MINUTES, THE OIL QUANTITY DECREASED TO 1.25 GALLONS	.  THE NR 1 ENGINE WAS SHUT DOWN AND THE AIRCRAFT RETURNED TO ITS DEPARTURE POINT.  POST-FLIGHT INVESTIGATION FOUND THE 	BEARING/SLINGER RING FOR THE DRIVE SHAFT TO WHICH THE STARTER CONNECTS HAD SHIFTED IN ITS HOUSING, ALLOWING ENGINE OIL T	O FLOOD THE CAVITY AND VENT OVERBOARD.  THE ENGINE ACCESSORY GEARBOX IS BEING REPLACED.		2	L	7	3 	4F	4	F		A3WE    	E2EA
1998122400454	19981224	00454	EA  	1998	12	24	CA981209004      	1	19981124	G	5543	21515061800	TAB             			CNDAIR	CL215 	CL2151A10   		EA  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3013 								(CAN) MILLED SKIN P/N 215-15062-2 HAS A 2.75 INCH CRACK FORWARD OF FRONT MOUNTING HOLES ON BOTH LOWER MASS BALANCE WEIGH	TS.  (APPROXIMATELY .3125 INCH TO .3750 INCH FORWARD OF HOLES).  EXPOSED RIB IS CRACKED AT FLANGE RADIUS.  SB 215-A435 A	DDITIONAL WEIGHTS WERE INCORPORATED.  SDR CA981007005.  CRACKED MASS BALANCE ARM COULD POSSIBLY BE ASSOCIATED.  AFTER  D	ISASSEMBLY, ALL FOUR RIBLETS USED FOR THE UPPER AND LOWER MASS BALANCE WEIGHT PICKUP WERE FOUND TO HAVE MULTIPLE CRACKS 	TO THE RIBLETS.		2	H	7	2 	4R				A14EA
1999021200178	19990212	00178	SO  	1999	2	12	CA981209005      	1	19981129	G	2731	PE65016	CONTROL CABLE   			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					ELEVATOR	WORN            	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA								PCE56834			(CAN) TRIM JAMMED BELOW NEUTRAL POSITION, TRIM WORKS FROM NEUTRAL TO NOSE DOWN.  DURING REPLACEMENT OF TELEFLEX CABLE, F	OUND BOX TRANSMISSION GEAR LOOSE, TRANSMISSION REPLACED AND SYSTEM RIGGED.  IT WAS DETERMINED THAT THE WEAR ON THE CABLE	 AT THE TRANSMISSION BOX WAS CAUSED BY A GEAR IN THE TRANSMISSION.  THE CAUSE OF THE LOOSE GEAR WAS ATTRIBUTED TO THE LO	SS OF AN ALLEN SCREW THAT SECURED THE GEAR.			1	L	7	2 	4T	4	T	 	A21SO   	E4EA
1999021200179	19990212	00179	CE  	1999	2	12	CA981209006      	1	19981209	G	3244	184F102	BALANCE PATCH   		95442075    	LEAR  	35    	35A         	5170602	CE  										MLG WHEEL	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			62   			MAR73748					(CAN) ON LANDING, PILOT REPORTED SEVERE NOISE AND VIBRATION FROM NOSE WHEEL.  RUBBER BALANCE PATCH ON INSIDE HAD TORN OF	F.   PART TC:  37.					2	L	7	2 	4F				A10CE
1999021200180	19990212	00180	SO  	1999	2	12	CA981209007      	1	19981118	G	5343	159WM100471	FITTING         			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					FRONT SPAR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								16272			(CAN) UPLOCK FRAME ATTACH FITTING FOR MAIN LANDING GEAR FOUND BROKEN AT FRONT SPAR.						2	L	7	2 	4T	4	T		1A17    	E297
1999021200181	19990212	00181	EA  	1999	2	12	CA981209009      	1	19981203	G	2750		BPSU            			CNDAIR	CL600 	CL6002B19   		EA  										TE FLAP	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CR	CRUISE         	1			CA											(CAN) DURING FLIGHT AT FL 370, FLAP FAIL WARNING MESSAGE CAME ON.  AIRCRAFT RETURNED TO BASE.  MAINTENANCE UNABLE TO DUP	LICATE FAULT, FLAP ACTUATORS LUBRICATED AND AIRCRAFT TEST FLOWN, FLAPS CHECKED OK.  A SECOND INCIDENT OCCURRED AND  AGAI	N NO FAULT FOUND.  AFTER FURTHER TROUBLESHOOTING, ONE OF THE TWO BPSU IS SUSPECT CAUSING THE PROBLEM.				2	L	7	2 	4F			RT	A21EA
1999021200182	19990212	00182	EA  	1999	2	12	CA981209010      	2	19981130	G	8520	LW12030	CRANKCASE       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2B   	41532	EA  					ENGINE	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA				556  				L787661			(CAN) DURING INSPECTION, THE PRESENCE OF AN OIL LEAK AT THE LOWER FORWARD STUD AT NR 2 CYLINDER LED TO FINDING A CRACK 1	.50 INCHES LONG IN THE CRANKCASE, WHICH WAS VERIFIED BY A FLUORESCENT PENETRANT INSPECTION.  THE ENGINE WAS REPLACED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1999021200183	19990212	00183	SW  	1999	2	12	CA981209011      	1	19981130	G	3297	D309	WIRE            		SV315       	SWRNGN	SA227 	SA227AC     	8780603	SW  	GARRTT	TPE331	TPE33111U   	01514	WP  	ROTOL	R321	R321482F8   	GL  	MLG	CHAFED          	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								P44424C	DRG57282		(CAN) AFTER TAKEOFF, LANDING GEAR WOULD NOT RETRACT AND LANDING GEAR CIRCUIT BREAKER WAS TRIPPED.  MAINTENANCE FOUND THA	T THE INSULATION ON THE WIRE COMING FROM DIODE 309 AT TS 305/TS 311 WAS WORN ALLOWING IT TO SHORT OUT.					2	L	7	2 	4T	4	T	RT	A8SW    	E4WE	6	C	P61GL
1999021200184	19990212	00184	SO  	1999	2	12	CA981214001      	1	19981123	G	8120	4091709001	SHAFT           	GARRTT      		PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540F2BD  	41532	EA  					TURBOCHARGER	CRACKED         	W				E				ENGINE SHUTDOWN         				R			PARTIAL RPM/PWR LOSS      			CR	CRUISE         	1			CA				286  		AJ018572		RL97668A			(CAN) THE SHAFT JOINING THE TWO IMPELLERS IN THE TURBOCHARGER WAS FOUND CRACKED.  THIS ALLOWED THE EXHAUST SIDE IMPELLER	 TO SEPARATE FROM THE SHAFT.  THE INTAKE IMPELLER STAYED IN PLACE, BUT DUE TO IMBALANCE, SUSTAINED SOME BLADE DAMAGE.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1999021200185	19990212	00185	SO  	1999	2	12	CA981214003      	1	19981207	G	7922	53E19600	NUT             		LW10917     	PIPER 	PA31  	PA31350     	7103110	SO  	LYC   	O540  	TIO540J2BD  	41532	EA  					THERMO VALVE	SEPARATED       	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				573  		42018		RL309961A			(CAN) ENGINE WAS RECEIVED FOR REPAIR.  VERNATHERN VALVE WAS REMOVED FOR CLEANING AND THE NUT WAS FOUND MISSING.  THE NUT	 WAS FOUND IN AN EXTERNAL OIL LINE.  NUT WAS CRIMPED AT OVERHAUL IN ACCORDANCE WITH SERVICE BULLETIN NR 518.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1999012900219	19990129	00219	CE  	1999	1	29	CA981214004      	1	19981207	G	2410	830057	INDICATOR       		C6115050201 	CESSNA	208   	208B        	2073701	CE  										COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			10224								(CAN) STANDBY ALTERNATOR DRIVE SHEARED (P/N 2601271-8) SEVERAL TIMES DURING A PERIOD OF SEVERAL DAYS.  THIS OCCURRED IN 	THE AIR, DURING TAXI, OR DURING ENGINE RUN.  TROUBLESHOOTING EVENTUALLY LED TO NOTING THE STANDBY INOP LIGHT WAS FADING 	ON AND OFF CAUSING THE TECH TO CHECK THE R1 RESISTOR, SEE WIRING DIAGRAM 24-31-01-01, SHEET 2.  RESISTOR VALUE HAD INCRE	ASED FROM ITS NORM AL 100 OHMS TO 150 OHMS CAUSING THE ALTERNATOR TO LOAD TO FULL CAPACITY, AND THEN UNLOAD SEVERAL TIME	S PER SECOND.  RESULTANT LOAD/UNLOAD CAUSED DRIVE PULLEY SHAFT TO FAIL.  PART TC:  6,730.		1	H	7	1 	3T				A37CE
1999021200186	19990212	00186	SO  	1999	2	12	CA981214005      	1	19981130	G	3233	4204200	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			15897								(CAN) RIGHT MAIN LANDING GEAR WOULD NOT LOCK UP DURING RETRACTION TESTS AT A ROUTINE EVENT NR 4 INSPECTION.  THE ARM THA	T CONNECTED DIRECTLY TO PISTON ACTUATOR WAS FOUND CRACKED.					1	L	7	2 	3O				A20SO
1998122400455	19981224	00455	EA  	1998	12	24	CA981214006      	1	19981124	G	5543	215150622	SKIN            		21515061800 	CNDAIR	CL215 	CL2151A10   		EA  										RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2750 								(CAN) MILLED SKIN FOUND WITH A CRACK FORWARD OF FRONT MOUNTING HOLES ON BOTH LOWER MASS BALANCE WEIGHTS.  EXPOSED RIB IS	 ALSO CRACKED AT FLANGE RADIUS.  SB 215-A435 ADDITIONAL WEIGHTS WERE INCORPORATED.  CRACKED MASS BALANCE ARM COULD BE AS	SOCIATED.  ALL FOUR RIBLETS USED FOR UPPER AND LOWER MASS BALANCE WEIGHT PICKUPS WERE FOUND TO HAVE MULTIPLE CRACKS TO R	IBLETS.			2	H	7	2 	4R				A14EA
1999021200187	19990212	00187		1999	2	12	CA981214007      	4	19981109	G	3414	KMA1001	INDICATOR       			BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					COCKPIT	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						NT715		653499			(CAN) LEFT MACH/AIRSPEED INDICATOR LEAKING, REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200188	19990212	00188	NM  	1999	2	12	CA981214008      	1	19981114	G	2751	10129932	INDICATOR       			BOEING	727   	72727C      	138400J	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					TE FLAPS	MALFUNCTIONED   	W				A				UNSCHED LANDING         				F			FLT CONT AFFECTED         			CL	CLIMB          	1			CA						1731ANV		653499			(CAN) INBOARD FLAPS WOULD NOT EXTEND OR RETRACT.  INBOARD POSITION INDICATOR REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200189	19990212	00189	NM  	1999	2	12	CA981214009      	1	19981110	G	5270	21EN96	SWITCH          			BOEING	727   	727217      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					CARGO DOOR	MISRIGGED       	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			298  								(CAN) IN CRUISE, BOTH RED CARGO DOOR LIGHTS AND MAIN CARGO DOOR NOT CLOSED, AMBER LIGHTS ON IN DESCENT AT 7.0 DIFF, ALL 	LIGHTS OUT.  DOOR TESTED PER A.E.I. M/M SERVICEABLE.  ADJUSTED CARGO DOOR CLOSED MICROSWITCH.   PART TC:  162.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1999021200190	19990212	00190	NM  	1999	2	12	CA981214010      	1	19981117	G	2751	1812995	INDICATOR       		1812995     	BOEING	727   	727217      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					TE FLAPS	MALFUNCTIONED   	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						U171G					(CAN) FLAPS WENT TO 2 DEGREES, THEN LOCKED OUT, INBOARD FLAP POSITION INDICATOR REPLACED.						2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1999021200191	19990212	00191	NM  	1999	2	12	CA981214011      	1	19981111	G	3510	10610442	COMPENSATOR     		6559873108  	BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					O2 SYSTEM	LEAKING         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA											(CAN) OXYGEN LEAK AT CONNECTIONS TO CREW OXYGEN SHUTOFF VALVE AND AT CONNECTORS TO THERMAL COMPENSATOR AND REGULATOR.  V	ALVE REPLACED.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200192	19990212	00192	NM  	1999	2	12	CA981214012      	1	19981119	G	3510	280001	REGULATOR       			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						4464					(CAN) 1ST OBSERVERS DILUTER DEMAND REGULATOR EMERGENCY SUPPLY NOT FULLY CLOSING.  REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200193	19990212	00193	NM  	1999	2	12	CA981214013      	1	19981127	G	3510	106017436	LINE            			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					COCKPIT	PUNCTURED       	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA											(CAN) 2ND OFFICERS DILUTER DEMAND SUPPLY HOSE HAS A SMALL HOLE.  REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200194	19990212	00194	CE  	1999	2	12	CA981214014      	1	19981126	G	2720	24670011	TORQUE TUBE     			CESSNA	172   	172RG       	2072438	CE  	LYC   	O360  	O360F1A6    	41514	EA  	MCAULY	2D34C	B2D34C220   	GL  	RUDDER PEDAL	BROKEN          	W				K				NONE                    				F			FLT CONT AFFECTED         			TX	TAXI/GRND HDL  	1			CA			7357 					RL2697236A	800966		(CAN) WHILE TAXIING, THE PILOTS RIGHT RUDDER PEDAL TORQUE TUBE FAILED.  WELD HAD BROKEN.						1	H	7	1 	3O	3	O		3A17    	E286	5	C	P7EA
1999021200195	19990212	00195	NM  	1999	2	12	CA981214015      	1	19981207	G	2430	CSP6575	BUS BAR         		82410379101 	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					DC SYSTEM	LOOSE           	W				A	H			UNSCHED LANDING         	DEACTIVATE SYST/CIRCUITS			H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		AP	APPROACH       	1			CA			7324 					PCE120030			(CAN) THE LEFT MAIN DISTRIBUTION BUS BAR BECAME LOOSE FROM THE FOUR, 50-AMP CIRCUIT BREAKERS THAT ARE IN THE LEFT COCKPI	T CIRCUIT BREAKER PANEL.  THIS CONDITION CAUSED THE FOUR 50-AMP CIRCUIT BREAKERS TO OPEN AND THE AIRCRAFT LOST THE LEFT 	MAIN DC BUS WITH NO DC BUS FAULT LIGHT INDICATION ALTHOUGH THERE WERE MANY OTHER AMBER FAULT LIGHTS ILLUMINATED.  BUS BA	R WAS SECURED AND CB'S RESET, SYSTEM CHECKED OK.			2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999021200196	19990212	00196	NM  	1999	2	12	CA981214016      	1	19981201	G	2821	MS243913KL	FILTER PLUG     	STWARNER    	10839F      	DHAV  	DHC8  	DHC8102     	2809003	NM  	PWA   	120   	PW120A      		NE  					FUEL SYSTEM	LEAKING         	W				K				NONE                    				K			FLUID LOSS                			TX	TAXI/GRND HDL  	1			CA			36   			WA11615		TM120816			(CAN) NR 2 ENGINE LOW PRESSURE FUEL FILTER DRAIN PLUG FOUND LEAKING.  PLUG WAS FOUND LOOSE EVEN THOUGH IT WAS LOCKED WIR	ED.   PART TC:  3,840.					2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999021200197	19990212	00197	CE  	1999	2	12	CA981214017      	1	19981207	G	5520	115610010169	RIB             		115610010351	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B124A		PCE50339			(CAN) DURING REMOVAL OF TORQUE TUBES, END RIBS FOUND TO BE CRACKED AT RIB/SKIN TO TORQUE ATTACHMENT POINTS AND FORWARD C	ORNERS OF END RIB.  SKIN/RIB DIMPLES THOUGHT TO BE CRACKED DUE TO OVER COUNTERSINKING TORQUE TUBE ASSEMBLY ATTACH POINTS	.  TORQUE TUBES ONLY COME WITH PILOT HOLES.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1999021200198	19990212	00198	CE  	1999	2	12	CA981214018      	1	19981207	G	5520	115610010169	RIB             		115610010352	BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						B156A		PCE50339			(CAN) DURING REMOVAL OF TORQUE TUBES, END RIBS FOUND TO BE CRACKED AT RIB/SKIN TO TORQUE ATTACHMENT POINTS AND FORWARD C	ORNERS OF END RIB.  SKIN/RIB DIMPLES THOUGHT TO BE CRACKED DUE TO OVER COUNTERSINKING TORQUE TUBE ASSEMBLY ATTACHMENT PO	INTS.  TORQUE TUBES ONLY COME WITH PILOT HOLES.				1	L	7	2 	3T	4	T		A14CE   	E4EA
1999021200199	19990212	00199	SO  	1999	2	12	CA981214019      	1	19981120	G	2140	88D9310	COMBUSTION TUBE 	JANITROL    	90D382      	PIPER 	PA44  	PA44180     	7104402	SO  										HEATER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			882  			A95080021					(CAN) DURING COMPLIANCE WITH JANAERO AD 96-20-07, THE PRESSURE DECAY TEST REVEALED A CRACK AT THE BASE OF THE TUBE WHICH	 HOLDS THE PRESSURE SWITCH FOR COMBUSTION AIR LOCATED AT THE AIR INLET ON THE COMBUSTION TUBE ASSEMBLY.  UNIT REMOVED FO	R REPAIR.  AT SUBSEQUENT AIRCRAFT INSPECTIONS (50 HR INTERVALS), INSPECT THE WELD AREA WHERE THE TUBE IS ATTACHED.  THE 	COMBUSTION AIR TUBE WILL BE INSPECTED WITH LIGHT PRESSURE APPLIED TO THE COMBUSTION AIR PRESSURE SWITCH TO SEE IF FURTHE	R CRACKING HAS OCCURRED.		1	L	7	2 	3O				A19S0
1999022000001	19990220	00001	EU  	1999	2	20	CA981214020      	1	19980921	G	3251	Z4242170001	SPRING          		L24242370000	ZLIN  	242   	Z242L       	9970204	EU  										NLG STEERING	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2236 								(CAN) DURING TAXI, STUDENT NOTED PLAY IN NOSE WHEEL STEERING.  INSPECTION FOUND THE LEFT STEERING SPRING BROKEN.  STUDEN	TS REMINDED TO START AIRCRAFT ROLLING BEFORE TURNING NOSE GEAR.					1	L	7	1 	3O			0	A76EU
1999021900014	19990219	00014	CE  	1999	2	19	CA981214023      	1	19981202	G	7500	31032	SEAL            			LEAR  	60    	60LEAR      	5170707	CE  	PWA   	305   	PW305A      	52128	NE  					TAIL COMPARTMENT	IMPROPER        	W				A	B	G		UNSCHED LANDING         	EMER. DESCENT           	O2 MASK DEPLOYED        		B	O		SMOKE/FUMES/ODORS/SPARKS  	OTHER                     		IN	INSP/MAINT     	1			CA			4473 					PCE305242			(CAN) IN CRUISE AT 43,000 FEET, BOTH BLEED AIR LIGHTS CAME ON INDICATING AN OVERHEAT CONDITION IN THE TAIL COMPARTMENT. 	 LIGHT OFF WITH LEFT BLEED SWITCH IN EMERGENCY.  SHORTLY AFTER, SMOKE FILLED THE COCKPIT AND CABIN.  EMERGENCY DESCENT I	NITIATED AND OXYGEN MASKS DEPLOYED.  HYDRAULIC PRESSURE LOST ON BOTH SIDES, BUT WAS RECOVERED AT APPROXIMATELY 30,000 FE	ET.  SMOKE DISSIPATED DURING THE DESCENT.  TWO SEALS ON BLEED AIR COUPLING WERE LEAKING AND INSTALLED IMPROPERLY.  HYDRA	ULIC RESERVOIR VACUUM RELIEF VALVE WAS ALSO DEFECTIVE.		2	L	7	2 	4F	4	F	RT	A10CE   	E35NE
1999021200201	19990212	00201		1999	2	12	CA981214024      	4	19980901	G	3416	AR850	ENCODER         			PIPER 	PA28  	PA28161     	7102803	SO  	LYC   	O320  	O320D3G     	41508	EA  					COCKPIT	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						53672		L803139A			(CAN) ENCODER REPORTS WRONG ALTITUDE CODES.  THIS PROBLEM IS A RECURRING ONE AND ENCODER NARCO AR850 S/N 53672 REPLACED 	WITH AMERI-KING AR350 S/N 3526457.					1	L	7	1 	3O	3	O		2A13    	E274
1999021200202	19990212	00202	CE  	1999	2	12	CA981216001      	1	19981130	G	2810		FUEL TANK       			CESSNA	172   	172Q        	2072437	CE  	LYC   	O360  	O360A4N     	41514	EA  					FUEL SYSTEM	CONTAMINATED    	W				C				ABORTED TAKEOFF         				Y			ENGINE STOPPAGE           			TO	TAKEOFF        	1			CA								L3056736A			(CAN) ENGINE STOPPED SHORTLY AFTER TAKEOFF.  PILOT MANAGED TO LAND SAFELY ON SAME RUNWAY ABOUT 1 LITER OF WATER FOUND IN	 RIGHT HAND WING TANK, FUEL SCREEN AND CARBURETOR LAST FLIGHT WAS 12 DAYS PREVIOUS AND IT HAD BEEN RAINING FOR THE PAST 	12 DAYS.  ALL TANK CAPS, ETC., SECURE.  PILOT POSSIBLY NOT EXPERIENCED ENOUGH TO RECOGNIZE WATER IN TANK.  UNKNOWN HOW W	ATER GOT INTO TANK.			1	H	7	1 	3O	3	O	NT	3A12    	E286
1999021200203	19990212	00203	SO  	1999	2	12	CA981216002      	2	19981205	G	8550		DRIVE           			CESSNA	337   	337F        	2075725	CE  	CONT  	O360  	IO360C      	17025	SO  	MCAULY	2AF34C	D2AF34C301  	GL  	OIL PUMP	BROKEN          	W				E				ENGINE SHUTDOWN         				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			1535 					351031	735763		(CAN) THE REAR ENGINE HAD AN UNCOMMANDED SHUTDOWN IN-FLIGHT.  THE AIRCRAFT LANDED WITH ONLY THE FRONT ENGINE OPERATING. 	 INVESTIGATION FOUND THE ENGINE OIL PUMP DRIVE BROKEN.					1	H	7	2 	3O	3	O		A6CE    	E1CE	5	C	P5EA
1999040200163	19990402	00163	EA  	1999	4	2	CA981216003      	2	19981204	G	7322	31747000	JOINT           		9549302     	PIPER 	PA34  	PA34200     	7103405	SO  	LYC   	O360  	IO360C1E6   	41514	EA  					THROTTLE BODY	FAILED          	W				L	A	E		ABORTED APPROACH        	UNSCHED LANDING         	ENGINE SHUTDOWN         		O			OTHER                     			AP	APPROACH       	1			CA			1542 					RL1981051A			(CAN) NO RESPONSE WHEN PILOT THROTTLE BACK ON LEFT ENGINE. THE BALL HAD COME OUT OF THE JOINT ASSEMBLY AT THE THROTTLE B	ODY.   RIGHT ENGINE THROTTLE BALL JOINT HAD BEEN REPLACED 13.1 HOURS PREVIOUS.  SUMBITTER NOTES THAT THEY ARE FOLLOWING 	PIPER SL 747 (WEAR CHECK) AND REPLACING THE JOINT ASSY EVERY 1200 HOURS.				1	L	7	2 	3O	3	O		A7SO    	1E10
1999021200204	19990212	00204	SW  	1999	2	12	CA981216004      	1	19981207	G	5711	5371	SPAR            			BBAVIA	8     	8GCBC       	1220803	SW  	LYC   	O360  	O360A2A     	41514	EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1273 					L1868236A			(CAN) SPAR INSPECTION AS DETAILED IN SL 406A FOUND WITH A 2 INCH CRACK.  WOOD SPAR HAD BEEN INVOLVED IN A FLIP OVER PREV	IOUSLY.					1	H	7	1 	3O	3	O		A21CE   	E286
1999040200164	19990402	00164	SO  	1999	4	2	CA981216005      	1	19981204	G	2752	451813	ACTUATOR        			PIPER 	PA31  	PA31350     	7103110	SO  										TE FLAP	BROKEN          	W				O				OTHER                   				J			WARNING INDICATION        			TX	TAXI/GRND HDL  	1			CA			5496 								(CAN) FLAP ACTUATOR BROKEN, THE EXTERNAL HOUSING SEPARATED.						1	L	7	2 	3O				A20SO
1999021200210	19990212	00210	NM  	1999	2	12	CA981216012      	1	19981116	G	5330	65184173	PANEL           			BOEING	727   	72782       	1384029	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 294-310	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36854					649672			(CAN) NOSE WHEELWELL AFT TOP PANEL/INTERIOR WEB AFT OF STA 294 TO STA 310 CORRODED.   PART TC:  53,055.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200211	19990212	00211	NM  	1999	2	12	CA981216013      	1	19981124	G	5311	6515932	FRAME           			BOEING	727   	72782       	1384029	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					BS 500-620	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			36854	1600 				649672			(CAN) SEVERAL BELT FRAMES OPPOSITE MAIN CARGO DOOR RT STA 500 TO STA 620 DAMAGED, SUSPECT DUE TO IMPROPER PALLET LOADING	.   PART TC:  35,055.					2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021900403	19990219	00403	SO  	1999	2	19	CA981216029      	1	19981207	G	3221	45318000	LINK            		4438800     	PIPER 	PA31  	PA31350     	7103110	SO  										NLG	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			11405								(CAN) SCISSORS OFTEN DISCONNECTED WHEN TOWING.  THE LOWER SCISSOR IS THEN LEFT DRAGGING ON THE TIRE WHICH GRINDS ON THE 	CASTING, WEARING IT.  IN ADDITION, BOTH SCISSORS WERE FOUND WARPED FROM STRAIN CAUSED BY TURNING WITH BRAKES INSTEAD OF 	STEERING AND THE SUDDEN GRABBING WHEN TAXIING TOO FAST ON ICY SURFACE.  ALSO, FOUND THE BUSHINGS INSTALLED THE WRONG WAY	.  THE FLANGED PORTION MUST BE ON THE OUTSIDE WITH A SPACER BETWEEN THE LINKS.  THE LINKS HAD BEEN INVERTED TOP TO BOTTO	M.		1	L	7	2 	3O				A20SO
1999040200165	19990402	00165	SO  	1999	4	2	CA981216031      	1	19981128	G	5280	466522	HINGE           		4752031     	PIPER 	PA31  	PA31350     	7103110	SO  										RT MLG DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) RIGHT HAND FORWARD DOOR HINGE FOUND CRACKED ACROSS THE CASTING SEAM.  HINGE HAD BEEN INSTALLED PER SB 682 WHICH WA	S TO ELIMINATE REPETITIVE INSPECTION.					1	L	7	2 	3O				A20SO
1999043000093	19990430	00093	EA  	1999	4	30	CA981230001      	1	19981203	G	3246	6A0300007	SPREADER BAR    	WIPLINEINC  	6000        	DHAV  	DHC2  	DHC2MK3     	2800107	EA  	PWA   	PT6   	PT6A20      	52043	EA  					FLOAT	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1532 					PCE21710			(CAN) WHILE ADJUSTING THE FLOAT FLYING WIRES, IT WAS NOTICED THAT THE FLOATS WOULD SPRING OUTWARD AND AFT.  SPREADER BAR	 FOUND BROKEN.  FRACTURE WAS INSIDE THE FLOAT AND COULD NOT BE SEEN WITH FLYING WIRES ATTACHED.  FLYING WIRES WERE HOLDI	NG FLOATS TOGETHER.				1	H	7	1 	3T	3	T		A806    	E4EA
1999021200221	19990212	00221	SW  	1999	2	12	CA981230007      	1	19981206	G	6710	206001397001	PIVOT           			BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					CYCLIC SUPPORT	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								CAE801008BA			(CAN) PILOT REPORTED NOT BEING ABLE TO ADJUST CYCLIC FRICTION.  THE FRICTION ADJUSTMENT WOULD TURN, BUT FRICTION WOULD N	OT INCREASE.  ATTEMPTS AT ADJUSTING THE MINIMUM FRICTION DID NOT WORK.  WHEN REMOVING SUPPORT ASSY TO CHANGE THE FRICTIO	N BEARING, A CRACK IN THE PAINT WAS NOTED IN THE RELIEF HOLE AT THE END OF THE SLOT.  THE PAINT WAS REMOVED AND THE CRAC	K WAS VERIFIED UNDER MAGNIFICATION.  IT IS POSSIBLE THAT THE FRICTION BEARING BEING WORN HAD CAUSED ATTEMPTS TO OVERTIGH	TEN THE ASSY THEREBY CAUSING EXCESSIVE STRESS IN THE RELIEF HOLE AREA LEADING TO THE CRACK.  REPAIRED/REPLACED.		1	G	7	1 	3U	3	U		H2SW    	E4CE
1999021200222	19990212	00222	CE  	1999	2	12	CA981230008      	1	19981207	G	2810	05235221	STRAP           		052600029   	CESSNA	172   	172M        	2072418	CE  						MCAULY	1C160	1C160DTM    	GL  	FUEL CELL	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7124 						732270		(CAN) EXCESSIVE FUEL STAINS NOTED ALONG LOWER SURFACE OF WING EXTENDING FROM ROOT ALONG REAR SPAR THE FULL LENGTH OF FLA	P AT STA 100.5.  FURTHER INVESTIGATION FOUND BOTH INBOARD STRAPS HAD SEPARATED AND WERE NO LONGER SECURING THE TANK.  LE	AK WAS CAUSED BY OUTBOARD STRAPS LEANING IN TOWARD THE OUTBOARD SIDE OF TANK AND WEARING A HOLE INTO TANK.				1	H	7	1 	3O			NT	3A12    		5	N	P910
1999021200223	19990212	00223	EU  	1999	2	12	CA981230009      	2	19981210	G	7310	50010446001	ACTUATOR        			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					FUEL TRIM	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CL	CLIMB          	1			CA						8975J		16227			(CAN) FUEL TRIM ACTUATOR FAILED AFTER TAKEOFF, UNABLE TO CHANGE FUEL TRIM SETTING.  AIRCRAFT RETURNED TO BASE.  THE UNIT	 WAS REPLACED.					2	L	7	2 	4T	4	T		1A17    	E297
1999030500179	19990305	00179	NM  	1999	3	5	CA981230010      	1	19981210	G	2722	591743	CAP             		65448613    	BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					ACTUATOR	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			53052			372A		P665183			(CAN) HYDRAULIC FLUID FOUND LEAKING FROM EMPENNAGE ON WALK-AROUND.  RUDDER PCU CAP BODY SEPARATED FROM THREADED PORTION,	 RETAINED IN AREA BY LOCKING WIRE.  THE CAP BODY HAD BROKEN AWAY FROM THE THREADED PORTION WITH THE THREADED PORTION STI	LL INSERTED IN THE PCU.  THE BROKEN AREA INDICATES A FRESH BREAK.  NO EVIDENCE OF IT BEING CRACKED FOR ANY LENGTH OF TIM	E BEFORE COMPLETE FAILURE.  NEW CAP INSTALLED PER BOEING OVERHAUL MANUAL.  PART TC:  68,717.			2	L	7	2 	4F	4	F		A16WE   	E2EA
1999021200225	19990212	00225	SW  	1999	2	12	CA981230012      	1	19981211	G	7603		PIVOT PIN       		205060727011	BELL  	205   	205A1       	1181414	SW  	LYC   	T53   	T5313B      	41549	NE  					POWER LEVER	BROKEN          	W				O				OTHER                   				O			OTHER                     			DE	DESCENT        	1			CA								LE07560A			(CAN) PILOT REPORTED THAT THE ENGINE WOULD NOT SPOOL DOWN WHEN HE TRIED TO CLOSE THE TWIST GRIP.  FOUND THE PIVOT PIN ON	 THE TORQUE TUBE ASSY BROKEN OFF ON THE RT END.  REPLACED.					1	G	7	1 	4U	4	U		H1SW    	E17EA
1999052800002	19990528	00002	SO  	1999	5	28	CA981230013      	1	19981210	G	5343	9555400	BRACKET         			PIPER 	PA34  	PA34200T    	7103406	SO  	CONT  	O360  	TSIO360EB   	17025	SO  					NLG	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3329 					234709R			(CAN) AFTER READING FEED-BACK 1/98 OF NOSE LANDING GEAR ATTACH, IT WAS NOTED THAT ATTACH POINT AND FIREWALL MOVED WHEN F	ORCE APPLIED.   INSPECTION FOUND THE STABILATOR PULLEY BRACKET WAS CRACKED AND THE RIVETS SHEARED WHICH ATTACH THE NOSE 	GEAR MOUNT FITTING.  SUBMITTER RECOMMENDS AN AD.				1	L	7	2 	3O	3	O		A7SO    	E9CE
1999040200167	19990402	00167	SO  	1999	4	2	CA981230014      	1	19981214	G	2140	42036	SWITCH          		B39059      	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					HEATER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1771583		RL82661A			(CAN) COMPLIANCE WITH AD 96-20-07 FOUND THE PRESSURE SWITCH UNSERVICEABLE.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1999040200168	19990402	00168	CE  	1999	4	2	CA981230015      	1	19981215	G	3233	1153800025	MOTOR           			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					MLG	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA								50054			(CAN) ON APPROACH, THE GEAR SELECTED DOWN AND NOTHING HAPPENED.  RESET RELAY STILL NOTHING.  MANUAL EXTENSION USED AND G	EAR LOCKED DOWN.  INVESTIGATION FOUND THE GEAR MOTOR SEEMED A LITTLE LAZY.   SUSPECT MOTOR HAS FLAT SPOT.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1999040200169	19990402	00169	CE  	1999	4	2	CA981230016      	1	19981214	G	6120	993800075	CONTROL CABLE   			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      	 	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROP CONTROL	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			7373 					52576	BU19943		(CAN) PROPELLER CONTROL CABLE FOUND BROKEN AT THE END OF THE CABLE UNDER THE PEDESTAL.						1	L	7	2 	3T	4	T	 	A14CE   	E4EA	6	C	P15EA
1999040200170	19990402	00170	NM  	1999	4	2	CA981230017      	1	19981212	G	3397		WIRE            			DHAV  	DHC8  	DHC8301     	       	NM  										E/E BAY	CHAFED          	W				K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			CA											(CAN) WIRE LOOM RUNNING TO RELAY PANEL NR 1 CONSIDERED TOO LONG AND IS CHAFING.  WIRE 3344-4B18 WAS CHAFING ON RELAY; 33	41-K2.  WHEN POWER APPLIED TO AIRCRAFT, THE WIRE WELDED ITSELF TO K2 TERMINAL B2.  THIS TURNED THE LEFT FLARE LIGHT ON A	ND IT WOULD ONLY GO OUT WHEN THE TAXI POWER CIRCUIT BREAKER WAS PULLED.  20 OTHER AIRCRAFT CHECKED AND CHAFING WAS NOTED	 ON ONE OTHER.  SUBMITTER ALSO NOTES THAT IN RELAY PANEL NR 2, IF A DOOR CABLE SHOULD BREAK OR DROOP ON THESE RELAYS, TH	E RELAYS WOULD BE SHORTED.		2	H	7	2 	4T			RT	A13NM
1999040200171	19990402	00171	SO  	1999	4	2	CA981230018      	1	19981208	G	2752	1202001	MOTOR           			PIPER 	PA31  	PA31350     	7103110	SO  										TE FLAP	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			9420 								(CAN) THE FLAP ACTUATOR MOTOR CASE THROUGH BOLTS WERE FOUND LOOSE.  THIS COULD CAUSE THE FLAPS TO LOCK.						1	L	7	2 	3O				A20SO
1999040200172	19990402	00172	CE  	1999	4	2	CA981230019      	1	19981215	G	3230		CONNECTOR       			BEECH 	99    	99          	1154002	CE  	PWA   	PT6   	PT6A20      	52043	EA  					MLG	CONTAMINATED    	W				A				UNSCHED LANDING         				O			OTHER                     			CL	CLIMB          	1			CA								PCE20586			(CAN) JUST AFTER TAKEOFF WHEN GEAR SELECTED UP, THE GEAR STAYED DOWN AND THE LANDING GEAR CIRCUIT BREAKER TRIPPED.   AIR	CRAFT RETURNED OK.  THE RIGHT GEAR SAFETY SWITCH CANNON CONNECTOR WAS DISCONNECTED AND CLEANED.					1	L	7	2 	3T	3	T		A14CE   	E4EA
1999043000094	19990430	00094	CE  	1999	4	30	CA981230021      	1	19981218	G	5520	5061000090	BRACKET         		50610000491 	BEECH 	90    	C90A        	1152911	CE  	PWA   	PT6   	PT6A21      	52043	EA  					ELEVATOR	SCRAPPED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3512 			502		PCE25675			(CAN) CRACK FOUND ON THE ELEVATOR INBOARD RIB BRACKET.  FURTHER INVESTIGATION FOUND THAT THE INBOARD RIB P/N 50-610000-3	55 AND THE FRONT SPAR FLANGE ALSO HAD CRACKS AT THE RIVET AND BOLT HOLES.  CLUSTERS OF METAL FILINGS WERE TRAPPED BETWEE	N THE BRACKET AND THE RIB.  IT WAS CONCLUDED THAT STRESS RIZERS WERE FORMED BY THE FOD BETWEEN THE TWO ASSEMBLIES LEFT T	HERE DURING MANUFACTURE.			1	L	7	2 	3T	4	T	RT	3A20    	E4EA
1999021200227	19990212	00227	NE  	1999	2	12	CA981230022      	3	19981028	G	6111	A7111D2	BLADE           													HAMSTD	54H	54H60117    	NE  	PROPELLER	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA									226865		(CAN) PROPELLER BLADE S/N'S 822228, 822230 WERE REMOVED FROM SERVICE AND SCRAPPED FOR BELOW MINIMUM TIP WIDTH (26 FEB 96	).  BLADES WERE INSPECTED (23 FEB 96) WITH INDICATIONS OF HEAVY CORROSION IN THE BLADE BUTT FILLET AREA.  THERE WAS NO I	NDICATION OF CRACKS.  BLADES WERE MACHINED (19 OCT 98) FOR EXPERIMENTAL TRIALS.  BLADES WERE ACID ETCHED AND FLUORESCENT	 PENETRANT INSPECTED AND CRACKS WERE FOUND IN THE BLADE BUTT FILLET AREA.  PRELIMINARY ANALYSIS INDICATES THE CRACKS ARE	 A RESULT OF STRESS CORROSION.												6	C	P906
1999021200228	19990212	00228	EA  	1999	2	12	CA981230023      	2	19981130	G	7230	3012521	STATOR          			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					1ST STAGE	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2496 				PCE40592			(CAN) ENGINE SENT FOR REPAIR OF UPPER ENGINE MOUNT BOLT HOLES AND FOD DAMAGE.  FOLLOWING OVERHAUL LEVEL CLEAN-UP AND NDT	 OF COMPRESSOR COMPONENTS, THE 1ST STAGE COMPRESSOR STATOR WAS FOUND TO BE CRACKED AT COMPRESSOR TIE ROD BOLT RECESSES.					1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
1999021200229	19990212	00229	NM  	1999	2	12	CA981230024      	1	19981204	G	3260	H1010153	SWITCH          			BOEING	727   	727221      	1384071	NM  	PWA   	JT8   	JT8D17      	52049	NE  					NLG	FAILED          	W				O				OTHER                   				N			FALSE WARNING             			NR	NOT REPORTED   	1			CA											(CAN) NOSE GEAR UNSAFE LIGHT ILLUMINATED IN-FLIGHT WITH GEAR HANDLE UP, NLG LOCK AND POSITION SWITCHES REPLACED.						2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200230	19990212	00230	CE  	1999	2	12	CA981230025      	1	19981215	G	3242	C30020	CALIPER HOUSING 			CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					BRAKE	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						031001		RL2419015			(CAN) CRACK FOUND ON THE CALIPER HOUSING IN THE PIN LUG AREA.						1	H	7	1 	3O	3	O	NT	3A19    	E223
1999021200232	19990212	00232	EU  	1999	2	12	CA981230027      	1	19981219	G	2435	23080006	BEARING         		23080006    	BRAERO	DH125 	BAE125800A  	1500285	EU  										START/GENERATOR	FAILED          	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA				769  		2102					(CAN) EN ROUTE, PILOT NOTED VIBRATION AND NOISE FROM RT ENGINE, ENGINE SECURED AND EMERGENCY DECLARED, AIRCRAFT LANDED O	K.  RT ENGINE STARTER GENERATOR BEARING FAILURE.  REPLACED.   PART TC:  618.					2	L	7	2 	4F			RT	A3EU
1999021200234	19990212	00234	EA  	1999	2	12	CA981230029      	1	19981217	G	7714	MS280541	SHAFT           			DHAV  	DHC7  	DHC7102     	2802708	EA  	PWA   	PT6   	PT6A50      	52043	EA  	HAMSTD	24PF	24PF305     	GL  	TACHOMETER	SHEARED         	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			358  			C4593					(CAN) WHILE IN CRUISE, THE NR 1 ENGINE TACHOMETER FAILED, THE FLIGHT CONTINUED TO ITS DESTINATION WITHOUT PROBLEMS.  POS	T-FLIGHT INSPECTION FOUND THE TACHOMETER DRIVE SHAFT SHEARED.  THE TACHOMETER WAS REPLACED AND THE AIRCRAFT RETURNED TO 	SERVICE.				2	H	7	4 	4T	4	T		A20EA   	E4EA	6	C	P1NE
1999021200235	19990212	00235	CE  	1999	2	12	CA981230030      	1	19981230	G	5541	143100213	RIB             		143100088   	CESSNA	337   	337G        	2075730	CE  	CONT  	O360  	IO360K      	17025	SO  					RUDDER	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6447 					5OR448			(CAN) .75 INCH CRACK FOUND ON RIGHT RUDDER UPPER RIB WHERE THE MASS BALANCE WEIGHT ATTACHES.  REPLACEMENT RIB FABRICATED	 PER SRM AND AC43.13 GUIDELINES.					1	H	7	2 	3O	3	O		A6CE    	E1CE
1999021200236	19990212	00236		1999	2	12	CA981230031      	4	19981126	G	6122	252476914	GOVERNOR        	BENDIX      		BELL  	206   	206B        	1181511	SW  	ALLSN 	250C  	250C20      	03013	GL  					PROPELLER	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA				451  				CAE800419BA			(CAN) AT 100 PERCENT, THE RPM SURGED UP AND DOWN.  THE GOVERNOR WAS REPLACED.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1999040200173	19990402	00173		1999	4	2	CA981230033      	1	19981203	G	2434	97079	CONNECTOR       	LUCAS       	31435       															GENERATOR	MISMANUFACTURED 	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						97079					(CAN) THIS MODEL GENERATOR USED ON THE CESSNA X AIRCRAFT, HOWEVER, THIS PARTICULAR ONE WAS USED IN LOAD BANK FOR LOADING	 GEARBOX DURING ENGINE TEST INTERMITTENT, ELECTRICAL PROBLEM NOTED. THE FEMALE CONNECTOR ON THE GENERATOR HAD PINS H AND	 A REVERSED.
1999021200238	19990212	00238	CE  	1999	2	12	CA981230034      	1	19981208	G	2810	CAV170	VALVE           			CESSNA	150   	150G        	2071816	CE  	CONT  	O200  	O200A       	17020	SO  	MCAULY	1A101	1A101DCM    	GL  	FUEL DRAIN	LEAKING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								669387A	G1247		(CAN) ONE FUEL DRAIN LEAKING AND THE OTHER STUCK.  FOUND THE STUCK DRAIN HEAVILY CORRODED WITH CORROSION ON THE PLUNGER 	ON THE INSIDE OF THE TANK.					1	H	7	1 	3O	3	O		3A19    	E252	5	N	P918
1999021200239	19990212	00239	EU  	1999	2	12	CA981230035      	1	19981208	G	7722	56785538012	INDICATOR       			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	NR 2 ENGINE ITT	FAULTY          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			15019					120631	900215		(CAN) DURING CLIMB, THE NR 2 ENGINE ITT GAUGE INDICATED OVER LIMIT ON THE ANALOG INSTRUMENT.  THE DIGITAL INSTRUMENT IND	ICATED NORMAL. THE CREW ELECTED TO RETURN TO THE DEPARTURE POINT.  THE ITT GAUGE WAS REPLACED AND THE SYSTEM WAS SERVICE	ABLE.   PART TC:  17,955.				2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE
1999021200240	19990212	00240	SO  	1999	2	12	CA981230036      	1	19981218	G	2782	D22466	ACTUATOR        			EMB   	110   	EMB110P1    	3260122	SO  	PWA   	PT6   	PT6A34      	52043	EA  					LE FLAP	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						1272		PCE57160			(CAN) FLAP ACTUATOR DUST COVER FOUND DAMAGED.   NO REPORTED FLAP OPERATION SNAGS.   PART TC:  5,015.						1	L	7	2 	4T	4	T		A21SO   	E4EA
1999021200241	19990212	00241	CE  	1999	2	12	CA981230037      	1	19981203	G	2421	646655	DRIVE           		649304      	CESSNA	404   	404CESSNA   	2075901	CE  						MCAULY	3FF32	3FF32C501   	GL  	ALTERNATOR HUB	LOOSE           	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			712  			12690210R			804566		(CAN) ALTERNATOR HUB DRIVE SEAL BECAME UNGLUED.						1	L	7	2 	3O				A25CE   		5	C	P45GL
1999021200242	19990212	00242	CE  	1999	2	12	CA981230038      	1	19981210	G	6120	1003690131	SWITCH          			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB4T	HCB4TN3     	GL  	LT PROPELLER	FAILED          	W				A				UNSCHED LANDING         				R			PARTIAL RPM/PWR LOSS      			CL	CLIMB          	1			CA								PCE50450	EAA1147		(CAN) AFTER TAKEOFF, THE LEFT HAND PROPELLER TENDED TO FEATHER.  THE PILOT CONTROLLED THE FAILURE AND MADE AN EMERGENCY 	LANDING.  INVESTIGATION REVEALED THE LOW PITCH SWITCH WAS NOT WORKING AND THERE WAS A WORN CARBON BRUSH IN THE MECHANISM	.				1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA
1999021200243	19990212	00243	NM  	1999	2	12	CA981230039      	1	19981212	G	3260	6552811115	ACCESSORY UNIT  			BOEING	737   	737242C     	1384478	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					MLG	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA								674277			(CAN) THRUST REVERSER ISOLATION VALVE LIGHT ILLUMINATED STEADY.  AIRCRAFT RETURNED.  LANDING GEAR ACCESSORY UNIT REPLACE	D PER M.M.  NLG FLIGHT TO GROUND SWITCH ADJUSTED.  AIRCRFAFT RETURNED TO SERVICE.					2	L	7	2 	4F	4	F		A16WE   	E2EA
1999040200174	19990402	00174	SO  	1999	4	2	CA981230041      	1	19981212	G	5521	40075014	SPAR            		5423220     	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					ELEVATOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			7731 			311376		L330061A			(CAN) INSPECTION PER SB 998A.  LEFT HAND SPAR FOUND CRACKED AT THE VERY TIP, OUTBOARD RIB CONNECTION.  NEW SPAR, NR 4007	5-020 INSTALLLED.					1	L	7	2 	3O	3	O		A20SO   	E14EA
1999021200244	19990212	00244	EA  	1999	2	12	CA981230043      	1	19981209	G	3246	9532472	WHEEL           	GOODYEARAERO		FRCHLD	F27   	F27F        	3373008	EA  	RROYCE	DART  	DART5297E   	54507	EU  					LT MLG	RUPTURED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				403  		473		13565			(CAN) AFTER LANDING AND DURING TAXI, THE LEFT OUTBOARD WHEEL HALF SEPARATED ALONG THE CIRCUMFERENCE.  THE WHEEL HAD BEEN	 INSPECTED AT THE LAST TIRE CHANGE AND WAS OK.  NO DAMAGE TO LANDING GEAR AS A RESULT OF SEPARATION.  INVESTIGATION AFTE	R THE INCIDENT REVEALED THAT AN EXISTING CRACK OF 3.5 INCHES LONG SUDDENLY INCREASED LEADING TO THE FRACTURE.  AN NDT CH	ECK AT EVERY TIRE CHANGE IS NOW IN FORCE.   PART TC:  355.			2	H	7	2 	4T	4	T		7A1     	E297
1999012200318	19990122	00318	EU  	1999	1	22	CA981230044      	2	19981030	G	7250	JR24217	BLADE           								RROYCE	SPEY  	SPEY5118    	54523	EU  					2ND STAGE	DAMAGED         	W				E				ENGINE SHUTDOWN         				M			OVER TEMP                 			IN	INSP/MAINT     	1			CA								8794			(CAN) DURING START AT 16 PERCENT, PILOT HEARD A LOUD BANG. THE FUEL FLOW WAS GOOD, TEMP AT 410 CELSIUS.  THEN A SECOND B	ANG AND TEMP AT 700 CELSIUS (MAX IS 570 CELSIUS).  ENGINE WAS SHUTDOWN.  INSPECTION FOUND LP TURBINE BLADES DEFORMED WIT	H PIECES OF STAGE 2 BLADES LOCATED BETWEEN THE LP2 TURBINE AND MIXER.  DEBRIS FOUND IN REAR BYPASS DUCT.  STAGE 1 TURBIN	E BLADES SHOWED VIRTUALLY NO DAMAGE, BOTH STAGE 1 AND 2 NOZZLE GUIDE VANES SHOWED HEAVY DAMAGE. THERE WAS NO METAL IN TH	E FILTER.  LAB ANALYSIS SHOWED SEVERE STRUCTURAL CHANGE OF STAGE 1 TURBINE BLADES INDICATIVE OF SEVERE OVERHEAT CONDITIO	N.  INVESTIGATION CONTINUES INTO CAUSE OF THE FAILURE.						4	F			E2EU
1999040200175	19990402	00175		1999	4	2	CA981230045      	1	19981211	G	2822	236	PUMP            	SECONDOMONA 	SM2212A     															FUEL SYSTEM	SEIZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA						236					(CAN) ELECTRICAL COMPONENTS CORRODING PREMATURELY BECAUSE OF EXTERNAL TEMPERATURE, AND  CONDENSATION.  PUMP, BEARING, AN	D SHAFT HAD BEEN RECENTLY RECONDITIONED.  PUMP WAS RECEIVED AGAIN 5 MONTHS LATER.
1999040200176	19990402	00176	SO  	1999	4	2	CA981230046      	1	19981214	G	2510	110731917	SHOULDER BELT   			PIPER 	PA31  	PA31350     	7103110	SO  										COCKPIT	FAILED          	W				O				OTHER                   				O			OTHER                     			AP	APPROACH       	1			CA											(CAN) ON APPROACH IN TURBULENCE, THE PILOT'S SHOULDER HARNESS UNCOUPLED FROM THE LAP BELT.  THIS HAD HAPPENED ON ONE PRE	VIOUS OCCASION WHEN HE HAD JUST BENT FORWARD.  SUBMITTER NOTED THAT CESSNA SB SEB96-2 APPLIES TO SAME TYPE OF BELT AND P	ROBLEM, THUS, THEY INSTALLED THE BUSHING P/N 2237-3 WHICH IS CALLED UP IN CESSNA SB.				1	L	7	2 	3O				A20SO
1999021900404	19990219	00404	EA  	1999	2	19	CA981230048      	1	19981217	G	2611	473052	SMOKE DETECTOR  			CNDAIR	CL600 	CL6002B19   		EA  										CARGO BAY	MALFUNCTIONED   	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CR	CRUISE         	1			CA											(CAN) IN CRUISE AT 33,000 FEET, FLIGHT CREW REPORTED THE 'SMOKE CARGO' WARNING EICAS MESSAGE ON.  'CARGO SMOKE MEMORY IT	EMS' PERFORMED, BUT LIGHT STAYED ON.  EMERGENCY DECLARED AND AIRCRAFT LANDED OK.  INVESTIGATION FOUND NO EVIDENCE OF SMO	KE OR FIRE. SMOKE DETECTOR GAVE FALSE WARNING.				2	L	7	2 	4F			RT	A21EA
1999021900405	19990219	00405	EA  	1999	2	19	CA981230049      	1	19981217	G	2611	473052	SMOKE DETECTOR  			CNDAIR	CL600 	CL6002B19   		EA  										CARGO BAY	FAILED          	W				A	F			UNSCHED LANDING         	ACTIVATE FIRE EXT.      			N	W		FALSE WARNING             	INADEQUATE Q C            		CR	CRUISE         	1			CA											(CAN) ON INBOUND LEG, CREW ALERTED TO SMOKE ALARM IN CARGO COMPARTMENT.  HALON BOTTLES DISCHARGED AND AN EMERGENCY DECLA	RED.  AIRCRAFT LANDED OK.  EMERGENCY EXITS USED AND SOME DAMAGE DONE TO EXIT WINDOWS AND WING, AND SOME OTHER MINOR DAMA	GE.  AIRCRAFT SMOKE DETECTOR HAD BEEN MODIFIED TO WALTER KIDDE SL 92-3, BUT APPEARS NOT TO HAVE BEEN CARRIED OUT CORRECT	LY.			2	L	7	2 	4F			RT	A21EA
1999021200250	19990212	00250	EA  	1999	2	12	CA981230057      	2	19981008	G	7314	3022375	SEAL            			DHAV  	DHC6  	DHC6300     	2802606	EA  	PWA   	PT6   	PT6A27      	52043	EA  					FUEL PUMP	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CL	CLIMB          	1			CA								PCE41410			(CAN) THE NR 2 ENGINE OIL PRESSURE DROPPED BELOW 80 PSI ON FLIGHT.  THE POWER WAS REDUCED AND THE AIRCRAFT LANDED.  POST	-FLIGHT INSPECTION FOUND OIL ON THE ENGINE COWLING.  IT WAS DETERMINED THAT THE OIL WAS LEAKING FROM THE FUEL PUMP DRAIN	.  THE NR 2 ENGINE FUEL PUMP DRIVE SEAL WAS FOUND DEFECTIVE.  A NEW SEAL WAS INSTALLED AND THE OIL LEVEL REPLENISHED.  A	N ENGINE GROUND RUN WAS CARRIED OUT AND THERE WERE NO LEAKS.			1	H	7	2 	3T	4	T	RT	A9EA    	E4EA
1999040200178	19990402	00178	CE  	1999	4	2	CA981230060      	1	19981208	G	5740	8278414	BOLT            			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  					WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			789  					PCE41728			(CAN) WHILE DOING AD CF-81-25R5, NDT TEST SHOWED A SMALL CRACK IN THE RADIUS OF THE BOLT HEAD.  IT IS POSSIBLE THAT CRAC	K IS OVERLAP OF CAD PLATING.					1	L	7	2 	3T	4	T		A14CE   	E4EA
1999021200251	19990212	00251	NE  	1999	2	12	CA981230062      	2	19981214	G	7210	310119101	BEARING         								PWA   	118   	PW118       		NE  					GEARBOX	SPALLED         	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			26473	9426 		16A895		115103			(CAN) THE ENGINE WAS SENT FOR INVESTIGATION AND OVERHAUL AFTER THE OPERATOR REPORTED THE REDUCTION GEARBOX WAS MAKING ME	TAL.  INVESTIGATION FOUND THE REDUCTION GEARBOX WAS MAKING METAL DUE TO A SPALLED NR 10 BEARING.  THE BEARING OPERATED F	OR 26,473.3 HOURS AND IT WAS THOUGHT LIKELY THE BEARING WHICH NOW HAS A SOFT TIME OF 8,000 HOURS, FAILED DUE TO LIFE LIM	ITATIONS.  MAGNETISM FOUND ON VARIOUS COMPONENTS WAS INDICATIVE OF A LIGHTNING STRIKE.  THE NR 15 AND NR 19 BEARINGS HAD	 ELECTRICAL DAMAGE (ARCING) CONSISTENT WITH HIGH LEVELS OF ELECTRICAL CURRENT.  MAGNETISM WAS NOTED ON THE RT NR 10 BEAR	ING AND IT IS CONSIDERED POSSIBLE THE BEARING SPALLED DUE TO ELECTRICAL PITTING.   PART TC:  26,609.						4	T			E20NE
1999021200252	19990212	00252	EA  	1999	2	12	CA990111001      	2	19981218	G	8530	5015	STUD            			CESSNA	172   	172P        	2072436	CE  	LYC   	O320  	O320D2J     	41508	EA  					NR 1 CYLINDER	BROKEN          	W				D				RETURN TO BLOCK         				E			VIBRATION/BUFFET          			TX	TAXI/GRND HDL  	1			CA				1330 				L1198039A			(CAN) DURING TAXI, A VIBRATION WAS FELT FROM THE ENGINE.  INSPECTION AFTER RETURN TO RAMP FOUND ONE .50 INCH STUD AND TH	REE .3750 STUDS AT NR 1 CYLINDER BROKEN.  ALL CYLINDERS WERE REMOVED AND INSPECTED FOR CRACKS AND CONFORMITY.  ALL CYLIN	DERS WERE SERVICEABLE AND REINSTALLED WITH NEW GASKETS. THE ENGINE WAS GROUND RUN AND TEST FLOWN SERVICEABLE.				1	H	7	1 	3O	3	O	NT	3A12    	E274
1999012200319	19990122	00319	EA  	1999	1	22	CA990111002      	2	19981221	G	7322	105288	CARBURETOR      			CESSNA	172   	172Q        	2072437	CE  	LYC   	O360  	O360A4N     	41514	EA  					ENGINE	MALFUNCTIONED   	W				A				UNSCHED LANDING         				R	Y		PARTIAL RPM/PWR LOSS      	ENGINE STOPPAGE           		NR	NOT REPORTED   	1			CA				1702 				L3113736A			(CAN) DURING FLIGHT, THE PILOT NOTICED A SMALL DROP IN POWER AND RETURNED TO THE AIRPORT.  SHORTLY BEFORE TOUCH DOWN THE	 ENGINE QUIT.  ONCE CLEAR OF THE RUNWAY THE ENGINE WAS RESTARTED AND RAN OK.  SUSPECTING CARBURETOR PROBLEM, THE CARBURA	TOR WAS REPLACED.  THE CARBURETOR SENT FOR INVESTIGATION AND REPAIR.				1	H	7	1 	3O	3	O	NT	3A12    	E286
1999043000096	19990430	00096	CE  	1999	4	30	CA990111003      	1	19981230	G	2752	100384040	MOTOR           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					TE FLAP	FAILED          	W				G				O2 MASK DEPLOYED        				B			SMOKE/FUMES/ODORS/SPARKS  			CR	CRUISE         	1			CA			2799 			2069		PCEPS0149			(CAN) CREW DETECTED AN ODOR FOLLOWED BY SMOKE.  DEPLOYED OXYGEN.  LANDING MADE OK.  THE FLAP MOTOR WAS FOUND BLACKENED A	ND EMITTING ODOR.  MOTOR WAS SEIZED.  THE 20-AMP CIRCUIT BREAKER HAD TRIPPED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999043000098	19990430	00098	CE  	1999	4	30	CA990111005      	1	19981211	G	5753	12210108	TRACK           			CESSNA	182   	TR182       	2072735	CE  						MCAULY	3D32C	B3D32C407   	GL  	TE FLAP	BENT            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1695 						820802		(CAN) BOTH RIGHT HAND FLAP TRACKS FOUND BENT.						1	H	7	1 	3O				3A13    		5	C	EXPP
1999012900953	19990129	00953	WP  	1999	1	29	CA990111006      	1	19981214	G	6320	B1151	BEARING         			ROBSIN	R44   	R44         	7640120	WP  	LYC   	O540  	O540F1B5    	41532	EA  					MAIN ROTOR	MISINSTALLED    	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			937  					L2479140A			(CAN) DURING MAIN ROTOR REPLACEMENT, A LARGE AMOUNT OF ROTATIONAL PLAY, APPROXIMATELY 2 INCHES DISCOVERED, MAX SHOULD BE	 0.060 INCH.  UPPER YOKE ASSY BEARINGS IMPROPERLY INSTALLED, NOT PRESSED IN DEEP ENOUGH AND AT AN ANGLE, SCORING THE YOK	E.  INBOARD ARM ATTACH BOLT WAS NOT PROPERLY TORQUED.  INBOARD ARM AND OUTER BOLT HOLE BADLY ELONGATED.  REPLACED YOKE A	SSY, SPACERS, BOLT AND ARM.			1	G	7	1 	3O	3	O		H11NM   	E295
1999021200253	19990212	00253	SW  	1999	2	12	CA990111007      	1	19981215	G	5730	273101712	RIVETS          			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					WS 98 & 100	SHEARED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			17984					P54151			(CAN) THE RIVETS WHICH FASTEN THE UPPER WING SKIN TO THE FLAP ACTUATOR CASTING ASSEMBLY WERE FOUND SHEARED AND PULLED TH	ROUGH, AT WS 98.385 AND WS 100.635.  THIS AREA IS DIRECTLY BEHIND THE EXHAUST STACK, APPEARS TO BE THE KEY FACTOR TO THE	 DEFECT.  FLEET BEING INSPECTED.  RIVETS WERE PULLED THROUGH WHERE THE UPPER WING SKIN IS ATTACHED.   PART TC:  28,383.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999021200254	19990212	00254	EU  	1999	2	12	CA990111008      	1	19981221	G	2921	AIR872541	ACCUMULATOR     			BRAERO	748   	HS7482A     	4231001	EU  										HYDRAULIC SYSTEM	LEAKING         	W				C				ABORTED TAKEOFF         				K			FLUID LOSS                			TO	TAKEOFF        	1			CA				1604 		LK0690					(CAN) ON TAKEOFF AFTER GEAR SELECTED UP, BOTH HYDRAULIC FLOW LIGHTS ILLUMINATED.  AIRCRAFT RETURNED TO BLOCKS.  HYDRAULI	C ACCUMULATOR HAD INTERNAL LEAK, REPLACED.  HYDRAULIC SYSTEM TOPPED UP.  AIRCRAFT SERVICEABLE.   PART TC:  1,384.					2	L	7	2 	3T				A24EU
1999021900406	19990219	00406	CE  	1999	2	19	CA990111009      	1	19981221	G	2435	133M	BRUSHES         	BENDIX      	30B3749B    	LEAR  	25    	25B         	5170511	CE  	GE    	CJ610 	CJ6106      	30006	NE  					START/GEN	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			76   			133M		241C210A			(CAN) BRUSHES WORN IN JUST 100 HOURS TIME IN-SERVICE THE FIRST TIME.  THEN REPAIRED AND WORN IN 76 HOURS THE SECOND TIME	.  BRUSH HOLDER END BELL ASSY INCORRECTLY RIGGED CAUSING A HIGH FIELD CURRENT.					2	L	7	2 	4J	4	J		A10CE   	1E16
1999043000099	19990430	00099	CE  	1999	4	30	CA990111010      	1	19981226	G	3240	1013800157	HOSE            			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	MCAULY	4HFR34	4HFR34C754  	NE  	BRAKE DEICE	DETERIORATED    	W				O				OTHER                   				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		LD	LANDING        	1			CA			154  					PCE81062	300783		(CAN) NR 1 AND NR 2 TIRES BLEW ON LANDING DUE TO BEING FROZEN. THE LEFT BRAKE DE-ICE HOSE HAD DETERIORATED FROM THE HEAT	 AND BROKE INTO SMALL PIECES, PLUGGING THE LINE TO THE HEAT MANIFOLDS AND LETTING BRAKE DE-ICE PRESSURE ESCAPE.					1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	3PNE
1999021200255	19990212	00255	NM  	1999	2	12	CA990111011      	1	19981229	G	2910	10320421	REGULATOR       			BOEING	737   	737275      	1384485	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					HYDRAULIC SYSTEM	CRACKED         	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA						061B		P665183			(CAN) HYDRAULIC REGULATED FLOW REGULATOR BODY CRACKED 360 DEGREES AROUND END ONE INCH FROM END FITTING.  REPLACED.						2	L	7	2 	4F	4	F		A16WE   	E2EA
1999021200256	19990212	00256	NM  	1999	2	12	CA990111013      	1	19981223	G	2140	32140211	VALVE           			BOEING	727   	72722       	1384002	NM  	PWA   	JT8   	JT8D7B      	52053	NE  					RT PACK	INTERMITTENT    	W				A				UNSCHED LANDING         				M	J		OVER TEMP                 	WARNING INDICATION        		CL	CLIMB          	1			CA				2001 		P168		648824			(CAN) DURING CLIMB, RT AIR CONDITIONING PACK TRIPPED WITH DUCT OVERHEAT.  RT MIX VALVE REMAINED FULL HOT AND WOULD NOT R	ESPOND TO SELECT POSITION.  RT PACK REQUIRED FOR SMOKE EVACUATION.  AIRCRAFT RETURNED.  MIX VALVE WORKED A FEW TIMES THE	N FAILED, REPLACED.   PART TC:  1,601.				2	L	7	3 	4F	4	F		A3WE    	E2EA
1999021200257	19990212	00257	NE  	1999	2	12	CA990111014      	2	19981211	G	7313	3011158	LOCK PLATE      								PWA   	PT6   	PT6A67D     		NE  					FUEL NOZZLE	MISSING         	W				A				UNSCHED LANDING         				K	X	W	FLUID LOSS                	ENGINE FLAMEOUT           	INADEQUATE Q C            	CL	CLIMB          	1			CA			100  					PCEPRO102			(CAN) DURING CLIMB-OUT,THE ENGINE LOST POWER.  THE WINDSHIELD BECAME OBSCURED WITH FUEL AND THE ENGINE FLAMED OUT.  THE 	AIRCRAFT MADE A 180 DEGREE AND LANDED SAFELY.  POST-FLIGHT INVESTIGATION FOUND THE FUEL TRANSFER LOCKING PLATE ON NR 14 	FUEL NOZZLE WAS NOT INSTALLED AT THE MANUFACTURER.   PART TC:  77.									4	T			E26NE
1999012900954	19990129	00954	NE  	1999	1	29	CA990111015      	2	19980831	G	7532	9550158260	BLEED VALVE     			SNIAS 	350   	AS350B      	8680801	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	CONTAMINATED    	W				O				OTHER                   				R			PARTIAL RPM/PWR LOSS      			LD	LANDING        	1			CA			2071 			557		946			(CAN) BLEED VALVE BUTTERFLY VALVE WAS FOUND TO BE OUT OF RIG POSSIBLY SINCE OVERHAUL. THE RACK AND PINION RIGGING OF THE	 SECTOR GEAR WAS OUT BY ONE TOOTH RESULTING IN NON-PERPENDICULAR CONDITION TO THE AIR FLOW.  INTERNAL COMPONENTS OF THE 	VALVE VERY DIRTY CONDITION FROM ENGINE BLEED AIR AND FINE METAL DUST FROM INTERNAL SPRING VIBRATION AND CHAFING ON THE V	ALVE HOUSING.  DIRTY CONDITION MAY HAVE CAUSED DELAYED CLOSING UNDER HIGH POWER SETTING.			1	G	7	1 	3U	3	U		H9EU    	E19EU
1999061000014	19990610	00014	EU  	1999	6	10	CA990111016      	1	19981201	G	2435	03601018	BEARING         	AVITECH     	23079005    	BAG   	JETSTM	JETSTM4112  		EU  						ROTOL	R333	R333482F12  	GL  	START/GENERATOR	FAILED          	W				O				OTHER                   				H			ELECT. POWER LOSS-50 PC   			NR	NOT REPORTED   	1			CA			800  			5870			DRG189488		(CAN) GENERATOR WOULD NOT COME ON-LINE.  ARMATURE BEARING AT THE ANTI-DRIVE END HAD DISINTEGRATED.  BALL CAGE AND OUTER 	SEAL WERE MISSING AND THE ARMATURE WAS CONTAINED ONLY BY STATOR HOUSING.  CAGE AND SEAL PIECES WERE FOUND EMBEDDED IN AR	MATURE AND FIELD COILS.  THE ARMATURE AND FIELD POLE STACKS WERE RUBBED BEYOND REPAIR.  FAN DAMAGED FROM RUBBING ON AIR 	INLET, AND END BEARING LINER FOUND WORN DOWN.  CAUSE OF BEARING FAILURE CAN BE IMPROPER INSTALLATION OR ARMATURE IMBALAN	CE.   BEARING IS CORRECT PART.		1	L	7	2 	4T			RT	A196    		6	C	P61G
1999030500180	19990305	00180	EU  	1999	3	5	CA990111025      	1	19981212	G	2720		ROD             			START 	SALTO 	H101        		EU  										RUDDERVATOR	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1009 								(CAN) DURING 10 YEAR LONG SERVICE LIFE INSPECTION PROGRAM, EXCESSIVE WEAR ON THE OUTER SURFACE OF BOTH RUDDERVATOR CONTR	OL RODS WAS OBSERVED. THIS WEAR IS IN THE ROD CENTER SECTION WHERE IT PASSES THROUGH THE MID-FUSELAGE CENTER SECTION GUI	DE ROLLERS.  FOUR FLAT SPOTS ON THE TUBE SURFACE ARE WORN TO AN AVERAGE OF 20 PERCENT OF THE WALL THICKNESS OF 1.0 MM. T	HE WEAR ON THESE TUBES CANNOT BE SEEN UNLESS THE ROD IS COMPLETELY REMOVED FROM THE AIRCRAFT.  REPLACED.			1	K	0	0 					G28EU
1999021200262	19990212	00262	NM  	1999	2	12	CA990111027      	1	19981218	G	2131	7612608	CONTROLLER      			BOEING	727   	727260      		NM  	PWA   	JT8   	JT8D17      	52049	NE  					CABIN PRESSURE	FAILED          	W				O				OTHER                   				K			FLUID LOSS                			DE	DESCENT        	1			CA				97   				P689955			(CAN) ON DESCENT, PRESSURIZATION MODE SET TO LAND AT 3,550 FEET.  CABIN DESCENDED TO SEA LEVEL.  PRESSURIZATION REINSTAT	ED USING STANDBY MODE.  CABIN PRESSURE CONTROLLER REPLACED.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1999021200263	19990212	00263	NM  	1999	2	12	CA990111029      	1	19981219	G	5311		FRAME           			BOEING	727   	727277      	138408S	NM  	PWA   	JT8   	JT8D15      	52051	NE  					BS 1166	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			62100					695337			(CAN) FRAME DAMAGED AT STA 1166 LT SIDE OF A/C 4 INCHES ABOVE FLOOR LEVEL BY CARGO PALLET.  BENT BACK AND FLANGE TORN AN	D 1.5 INCH CRACK IN FRAME.  REPAIRED.   PART TC:  37,619.					2	L	7	3 	4F	4	F	RT	A3WE    	E2EA
1999052800007	19990528	00007	CE  	1999	5	28	CA990111034      	1	19981222	G	3020	651445023	TUBE            			CESSNA	500   	550         	2076604	CE  	PWA   	JT15  	JT15D4      	52112	NE  					ANTI-ICE SYSTEM	CHAFED          	W				O				OTHER                   				N			FALSE WARNING             			DE	DESCENT        	1			CA			3177 					71747			(CAN) ON DESCENT, THE LEFT ENGINE ANTI-ICE ANNUNCIATION WOULD NOT EXTINGUISH WITHIN 2 MINUTES AFTER SELECTED PER OPERATI	NG MANUAL. TWO CONTACTS OF TEMP LO SWITCH P/N S105 WHICH ARE ON INSIDE OF THE LEFT HEATED LEADING EDGE WERE FOUND SHORTI	NG ACROSS AN ALUMINUM PNEUMATIC AIR DELIVER TUBE.  SHORT WAS PROVIDING A CONSTANT GROUND TO KEEP LIGHT ON.				1	L	7	2 	4F	4	F		A22CE   	E1NE
1999021200268	19990212	00268	CE  	1999	2	12	CA990111051      	1	19981115	G	5610	9031002P	WINDSHIELD      			BEECH 	100   	B100        	1152919	CE  	GARRTT	TPE331	TPE3316252B 	01514	WP  					COCKPIT	CRACKED         	W				A				UNSCHED LANDING         				O			OTHER                     			CR	CRUISE         	1			CA								CDA3597			(CAN) IN CRUISE, THE COPILOT'S WINDSHIELD SUDDENLY CRACKED.  AIRCRAFT LANDED OK.						1	L	7	2 	4T	4	T		A14CE   	E2WE
1999021200269	19990212	00269	SW  	1999	2	12	CA990111052      	1	19981218	G	3213	OAS545355A	YOKE            			SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NLG WHEEL	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			13875					P54142C			(CAN) DURING INSPECTION FOR AD 96-19-05, TWO .25 INCH CRACKS, ONE ON THE NOSE AND THE OTHER ON THE LEFT SIDE WERE FOUND.	  THESE CRACKS ONLY VISIBLE WITH SPECIAL INSTRUMENTS.  NOSE GEAR P/N 27-52500-007.   PART TC:  14,527.					2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
1999052800008	19990528	00008	EA  	1999	5	28	CA990111053      	1	19981222	G	2730	215T9249113	ACTUATOR        			CNDAIR	CL215 	CL2156B11415		EA  										ELEVATOR	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			529  								(CAN) DURING FIRST 72 HOUR INSPECTION, AN ANNOMALY WAS FOUND WITH THE TWO ELEVATOR ACTUATORS. THERE WAS PLAY BETWEEN THE	 SPHERICAL BEARING BALL AND THE RACE OF THE CONNECTION BETWEEN THE ACTUATOR AND ELEVATOR.					2	H	7	2 	4T			RT	A14EA
1999021200270	19990212	00270	EU  	1999	2	12	CA990111054      	1	19981229	G	7931	81071100010A	TRANSMITTER     			AEROSP	ATR42 	ATR42300    	8680920	EU  	PWA   	120   	PW120       		NE  	HAMSTD	14SF	14SF5       	NE  	NR 1 ENGINE	READS LOW       	W				A	E			UNSCHED LANDING         	ENGINE SHUTDOWN         			N			FALSE WARNING             			CR	CRUISE         	1			CA								120352	870322		(CAN) DURING CRUISE, THE CREW NOTICED THE OIL PRESSURE INDICATION ON NR 1 ENGINE WAS LOW.  THE ENGINE WAS SHUT DOWN.  TH	E AIRCRAFT RETURNED TO ITS DEPARTURE POINT.  THE OIL PRESSURE TRANSMITTER WAS CONFIRMED AS THE FAULT AND WAS REPLACED.					2	H	7	2 	4T	4	T	RT	A53EU   	E20NE	6	C	P7NE
1999021200271	19990212	00271	NM  	1999	2	12	CA990111055      	1	19981217	G	2923	55098D8	PLATE           			BOEING	737   	7372A9C     	1384495	NM  	PWA   	JT8   	JT8D9A      	52048	NE  					HYD PUMP	MISSING         	W				K				NONE                    				K			FLUID LOSS                			CR	CRUISE         	1			CA						124572H		674382			(CAN) LOST A SYSTEM HYDRAULIC PRESSURE, NR 1 ENGINE HYDRAULIC PUMP INOPERABLE.  FOUND BLANKING PLATE ON SIDE OF PUMP WAS	 SEPARATED FROM PUMP.  PUMP REPLACED, PUMP CASE DRAIN FILTERS REPLACED, FUNCTIONAL AND LEAK CHECK CARRIED OUT SERVICEABL	E.				2	L	7	2 	4F	4	F		A16WE   	E2EA
1999052800009	19990528	00009	SO  	1999	5	28	CA990111057      	1	19981222	G	2810	3119202	RETAINER        			PIPER 	PA23  	PA23250     	7102308	SO  	LYC   	O540  	IO540C4B5   	41532	EA  					FUEL FILLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			6916 					L372748			(CAN) CARRYING OUT AD 88-21-07R1 TO PREVENT WATER ENTERING FUEL FILLER, 2 RIVETS HOLDING THE RETAINING PLATE TO COVER WE	RE FOUND POPPED.  AT REMOVAL , THE RUBBER GASKET P/N 31190-00, WAS FOUND ROTTEN.					1	L	7	2 	3O	3	O		1A10    	1E4
1999021200272	19990212	00272	EA  	1999	2	12	CA990111058      	2	19980904	G	8520	SL18840	CAMSHAFT        			CESSNA	177   	177RG       	2073709	CE  	LYC   	O360  	IO360A1B6   	41514	EA  	MCAULY	2D34C	B2D34C207   	GL  	ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			223  					L982551A	830489		(CAN) THE ENGINE WAS REMOVED DUE TO METAL CONTAMINATION IN THE OIL.  DURING DISASSEMBLY OF THE ENGINE, PREMATURE WEAR WA	S NOTICED OF THE LIFTER BODY FACE AND OF THE INTAKE AND EXHAUST VALVES OF NR 1 CYLINDER; OF THE INTAKE VALVE OF NR 3 CYL	INDER IN THE FORM OF SPALLING AND GALLING AND OF THE AFFECTED CAMSHAFT LOBES. THE FOUR PISTONS HAD SCRATCHES AND MANY ME	TAL PARTICLES IMPREGNATED IN THE PISTON FACE.  ALL DEFECTIVE PARTS WERE REPLACED AND THE ENGINE WAS REPAIRED.			1	H	7	1 	3O	3	O		A20CE   	1E10	5	C	P7EA
1999052800010	19990528	00010	CE  	1999	5	28	CA990111059      	1	19981216	G	2435	23085001	GENERATOR       	LUCAS       		BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					START/GENERATOR	OVERHEATED      	W				A				UNSCHED LANDING         				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		CR	CRUISE         	1			CA			968  			521		PCE32185			(CAN) GENERATOR LIGHT ON IN-FLIGHT.  NO STARTER FUNCTION AFTER LANDING.   BURNT ELECTRICAL SMELL AT GENERATOR.  REPLACED	 GENERATOR.					2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1999021900416	19990219	00416	SO  	1999	2	19	CA990115001      	1	19981220	G	3230		CIRCUIT BREAKER 			PIPER 	PA30  	PA30        	7103002	SO  	LYC   	O320  	IO320B1A    	41508	EA  					MLG	FAILED          	W				B	A			EMER. DESCENT           	UNSCHED LANDING         			P			NO WARNING INDICATION     			AP	APPROACH       	1			CA								32055			(CAN) LANDING GEAR CIRCUIT BREAKER TRIPPED INTERNALLY, BUT THE BREAKER DID NOT TRIP.						1	L	7	2 	3O	3	O		A1EA    	1E12
1999021200275	19990212	00275	NE  	1999	2	12	CA990115003      	3	19981217	G	6111	R6510A0	BLADE           													HAMSTD	23E	23E50       	NE  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				430  					P89690		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  THE PROPELLER BLADES WERE FOUND CORRODED AT THE TAPER BORES.																6	C	P603
1999021200276	19990212	00276	GL  	1999	2	12	CA990115004      	3	19981229	G	6110	2464	PROPELLER       			MOONEY	M20   	M20B        	5870206	SW  	LYC   	O360  	O360A1D     	41514	EA  	MCAULY	2D36C	2D36C14     	GL  	NOSE	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L2650136A	61865		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  EXTENSIVE WEAR AND CORROSION MADE THE PROPELLER UNREPAIRABLE. THE PR	OPELLER WAS RETURNED TO THE CUSTOMER.					1	L	7	1 	3O	3	O		2A3     	E286	5	C	P901
1999021200277	19990212	00277	GL  	1999	2	12	CA990115005      	3	19981111	G	6114	B3406	HUB             			BEECH 	100   	A100        	1152915	CE  	PWA   	PT6   	PT6A28      		EA  	HARTZL	HCB4T	HCB4TN3     	GL  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3202 	1778 				PCE42500	EAA1117		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE CYLINDER WAS FOUND WORN BEYOND LIMITS.						1	L	7	2 	3T	4	T		A14CE   	E4EA	6	C	P40EA
1999021200278	19990212	00278	GL  	1999	2	12	CA990115006      	3	19981112	G	6111	A1635158	BLADE           													MCAULY	3FF32	3FF32C501   	GL  	PROPELLER	LOOSE           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				1666 					806493		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  PROPELLER BLADE PIN BASE SCREW WAS FOUND LOOSE.																5	C	P45GL
1999021200279	19990212	00279	GL  	1999	2	12	CA990115007      	3	19981112	G	6111	F7666A	BLADE           			CESSNA	172   	172G        	2072420	CE  	LYC   	O360  	O360A1A     	41514	EA  	HARTZL	HCC2Y	HCC2YK1     	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1659 	198  				L1744336A	CH11711		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  SEVERE STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES LEADING EDGES.						1	H	7	1 	3O	3	O	NT	3A12    	E286	5	C	P920
1999021200280	19990212	00280	GL  	1999	2	12	CA990115008      	3	19981130	G	6111	V8433	BLADE           			CESSNA	310   	310B        	2074208	CE  	CONT  	O470  	O470M       	17026	SO  	HARTZL	HC82V	HC82V*      	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				141  				536396HR	TF1410		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION. THE PROPELLER BLADES WERE FOUND STONE DAMAGED.  THE PROPELLER BLADES 	WERE TRIMMED.					1	L	7	2 	3O	3	O		3A10    	E273	5	C	P23EA
1999021200281	19990212	00281	GL  	1999	2	12	CA990115009      	3	19981130	G	6111	V8433	BLADE           			CESSNA	310   	310B        	2074208	CE  	CONT  	O470  	O470M       	17026	SO  	HARTZL	HC82V	HC82V*      	GL  	PROPELLER	DAMAGED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1509 	141  				536396HR	F1478N		(CAN) PROPELLER RECEIVED FOR CORROSION INSPECTION.  STONE DAMAGE WAS FOUND ON THE PROPELLER BLADES.  THE BLADES WERE TRI	MMED.					1	L	7	2 	3O	3	O		3A10    	E273	5	C	P23EA
1999012900220	19990129	00220	EU  	1999	1	29	CA990115013      	2	19981218	G	7250		TURBINE         			FOKKER	F28   	F28FOKKER*  		EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					ENGINE	DAMAGED         	W				C				ABORTED TAKEOFF         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		TO	TAKEOFF        	1			CA								9036			(CAN) TAKEOFF WAS ABORTED DUE TO ENGINE VIBRATION, WHICH WAS HEAVIEST AT 92% N2, AND UNSTABLE ENGINE PARAMETERS. ICING C	ONDITIONS WERE PRESENT. NEITHER CLEANING NOR FUEL BLEED CLEARED THE PROBLEM. VISUAL INSPECTION FOUND THE LOW PRESSURE TU	RBINE DAMAGED, WITH A BLADE MISSING.				2	H	7	2 	4F	4	F		A20EU   	E2EU
1999012900221	19990129	00221	EU  	1999	1	29	CA990115025      	2	19981118	G	7250		BLADE           			FOKKER	F28   	F28MK1000   	4990808	EU  	RROYCE	SPEY  	SPEY55515   	54521	EU  					TURBINE SECTION	FAILED          	W				E				ENGINE SHUTDOWN         				E	J		VIBRATION/BUFFET          	WARNING INDICATION        		CR	CRUISE         	1			CA								9117			(CAN) PROVISIONAL ASSESSMENT IS THE LP TURBINE HAD A BLADE FAILURE.						2	L	7	2 	4F	4	F	RT	A20EU   	E2EU
1999021200287	19990212	00287	EU  	1999	2	12	CA990115027      	1	19981220	G	2740	68560671	CONTROL CABLE   			PARTEN	P68   	P68C        	6780105	EU  	LYC   	O360  	IO360A1B6   	41514	EA  					STAB TRIM	FRAYED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2664 			320282		L2370951A			(CAN) STABILIZER TRIM TAB CABLE FOUND FRAYED AROUND THE PULLEYS AT STA. 4						1	H	7	2 	3O	3	O	 	A31EU   	1E10
1999021200290	19990212	00290	NE  	1999	2	12	CA990115031      	2	19981222	G	7260	310063001	BEARING         			DHAV  	DHC8  	DHC8*       		NM  	PWA   	120   	PW120A      		NE  					GEARBOX	FAILED          	W				E				ENGINE SHUTDOWN         				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			23804	2513 				120204			(CAN) THE ENGINE HAD AN UNCOMMANDED SHUTDOWN AT 9,000 FEET.  THE ENGINE WAS SENT FOR INVESTIGATION AND IT WAS DETERMINED	 THE ENGINE SHUTDOWN WAS A LOSS OF FUEL FLOW AS A RESULT OF LOSS OF DRIVE TO THE ACCESSORY GEARBOX.  THIS WAS A RESULT O	F A FAILURE OF THE UPPER TOWERSHAFT BEARING WHICH CAUSED LOSS OF LOCATION OF THE UPPER END OF THE TOWERSHAFT ASSEMBLY, A	LLOWING THE UPPER SPIRAL BEVEL GEAR TO MOVE OUT OF ENGAGEMENT AND THEREBY LOSE DRIVE TO THE ACCESSORY GEARBOX AND THE FU	EL PUMP DRIVE.   PART TC:  32,575.		2	H	7	2 	4T	4	T	RT	A13NM   	E20NE
1999021200291	19990212	00291	NE  	1999	2	12	CA990115032      	2	19981224	G	7240	311237901	RING            			AEROSP	ATR72 	ATR72       		EU  	PWA   	PW120 	PW127       		NE  					COMBUSTION LINER	MISSING         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1964 					AV0025			(CAN) THE ENGINE WAS SENT FOR REPAIR AND INVESTIGATION AFTER A BORESCOPE INSPECTION FOUND THE OUTER COMBUSTION LINER DAM	AGED.  DISASSEMBLY FOUND THE ENGINE HAD A 1.25 INCH LONG SECTION OF THE MAIN COOLING RING MISSING FROM THE OUTER COMBUST	ION LINER.  THE INNER COMBUSTION LINER HAD MULTIPLE CIRCUMFERENTIAL CRACKS NEAR THE FORWARD FLANGE SUPPORT RING.  THE TR	AILING EDGE LIP OF THE HP VANE SEGMENTS HAD CRACKS AND VOIDS ASSOCIATED WITH CORROSION OR HOT GAS DETERIORATION.   PART 	TC:  2,705.		2	H	7	2 	4T	4	T	RT		E20NE
1999022000002	19990220	00002	EA  	1999	2	20	CA990119001      	1	19981216	G	5711	22B4131A	FITTING         			SCWZER	SG2   	SGS233      	8051604	EA  										WING	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3867 								(CAN) MPI OF SPAR FITTING REVEALED A CRACK IN THE CENTER OF THE WELD STARTING AT THE END AND GOING AFT.  UNABLE TO DETER	MINE HOW FAR BACK THE CRACK GOES.  FITTING REQUIRES COMPLETE REMOVAL.  MANUFACTURER NOTIFIED.					1	K	0	0 					G2EA
1999021200293	19990212	00293	EA  	1999	2	12	CA990119002      	2	19981223	G	7200		ENGINE          			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 1	MALFUNCTIONED   	W				O				OTHER                   				M	J		OVER TEMP                 	WARNING INDICATION        		CR	CRUISE         	1			CA			13492	3432 				60220			(CAN) NR 1 ENGINE EXHIBITED HIGH ITT, CAUSING A MARGINAL POWER ASSURANCE CHECK.  THE ENGINE WAS REPLACED AND THE AIRCRAF	T RETURNED TO SERVICE.   PART TC:  7,225.					1	G	7	1 	4U	4	U		H4SW    	E22EA
1999021200946	19990212	00946	SW  	1999	2	12	CA990119011      	1	19981229	G	3213	20405040049	CROSS TUBE      		204050400001	BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					MLG	CRACKED         	W				K				NONE                    				O			OTHER                     			LD	LANDING        	1			CA								LE08135			(CAN) CROSS TUBE SHEARED ON LANDING CAUSING DAMAGE TO FUSE AND TAIL BOOM.  CRACK IS BELIEVED TO HAVE STARTED AT AN INTER	NAL CORROSION PIT OR VOID.					1	G	7	1 	4U	4	U		H1SW    	E1EA
1999012900955	19990129	00955	NE  	1999	1	29	CA990119026      	2	19980825	G	7261	LK74838	OIL PUMP        		M06626AB    	BOEING	757   	75723A      	1384967	NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					NR 2 ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J	E		WARNING INDICATION        	VIBRATION/BUFFET          		CR	CRUISE         	1			CA						DM3750		30739			(CAN) DURING FLIGHT, EICAS MESSAGE INDICATED LOSS OF OIL PRESSURE AND HIGH VIBRATIONS ON NR 2 ENGINE.  AIRCRAFT DIVERTED	.  ENG DISASSEMBLY AND REMOVAL OF OIL PUMP FOUND LOSS OF DRIVE AT THE OIL PUMP QUILL SHAFT.  SUBSEQUENT STRIP OF 06 MODU	LE REVEALED LOSS OF TORQUE AT THE OIL PUMP DRIVE GEAR SECURING RING NUT AND COMPLETE WEAR-AWAY OF SPLINES ON THE HIGH PR	ESSURE FUEL PUMP GEARSHAFT AND THE MATING SPLINES IN OIL PUMP DRIVE GEAR.  NO OTHER GEAR TRAIN WAS FOUND DEFECTIVE WITHI	N THE GEARBOX.  STRIP OF THE OIL PUMP FOUND NO SIGNIFICANT DAMAGE.  LOSS OF DRIVE TO OIL PUMP CAUSED LOSS OF OIL FEED TO	 THE ENG.  LOSS OF OIL FEED RESULTED IN OVERHEATING OF HIGH PRESSURE TURBINE BEARING AND  CAUSED THE BEARING TO FAIL.	2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
1999021200957	19990212	00957	NM  	1999	2	12	CA990119027      	1	19981231	G	2131	32143067	VALVE           		32143067    	BOEING	757   	757236      		NM  	RROYCE	RB211 	RB211535E4  	54555	NE  					CABIN PRESSURE	FAILED          	W				B	G			EMER. DESCENT           	O2 MASK DEPLOYED        			W	J		INADEQUATE Q C            	WARNING INDICATION        		CR	CRUISE         	1			CA						515C		30649			(CAN) DURING CRUISE AT FL 350 FEET, THE CABIN ALTITUDE STARTED TO FLUCTUATE 1,000 FEET PER MINUTE.  CHANGED THE SELECTOR	 TO AUTO NR 1, NO CHANGE.  DURING DESCENT FROM 350 FEET, THE CABIN RATE STAYED 1,500 FEET PER MIN CLIMB.  MANUAL CONTROL	 NON-EFFECTIVE.  OXYGEN MASKS WERE DEPLOYED AND AIRCRAFT RETURNED.  NR 2 PRESSURE REGULATOR REPLACED.				2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
1999052800021	19990528	00021	CE  	1999	5	28	CA990119045      	1	19981228	G	2435	23085001	GENERATOR       			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  					START/GENERATOR	CONTAMINATED    	W				O				OTHER                   				H	J		ELECT. POWER LOSS-50 PC   	WARNING INDICATION        		NR	NOT REPORTED   	1			CA			547  			96413		PCE32185			(CAN) GENERATOR U/S.  NO START FUNCTION AFTER LANDING.  COMMUTATOR CONTAMINATED WITH OIL AND HAD SHORTED.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA
1999021900445	19990219	00445	EU  	1999	2	19	CA990125019      	1	19981215	G	6410	10531754	BLADE           			BOLKMS	105   	BO105C      	5626005	EU  	ALLSN 	250C  	250C20B     	03013	GL  					TAIL ROTOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			4406 			1668		CAE836045			(CAN) THREE CRACKS IN THE SURFACE OF THE BLADE THRUST FACE.  EACH APPROXIMATELY 1.5 INCHES TO 2 INCHES LONG.  CRACK LOCA	TED ABOUT 2/3 OF THE DISTANCE OUT FROM THE BLADE ROOT.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1999031200274	19990312	00274	NE  	1999	3	12	CA990129001      	3	19981218	G	6114		SHAFT           													HAMSTD	2D	2D30        	NE  	PROPELLER	BROKEN          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA											(CAN) PROPELLER COUNTERWEIGHT SHAFT WAS FOUND BROKEN.																5	C	P206
1999031200275	19990312	00275	NE  	1999	3	12	CA990129002      	3	19981215	G	6111	A32042	SCREW           			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3I     	NE  	PROPELLER	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3037 				PCEPS0115	HJ786		(CAN) INSPECTION FOUND THE BLADE SCREWS WORN, CAUSING BLADE LOOSENESS.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
1999031200276	19990312	00276	GL  	1999	3	12	CA990129003      	3	19981112	G	6110		BEARING         			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  	HARTZL	HCB3T	HCB3TN3     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2993 				PCE80594	BU7445		(CAN) INSPECTION FOUND MAJOR CORROSION, IN THE COMMON AREA, BETWEEN THE O- RING AND THE BEARING.						1	L	7	2 	4T	4	T		A24CE   	E4EA	6	C	P15EA
1999031200277	19990312	00277	GL  	1999	3	12	CA990129004      	3	19981223	G	6110	57A1851T	BEARING         			BEECH 	1900  	1900C       	1154161	CE  	PWA   	PT6   	PT6A65B     	52043	EA  	HARTZL	HCB4M	HCB4MP3     	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				3327 				GG32044	FWA2094		(CAN) CORROSION - SEAL AREA BEARING.						2	L	7	2 	4T	4	T	RT	A24CE   	E4EA	6	C	P56GL
1999031200278	19990312	00278	GL  	1999	3	12	CA990129005      	3	19981211	G	6114	D4993	BUSHING         													HARTZL	HCD4N3	HCD4N3A     	GL  	PROP HUB	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				2922 					FY839		(CAN) BUSHING WORN BEYOND REPAIR.  BUSHING REPLACED.																5	C	STC
1999031200279	19990312	00279	GL  	1999	3	12	CA990129006      	3	19981128	G	6114	H5347	HUB             			CESSNA	206   	P206A       	2073308	CE  	CONT  	O520  	IO520A      	17032	SO  	MCAULY	2A34C	E2A34C73    	GL  	PROPELLER	CORRODED        	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				115  				1112325A	771968HUB		(CAN) HEAVY EXTERNAL CORROSION ON THE PROPELLER HUB.						1	H	7	1 	3O	3	O		A4CE    	E5CE	5	C	P3EA9
1999031200280	19990312	00280	CE  	1999	3	12	CA990129011      	1	19981229	G	7921	649479	OIL COOLER      			CESSNA	414   	414A        	2075907	CE  	CONT  	O520  	TSIO520NB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				182  		I94157263		2061939E			(CAN) OIL COOLER (P/N 649479) WAS DELIVERED AND INSTALLED WITH AN OVERHAULED ENGINE.  AS WINTER APPROACHED THE ENGINE OI	L TEMPERATURE, DURING CRUISE, BEGAN TO DROP.  WITH AMBIENT AIR TEMPERATURE -20 DEGREES CELSIUS, THE ENGINE OIL TEMPERATU	RE WAS BELOW THE BOTTOM OF THE GREEN ARC, ON THE COCKPIT GAUGE.  ORIGINAL EQUIPMENT OIL COOLER (HARRISON P/N 636900R).  	REPLACED CONTINENTAL COOLER AND THE PROBLEM WENT AWAY.			1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1999031200282	19990312	00282	CE  	1999	3	12	CA990202004      	1	19981228	G	7921	649479	OIL COOLER      			CESSNA	402   	402C        	207590R	CE  	CONT  	O520  	TSIO520VB   	17040	SO  	MCAULY	3AF32C	3AF32C505   	GL  	ENGINE	FAILED          	W				A				UNSCHED LANDING         				J			WARNING INDICATION        			CR	CRUISE         	1			CA				163  		I94157263		290633R	600853		(CAN) OIL COOLER (P/N 649479) WAS DELIVERED AND INSTALLED WITH AN OVERHAULED ENGINE.  AS WINTER APPROACHED THE ENGINE OI	L TEMPERATURE, DURING CRUISE, BEGAN TO DROP.  WITH AMBIENT AIR TEMPERATURE -20 DEGREES CELSIUS, THE ENGINE OIL TEMPERATU	RE WAS BELOW THE BOTTOM OF THE GREEN ARC, ON THE COCKPIT GAUGE. ORIGINAL EQUIPMENT OIL COOLER (HARRISON P/N 636900R). RE	PLACED CONTINENTAL COOLER AND THE PROBLEM WENT AWAY.			1	L	7	2 	3O	3	O		A7CE    	E8CE	5	C	P22EA
1999022600208	19990226	00208	SO  	1999	2	26	CA990202006      	1	19981201	G	2910	159H10002698P4	LINE            			GULSTM	G159  	G159        	3952202	SO  	RROYCE	DART  	DART5298X   	54507	EU  					NLG WW	CRACKED         	W				O				OTHER                   				K			FLUID LOSS                			LD	LANDING        	1			CA								16062			(CAN) ON GEAR EXTENSION, THE CREW OBSERVED FLUCTUATING HYDRAULIC PRESSURE.  GEAR EXTENDED SLOWLY.  AFTER LANDING, COMPLE	TE LOSS OF HYDRAULIC PRESSURE AND FLUID.  TWO LEFT MAIN TIRES BLEW.  MAINTENANCE FOUND A CRACKED LINE FLARE ON THE AUX/M	AIN HYDRAULIC SELECTOR IN THE NOSE WHEELWELL.				2	L	7	2 	4T	4	T		1A17    	E297
1999052800042	19990528	00042	NM  	1999	5	28	CA990203002      	1	19981230	G	5700	57085	FLYING WIRE     			CHRIS 	HUSKY 	A1          	221020X	NM  										WING	BROKEN          	W				O				OTHER                   				E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CR	CRUISE         	1			CA			40   								(CAN) IN CRUISE ,THE PILOT FELT THE NOW FAMILIAR THUMP OF A FLYING BREAKING.  THIS IS THIRD TIME.  HOWEVER, THIS TIME IT	 WAS THE UPPER RIGHT HAND WIRE.  PILOT REPORTED THAT THE WIRE SEEMED A LITTLE TIGHTER DUE, HE THOUGHT, TO CONTRACTION OF	 STEEL IN COLD TEMPERATURES.				1	H	7	1 	3O			NC	A22NM
1999030500185	19990305	00185	NE  	1999	3	5	CA990203009      	2	19981126	G	7250	MO3	TURBINE WHEEL   			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					ENGINE	FAILED          	W				O				OTHER                   				Y			ENGINE STOPPAGE           			CR	CRUISE         	1			CA			3292 					9310			(CAN) ENGINE FAILED IN-FLIGHT.  POSSIBLE CAUSE WAS THE UNCONTAINED FAILURE OF THE TURBINE WHEEL.  PART TC:  5,164.						1	G	7	1 	3U	3	U		H9EU    	E19EU
1999052800078	19990528	00078	NE  	1999	5	28	CA990219008      	2	19981220	G	7260	3353107060	SEAL            								GE    	CFM56 	CFM565A     	13802	NE  					STARTER DRIVE	WORN            	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA			19716					731802			(CAN) DURING FLIGHT, THE CREW NOTICED A SMALL BUT STEADY DECREASE IN THE OIL QUANTITY ON NR 1 ENGINE.  THE AIRCRAFT WAS 	DIVERTED AND A POST-FLIGHT INSPECTION FOUND THE STARTER DRIVE PAD CARBON SEAL LEAKING.   THE CARBON SEAL WAS REPLACED AN	D GROUND CHECKED SERVICEABLE.									4	F			E29NE
1999081200355	19990812	00355	EA  	1999	8	12	CA990226008      	2	19981015	G	8520		GEAR            			GULSTM	680   	680         	0141602	SW  	LYC   	O480  	GSO480B1A6  	41529	EA  					CRANKSHAFT	SHEARED         	W				O				OTHER                   				E			VIBRATION/BUFFET          			CR	CRUISE         	1			CA			917  					L29133			(CAN) PILOT REPORTED SUDDEN STOPPAGE.  POST-FLIGHT INSPECTION FOUND THE CRANK GEAR MOUNTED ON THE CRANKSHAFT HAD SHEARED	 AND SPLIT.  IT DID A 180 DEGREE ROTATION AND REPLACED ITSELF, CAUSING THE ENGINE TO BE 180 DEGREES OFF TIMING.					1	H	7	2 	3O	3	O		2A4     	E284
1999081200440	19990812	00440	SO  	1999	8	12	CA990310032      	1	19981206	G	3260	1CH214	SWITCH          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG	FAILED          	W				L				ABORTED APPROACH        				N			FALSE WARNING             			AP	APPROACH       	1			CA			9854 					L12361			(CAN) DURING APPROACH,THE CREW SELECTED GEAR DOWN AND DID NOT GET A GREEN NOSE LOCKED INDICATION. THEY FLEW FOR ABOUT 20	 MINUTES WHILE CYCLING THE GEAR TO TRY TO GET AN INDICATION.  INSPECTION REVEALED THE NOSE GEAR DOWN AND LOCKED MICROSWI	TCH P/N 1CH21-4 WAS FOUND DEFECTIVE.				1	L	7	2 	3O	3	O		A20SO   	E14EA
1999081200441	19990812	00441	SO  	1999	8	12	CA990310033      	1	19981207	G	3260	1CH214	SWITCH          			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					MLG	INTERMITTENT    	W				O				OTHER                   				N			FALSE WARNING             			AP	APPROACH       	1			CA			9863 					L12361			(CAN) DURING APPROACH, THE CREW WERE UNABLE TO GET A 'DOWN AND LOCKED GREEN LIGHT' ON THE NOSE GEAR. THEY CYCLED THE GEA	R SEVERALTIMES AS WELL AS TRYING THE HAND PUMP.  INVESTIGATION REVEALED AN INTERMITTENT CIRCUIT IN THE 'DOWN AND LOCKED'	 CLOSED SIDE OF THE SWITCH, WHICH PREVENTED PROPER INDICATION.  INDICATIONS ARE THAT THE ORIGINAL SWITCH INSTALLED IN TH	E AIRCRAFT, AND HAD NEVER BEEN CHANGED.			1	L	7	2 	3O	3	O		A20SO   	E14EA
1999081200443	19990812	00443	SO  	1999	8	12	CA990310035      	1	19980908	G	8120	LW12690	FITTING         			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					TURBOCHARGER	RESTRICTED      	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			R	J		PARTIAL RPM/PWR LOSS      	WARNING INDICATION        		CR	CRUISE         	1			CA				10   				L726561A			(CAN) DURING CRUISE,THE NR 2 ENGINE LOST THE TURBO AND WENT NORMALLY ASPIRATED.  SMOKE WAS OBSERVED COMING FROM THE EXHA	UST, SO A PRECAUTIONARY SHUTDOWN WAS CARRIED OUT, DUE TO THE POSSIBILITY OF OIL LOSS FROM THE TURBO.  POST-FLIGHT INSPEC	TION REVEALED NO LOSS OF OIL FROM THE TURBO. THE SMOKE WAS COMING FROM THE ENGINE RUNNING RICH DUE TO LOSS OF TURBO BOOS	T PRESSURE. THE TURBOCHARGER WAS FOUND TO HAVE FAILED BEARINGS.  FURTHER INVESTIGATION FOUND THE OIL INLET RESTRICTED FI	TTING WAS 90 PERCENT PLUGGED, CAUSING LOSS OF OIL SUPPLY TO THE TURBO. THE TURBOCHARGER WAS REPLACED AND THE AICRAFT RET	URNED TO SERVICE.	1	L	7	2 	3O	3	O		A20SO   	E14EA
1999081200472	19990812	00472	SW  	1999	8	12	CA990310069      	1	19981120	G	2435	03600923	BEARING         	LUCAS       	23081018    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					START/GENERATOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						1600		CAE895012			(CAN) THE OEM USES BARDEN BEARINGS WITH THE LOGO AND THE PART NUMBER STAMPED ON.  THE BEARINGS FOUND IN THIS UNIT WERE C	OMMERCIAL FAFNIR BEARINGS.  SUBMITTER STATED THIS IS AN UNAPPROVED PART.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1999081200473	19990812	00473	SW  	1999	8	12	CA990310070      	1	19981124	G	2435	07111259	BEARING         	LUCAS       	23031004    	BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311A      	41549	NE  					START/GENERATOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						4758		LE12243			(CAN) THE BEARING REMOVED FROM THE UNIT WAS MADE BY SKF.  OEM DOES NOT USE SKF BEARINGS.  SUBMITTER STATED THIS IS AN UN	APPROVED BEARING.					1	G	7	1 	4U	4	U		H1SW    	E1EA
1999081200474	19990812	00474	SW  	1999	8	12	CA990310071      	1	19981124	G	2435	07111337	BEARING         	LUCAS       	23031004    	BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311A      	41549	NE  					START/GENERATOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						4758		LE12243			(CAN) THE BEARING REMOVED FROM THE UNIT WAS OF LOWER QUALITY THAN OEM USES AND THE WRONG MANUFACTURER.  SUBMITTER STATED	 THIS IS AN UNAPPROVED BEARING.					1	G	7	1 	4U	4	U		H1SW    	E1EA
1999081200475	19990812	00475		1999	8	12	CA990310072      	1	19981124	G	2822	4045685	BEARING         	ADEL        	723681      															BOOST PUMP	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						H1767H					(CAN) BEARING REMOVED MADE BY MRC.  SUBMITTER STATED THIS IS AN UNAPPROVED PART.  OEM USES SKF BEARINGS.
1999081200476	19990812	00476		1999	8	12	CA990310073      	1	19981124	G	7714	P13740	BEARING         	SMITHSIND   	KGA0409     															ROTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						BN9353					(CAN) BEARING REMOVED MADE BY FAFNIR.  SUBMITTER STATED THIS IS AN UNAPPROVED PART.  OEM USES BEARINGS MADE BY RHP.
1999081200477	19990812	00477		1999	8	12	CA990310074      	1	19981124	G	7714	P3216	BEARING         	SMITHSIND   	KGA0409     															ROTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						BN9353					(CAN) OEM USES RHP BEARINGS.   BEARING REMOVED WAS MADE BY FAFNIR.  SUBMITTER STATED THIS IS AN UNAPPROVED PART.
1999081200478	19990812	00478		1999	8	12	CA990310075      	1	19981124	G	7714	15D1507	BEARINGS        	GLOBE       	22A703      															ROTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						28912					(CAN) OEM USES BEARINGS MADE BY NMB.   BEARINGS REMOVED ARE MADE BY NTN.  SUBMITTER STATED THESE ARE UNAPPROVED PARTS.
1999081200479	19990812	00479		1999	8	12	CA990310076      	1	19981124	G	2822	4045685	BEARING         	HYDROAIRE   	85816       															BOOST PUMP	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						H539A					(CAN) OEM USES SEALED SKF BEARINGS.  BEARING REMOVED WAS MADE BY RHP AND SHIELDED ONLY.  SUBMITTER STATED THIS IS AN UNA	PPROVED PART.
1999081200480	19990812	00480		1999	8	12	CA990310077      	1	19981124	G	2822	4045685	BEARING         	HYDROAIRE   	85816       															BOOST PUMP	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						H1505A					(CAN) OEM USES SEALED SKF BEARINGS.  BEARINGS REMOVED WERE MADE BY RHP AND WERE SHIELDED ONLY.  SUBMITTER STATED THIS IS	 AN UNAPPROVED PART.
1999081200481	19990812	00481		1999	8	12	CA990310078      	1	19981124	G	7714	4149471P015	BEARINGS        	GE          	2CM9ABY7    															ROTOR	WRONG PART      	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA						D7440					(CAN) OEM USES SHIELDED NHBB BEARINGS.  BEARINGS REMOVED WERE BETTER QUALITY SEALED BEARINGS MADE BY NMB.  SUBMITTER STA	TED THIS IS AN UNAPPROVED PART.
1999081200499	19990812	00499	WP  	1999	8	12	CA990311004      	2	19981229	G	7230	331070511	SEAL            			SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NR 2 ENGINE	LEAKING         	W				A				UNSCHED LANDING         				K			FLUID LOSS                			CR	CRUISE         	1			CA			1769 					BUA21034			(CAN) NR 2 ENGINE HAD OIL PRESSURE FLUCTUATION IN CRUISE.  ON ROLL-OUT, THE NR 2 ENGINE OIL PRESSURE DROPPED AND THE LOW	 OIL WARNING ILLUMINATED. THE ENGINE WAS SHUT DOWN.  POST-FLIGHT INSPECTION FOUND OIL ON THE ENGINE NACELLE AND THE GEAR	 LEG. FURTHER INSPECTION FOUND THE OIL QUANTITY 5 QUARTS LOW.  THE OIL HAD LEAKED FROM THE HYDRAULIC PUMP SEAL DUE TO A 	PRESSURIZED GEARCASE RESULTING FROM A LEAKING COMPRESSOR SEAL. THE HYDRAULIC PUMP SEAL AND THE COMPRESSOR SEAL WERE REPL	ACED AND THE AIRCRAFT RETURNED TO SERVICE.		2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999081200500	19990812	00500	WP  	1999	8	12	CA990311006      	2	19981231	G	7321	89778017	FCU             	WOODWARD    		SWRNGN	SA226 	SA226AT     	8780405	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NR 1 ENGINE	MALFUNCTIONED   	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			J			WARNING INDICATION        			CR	CRUISE         	1			CA				4109 		1578178		P54098			(CAN) DURING SURGE, NR 1 ENG SURGED WITH EGT INCREASE, EGT REDUCED, ALL ENG PARAMETERS  NORMAL.  APPROX 2 MINUTES, ENG A	GAIN SURGED AND EGT RISE ENCOUNTERED, BUT POWER AND TEMPS COULD NOT BE REDUCED BY POWER LEVER.  ENG WAS SHUT DOWN AND AC	FT LANDED WITHOUT INCIDENT.  SUBSEQUENT GROUND RUNS COULD NOT DUPLICATE FAULT, SO IT WAS CONCLUDED ICING OF PT2 (ENG INL	ET SENSOR) WAS THE CAUSE.  CREW REPORTED INLET HEAT WAS OFF AS THERE WAS NO EVIDENCE OF VISIBLE MOISTURE.  FOLLOWING 2 F	LTS WERE UNEVENTFUL WITH ALL ENG PARAMETERS NORMAL.  FOLLOWING FLIGHTS, DURING START-UP, NR 1 ENG HAD TO BE ABORTED DUE 	TO AN OVERTEMP CONDITION.  NR 1 ENG FUEL CONTROL UNIT REPLACED, RIGGED, TESTED, AND ACFT RETURNED TO SERVICE.	2	L	7	2 	4T	4	T	RT	A5SW    	E4WE
1999081200502	19990812	00502	WP  	1999	8	12	CA990311008      	2	19981231	G	7321	89778017	FCU             	WOODWARD    		SWRNGN	SA226 	SA226TC     	8780404	SW  	GARRTT	TPE331	TPE33110UA  	01514	WP  					NR 1 ENGINE	MALFUNCTIONED   	W				E				ENGINE SHUTDOWN         				A			FLAME/FIRE                			NR	NOT REPORTED   	1			CA				1546 		1578228		P54143			(CAN) DURING START OF THE NR 1 ENGINE, FLAMES WERE NOTICED FROM THE TAILPIPE, WITH THE EGT RISING TO AN OVERTEMP CONDITI	ON.  THE ENGINE START WAS ABORTED.  POST ABORT, THE FUEL CONTROL UNIT WAS REPLACED, RIGGED AND TESTED SERVICEABLE.  THE 	AIRCRAFT WAS RETURNED TO SERVICE.				2	L	7	2 	4T	4	T	RT	A8SW    	E4WE
1999081200507	19990812	00507		1999	8	12	CA990311013      	1	19981231	G	6120		GOVERNOR        								PWA   	PT6   	PT6A67B     	52043	NE  					ENGINE	MISINSTALLED    	W				O				OTHER                   				W			INADEQUATE Q C            			LD	LANDING        	1			CA								PCEPR0050			(CAN) QUALITY CONTROL PROBLEM AFFECTING THE RELATIONSHIP OF THE NF GOVERNOR IN RELATION TO THE OVERSPEED GOVERNOR.  CORR	ECTION TO RIGGING WAS REQUIRED.										4	T			E26NE
1999081200526	19990812	00526		1999	8	12	CA990311033      	4	19981221	G	3416	280040102	INDICATOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			124  								(CAN) FLIGHT CREW REPORTED THAT RIGHT DIGITAL ALTIMETER DISPLAY FAILS INTERMITTENTLY.   ALTIMETER REPLACED.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200527	19990812	00527	CE  	1999	8	12	CA990311034      	1	19981221	G	7722	1303800415	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE ITT	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			124  								(CAN) CREW REPORTED THAT ITT ON RIGHT ENGINE WOULD STICK AT 800 DEGREES DURING START AND RESETTING THE POWER WOULD UNSTI	CK UNIT. MAINTENANCE REPLACED THE UNIT.  MANUFACTURED BY MEGGITT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200528	19990812	00528		1999	8	12	CA990311035      	4	19981221	G	3416	066030620008	INDICATOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			124  								(CAN) CREW REPORTED THAT THE LEFT ALTIMETER APPEARED TO BE APPROX 60 FEET OFF AT GROUND LEVEL.  TESTS CONFIRMED CALIBRAT	ION ERROR.  UNIT REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200530	19990812	00530	CE  	1999	8	12	CA990311037      	1	19981215	G	7714	1303800445	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	MALFUNCTION     	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			159  					PSO242			(CAN) RIGHT ENGINE NG INDICATOR NOT FUNCTIONING AT ALL.  MAINTENANCE REPLACED THE INDICATOR MANUFACTURED BY MEGGITT.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200531	19990812	00531		1999	8	12	CA990311038      	4	19981215	G	3416	280040102	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			12   					PSO242			(CAN) DURING AIRCRAFT DELIVERY FROM RAYTHEON, THE RIGHT ALTIMETER DIGITAL DISPLAY FAILED.  A REPLACEMENT WAS INSTALLED. 	 MANUFACTURED BY MEGGITT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200532	19990812	00532		1999	8	12	CA990311039      	4	19981215	G	3416	280040102	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			227  					PSO242			(CAN) DURING CRUISE, CREW NOTED THE RIGHT ALTIMETER DIGITAL DISPLAY INDICATING AND FLAGGED FAILED.  UNIT WAS REPLACED. M	ANUFACTURED BY MEGGITT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200533	19990812	00533	CE  	1999	8	12	CA990311040      	1	19981215	G	3030	0856MG3	PITOT HEAT      			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					FUSELAGE	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			265  					PSO242			(CAN) FLIGHT CREW REPORTED THAT THE LEFT PITOT HEAT ANNUNCIATOR WOULD NOT EXTINGUISH INDICATING NO HEAT.  THE PITOT TUBE	 WAS REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200536	19990812	00536	NE  	1999	8	12	CA990311043      	3	19981215	G	6140	1143800603	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  	HARTZL	HCE4A	HCE4A3I     	NE  	LT PROPELLER	STICKING        	W				O				OTHER                   				J			WARNING INDICATION        			CR	CRUISE         	1			CA			1293 					PCEPS0191	HJ927		(CAN) DURING CRUISE FLIGHT, CREW NOTICED THE LT PROP RPM INDICATOR TO BE STICKING BADLY.   MAINTENANCE REPLACED THE INDI	CATOR.  MANUFACTURED BY MEGGITT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE	5	C	P10NE
1999081200538	19990812	00538		1999	8	12	CA990311045      	4	19981215	G	3416	280040102	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	INTERMITTENT    	W				O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CA			1067 					PCEPS0191			(CAN) FLIGHT CREW REPORTED DIGITAL DISPLAY INTERMITTENT.  MAINTENANCE REPLACED UNIT WITH NEW.  MAUNFACTURED BY MEGGITT.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200539	19990812	00539	CE  	1999	8	12	CA990311046      	1	19981215	G	3243	9038000133	MASTER CYLINDER 			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					BRAKE	FAILED          	W				D				RETURN TO BLOCK         				O			OTHER                     			TX	TAXI/GRND HDL  	1			CA			99   								(CAN) DURING REPOSITIONING FROM HANGAR TO GATE, FLIGHT CREW NOTICED INCREASING LEVELS OF STEERING INPUT REQUIRED TO MAIN	TAIN DIRECTIONAL CONTROL. AIRCRAFT FINALLY STOPPED ON TAXIWAY AND WOULD NOT MOVE FORWARD WITH ENGINE POWER.  MAINTENANCE	 FOUND BRAKE PRESSURE LOCKED ON LT BRAKE ASSY.   MASTER CYLINDER WAS NOT ALLOWING BRAKE RELEASE.  LINE WAS CRACKED.  THE	 AIRCRAFT WAS TOWED BACK TO HANGAR AND THE MASTER CYLINDER REPLACED.			2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200541	19990812	00541		1999	8	12	CA990311048      	4	19981215	G	3421	7926694001	GYRO            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					COCKPIT VG	MALFUNCTIONED   	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1950 					PCEPS0160			(CAN) FLIGHT CREW REPORTED THE RIGHT ADI VERY SLOW TO SPOOL.  MAINTENANCE REPLACED UNIT.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200542	19990812	00542	CE  	1999	8	12	CA990311049      	1	19981215	G	5230	1145140587	BRACKET         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			2020 					PCEPS0160			(CAN) DURING ROUTINE MAINTENANCE, THE FORWARD CARGO DOOR, SMALL GAS STRUT DOOR TO SILL ATTACH BRACKET WAS FOUND CRACKED.	   BRACKET ASSY REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200543	19990812	00543	CE  	1999	8	12	CA990311050      	1	19981215	G	7933	1303800455	INDICATOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					OIL PRESSURE	STICKING        	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			2032 					PCEPS0160			(CAN) CREW REPORTED RIGHT OIL PRESSURE INDICATOR STICKING THROUGH RANGE.  MAINTENANCE REPLACED WITH SERVICEABLE UNIT.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200544	19990812	00544	CE  	1999	8	12	CA990311051      	1	19981215	G	2750		TE FLAP         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					WING	STUCK           	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								PCEPS0160			(CAN) CREW REPORTED FLAPS STUCK AT 17 DEGREES.  MAINTENANCE CLEANED AND CHECKED SAFETY LOCKOUTS AND VERIFIED OPERATION.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200545	19990812	00545		1999	8	12	CA990311052      	4	19981215	G	3416		LINE            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	LEAKING         	W				O				OTHER                   				O			OTHER                     			CL	CLIMB          	1			CA								PCEP0165			(CAN) DURING CLIMB, FLIGHT CREW NOTICED THE NR 2 ALTIMETER TO BE JERKING DURING THE ASCENT.   MAINTENANCE CHECKED AND FO	UND THAT THE STATIC SYSTEM HAD A SMALL LEAK IN THE FORWARD CLOSET AREA.  LEAK REPAIRED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200546	19990812	00546	CE  	1999	8	12	CA990311053      	1	19981215	G	3250	993880047	ACTUATOR        			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					NLG STEERING	FAILED          	W				C				ABORTED TAKEOFF         				O			OTHER                     			TO	TAKEOFF        	1			CA			1794 					PCEP0165			(CAN) DURING TAKEOFF, FLIGHT CREW NOTED THAT THE STEERING DISCONNECT ACTUATOR DID NOT FUNCTION.  MAINTENANCE REPLACED TH	E ACTUATOR WHICH WAS GRINDING BADLY.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200547	19990812	00547	CE  	1999	8	12	CA990311054      	1	19981215	G	5230	1145140587	BRACKET         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					CARGO DOOR	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1920 					PCEPS0163			(CAN) DURING MAINTENANCE ACTIVITY, CARGO DOOR FORWARD SMALL GAS STRUT ATTACH BRACKET WAS FOUND CRACKED AT SILL POINT.  B	RACKET WAS REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200548	19990812	00548	CE  	1999	8	12	CA990311055      	1	19981215	G	2750		FLAP            			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					WING	OUT OF ADJUST   	W				O				OTHER                   				F			FLT CONT AFFECTED         			AP	APPROACH       	1			CA								PCEPS0163			(CAN) DURING APPROACH, FLIGHT CREW FOUND FLAPS STUCK AT 17 DEGREES.  MAINTENANCE ADJUSTED THE LEFT LOCKOUT SWITCH CHECKE	D OK.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200550	19990812	00550		1999	8	12	CA990311057      	4	19981215	G	3416	280040102	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			1015 					PCEPSO197			(CAN) FLIGHT CREW REPORTED RIGHT ALTIMETER DIGITAL DISPLAY WOULD FAIL AND FLAG.  UNIT REPLACED WITH NEW.  MANUFACTURED B	Y MEGGITT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200551	19990812	00551		1999	8	12	CA990311058      	4	19981215	G	3416	280040102	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					ALTIMETER	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			219  					PCEPS0209			(CAN) FLIGHT CREW REPORTED THE RIGHT ALTIMETER DIGITAL DISPLAY FLAGGED FAIL  MAINTENANCE REPLACED THE UNIT.  MANUFACTURE	D BY MEGGITT.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200552	19990812	00552	CE  	1999	8	12	CA990311059      	1	19981215	G	7712	1143800653	INDICATOR       			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     	 	NE  					ENGINE TORQUE	FAILED          	W				O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			CA			570  					PCEPS0209			(CAN) FLIGHT CREW REPORTED FLUCTUATIONS ON THE RIGHT TORQUE INDICATOR WITH NO CORRESPONDING PARAMETER SHIFTS.  RIGHT TOR	QUE INDICATOR REPLACED.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200553	19990812	00553	CE  	1999	8	12	CA990311060      	1	19981215	G	7712	1143800653	INDICATOR       	MEGGITT     		BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					LT ENGINE TORQUE	FAILED          	W				A				UNSCHED LANDING         				N			FALSE WARNING             			CL	CLIMB          	1			CA			580  					PCEPS0209			(CAN) DURING TAKEOFF ROLL, FLIGHT CREW DETECTED SEVERAL INDICATORS SUGGESTING POWER SETTINGS NOT AS SELECTED.  AFTER SUC	CESSFUL TAKEOFF, CREW DETERMINED THE LEFT ENGINE HAD RECEIVED EXCESSIVE TORQUE FOR AN UNDETERMINED LENGTH OF TIME.  THE 	FDR REVEALED THE LT ENGINE HAD RECEIVED OVER 5,000 POUNDS TORQUE FOR APPROX 36 SECONDS, AND ABOVE 4,300 POUNDS.  TORQUE 	FOR LONGER THAN 63 SECONDS.   THE ENGINE POWER SECTION WAS REMOVED FOR OVERHAUL.  THE TORQUE INDICATOR WAS FOUND TO BE S	TICKING BADLY AT APPROXI 3,500 POUNDS TORQUE, WHICH IS AROUND THE TAKEOFF SETTING FOR THAT DAY.   DUE TO INCORRECT DISPL	AY OF APPLIED POWER, THE FLIGHT CREW PUSHED THROUGH THIS LIMIT.  THE GAUGE WAS MANUFACTURED BY MEGGITT.	2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200554	19990812	00554	NE  	1999	8	12	CA990311061      	2	19981215	G	7412	103815504C	EXCITER         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					RT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			80   					PSO231			(CAN) DURING ROUTINE START, CREW REPORTED NO IGNITION ON RIGHT ENGINE.  MAINTENANCE REPLACED THE IGNITION EXCITER.						2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200555	19990812	00555	NE  	1999	8	12	CA990311062      	2	19981215	G	7412	103815504C	EXCITER         			BEECH 	1900  	1900D       	1154162	CE  	PWA   	PT6   	PT6A67D     		NE  					LT ENGINE	FAILED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			112  					PSO231			(CAN) CREW REPORTED THE LEFT ENGINE WOULD NOT IGNITE DURING START SEQUENCE.  MAINTENANCE REPLACED THE LEFT IGNITION EXCI	TER ASSY.					2	L	7	2 	4T	4	T	RT	A24CE   	E26NE
1999081200585	19990812	00585	CE  	1999	8	12	CA990318017      	1	19981023	G	5610	2087	WINDSHIELD      			CESSNA	210   	T210N       	2073456	CE  	CONT  	O520  	TSIO520R    	17040	SO  	MCAULY	D3A34	D3A34C402   	GL  	COCKPIT	CRAZED          	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			3634 					230230R	790952		(CAN) WINDOW CRAZED BEYOND LIMITS.   REPLACED.						1	H	7	1 	3O	3	O		3A21    	E8CE	5	C	P47GL
1999081200586	19990812	00586	CE  	1999	8	12	CA990318018      	1	19981111	G	2120		DUCT            			BEECH 	100   	100BEECH    	1152916	CE  	PWA   	PT6   	PT6A28      		EA  					AIR DISTRIBUTION	RUPTURED        	W				K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			CA								51421			(CAN) DUCT BETWEEN CROSSOVER DUCT AND ELECTRIC HEATER GOT A HOLE IN IT AND REDUCED PRESSURIZATION.						1	L	7	2 	3T	4	T		A14CE   	E4EA
1999081200587	19990812	00587	SO  	1999	8	12	CA990318019      	1	19981126	G	2910	268	TEE             	OZONE       	OAS29301    	PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  					HYD MANIFOLD	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA				217  		268		L770861A			(CAN)  HYDRAULIC MANIFOLD CRACKED.						1	L	7	2 	3O	3	O		A20SO   	E14EA
1999081200588	19990812	00588	SO  	1999	8	12	CA990318020      	1	19981203	G	3060	77579	SLIP RING       			PIPER 	PA31  	PA31        	7103102	SO  	LYC   	O540  	TIO540A2C   	41532	EA  	HARTZL	HCE3Y	HCE3YR2A    	GL  	PROP DEICE	SHORTED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								L770861A	DJ8612A		(CAN) SLIP RING (TRACKS) WERE SHORTED OUT.						1	L	7	2 	3O	3	O		A20SO   	E14EA	5	C	P33EA
1999042100078	19990421	00078	NE  	1999	4	21	CA990318067      	2	19980508	G	7230	UL35848	ANNULUS FILLER  			BOEING	757   	757*        		NM  	RROYCE	RB211 	RB211535E437	54555	NE  					NR 1 ENGINE	FAILED          	W				D	E	F		RETURN TO BLOCK         	ENGINE SHUTDOWN         	ACTIVATE FIRE EXT.      		A			FLAME/FIRE                			TO	TAKEOFF        	1			CA						DM3970		31222			(CAN) DURING TAKEOFF, FAN ANNULUS FILLER RELEASED.  LOUD BANK WAS HEARD WITH REPORTED TAIL PIPE FLAME.  TAKEOFF ABORTED 	AND FIRE BOTTLES DISCHARGED.  AIRCRAFT TOWED BACK TO GATE.  PRELIMINARY REPORT INDICATES FILLER BETWEEN 4 AND 5 FAN BLAD	ES FAILED PENETRATING FAN CASE EXPOSING FILLER WRAP BEFORE EXITING THE TAIL PIPE.  NR 8 FILLER MISSING AND NR 9 FILLER D	ISPLACED.  BALANCE OF FILLERS FOUND SATISFACTORY.  FAN BLADES HAD SUSTAINED SOME SECONDARY DAMAGE.  SOME COMPRESSOR BLAD	E DISTRESS.  FURTHER REPORT TO FOLLOW.		2	L	7	2 	4F	4	F	RT	A2NM    	E12EU
1999082700114	19990827	00114	SW  	1999	8	27	CA990412006      	1	19981020	G	7120	204060160007	MOUNT           		204030186009	BELL  	204   	204B        	1181404	SW  	LYC   	T53   	T5311B      	41549	NE  					ENGINE	WORN            	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA								LEO8130A			(CAN) DURING INSPECTION, GRAY PASTE WAS NOTED UNDER THE SERVICE DECK OF THE ENGINE MOUNTS.  REMOVAL OF THE ENGINE AND DE	CK DISCLOSED THE CRACKED BEAM CAP.  THE ENGINE WAS ABLE TO ROCK ON THE BEAM CAPS WHEN TORQUE WAS APPLIED.  LEFT AND RIGH	T BEAM CAPS AND ALL ENGINE MOUNT BEARINGS WERE REPLACED.				1	G	7	1 	4U	4	U		H1SW    	E1EA
1999043000103	19990430	00103	NE  	1999	4	30	CA990412018      	2	19980921	G	8500		ENGINE          			DHAV  	DHC3  	DHC3        	2800202	EA  	PWA   	R1340 	R134059     	52016	NE  					ENGINE BAY	MALFUNCTIONED   	W				A				UNSCHED LANDING         				B	E		SMOKE/FUMES/ODORS/SPARKS  	VIBRATION/BUFFET          		CR	CRUISE         	1			CA								PW13400			(CAN) DURING CRUISE, ENGINE VIBRATION AND LOSS OF RPM WAS NOTICED.  AIRCRAFT MADE PRECAUTIONARY LANDING ON LAKE.  DURING	 DESCENT, SMOKE FROM OIL WAS OBSERVED AND ENGINE WAS SHUT DOWN AFTER LANDING.  INITIAL INSPECTION INDICATES INTERNAL DAM	AGE.  ENGINE WILL BE REPLACED AND REPORT WILL FOLLOW WHEN AVAILABLE.				1	H	7	1 	3R	3	R		A815    	5E2
1999043000104	19990430	00104	NE  	1999	4	30	CA990412020      	2	19981015	G	7314	9234A8	PUMP            								GE    	CF700 	CF7002D2    	30010	NE  					NR 1 ENGINE	MAKING METAL    	W				A				UNSCHED LANDING         				X	J		ENGINE FLAMEOUT           	WARNING INDICATION        		CL	CLIMB          	1			CA			7106 	2390 				304435B			(CAN) ON CLIMB-OUT, NR 1 ENGINE DID NOT RESPOND TO POWER SETTING TO CLIMB POWER.  AIRCRAFT RETURNED TO POINT OF DEPARTUR	E.  POST-FLIGHT INVESTIGATION FOUND THE NR 1 ENGINE FUEL PUMP WAS MAKING METAL WHICH CONTAMINATED THE FCU AND THE FUEL N	OZZLES PREVENTING FUEL DELIVERY.  FUEL PUMP WAS REPLACED AND WILL BE INSPECTED FOR FAILURE FAULT.  FURTHER REPORT TO FOL	LOW.								4	F			E7EA
1999052800101	19990528	00101	NE  	1999	5	28	CA990430052      	2	19981228	G	7250		SHAFT           		MO3000A4    						RROYCE	TAY   	TAY65015    	54557	NE  					TURBINE	WORN            	W				C				ABORTED TAKEOFF         				E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			CA			18299					17270			(CAN) AIRCRAFT RETURNED TO DEPARTURE POINT AFTER HIGH ENGINE VIBRATIONS.  MAINTENANCE CONFIRMED VIBRATIONS AT 0.5 IPS ST	ARTING AT 57  PERCENT UP TO TAKEOFF POWER.  ENGINE DISASSEMBLY FOUND WEAR ON THE HP TURBINE SHAFT SPLINES END FACES, WHI	CH ALLOWED THE HP TURBINE DISC AND BLADES TO MOVE REARWARD AND THE BLADE SHROUD TO CONTACT THE NOZZLE GUIDE VANES BEHIND	 THEM CAUSING THE VIBRATIONS.  T HE SHAFT WAS PRE-SB 72-1327 STANDARD.								4	F			E25NE
1999052800103	19990528	00103	NE  	1999	5	28	CA990430055      	2	19981228	G	7260	EU10274	BEVEL GEAR      		SB131403    						RROYCE	TAY   	TAY65015    	54557	NE  					NR 2 ENGINE	STRIPPED        	W				E	A			ENGINE SHUTDOWN         	UNSCHED LANDING         			E	F		VIBRATION/BUFFET          	FLT CONT AFFECTED         		CL	CLIMB          	1			CA			16212			TM4380		17380			(CAN) ON CLIMB-OUT AT FL 220, THE NR 2 ENGINE GENERATOR LIGHT CAME ON AND THE ENGINE SURGED, THE ENGINE THEN ROLLED BACK	 TO IDLE FOR 3-5 SECONDS BEFORE FLAMING OUT.  THE ENGINE WAS SECURED AND THE AIRCRAFT DIVERTED.   POST-FLIGHT AN ENGINE 	START WAS ATTEMPTED AND THE STARTER SHAFT SHEARED.  CHIP DETECTORS AND THE OIL SCREENS WERE FOUND CLEAR.  ENGINE DISASSE	MBLED AND THE INTERNAL GEARBOX HAD FAILED.  BEVEL DRIVE AND HIGH SPEED GEAR SPLINES WERE FOUND STRIPPED, SO THE GEARBOX 	WAS NOT BEING DRIVEN.   INVESTIGATION INTO THE CAUSE OF THE SPLINE WEAR IS CONTINUING.							4	F			E25NE
1999082001002	19990820	01002	NE  	1999	8	20	CA990505001      	1	19980707	G	3340	4609467	PIVOT SHAFT     		4501221     	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					LANDING LIGHT	MELTED          	W				K				NONE                    				M	W		OVER TEMP                 	INADEQUATE Q C            		IN	INSP/MAINT     	1			CA						0413K		CAE890017S			(CAN) LANDING LIGHT SHAFT ASSY INSULATORS WERE FOUND BURNED.   IT APPEARS THAT THE FOLLOWING ARE UNAPPROVED PARTS: 46-09	43-1 BUS BAR, 46-0944-1 INSULATOR AND 46-0945-1.  INSULATORS DO NOT CONFORM TO MANUFACTURER'S SPECS AND HAVE THUS MELTED	.  THIS PART CARRIES THE ELECTRICAL CURRENT FOR THE LAMP CIRCUIT.				1	G	7	2 	3U	3	U		H1NE    	E1GL
1999070900396	19990709	00396	WP  	1999	7	9	CA990531005      	1	19980720	G	6310	369A5363	BEARING         		369A535051  	HUGHES	369   	369D        	4470706	WP  	ALLSN 	250C  	250C20B     	03013	GL  					TRANSMISSION	MISINSTALLED    	W				K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			CA				282  		6102		CAE830591			(CAN) DURING A 300 HOUR CLUTCH INSPECTION, AN INCORRECT P/N 369A5363 TYPE BEARING WAS FOUND TO BE INSTALLED IN THE -51 C	LUTCH.  THE BEARING WAS MARKED MRC R12.  THE O/H MANUAL STATES THAT THE BEARINGS MARKED MRC R12 MUST NOT BE INSTALLED IN	 A -51 CLUTCH.				1	G	7	1 	3U	3	U		H3WE    	E4CE
1999101500516	19991015	00516	NE  	1999	10	15	CA990907003      	3	19981008	G	6114	MWA1000	SHAFT           	HAMSTD      	2D30405     	DHAV  	DHC2  	DHC2MK1     	2800102	EA  	PWA   	R985  	R985AN14B   	52008	NE  	HAMSTD	2D	2D30        	NE  	PROP HUB	CRACKED         	W				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CA			1051 			112779		4216109	112779		(CAN) SHAFT FOUND CRACKED 80 PERCENT AROUND DIAMETER AT TAPER BEFORE THREADS.						1	H	7	1 	3R	3	R		A806    	5E1	5	C	P206
1998043000263	19980430	00263	EA  	1998	4	30	CHI2009          	1	19980119	G	6310	107DS2131	CLUTCH          		107D2003515 	BOEING	107   	1072        	9420604	EA  										NR 1 IDLER	SLIPPED         	B			CHIR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			NM	09	CGHFY	109  			XBW1607	2002				NR 1 CLUTCH SLIPPED IN-FLIGHT.  NO APPARENT DEFECTS FOUND ON INSPECTION.  DIMENSIONAL INSPECTION OF PINION AND HUB SHOW 	THEM TO BE WELL WITHIN LIMITS.  CLUTCH NEEDS TO BE INSPECTED BY HIGHER INSPECTION AUTHORITY.  (X)					2	G	7	2 	4U				1H16
1998043000264	19980430	00264	EA  	1998	4	30	CHI2010          	1	19980119	G	6310	107DS2131	CLUTCH          		107D2003515 	BOEING	107   	1072        	9420604	EA  										NR 1 IDLER	MALFUNCTIONED   	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	194CH	20   			XBW1606					NR 1 CLUTCH HAD OVERRUN DURING TOPPING CHECK AND WOULD NOT RE-ENGAGE.  NO PROBLEM FOUND WITH CLUTCHES, HUB OR PINION.  (	X)					2	G	7	2 	4U				1H16
1998022600073	19980226	00073	SW  	1998	2	26	CHI2023          	1	19980121	G	5311	206032308003S	FRAME           			BELL  	206   	206L1       	1182107	SW  										TB ATTACH	CRACKED         	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	832AH	4977 				45560				DURING INSPECTION, SUSPECTED CRACK WAS NOTED IN UPPER RT QUADRANT OF TAILBOOM ATTACH FRAME.  DYE-PEN CONFIRMED CRACK AND	 TAILBOOM WERE REMOVED.  A LARGER CRACK WAS DISCOVERED ON AFT SIDE OF FRAME, OUTBOARD OF UPPER LEFT HAND ATTACH BOLT HOL	E.  THIS CRACK WAS NOT VISIBLE WITH THE TAILBOOM INSTALLED AND WAS LOCATED APPROXIMATELY .375 INCH OUTBOARD OF HOLE AND 	.750 INCH LONG.  AFTER REMOVAL OF FRAME FOR REPLACEMENT, NOTED THE CRACKS WERE LOCATED ALONG SIDE THE UPPER EDGES OF THE	 FITTINGS PN 206-031-329-103, AND  -104.  THE FITTINGS HAVE SHARP EDGES THAT MAY HAVE CUT INTO FORWARD SIDE OF SHEET MET	AL FRAME.  (X)	1	G	7	1 	3U				H2SW
1998043000265	19980430	00265	WP  	1998	4	30	CHI2043          	1	19980206	G	6320	A02D31731	SEAL RING       		A02D301112  	KAWSKI	KV107 	KV1072      	4820101	WP  											UNBONDED        	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	184CH				XL118	4001				SEAL RING UNBONDED FROM SHAFT.  THIS WAS DISCOVERED DURING A TRANSMISSION CHANGE.  SUSPECT POOR QUALITY ADHESIVE USED DU	RING MANUFACTURE.  THIS HAS BEEN A PROBLEM IN THE PAST.  SUBMITTER HAS REPAIRED THIS BEFORE WITH 1442 B 1/2 IN THE FIELD	 AND AT OVERHAUL.  SUGGEST BETTER ADHESIVE USED AT MANUFACTURE, AND THE SEAL RING MOVED .110 INCH TO .250 INCH LOWER TO 	BETTER ENGAGE THE SEAL.			2	G	7	2 	4U				H1PC
1998032600326	19980326	00326	EA  	1998	3	26	CHI2069          	1	19980322	G	2612	61423473275	FIRE DETECTOR   	KIDDE       		BOEING	107   	1072        	9420604	EA  										NR 2 AFT UPPER	MALFUNCTIONED   	B			CHIR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	09	CFHFW	679  			1687	107				DETECTOR FAILED, CAUSED NR 2 FIRE LIGHT TO FALSELY ILLUMINATE.  DETECTOR SENT TO MFG FOR EVALUATION.  THIS DETECTOR IS P	ART OF STC SR00375SE.  (X)					2	G	7	2 	4U				1H16
1998040200003	19980402	00003	EA  	1998	4	2	CHI2077          	1	19980317	G	6220	114R22012	SHOULDER BOLT   		414R2002    	BOEING	234   	234         	1385049	EA  										ROTOR HEAD	FAILED          	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	241CH				HS52	MJ016				AFT ROTOR HEAD SHOULDER BOLT FAILED.  SUBMITTER STATED 114R22012 IS THE IMPROVED BOLT THAT IS SUPPOSED TO PREVENT THIS T	YPE OF FAILURE.					2	G	7	2 	4U				H9EA
1998041700617	19980417	00617	WP  	1998	4	17	CHI2080          	1	19980323	G	6220	369A1305	HOUSING         			HUGHES	369   	369C        	4470704	WP  										FEATHER BEARING	MISMANUFACTURED 	B			CHIR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	09										OPERATOR RECEIVED 2 NEW 369A1305 FEATHERING BEARING HOUSINGS THAT DID NOT HAVE THE HOLE DRILLED TO ATTACH THE 369D21333-	3 STRIKER PLATE.  THE FIRST ONE DID NOT HAVE THE HOLE DRILLED, THE SECOND ONE ORDERED UNDER WARRANTY DID NOT HAVE THE HO	LE EITHER.  SUBMITTER STATED NO QUALITY CONTROL AT MDHS.  CALLED AND ADVISED MDHS AFTER THE FIRST ONE AND ASKED THEM TO 	LOOK AT THE NEXT ONE THEY SENT TO BE SURE HOLE WAS THERE.  (X)			1	G	7	1 	3U			 	H3WE
1998050800490	19980508	00490	EA  	1998	5	8	CHI2087          	1	19980323	G	2612	473275	FIRE DETECTOR   	KIDDE       		BOEING	107   	1072        	9420604	EA  										AFT LOWER OTBD	MALFUNCTIONED   	B			CHIR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	09	CFHFW				1499	107				AFT LOWER OUTBOARD FIRE DETECTOR MALFUNCTION CAUSED FIRE LIGHT TO FALSELY ILLUMINATE.  INSTALLED PER STC SR00375SE.  (X)						2	G	7	2 	4U				1H16
1998050800489	19980508	00489	EA  	1998	5	8	CHI2088          	1	19980323	G	2612	473275	FIRE DETECTOR   			BOEING	107   	1072        	9420604	EA  										OUTBOARD	FAILED          	B			CHIR	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			NM	09	CFHFW				0464	107				FIRE DETECTOR MALFUNCTION CAUSED FIRE LIGHT TO FALSELY ILLUMINATE.  INSTALLED PER STC SR00375SE.  (X)						2	G	7	2 	4U				1H16
1998062600108	19980626	00108	SW  	1998	6	26	CHI3063          	1	19980521	G	6321	D01381	LINING          			BELL  	407   	407         		SW  										ROTOR BRAKE	BROKEN          	B			CHIR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	808TV	392  				53088				DURING PILOT'S PRE-FLIGHT, HE FOUND WHAT APPEARED TO BE ROTOR BRAKE LINING BELOW THE ENGINE DRIVE SHAFT AFT OF THE FIREW	ALL.  MAINTENANCE REMOVED BOTH BRAKE CALIPERS AND FOUND LT FWD AND RT AFT LININGS MISSING.  LINING APPEARS TO HAVE DEBON	DED AND FELL INTO THE ENGINE DECK.  BOTH THE ROTOR BRAKE DISK AND LININGS SHOWS NO SIGNS OF OVERTEMP.  (X)				1	G	7	1 	3U			O	H2SW
1998082800077	19980828	00077	NM  	1998	8	28	CS1R075K         	1	19980701	G	5220		DOOR            			AMD   	FALC50	FALCON2000  	2730170	NM  										RT EMERG EXIT	NOT SECURED     	B	L		CW1R	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			J			WARNING INDICATION        			TO	TAKEOFF        	1			EA	25	790M	1595 				19				DURING TAKEOFF, ROLL DOOR WARNING ILLUMINATED AND CREW ABORTED TAKEOFF.  AIRCRAFT RETURNED TO RAMP AND INSPECTION DETERM	INED THE EMERGENCY EXIT WAS NOT FULLY SECURED.					2	K	7	3 	4F			RT	A50NM
1999040200488	19990402	00488	SW  	1999	4	2	CZMA061348       	1	19981007	G	5521	205030856113	RIB             			BELL  	412   	412         	1182202	SW  										ELEVATOR	CRACKED         	E			CZMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	412BE	151  				33036				PART WAS PURCAHSED NEW AND USED AS A SPARE WHILE ORIGINAL AIRCRAFT EQUIPMEMT ELEVATOR WAS BEING REPAIRED.  PART WAS THEN	 SENT TO HELIPRO FOR EMBODIMENT OF T.B. 412-83-31.  RIB WAS DISCOVERED AS BEING CRACKED AT HELIPRO AND WAS RETURNED TO C	USTOMER FOR WARRANTY ADMIN.  REPLACED WITH SERVICABLE CUSTOMER SUPPLIED SPARE, WHICH WAS REPAIRED ORIGINAL AIRCRAFT EQUI	PMENT.  DEFECTIVE UNIT REPAIRED AT HELIPRO COMPLETIONS LTD.			1	G	7	2 	4U				H4SW
1999040200489	19990402	00489	SW  	1999	4	2	CZMA061349       	1	19981008	G	3411	412075719101	FITTING         			BELL  	412   	412         	1182202	SW  										STATIC PORT	DEFECTIVE       	E			CZMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SO	03	911BE	4386 				36018				DURING ANNUAL INSPECTION, NUT SECURING COVER TO THE THIRD STATIC PORT ON COPILOT'S SIDE WAS REMOVED TAKING THE THREADS O	F THE STATIC PORT WITH IT.  THE NUT IS A STAINLESS STEEL ELASTIC STOP NUT INSTALLED ON A SOFT ALUMINUM STATIC PORT. THIS	 MATERIAL COMBINATION LEADS TO THE EVENTUAL DESTRUCTION OF THE STATIC PORT AND CONSIDERABLE COST IN REPLACING SAME.  PIL	OT SIDE WAS ALSO DAMAGED, BUT REPAIRED USING APPROPRIATE TOOLING DIE.  (1/4 28).  NON-LOCKING WINGNUTS WITH LOCK WASHERS	 HAVE BEEN INSTALLED TO ALLEVIATE FURTHER DAMAGE, ALTHOUGH THIS IS CONTRARY TO THE BHT IPC.   REPLACED STATIC PORT (FITT	ING) WITH NEW PART FROM BHT.	1	G	7	2 	4U				H4SW
1999040900679	19990409	00679	SW  	1999	4	9	CZMA061412       	1	19980728	G	7920	70061L000V174A	LINE            			BELL  	412   	412         	1182202	SW  										ENGINE OIL	LEAKS           	E			CZMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SO	03	911BE					36018				HOSE ASSEMBLY LEAKED ON INITIAL INSTALL AT OIL COOLER END. RE-INSTALLED ORIGINAL HOSE WHICH WAS DEEMED SERVICABLE. ORIGI	NAL HOSE WAS PURCHASED WITH AIRCRAFT.					1	G	7	2 	4U				H4SW
1999011500591	19990115	00591		1999	1	15	ERAA059956       	4	19981208	G	3457	8143902240B	GPS             			SKRSKY	S61   	S61N        	8142104	NE  										COCKPIT	MALFUNCTIONED   	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	563EH					61808				NEW GPS INSTALLED ON AIRCRAFT BUT WOULD NOT POWER UP AND HAD TO BE REMOVED.						2	G	7	2 	4U				1H15
1999011500592	19990115	00592		1999	1	15	ERAA059957       	4	19981209	G	3444	4004437903	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	414EH					33007				ALTIMETER UNIT REPAIRED BY HONEYWELL , REF NR 267248.						1	G	7	2 	4U				H4SW
1999011500593	19990115	00593		1999	1	15	ERAA059958       	4	19981209	G	3416	1901350000	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	H			ERAA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	131EH					S595				NEW ALTIMETER WILL NOT TEST, COULD NOT BE INSTALLED ON AIRCRAFT.						1	G	7	2 	3U				H3EU
1999011500594	19990115	00594	EU  	1999	1	15	ERAA059959       	1	19981210	G	2910	E6886430062	B NUT           			BOLKMS	105   	BO105S      	5626006	EU  										HYDRAULIC SYS	DAMAGED         	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	292EH	512  				S843				B-NUT SAFETY WIRE HOLE TORN OUT DUE TO B-NUT MATERIAL BEING SOFT.						1	G	7	2 	3U				H3EU
1999011500595	19990115	00595	GL  	1999	1	15	ERAA059960       	2	19981211	G	7230	E6840406	NUT             			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	152EH					S701				NEW  TIEBOLT NUT WOULD NOT STRETCH BEFORE REACHING MAX TORQUE.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1999011500596	19990115	00596		1999	1	15	ERAA059968       	4	19981218	G	3457	8143802240A	GPS             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	415EH					33009				GPS UNIT WILL NOT COUPLE TO NAV ON AFCS SYSTEM.						1	G	7	2 	4U				H4SW
1999011500597	19990115	00597		1999	1	15	ERAA059969       	4	19981221	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	417EH					33031				AFCS COMPUTER UNIT HAS UNCOMMANDED LEFT ROLL.						1	G	7	2 	4U				H4SW
1999011500598	19990115	00598	EU  	1999	1	15	ERAA059970       	1	19981221	G	3213	10550103	SKID            			BOLKMS	105   	BO105S      	5626006	EU  										SKID TUBE	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	426EH					S552				NEW SKID TUBES COULD NOT BE USED ON AIRCRAFT.  NUTPLATES INSTALLED INCORRECTLY.  (.1250 INCH TOO SHORT.)						1	G	7	2 	3U				H3EU
1999011500599	19990115	00599	EU  	1999	1	15	ERAA059971       	1	19981221	G	3213	10550103	SKID            			BOLKMS	105   	BO105S      	5626006	EU  										SKID TUBE	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	290EH					S850				NEW SKID TUBE COULD NOT BE INSTALLED ON AIRCRAFT.  NUTPLATES INSTALLED INCORRECTLY (.1250 INCH TOO SHORT).						1	G	7	2 	3U				H3EU
1999011500600	19990115	00600		1999	1	15	ERAA059972       	1	19981221	G	3213	10550103	SKID            																	SKID TUBE	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03										NUTPLATES INSTALLED INCORRECTLY (.1250 INCH TOO SHORT).
1999011500601	19990115	00601	EU  	1999	1	15	ERAA059973       	1	19981221	G	3213	10550103	SKID            			BOLKMS	105   	BO105S      	5626006	EU  										SKID TUBE	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	151EH					S706				NEW SKID TUBE COULD NOT BE INSTALLED ON A/C DUE TO NUTPLATES INSTALLED INCORRECTLY (.1250 INCH TOO SHORT).						1	G	7	2 	3U				H3EU
1999011500602	19990115	00602	EU  	1999	1	15	ERAA059974       	1	19981221	G	3213	10550103	SKID            			BOLKMS	105   	BO105S      	5626006	EU  										SKID TUBE	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	148EH					S703				NEW SKID TUBE COULD NOT BE INSTALLED ON AIRCRAFT DUE TO NUTPLATES INSTALLED INCORRECTLY (.1250 INCH TOO SHORT).						1	G	7	2 	3U				H3EU
1999011500603	19990115	00603		1999	1	15	ERAA059976       	4	19981222	G	3444	7001840903	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										RADAR ALTIMETER	FAILED          	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	419EH					33043				TRANSCEIVER UNIT INTERMITTENT AND WILL NOT TEST.						1	G	7	2 	4U				H4SW
1999011500604	19990115	00604		1999	1	15	ERAA059977       	4	19981223	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	H			ERAA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	416EH					33011				AFCS COMPUTER UNIT SENT TO HONEYWELL FOR REPAIR AND RETURNED WITH A/C PITCH CHANNEL HARD OVER.   COULD NOT BE INSTALLED 	ON AIRCRAFT.					1	G	7	2 	4U				H4SW
1999011500605	19990115	00605		1999	1	15	ERAA059978       	4	19981223	G	3444	7001840903	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										RADAR ALTIMETER	MALFUNCTIONED   	H			ERAA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			AL	03	419EH					33043				TRANSCEIVER UNIT HAS 24 FLIGHT HOURS SINCE REPAIR.  NEEDLE GOES TO HIGH SIDE OF GAUGE AND NEVER COMES DOWN.						1	G	7	2 	4U				H4SW
1999022600386	19990226	00386	SW  	1999	2	26	ERAA060580       	1	19981224	G	6220	412010264101	BRACKET         			BELL  	412   	412         	1182202	SW  										YOKE ATTACH	LOOSE           	H			ERAA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			AL	03	168EH	149  				33067				OUTBOARD BUSHING LOOSE IN BORE.						1	G	7	2 	4U				H4SW
1999022600387	19990226	00387	SW  	1999	2	26	ERAA060581       	1	19981230	G	6320	212040263101	QUILL ASSY      			BELL  	412   	412         	1182202	SW  										TRANSMISSON	MISMANUFACTURED 	H			ERAA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			AL	03	177EH					33037				INSPECTION OF INPUT QUILL ASSY REVEALED THAT  INCORRECT SHIMMING PROCEDURE RESULTED IN CAP ASSY AND PINION HAVING TO BE 	REPLACED.  INSTALLED NEW CAP, BEARINGS, SEALANT PACKINGS.  PINION THAT WAS REMOVED WAS SENT TO ABLE METALLICS FOR REPLAT	ING DUE TO COPPER PLATING DAMAGE.				1	G	7	2 	4U				H4SW
1998091100068	19980911	00068	EA  	1998	9	11	GLBR98100        	2	19980717	G	7414		MAGNETO         	SLICK       	K3822       	CESSNA	150   	152         	2071835	CE  	LYC   	O235  	O235N2C     	41505	EA  					ENGINE	FAILED          	B			GLBR	O				OTHER                   				O			OTHER                     			CR	CRUISE         	1			CE	01	757DQ					15279660	RL2474515			LEFT MAGNETO QUIT IN-FLIGHT.  REMOVED AND REPLACED DISTRIBUTOR BLOCK AND GEAR ASSY IAW UNISON SPECS.  INSTALLED ONE ENGI	NE IAW TEXTRON LYC SPECS.  TIMED TO ENGINE.  MAGS CHECK GOOD.  (X)					1	H	7	1 	3O	3	O	NT	3A19    	E223
1998091800370	19980918	00370	CE  	1998	9	18	GLBR98101        	1	19980717	G	5320	1065301038	SUPPORT         			BEECH 	58    	58          	1152740	CE  										CABIN	BROKE           	B			GLBR	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			CE	01	458GL					TH1376				AFTER TAKE OFF PORT SIDE PASSENGER WINDOW SUPPORT BROKE.  REMOVED /REPLACED PORT AND STARBOARD TORQUE TUBES AND ONE EACH	 EMERGENCY CATCH SUPPORT ON PORT (FORWARD) WINDOW IAW MANUFACTURER'S SPECS.  PART TOTAL TIME: 7,570.7 HOURS.  (X)					1	L	7	2 	3O				3A16
1998040200726	19980402	00726	SW  	1998	4	2	HAI00000001      	1	19980326	G	6220	412010106101	BEARING         			BELL  	412   	412         	1182202	SW  										M/R RED	WORN            	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	900BH	1888 				33195				BEARING IS WORN EXCESSIVELY. REPLACED WITH NEW						1	G	7	2 	4U				H4SW
1998051500496	19980515	00496	GL  	1998	5	15	HAI00000002      	2	19980508	G	7532	23005366	BLEED VALVE     			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	FAILED          	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	899BH					51089				ENGINE FAILED POWER ASSURANCE CHECK DURING TEST FLIGHT FOLLOWING INSTALLATION OF ENGINE FOLLOWING EXTENDED MAINTENANCE I	NCLUDING BLEED VALVE OVERHAUL. INSTALLED REPLACEMENT OVERHAULED BLEED VALVE AND ENGINE TESTED AT +10%					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998012200401	19980122	00401	SW  	1998	1	22	HAIGJQR0159      	1	19980107	G	7810	212061202009	DUCT ASSY       			BELL  	212   	212         	1181420	SW  										LT EXHAUST	DEFECTIVE       	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	538  				35100				TO C/W TB212-97-163. REPLACED WITH NEW PART FROM BHT - O/H'D NOT AVAILABLE.  COULD NOT INSTALL WITHIN 30 DAYS, HAD TO GR	OUND SHIP TO INSTALL AND COULD NOT GROUND UNTIL DEC. 97.					1	G	7	1 	4U				H4SW
1998012200402	19980122	00402	SW  	1998	1	22	HAIGJQR0160      	1	19980107	G	3040	204070907001	CONVERTER       			BELL  	212   	212         	1181420	SW  										WIPER MOTOR	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	491  				35100				WIPER CONVERTER UNIT IS INOP. REPLACED WITH NEW PART FROM BHT						1	G	7	1 	4U				H4SW
1998020500079	19980205	00079	SW  	1998	2	5	HAIGJQR0161      	1	19980107	G	6420	212011713103	STOP            			BELL  	212   	212         	1181420	SW  										T/R HEAD	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	538  				35100				CORROSION ON MATING SURFACES REPLACED WITH NEW PART FROM BHT						1	G	7	1 	4U				H4SW
1998012200403	19980122	00403	SW  	1998	1	22	HAIGJQR0162      	1	19980107	G	6700	209011710005	TUBE            			BELL  	212   	212         	1181420	SW  										CONTROL	SCORED          	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	98W	419  				35100				SHAFT HAS HEAVY SCORING WHICH ALLOWS OIL TO SEEP BY. REPLACED WITH TUBE REMOVED FROM A/C AND SENT IN FOR LOCAL REPAIR -						1	G	7	1 	4U				H4SW
1998012200404	19980122	00404	SW  	1998	1	22	HAIGJQR0163      	1	19980115	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										DROOP COMP	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	86W	302  				4142				CORROSION - THE FAILURE RATE FOR THESE ACTUATORS, ALL P/N'S, ARE EXCESSIVE.  THE COMMON DISCREPANCY REPORT FROM THE OVER	HAUL SHOP SUGGESTS THAT THE COMPONENT IS NOT ADEQUATELY SEALED.  BEARINGS BAD, GREASE CONTAMINATED, ARMATURE CORRODED, E	TC. REPLACED WITH O/H'D UNIT FROM OUR OWN STOCK.				1	G	7	1 	3U				H2SW
1998042400284	19980424	00284	SW  	1998	4	24	HAIGJQR0166      	1	19980121	G	3040	204070907101	MOTOR           			BELL  	212   	212         	1181420	SW  										WIPER	MIS MARKED      	H			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	98W					35100				ORDERED 204-070-907-001, RH MOTOR, AND RECEIVED 204-070-907-101 WHICH IS A LH MOTOR.  SUBMITTER THINKS THIS HAS BEEN MIS	MARKED.					1	G	7	1 	4U				H4SW
1998042400285	19980424	00285		1998	4	24	HAIGJQR0169      	1	19980212	G	6220	206011120103	TRUNNION        																	M/R	DAMAGED         	H			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01										MFG. DAMAGE IN RADII. REPLACED WITH NEW TRUNNION.
1998030500669	19980305	00669	SW  	1998	3	5	HAIGJQR0170      	1	19980226	G	6220	204010937009	DAMPER ASSY     			BELL  	212   	212         	1181420	SW  										M/R	LEAKING         	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	98W	538  				35100				DAMPER HAS EXCESSIVE LEAKAGE. REPLACED DAMPER FROM CSF STOCK -						1	G	7	1 	4U				H4SW
1998030500670	19980305	00670	SW  	1998	3	5	HAIGJQR0171      	1	19980226	G	6220	204010937009	DAMPER ASSY     			BELL  	212   	212         	1181420	SW  										M/R	LEAKING         	H			GJQR	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			FS	01	98W	538  				35100				DAMPER ASSY EXCESSIVE LEAKAGE. REPLACED DAMPER FROM CSF STOCK -						1	G	7	1 	4U				H4SW
1998042400286	19980424	00286	SW  	1998	4	24	HAIGJQR0180      	1	19980410	G	6210	206015001107	BLADE           			BELL  	212   	212         	1181420	SW  										M/R	DAMAGED         	H			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			FS	01	98W					35100				RECEIVED NEW BLADE FROM BHT - DAMAGED. REPLACED WITH NEW BLADE FROM BHT						1	G	7	1 	4U			 	H4SW
1998042400287	19980424	00287	SW  	1998	4	24	HAIGJQR0181      	1	19980410	G	7931	APTE138A100G	TRANSMITTER     			BELL  	212   	212         	1181420	SW  										OIL SYS	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	579  				35100				TRANSMITTER INOP.						1	G	7	1 	4U				H4SW
1998042400288	19980424	00288	SW  	1998	4	24	HAIGJQR0182      	1	19980410	G	6710	412076620101	UNIVERSAL       			BELL  	212   	212         	1181420	SW  										COLLECTIVE	ROUGH           	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	782  				35100				BEARING FEELS GRAVELLY ON ONE END WITH BLACK SUBSTANCE COMING OUT OF IT. REPLACED WITH NEW PART FROM BHT.						1	G	7	1 	4U				H4SW
1998042400289	19980424	00289	SW  	1998	4	24	HAIGJQR0183      	1	19980410	G	6710	412076620101	UNIVERSAL       			BELL  	212   	212         	1181420	SW  										COLLECTIVE	ROUGH           	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	782  				35100				BEARING FEELS GRAVELLY ON ON END WITH BLACK SUBSTANCE COMING OUT. REPLACED WITH NEW PART FROM BHT.						1	G	7	1 	4U				H4SW
1998042400290	19980424	00290	EA  	1998	4	24	HAIGJQR0184      	2	19980410	G	7210	M274263215B	RING            			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					GR BOX	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	782  				35100				RETAINING RING CORRODED REPLACED WITH NEW PARTS FROM BHT						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998042400291	19980424	00291	SW  	1998	4	24	HAIGJQR0186      	1	19980410	G	6310	212040687001	COUPLING        			BELL  	212   	212         	1181420	SW  										M/R	PITTED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	782  				35100				PITTING BEYOND LIMITS. REPLACED WITH NEW PART FROM BHT						1	G	7	1 	4U				H4SW
1998042400292	19980424	00292	SW  	1998	4	24	HAIGJQR0187      	1	19980410	G	6310	212040688003S	COUPLING        			BELL  	212   	212         	1181420	SW  										ENG/XMSN	PITTED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	782  				35100				PITTING BEYOND LIMITS. REPLACED WITH NEW PART FROM BHT						1	G	7	1 	4U				H4SW
1998070300160	19980703	00160	SW  	1998	7	3	HAIGJQR0199      	1	19980611	G	6210	204011250113	BLADE           			BELL  	204   	UH1H        	1181407	SW  										MAIN ROTOR	MISMANUFACTURED 	H			GJQR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			NM	01	83NW	1128 				6413699				NEW BLADE INSTALLED 6/2/97.  BEST TRACK OBTAINED 1.0 IPS VERTICAL AT 80 KNOTS.  TRIED TO GET BLADES TO FLY TOGETHER FOR 	1,128 HRS.  PULLED BLADE AND PUT ANOTHER BLADE ON SHIP, TRACE NORMAL.  INSTALLED BLADE S/N AFS-11686 ON ANOTHER SHIP TO 	TRY TO USE - COULD NOT TRACK.  BLADES CROSS OVER IN HOVER!  REPLACED S/N AFS-11686 WITH NEW BLADE FROM BHT AND TRACK NOR	MAL.			1	G	7	1 	4U			 	EXPA1G71
1998070300161	19980703	00161	SW  	1998	7	3	HAIGJQR0200      	1	19980611	G	7722	1113034	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	01	98W	812  				35100				TOT INDICATOR INDICATOR INOPERATIVE.						1	G	7	1 	4U				H4SW
1998081400450	19980814	00450		1998	8	14	HAIGJQR0208      	1	19980724	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21566					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400451	19980814	00451		1998	8	14	HAIGJQR0209      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21697					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400452	19980814	00452		1998	8	14	HAIGJQR0210      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21716					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400453	19980814	00453		1998	8	14	HAIGJQR0211      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21648					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400454	19980814	00454		1998	8	14	HAIGJQR0212      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21222					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400455	19980814	00455		1998	8	14	HAIGJQR0213      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21694					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400456	19980814	00456		1998	8	14	HAIGJQR0214      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21717					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400457	19980814	00457		1998	8	14	HAIGJQR0215      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21718					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998081400458	19980814	00458		1998	8	14	HAIGJQR0216      	1	19980727	G	6410	204011702121	BLADE           																	TAIL ROTOR	CORRODED        	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01					A21719					CORRODED IN BUSHINGS.  REPLACED BLADES.
1998082100295	19980821	00295		1998	8	21	HAIGJQR0217      	4	19980812	G	3424	570074252005	GYRO            			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	62200	953  			GT160	35065				THIS UNIT WAS SENT INTO BELL IN 2/27/97 FOR REPAIR - BELL REPLACED RATE GYRO AND FUNCTIONAL TESTED.  THE SAME UNIT WAS S	ENT BACK TO BELL 6/98 FOR YAW CHANNEL ERRATIC.  BELL REPAIRED THIS UNIT AGAIN AND REPLACED THE RATE GYRO AGAIN.					1	G	7	1 	4U				H4SW
1998091100190	19980911	00190	SW  	1998	9	11	HAIGJQR0219      	1	19980831	G	2437	209070264003	DUAL AMMETER    			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	H			GJQR	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			FS	01	98W	837  				35100				PILOT REPORTS THAT NR 1 NEEDLE HANGS UP INTERMITTENTLY ON AMMETER.   REPLACED WITH NEW PART.						1	G	7	1 	4U				H4SW
1998091100191	19980911	00191	SW  	1998	9	11	HAIGJQR0220      	1	19980831	G	7332	212075037113	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	H			GJQR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			FS	01	98W	843  				35100				INDICATOR HANGS UP ON START.  REPLACED WITH NEW PART.						1	G	7	1 	4U				H4SW
1998111100005	19981111	00005	SW  	1998	11	11	HAISUPR0009      	1	19981016	G	5302	206020123048S	RIB             			BELL  	206   	206B        	1181511	SW  										TAIL BOOM	CRACKED         	H				K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	05	1080N	9574 				3579				RIGHT TAILBOOM ATTACH FITTING P/N 206-020-121-010 CRACKED.  (PART OF LISTED ASSY.)  REPLACED RIB ASSEMBLY.						1	G	7	1 	3U			 	H2SW
1999051400173	19990514	00173	EU  	1999	5	14	HCMA061980       	1	19980616	G	6410	350A33215300	BEARING         			SNIAS 	350   	AS350BA     	8680817	EU  										TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	862BH	597  				2713				RUBBER IS CRACKED AND DETERIORATED BEYOND LIMITS.						1	G	7	1 	3U			NC	H9EU
1999051400174	19990514	00174	EU  	1999	5	14	HCMA061984       	1	19980617	G	6510	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					PITCH CONTROL	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	196BH	693  				3036	9531			PC LINK BALL JOINT WORN BEYOND LIMITS.						1	G	7	1 	3U	3	U		H9EU    	E19EU
1999051400175	19990514	00175	EU  	1999	5	14	HCMA061987       	1	19980618	G	6510	SL100153B	PIN             			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	196BH	727  				3036	9531			EXPANSION PIN PART HAS  EXCESSIVE PLAY.						1	G	7	1 	3U	3	U		H9EU    	E19EU
1999051400176	19990514	00176	EU  	1999	5	14	HCMA061999       	1	19980821	G	6510	7704411	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	LEAKING         	E			HCMA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			WP	13	196BH	907  				3036				MAGNETIC SEAL LEAKS.						1	G	7	1 	3U				H9EU
1999051400177	19990514	00177	EU  	1999	5	14	HCMA062000       	1	19980821	G	8011	P600705	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										STARTER	LOOSE           	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	196BH	967  				3036				BEARING SPINNING ON MOUNTING FLANGE.						1	G	7	1 	3U				H9EU
1999051400178	19990514	00178	EU  	1999	5	14	HCMA062001       	1	19980821	G	6410	355A09103601	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					TAIL ROTOR	CRACKED         	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	997BH	996  				2666	9246			BEARING CRACKED BEYOND LIMITS.						1	G	7	1 	3U	3	U		H9EU    	E19EU
1999051400179	19990514	00179	EU  	1999	5	14	HCMA062017       	1	19981222	G	6410	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					TAIL ROTOR	WORN            	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	997BH	832  				2666	9246			BEARING IS DISTORTED OUT OF LIMITS.						1	G	7	1 	3U	3	U		H9EU    	E19EU
2000030400175	20000304	00175	EU  	2000	3	4	HCMA066231       	1	19980303	G	6500	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DAMAGED         	E			HCMA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	13	992BH	602  				2889				BEARING DAMAGED BEYOND LIMITS AND THERE IS NO J GAP.						1	G	7	1 	3U				H9EU
1998012200432	19980122	00432		1998	1	22	HEEA0012447      	1	19980105	G	7921	3701020000	COOLER          																	ENG OIL	DAMAGED         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										OIL COOLER RECEIVED WITH CONCEALED DAMAGE.
1998012200433	19980122	00433		1998	1	22	HEEA0012448      	1	19980105	G	2822	9A1746	CARTRIDGE       																	FUEL SYS	DEFECTIVE       	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03										CARTRIDGE NOT WORKING.  LIGHT CAME ON DURING FLIGHT.
1998012200434	19980122	00434		1998	1	22	HEEA0012449      	1	19980105	G	2822	9A1746	CARTRIDGE       																	NR 2 FUEL PUMP	DEFECTIVE       	E			HEEA	O				OTHER                   				J			WARNING INDICATION        			NR	NOT REPORTED   	1			SW	03										NR2 FUEL PUMP FAILED IN FLIGHT.
1998012200435	19980122	00435		1998	1	22	HEEA0012450      	1	19980105	G	2822	9A1746	CARTRIDGE       																	FUEL PUMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FUEL PUMP CARTRIDGE INOPERATIVE.  CIRCUIT BREAKER POPPING.
1998042900445	19980429	00445	GL  	1998	4	29	HEEA0012543      	2	19980107	G	7260	6894171	GEAR BOX        								ALLSN 	250C  	250C20B     	03013	GL  					ENG ACESSORY	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		4774 					CAE836429			GEARBOX REMOVED DUE TO HIGH GEARBOX PRESSURE ON TEST CELL.  VISUAL INSPECTION REVEALED:  A 1/4" X 3/4" X 3/4" BLACK RUBB	ER MATERIAL LODGED IN GEARBOX VENT.  REMOVED MATERIAL										3	U			E4CE
1998021900032	19980219	00032		1998	2	19	HEEA0012802      	4	19980205	G	2312	40001278500	TRANSCEIVER     		RT40        															COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSCEIVER WEAK POWER OUT.  POWER AMPLIFIER ON RT ASSEMBLY BAD.
1998021900070	19980219	00070		1998	2	19	HEEA0012845      	4	19980205	G	3425	071105304	SYNCHRO         		KA51A       															COCKPIT HSI	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CANNOT CALIBRATE SYNCHRO.  HSI READS 5 OFF.
1998022600025	19980226	00025	EA  	1998	2	26	HEEA0012971      	2	19980210	G	7322	25244405	FUEL CONTROL    								PWA   	PT6   	PT6A27      	52043	EA  					ENGINE	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FUEL CONTROL DEFECTIVE.  BENCH CHECK AS RECEIVED DUE TO:  REPORTED ENGINE SHUTDOWN,  ONCE 60% N1 SPEEDS ARE REACHED DURI	NG START UP.										4	T			E4EA
1998022600023	19980226	00023	GL  	1998	2	26	HEEA0012987      	2	19980210	G	7230	6896888	SCROLL          		23051643    						ALLSN 	250C  	250C30S     	03013	GL  					ENG COMP	MISALIGNED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC90484		CAE890180S			COMPRESSOR REPAIR DUE TO LOW POWER ON TEST CELL.  INSPECTION OF COMPRESSOR PARTS REVEALED:  MISALIGNMENT OF SCROLL ASSEM	BLY TURNING VANES. INSTALLED A PHI OVERHAULED SCROLL.										3	U			E1GL
1998021900798	19980219	00798		1998	2	19	HEEA0013009      	1	19980210	G	3412	271600	THERMOMETER     																	OAT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TEMPERATURE OFF 70 ON OAT.
1998031200670	19980312	00670		1998	3	12	HEEA0013220      	4	19980304	G	3421	222375033103	INDICATOR       																	COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ATTITUDE INDICATOR PRECESSES.
1998032600677	19980326	00677		1998	3	26	HEEA0013405      	1	19980318	G	7722	50061051	INDICATOR       																	ENG TOT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ENG TOT NEEDLE STICKS.
1998040200344	19980402	00344		1998	4	2	HEEA0013440      	1	19980318	G	2430	51509002R	CONTROL UNIT    																	NR 2 DC SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NR 2 GENERATOR WOULD NOT COME ON LINE.
1998040200358	19980402	00358	GL  	1998	4	2	HEEA0013455      	2	19980319	G	7323	252469211	GOVERNOR        								ALLSN 	250C  	250C30      	03013	GL  					ENGINE	MIS REPAIRED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVED FROM STOCK.  WHEN WOOD BLOCK REMOVED FOUND CIRCLIP LAGGING IN BLOCK.  NEVER INSTALLED ON AIRCRAFT. INSPECTED GO	VERNOR WHEN RECEIVED IN SHOP.  FOUND DRIVE COUPLING ON DRIVE SHAFT TO STILL HAVE 934 BONDING AND IN GOOD SHAPE.  INSPECT	ED SUSPECTED CLIP RECEIVED WITH GOVERNOR AND CLIP DOES NOT BELONG ON GOVERNOR  (CANNOT IDENTIFY CLIP)									3	U			E1GL
1998040200799	19980402	00799		1998	4	2	HEEA0013541      	4	19980326	G	3453	4530103	LORAN           		ARNAV21     															COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										RECEIVER FALLS OFF LINE.
1998041000701	19980410	00701		1998	4	10	HEEA0013613      	4	19980326	G	3444	7001840903	TRANSCEIVER     																	RADAR ALT	DEFECTIVE       	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03										FAILS TEST 5.1 AND 5.2 ON SST AND WILL NOT ADJUST.
1998041000733	19980410	00733		1998	4	10	HEEA0013647      	4	19980326	G	3422	5208130004	INDICATOR       																	COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										HORIZ INDICATOR AEM LIGHT COMES ON IN NORMAL POSITION.
1998041700030	19980417	00030		1998	4	17	HEEA0013703      	4	19980402	G	3416	A30	ENCODER         																	COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ALTITUDE ENCODER INOPERATIVE.
1998041700178	19980417	00178		1998	4	17	HEEA0013775      	3	19980402	G	6114		HUB             			KING A														PROP	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH	7343 				BL3				BLADE GRIP SEALS LEAKING GREASE.  LOOSE DEVICE SLIP RING.
1998041700200	19980417	00200		1998	4	17	HEEA0013803      	1	19980402	G	2820	1036484	VALVE           			KING A														FUEL SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30PH					BB635				VALVE HAS EXCESSIVE LEAKAGE.
1998041700201	19980417	00201		1998	4	17	HEEA0013804      	1	19980402	G	2422	PC17	INVERTER        			KING A														AC SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH					BL3				INVERTER WILL NOT COME ON LINE.  WORKED FOR ONE HOUR AFTER CLEANING CANNON PLUG.
1998041700218	19980417	00218		1998	4	17	HEEA0013826      	1	19980402	G	3340	200063710000	POWER SUPPLY    																	STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STROBE POWER SUPPLY BLOWS FUSE.
1998042400324	19980424	00324	GL  	1998	4	24	HEEA0013882      	2	19980410	G	7230	6898960	SCROLL          								ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  HOLE IN INNER SHROUD AT PARTICLE SEPARATOR MOUNT BOLT HOLE.											3	U			E1GL
1998050800619	19980508	00619		1998	5	8	HEEA0013978      	1	19980420	G	7933	648180121	INDICATOR       																	OIL TEMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										OIL TEMP IND DID NOT WORK.  180 DEGREE OUT OF ALIGNMENT.
1998050800642	19980508	00642	GL  	1998	5	8	HEEA0014004      	2	19980421	G	7230	6887619	SEAL            		23033191    						ALLSN 	250C  	250C28B     	03013	GL  					ENG COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC70662		CAE860213			COMPRESSOR DISASSEMBLED DUE TO LOW POWER ON TEST CELL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED:  CRACKED AND FLAKING 	ON SEAL CARBON OUTER EDGE. INSTALLED A NEW SEAL.										3	U			E1GL
1998050801129	19980508	01129	GL  	1998	5	8	HEEA0014091      	2	19980430	G	7230	230052711	SPLINE ADAPTER  								ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	MIS MFG         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MEASURED (.9853) .0002 BELOW SPECS .9855 - .9860 ON SPLINED ADAPTER O.D.											3	U			E1GL
1998052200536	19980522	00536		1998	5	22	HEEA0014165      	1	19980511	G	7714	8DJ131LAV1	INDICATOR       																	TRIPLE TACH	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRIPLE TACH INDICATOR EXCESSIVE NEEDLE SPLIT.
1998052200556	19980522	00556		1998	5	22	HEEA0014185      	1	19980512	G	2435	23046313	STATOR          		23046020    															START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					10720					CAUSES STARTER GENERATOR TO HAVE EXCESSIVE ARCHING ON TEST STAND AND REPLACEMENT CORRECTED PROBLEM.
1998062600547	19980626	00547	EU  	1998	6	26	HEEA0014413      	1	19980601	G	7931	648180101	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				FLUCTUATES IN-FLIGHT, TO HIGH SIDE.						1	G	7	1 	3U				H9EU
1998062600406	19980626	00406	SW  	1998	6	26	HEEA0014414      	1	19980601	G	6310	406040500123	FREEWHEEL UNIT  			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	405PH	552  				53207				LEAKING OIL FROM MAG SEAL FORWARD PAD SEAL.						1	G	7	1 	3U			O	H2SW
1998062600407	19980626	00407	SW  	1998	6	26	HEEA0014416      	1	19980601	G	6300	407010201101	BEAM ASSEMBLY   			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	156  				53114				M/R BEAM WORN SPOT FROM HYDRAULIC HOSE.						1	G	7	1 	3U			O	H2SW
1998062600548	19980626	00548	EU  	1998	6	26	HEEA0014417      	1	19980601	G	6710	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6100R	1121 				2862				SERVO LEAKING.						1	G	7	1 	3U				H9EU
1998062600408	19980626	00408	SW  	1998	6	26	HEEA0014418      	1	19980601	G	6321	206340301103	ROTOR BRAKE     			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	552  				53207				ROTOR BRAKE WEAK AND WORN.						1	G	7	1 	3U			O	H2SW
1998062600409	19980626	00409	SW  	1998	6	26	HEEA0014419      	1	19980601	G	6730	206076062105	SERVO           			BELL  	407   	407         		SW  										M/R	CHATTERING      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	447PH	1199 				53114				SERVO CHATTERING INTERMITTENTLY CAUSING HIGH FREQUENCY.						1	G	7	1 	3U			O	H2SW
1998070200005	19980702	00005	SW  	1998	7	2	HEEA0014420      	1	19980601	G	3260	602EN6026	SWITCH          			BELL  	407   	407         		SW  										MLG	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407PH					53003				SWITCH WITH INTERMITTENT OPERATION CAUSES CAUTION PANEL TO COME ON DIM, THEN BRIGHT.						1	G	7	1 	3U			O	H2SW
1998062600410	19980626	00410	SW  	1998	6	26	HEEA0014421      	1	19980601	G	7933	MS280343	SENSOR          			BELL  	407   	407         		SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	457PH					53147				SENSOR CAUSING HIGH OIL TEMP READING.						1	G	7	1 	3U			O	H2SW
1998062600411	19980626	00411	SW  	1998	6	26	HEEA0014422      	1	19980601	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				FOUND CRACKED T/R DRIVE SHAFT DISC PACK COUPLING.						1	G	7	1 	3U			O	H2SW
1998062600412	19980626	00412	SW  	1998	6	26	HEEA0014423      	1	19980601	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				NR 1 LAMINATE CRACKED.						1	G	7	1 	3U			O	H2SW
1998062600413	19980626	00413	SW  	1998	6	26	HEEA0014424      	1	19980601	G	6720	406312103101	BEARING         			BELL  	407   	407         		SW  										T/R LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS-2193 AND NHFS-2195.						1	G	7	1 	3U			O	H2SW
1998062600414	19980626	00414	SW  	1998	6	26	HEEA0014425      	1	19980601	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	EXCESSIVE GAP   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				EXCESSIVE GAP BETWEEN DISC.						1	G	7	1 	3U			O	H2SW
1998062600415	19980626	00415	SW  	1998	6	26	HEEA0014426      	1	19980601	G	2437	M803B205VBATT	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				BATTERY INDICATOR GAUGE HAS INOPERATIVE LCD SEGMENT ON THE Y10 VOLT NUMBER, LT LOWER VERTICAL LCD SEGMENT.						1	G	7	1 	3U			O	H2SW
1998062600416	19980626	00416	SW  	1998	6	26	HEEA0014427      	1	19980601	G	7120	407060111101	BEARINGS        			BELL  	407   	407         		SW  										ENGINE MOUNT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				BEARINGS WORN IN BIPOD MOUNT.						1	G	7	1 	3U			O	H2SW
1998062600417	19980626	00417	SW  	1998	6	26	HEEA0014428      	1	19980601	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				WHILE COMPLYING WITH AD 97-24-17, DISCOVERED DISC PACK COUPLING DIRECTLY BEHIND OIL COOLER HAD A CRACKED DISC.						1	G	7	1 	3U			O	H2SW
1998062600418	19980626	00418	SW  	1998	6	26	HEEA0014429      	1	19980601	G	3210	MS2774324	RELAY           			BELL  	407   	407         		SW  										MLG SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				MLG RELAY STUCK CLOSED.						1	G	7	1 	3U			O	H2SW
1998062600549	19980626	00549	EU  	1998	6	26	HEEA0014430      	1	19980601	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	127  				2820				T/R PITCH CONTROL ROD BEARING WORN.						1	G	7	1 	3U				H9EU
1998062600419	19980626	00419	SW  	1998	6	26	HEEA0014431      	1	19980601	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				CRACKED DISC ON T/R DISC COUPLING.						1	G	7	1 	3U			O	H2SW
1998062600420	19980626	00420	SW  	1998	6	26	HEEA0014432      	1	19980601	G	2822	407362013101	PRESSURE SWITCH 			BELL  	407   	407         		SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	427PH					53059				BOOST PUMP SWITCH HAS INTERMITTENT CONTACT PROBLEMS.						1	G	7	1 	3U			O	H2SW
1998062600421	19980626	00421	SW  	1998	6	26	HEEA0014433      	1	19980601	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998062600422	19980626	00422	SW  	1998	6	26	HEEA0014434      	1	19980601	G	7920	70037A090000	HOSE ASSEMBLY   			BELL  	407   	407         		SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	408PH					53228				HOSE LEAKING.						1	G	7	1 	3U			O	H2SW
1998062600550	19980626	00550	EU  	1998	6	26	HEEA0014435      	1	19980601	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										OIL PRESS IND	MALFUNCTION     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				PRESSURE INDICATOR DROPS TO BELOW RED LINE AT 100 PERCENT THROTTLE.						1	G	7	1 	3U				H9EU
1998062600551	19980626	00551	EU  	1998	6	26	HEEA0014436      	1	19980601	G	6520	350A33215001	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				T/R HAS WORN BEARING.						1	G	7	1 	3U				H9EU
1998062600423	19980626	00423	SW  	1998	6	26	HEEA0014437      	1	19980601	G	6520	406040453101	SEAL            			BELL  	407   	407         		SW  										T/ROTOR GEAR BOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	405PH					53207				T/R GEARBOX SEAL LEAKING.						1	G	7	1 	3U			O	H2SW
1998062600424	19980626	00424	SW  	1998	6	26	HEEA0014438      	1	19980601	G	3212	206050247131	FLOAT COVER     			BELL  	407   	407         		SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				FLOAT COVER WORN.						1	G	7	1 	3U			O	H2SW
1998062600425	19980626	00425	SW  	1998	6	26	HEEA0014439      	1	19980601	G	6500	406040060105	HOUSING         			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				GROOVES WORN INTO T/R FILTER HOUSING.						1	G	7	1 	3U			O	H2SW
1998062600426	19980626	00426	SW  	1998	6	26	HEEA0014440      	1	19980601	G	6720	406312103101	BEARING         			BELL  	407   	407         		SW  										T/R LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				T/R BEARINGS WORN.						1	G	7	1 	3U			O	H2SW
1998062600427	19980626	00427	SW  	1998	6	26	HEEA0014441      	1	19980601	G	6320	357950111452	SHAFT           			BELL  	407   	407         		SW  										M/R GEARBOX	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				M/R GEARBOX HAS GROOVE CUT IN SHAFT BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW
1998062600386	19980626	00386	GL  	1998	6	26	HEEA0014442      	2	19980601	G	7230	23007208	DIFFUSER        		23033191    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	3892R				CAC70726	45594	CAE860059			RECEIVING INSPECTION REVEALED:  DISTORTED BEYOND SERVICEABLE LIMITS ON VANE ASSY.  (VANE L/E).						1	G	7	1 	3U	3	U	 	H2SW    	E1GL
1998062600387	19980626	00387	GL  	1998	6	26	HEEA0014443      	2	19980601	G	7260	230595681	BEARING         		23035179    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GEARBOX	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	22342				CAG90183	760096	CAE890431S			RECEIVING INSPECTION REVEALED:  RUST BEYOND SERVICEABLE LIMITS ON 3 AND 4 CAGE.  INSTALLED A NEW 3 AND 4 CAGE.						1	G	7	2 	3U	3	U	 	H1NE    	E1GL
1998062600428	19980626	00428		1998	6	26	HEEA0014444      	4	19980602	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				OFF FLAG STICKS, AND IS SLOW TO PULL.						1	G	7	2 	4U				H4SW
1998062600429	19980626	00429	SW  	1998	6	26	HEEA0014445      	1	19980602	G	2436	51539002N	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				CONTROL UNIT FAILED.  GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	4U				H4SW
1998062600552	19980626	00552	EU  	1998	6	26	HEEA0014446      	1	19980602	G	6240	DL43638	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				NR 2 NR NEEDLE LAGS BEHIND AND IS RATCHETY.						1	G	7	2 	3U				H3EU
1998062600430	19980626	00430	SW  	1998	6	26	HEEA0014447      	1	19980602	G	2422	ASH4501	INVERTER        			BELL  	412   	412         	1182202	SW  										AC SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				INVERTER HAS LOW OUTPUT.						1	G	7	2 	4U				H4SW
1998062600431	19980626	00431	SW  	1998	6	26	HEEA0014448      	1	19980602	G	2422	1A2501D	INVERTER        			BELL  	212   	212         	1181420	SW  										AC SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				INVERTER HAS LOW AC OUTPUT.						1	G	7	1 	4U				H4SW
1998062600432	19980626	00432	SW  	1998	6	26	HEEA0014449      	1	19980602	G	7712	212070160101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	SHORTED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				NR 2 NEEDLE PEGS AND BLOWS BREAKER.						1	G	7	1 	4U				H4SW
1998062600433	19980626	00433	SW  	1998	6	26	HEEA0014450      	1	19980602	G	7722	212075067105	INDICATOR       			BELL  	412   	412         	1182202	SW  										ITT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				ITT INDICATOR READS HIGH AFTER WARM- UP.						1	G	7	2 	4U				H4SW
1998062600434	19980626	00434	SW  	1998	6	26	HEEA0014451      	1	19980602	G	7712	412075008113	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				ENGINE TORQUE NR 2 NEEDLE DOES NOT OPERATE.						1	G	7	2 	4U				H4SW
1998062600435	19980626	00435		1998	6	26	HEEA0014452      	4	19980602	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				GYRO FAILED, WOULD NOT ALLOW COPILOT RT FLAG TO PULL ON ATT. INDICATOR.						1	G	7	2 	4U				H4SW
1998062600436	19980626	00436	SW  	1998	6	26	HEEA0014453      	1	19980602	G	6240	212070108007	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				ROTOR NEEDLE READS LOW.  SEVERE SPLIT ONE AND 2 NEEDLE.						1	G	7	1 	4U				H4SW
1998062600437	19980626	00437		1998	6	26	HEEA0014454      	4	19980602	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				TURN RATE NEEDLE OSCILLATES.						1	G	7	2 	4U				H4SW
1998062600438	19980626	00438		1998	6	26	HEEA0014455      	4	19980602	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				OFF FLAG FLUCTUATES ON AND OFF.						1	G	7	2 	4U				H4SW
1998062600439	19980626	00439		1998	6	26	HEEA0014456      	4	19980602	G	2210	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2149S					36002				COMPUTER DOES NOT COME ON-LINE.						1	G	7	2 	4U				H4SW
1998070200004	19980702	00004		1998	7	2	HEEA0014457      	4	19980602	G	3421	501145301	GYRO            			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3122G					760232				PITCH AT ADS KEEPS SLOWLY MOVING UP.   TIME SINCE REPAIR 9:50 HOURS.						1	G	7	2 	3U				H1NE
1998062600440	19980626	00440		1998	6	26	HEEA0014458      	4	19980602	G	2562	ELT910	CASE            			BELL  	206   	206L3       	1182108	SW  										ELT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				ELT CASE HAS CORROSION.						1	G	7	1 	3U				H2SW
1998062600553	19980626	00553	EU  	1998	6	26	HEEA0014459      	1	19980602	G	7100	4545005	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE COMPART	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	135AE					S838				DOES NOT CLOSE COMPLETELY WHEN ECU STARTER OFF.						1	G	7	2 	3U				H3EU
1998062600554	19980626	00554	EU  	1998	6	26	HEEA0014460      	1	19980602	G	2820	209072433105	VALVE           			BOLKMS	117   	BK117A4     	5626017	EU  										ENGINE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				LITTLE RISE IN TOT WHEN ECU TURNED ON.						1	G	7	2 	3U				H13EU
1998062600555	19980626	00555		1998	6	26	HEEA0014461      	4	19980602	G	3425	066304607	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				INDICATION ERRATIC.						1	G	7	2 	3U				H3EU
1998062600441	19980626	00441		1998	6	26	HEEA0014462      	4	19980602	G	3444	7001840913	TRANSPONDER     			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				TRANSPONDER INOPERATIVE.						1	G	7	1 	4U				H4SW
1998062600556	19980626	00556	GL  	1998	6	26	HEEA0014463      	2	19980602	G	7320	1564T1005	ACTUATOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR INOPERATIVE.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998062600557	19980626	00557	GL  	1998	6	26	HEEA0014464      	2	19980602	G	7320	1564T1005	SERVO MOTOR     			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50293					S677				SERVO WILL NOT EXTEND OR RETRACT.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998062600558	19980626	00558	GL  	1998	6	26	HEEA0014465      	2	19980602	G	7320	1564T1005	SERVO MOTOR     			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911DD					S830				UNABLE TO ADJUST AND SLIP.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998062600442	19980626	00442		1998	6	26	HEEA0014466      	4	19980602	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2014K					33020				COMPUTER WILL NOT TEST IN YAW POSITION.						1	G	7	2 	4U				H4SW
1998062600388	19980626	00388	CE  	1998	6	26	HEEA0014467      	1	19980602	G	2140	EM6401	BLOWER          			BEECH 	200   	200CBEECH   	1152926	CE  										HEAT SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	500PH					BL29				HEATER BLOWER  INOPERATIVE.						1	L	7	2 	4T				A24CE
1998062600443	19980626	00443	SW  	1998	6	26	HEEA0014468      	1	19980602	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600444	19980626	00444	SW  	1998	6	26	HEEA0014469      	1	19980602	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ACTUATOR HAS NO MOVEMENT.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600445	19980626	00445	SW  	1998	6	26	HEEA0014470      	1	19980602	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					DROOP COMP.	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										END OF OUTPUT SHAFT SPLIT.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600446	19980626	00446	SW  	1998	6	26	HEEA0014471      	1	19980602	G	6240	206076373001	TACH GEN        			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2124Z					45646				M/R LOW RPM LIMIT LIGHT STAYS ON.						1	G	7	1 	3U				H2SW
1998062600447	19980626	00447	SW  	1998	6	26	HEEA0014472      	1	19980602	G	2822	164A1681	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LOW PRESSURE    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				PUMP HAS LOW PRESSURE AND LOUD NOISE.						1	G	7	2 	4U				H4SW
1998062600448	19980626	00448	SW  	1998	6	26	HEEA0014473      	1	19980602	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31821					51076				ACTUATOR INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600449	19980626	00449		1998	6	26	HEEA0014474      	4	19980602	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				AFCS KICKING.						1	G	7	2 	4U				H4SW
1998062600450	19980626	00450	SW  	1998	6	26	HEEA0014475      	1	19980602	G	7714	206076373001	SPLINE          			BELL  	206   	206L1       	1182107	SW  										TACH GENERATOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078D					45397				TACHOMETER/GENERATOR HAS EXCESSIVE SPLINE WEAR.						1	G	7	1 	3U				H2SW
1998062600451	19980626	00451	SW  	1998	6	26	HEEA0014476      	1	19980602	G	7712	407375003107	LENS            			BELL  	407   	407         		SW  										INDICATOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH	83   				53228				TORQUEMETER LENS CRACKED.						1	G	7	1 	3U			O	H2SW
1998062600452	19980626	00452	SW  	1998	6	26	HEEA0014477      	1	19980602	G	7920	70037A090000	HOSE            			BELL  	407   	407         		SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				ENGINE OIL HOSE LEAKING.						1	G	7	1 	3U			O	H2SW
1998062600453	19980626	00453	SW  	1998	6	26	HEEA0014478      	1	19980602	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P	10903				33012				HOLE IN THE OUTBOARD LEADING EDGE STRIP NEAR THE TIP.						1	G	7	2 	4U				H4SW
1998062600454	19980626	00454	SW  	1998	6	26	HEEA0014479      	1	19980602	G	5520	AB205030856121	MOUNTING FLANGE 			BELL  	212   	212         	1181420	SW  										ELVATOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				ELEVATOR MOUNTING FLANGE CRACKED.  REPLACED WITH SERVICEABLE ELEVATOR.						1	G	7	1 	4U				H4SW
1998062600559	19980626	00559	EU  	1998	6	26	HEEA0014480      	1	19980602	G	6310	4638202007	CLUTCH          		4638001001  	BOLKMS	105   	BO105S      	5626006	EU  										TRANSMISSION	SEIZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H	1049 			618	S833				CLUTCH LOCKED UP CAUSING DAMAGE TO INPUT PINION P/N 4638-302-002, S/N 2935, AND FREEWHEEL SHAFT P/N 4638-302-013 , S/N 8	9.  REPLACED DAMAGED PARTS WITH NEW PARTS AND PERFORMED LOAD TEST TO TRANSMISSION AND INSPECTION AFTER LOAD TEST AND RET	URNED TO SERVICE.				1	G	7	2 	3U				H3EU
1998062600455	19980626	00455		1998	6	26	HEEA0014481      	4	19980602	G	3421	5040017901	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2759U					45267				ATTITUDE INDICATOR WILL NOT HOLD LEVEL POSITION.  REPAIRED BROKEN WIRE TO ROTOR.  BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW
1998062600456	19980626	00456		1998	6	26	HEEA0014482      	4	19980602	G	3421	5040017901	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				INCORRECT DEGREE OF TILT FOR 412 INSTRUMENT PANEL, NEEDS BENCH CHECK.  BENCH CHECK GOOD.						1	G	7	2 	4U				H4SW
1998062600457	19980626	00457		1998	6	26	HEEA0014483      	4	19980602	G	3421	5040017901	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				FLAG WILL NOT PULL.  FOUND POSITIVE LEAD OF FLAG MOTOR BROKEN.  RESOLDERED BROKEN WIRE.  RECALIBRATED PITCH AND ROLL TIM	ES.  BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW
1998062600560	19980626	00560	EU  	1998	6	26	HEEA0014484      	1	19980602	G	6240	DL40440	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				NR 1 NEEDLE READS 3 PERCENT HIGHER THAN NR 2 NEEDLE, AND ROTOR NEEDLES.  INDICATOR HAS NOISY OPERATION INTERNALLY.  TIME	 SINCE REPAIR 362:20 HOURS.					1	G	7	2 	3U				H3EU
1998062600561	19980626	00561	EU  	1998	6	26	HEEA0014485      	1	19980602	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				MAST MOMENT INDICATOR HAS ERRATIC OPERATION.						1	G	7	2 	3U				H3EU
1998062600562	19980626	00562	EU  	1998	6	26	HEEA0014486      	1	19980602	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				MAST MOMENT TRANSMITTER, ERRATIC OPERATION.						1	G	7	2 	3U				H3EU
1998062600458	19980626	00458	GL  	1998	6	26	HEEA0014487      	2	19980602	G	7314	3881005	SPLINE          			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					FUEL PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5006F	1480 				45181				PUMP HAS EXCESSIVE DRIVE SHAFT SPLINE WEAR AND GEAR SPLINE WEAR.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600563	19980626	00563	GL  	1998	6	26	HEEA0014488      	2	19980602	G	7322	2537739	METERING VALVE  			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C30P     	03013	GL  					FLOW BODY	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR					S719				ENGINE DECELERATED.  BENCH TESTED UNIT AS RECEIVED.  FOUND FLOWS TO HANG.  INSPECTED UNIT AND FOUND METERING VALVE SLEEV	E, P/N 2537739.  UNIT TESTED.  REPLACED METERING VALVE SLEEVE, P/N 2537739, WITH SERVICEABLE METERING VALVE SLEEVE, P/N 	2537739.  BENCH TEST UNIT.				1	G	7	2 	3U	3	U		H3EU    	E1GL
1998062600389	19980626	00389		1998	6	26	HEEA0014489      	1	19980602	G	6710	41001687	LEVER           																	MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FOUND BUSHINGS ON BOTH LEVERS NOT REAMED PROPERLY TO INSERT BOLTS.  TIME SINCE REPAIR 0:00.
1998062600459	19980626	00459		1998	6	26	HEEA0014490      	4	19980602	G	3457	0845000000	GPS             		SKYNAV5000  	BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				GPS DATA FAILURE.  FOUND UNIT NOT PICKING UP SIGNAL FROM SATELLITES.						1	G	7	1 	4U				H4SW
1998062600564	19980626	00564		1998	6	26	HEEA0014491      	4	19980602	G	3457	0845000000	GPS             		SKYNAV5000  	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	818SH					S753				GPS INTERMITTENT AND SLOW TO SELECT.  FOUND SEVERAL BUTTONS TO BE INOPERATIVE.						1	G	7	2 	3U				H3EU
1998062600565	19980626	00565		1998	6	26	HEEA0014492      	4	19980602	G	2312	4000106000	CONTROL UNIT    		C1000       	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM					S683				LOST PROGRAMMING; WILL NOT RE-PROGRAM. PERFORMED PRELIMINARY INSPECTION.  UNABLE TO LOAD FREQUENCY INTO MEMORY.						1	G	7	2 	3U				H3EU
1998062600460	19980626	00460		1998	6	26	HEEA0014493      	4	19980602	G	2312	6222078001	TRANSCEIVER     		VHF251      	BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	515KA					51048				TRANSCEIVER WILL NOT RECEIVE OR TRANSMIT.  PERFORMED PRELIMINARY INSPECTION.  TROUBLESHOT AND FOUND PROBLEM ON SYNTHESIZ	ER BOARD.					1	G	7	1 	3U				H2SW
1998062600461	19980626	00461	SW  	1998	6	26	HEEA0014494      	1	19980602	G	2140	S50121	B-NUT           			BELL  	206   	206L3       	1182108	SW  										HEATER SYSTEM	CORRODED        	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	8592X					51508				HEATER SYSTEM BLEED AIR (RECEIVED PART WITH CORROSION B-NUT AREA) REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW
1998062600462	19980626	00462	SW  	1998	6	26	HEEA0014495      	1	19980603	G	6320	214040888101P	CASE            			BELL  	214   	214ST       	1182106	SW  										M/R	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		586  								GEARBOX NEEDS TO BE EVALUATED FOR REPAIR OF CORROSION OF AREA P, BOTH FLANGES.						2	G	7	2 	4U				H10SW
1998062600463	19980626	00463	SW  	1998	6	26	HEEA0014496      	1	19980604	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N	1950 				28106				STARTER WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW
1998062600464	19980626	00464		1998	6	26	HEEA0014497      	4	19980604	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				RT FLAG SLOW TO PULL AND RT POINTER STICKS.						1	G	7	2 	4U				H4SW
1998062600465	19980626	00465	SW  	1998	6	26	HEEA0014498      	1	19980604	G	7712	206075739103	TORQUEMETER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	979BH					51403				TORQUE GAUGE FLUCTUATING.						1	G	7	1 	3U				H2SW
1998062600466	19980626	00466		1998	6	26	HEEA0014499      	4	19980604	G	3420	1113025	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT HIS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				POINTER IS OFF BY 13 WHEN DIGITS ARE AT ZERO.						2	G	7	2 	4U				H10SW
1998062600467	19980626	00467	SW  	1998	6	26	HEEA0014500      	1	19980604	G	7712	96774181814	TRANSMITTER     			BELL  	212   	212         	1181420	SW  										ENGINE	READ HIGH       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				TORQUE READS HIGH OUT OF TOLERANCE.						1	G	7	1 	4U				H4SW
1998062600468	19980626	00468		1998	6	26	HEEA0014501      	4	19980604	G	3417	214175421101	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT ADC	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				ADC FAILED, ONLY ZERO DISPLAYED WHEN SETTING ATTEMPTED.						2	G	7	2 	4U				H10SW
1998062600469	19980626	00469	SW  	1998	6	26	HEEA0014502      	1	19980604	G	7712	96774181814	TRANSMITTER     			BELL  	212   	212         	1181420	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				TORQUEMETER READS LOW, OUT OF TOLERANCE.						1	G	7	1 	4U				H4SW
1998062600470	19980626	00470	SW  	1998	6	26	HEEA0014503      	1	19980604	G	6240	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ROTOR NEEDLE INOPERATIVE, NR 1 NEEDLE LAGS NR 2 NEEDLE.						1	G	7	2 	4U				H4SW
1998062600471	19980626	00471	SW  	1998	6	26	HEEA0014504      	1	19980604	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				TORQUE NR 1 NEEDLE STICKS AT 35 PERCENT INDICATION.						1	G	7	2 	4U				H4SW
1998062600566	19980626	00566	EU  	1998	6	26	HEEA0014505      	1	19980604	G	2424	51565000R	AC REGULATOR    			BOLKMS	105   	BO105S      	5626006	EU  										AC VOLTAGE SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				UNABLE TO ADJUST VOLTAGE.  REGULATOR FAILED.						1	G	7	2 	3U				H3EU
1998062600472	19980626	00472	SW  	1998	6	26	HEEA0014506      	1	19980604	G	2621	A352T	EXTINGUISHER    			BELL  	412   	412         	1182202	SW  										ENGINE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				FIRE EXTINGUISHER HAS HEAVY CORROSION.						1	G	7	2 	4U				H4SW
1998062600567	19980626	00567	EU  	1998	6	26	HEEA0014507      	1	19980604	G	7712	DK50440	TORQUEMETER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	724MB					S756				TORQUEMETER NR 2 NEEDLE STICKING IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998062600473	19980626	00473	SW  	1998	6	26	HEEA0014508      	1	19980604	G	3020	206062625003	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										ENGINE DE-ICE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2285B					3642				ENGINE DE-ICE ACTUATOR DOES NOT STEP MOTOR.						1	G	7	1 	3U				H2SW
1998062600474	19980626	00474	SW  	1998	6	26	HEEA0014509      	1	19980604	G	6320	204040760003	FILTER          			BELL  	412   	412         	1182202	SW  										GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				BUTTON WILL NOT STAY RESET.						1	G	7	2 	4U				H4SW
1998062600568	19980626	00568		1998	6	26	HEEA0014510      	4	19980604	G	2350	066105571	AUDIO PANEL     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81832					S828				ICS IS INOPERATIVE.						1	G	7	2 	3U				H3EU
1998062600569	19980626	00569	EU  	1998	6	26	HEEA0014511      	1	19980604	G	2841	1179405403	LIGHT           			BOLKMS	117   	BK117A3     	5626015	EU  										FUEL QTY IND	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911NC					7026				INSTRUMENT LIGHT IS INOPERATIVE.						1	G	7	2 	3U				H13EU
1998062600475	19980626	00475	SW  	1998	6	26	HEEA0014512      	1	19980604	G	2913	214076334101	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYDRAULC SYS	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				HYDRAULIC PUMP MAKING METAL.						2	G	7	2 	4U				H10SW
1998062600476	19980626	00476	SW  	1998	6	26	HEEA0014513      	1	19980604	G	2842	206063656001	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2777D					45299				TRANSMITTER HAS ERRATIC OUTPUT.						1	G	7	1 	3U				H2SW
1998062600570	19980626	00570	EU  	1998	6	26	HEEA0014514      	1	19980604	G	7332	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESSURE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B					S673				FUEL PRESSURE TRANSMITTER INOPERABLE.						1	G	7	2 	3U				H3EU
1998062600390	19980626	00390	NE  	1998	6	26	HEEA0014515      	1	19980604	G	7722	7645001076107	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				ENGINE TOT HAS NO INDICATION.  DRAWS EXCESSIVE CURRENT.						1	G	7	2 	3U				H1NE
1998062600477	19980626	00477	SW  	1998	6	26	HEEA0014516      	1	19980604	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					DROOP COMP	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5737T					45454				DROOP COMP ACTUATOR INTERMITTENTLY ERRATIC.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600571	19980626	00571		1998	6	26	HEEA0014517      	4	19980604	G	2350	066105571	AUDIO PANEL     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H					S833				ICS AND TRANSMITTER ARE INOPERATIVE.						1	G	7	2 	3U				H3EU
1998062600572	19980626	00572		1998	6	26	HEEA0014518      	4	19980604	G	2312	066105571	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										AUDIO PANEL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				VHF IS INOPERATIVE.						1	G	7	2 	3U				H3EU
1998062600478	19980626	00478	SW  	1998	6	26	HEEA0014519      	1	19980604	G	5210	206033601133	SKIN            			BELL  	206   	206L1       	1182107	SW  										PASSENGER DOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2249Z					45753				DOOR INSPECTION FOUND CORROSION BLEEDING OUT FROM INNER AND OUTER SKINS AND CORROSION BLEEDING OUT FROM FIBERGLASS CORNE	R FAIRING.					1	G	7	1 	3U				H2SW
1998062600479	19980626	00479	SW  	1998	6	26	HEEA0014520      	1	19980604	G	7931	206075677103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54641					51184				OIL GAUGE READING HIGH 3-5 PSI.						1	G	7	1 	3U				H2SW
1998062600480	19980626	00480	SW  	1998	6	26	HEEA0014521      	1	19980604	G	7714	214175251103	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										TRIPLE TACH	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				INDICATOR INTERMITTENT.						2	G	7	2 	4U				H10SW
1998062600481	19980626	00481		1998	6	26	HEEA0014522      	4	19980604	G	2212	222305005101	SENSOR          			BELL  	214   	214ST       	1182106	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806					28140				WHEN ATTITUDE HOLD ENGAGED, AIRCRAFT HUNTS 200 FEET TO 300 FEET UP AND DOWN.						2	G	7	2 	4U				H10SW
1998062600482	19980626	00482	SW  	1998	6	26	HEEA0014523      	1	19980604	G	6720	214001540109	BEARINGS        			BELL  	214   	214ST       	1182106	SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806					28140				T/R PITCH WILL NOT STAY ENGAGED.  BAD BEARINGS.						2	G	7	2 	4U				H10SW
1998062600483	19980626	00483	SW  	1998	6	26	HEEA0014524      	1	19980604	G	6340	214074280107	LIMIT DETECTOR  			BELL  	412   	412         	1182202	SW  										RPM LIMIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				RPM LIMIT LIGHT COMES ON TOO EARLY.						1	G	7	2 	4U				H4SW
1998062600484	19980626	00484	SW  	1998	6	26	HEEA0014525      	1	19980604	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				M/R NR 2 HELIPILOT DROPPING OFF LINE.						1	G	7	2 	4U				H4SW
1998062600485	19980626	00485	SW  	1998	6	26	HEEA0014526      	1	19980604	G	2841	206075189001	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										FUEL QUANTITY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				INDICATOR IS NON-LINEAR THROUGH SCALE.  HAS FRICTION.						1	G	7	1 	3U				H2SW
1998062600391	19980626	00391	CE  	1998	6	26	HEEA0014527      	1	19980604	G	7722	9038402611	INDICATOR       			BEECH 	200   	200CBEECH   	1152926	CE  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH					BL3				TOT INDICATOR STICKS AT OR ABOVE 700C ON START.						1	L	7	2 	4T				A24CE
1998062600486	19980626	00486		1998	6	26	HEEA0014528      	4	19980604	G	2212	222305005101	SENSOR          			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X					33113				AUTOPILOT PORPOISES IN PITCH OR ALTIMETER OR VSI MODE.						1	G	7	2 	4U				H4SW
1998062600573	19980626	00573	EU  	1998	6	26	HEEA0014529      	1	19980604	G	2822	2C271	CARTRIDGE       			BOLKMS	105   	BO105S      	5626006	EU  										BOOST PUMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				BOOST PUMP DRAWING EXCESSIVE AMPERAGE.						1	G	7	2 	3U				H3EU
1998062600487	19980626	00487	SW  	1998	6	26	HEEA0014530      	1	19980604	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										BOOST PUMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078C					45392				BOOST PUMP DRAWING EXCESSIVE AMPERAGE.						1	G	7	1 	3U				H2SW
1998062600574	19980626	00574	EU  	1998	6	26	HEEA0014531      	1	19980604	G	2822	2C273	CARTRIDGE       			BOLKMS	105   	BO105S      	5626006	EU  										BOOST PUMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				BOOST PUMP DRAWING EXCESSIVE AMPERAGE.						1	G	7	2 	3U				H3EU
1998062600575	19980626	00575	EU  	1998	6	26	HEEA0014532      	1	19980604	G	2822	2C273	CARTRIDGE       			BOLKMS	105   	BO105S      	5626006	EU  										BOOST PUMP	LOW PRESSURE    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				BOOST PUMP HAS LOW PRESSURE.						1	G	7	2 	3U				H3EU
1998062600392	19980626	00392		1998	6	26	HEEA0014533      	4	19980604	G	2210	7611133	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										ROLL SLICE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				AMPLIFIER DRIVES ACTUATOR HARD OFF.						1	G	7	2 	3U				H1NE
1998062600393	19980626	00393	NE  	1998	6	26	HEEA0014534      	1	19980604	G	6710	7690001880106	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AMPLIFIER INOPERATIVE- WOULD NOT ALLOW ENGINE TO RECOVER.						1	G	7	2 	3U				H1NE
1998062600394	19980626	00394	NE  	1998	6	26	HEEA0014535      	1	19980604	G	7160	7630103902102	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AIR INTAKE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5128					760181				AIR INTAKE ACTUATOR FUNCTIONS INTERMITTENTLY.						1	G	7	2 	3U				H1NE
1998062600488	19980626	00488	SW  	1998	6	26	HEEA0014536      	1	19980604	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				NR 2 NEEDLE DOES NOT INDICATE.						1	G	7	2 	4U				H4SW
1998062600395	19980626	00395	NE  	1998	6	26	HEEA0014537      	1	19980604	G	3150	7655001001103	LIGHT           			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT MC	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	22342					760096				MASTER CAUTION LIGHT INOPERATIVE.						1	G	7	2 	3U				H1NE
1998062600489	19980626	00489		1998	6	26	HEEA0014538      	4	19980604	G	3416	8800	ENCODER ALT     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806					28140				ENCODER LOSES ALTITUDE.						2	G	7	2 	4U				H10SW
1998062600576	19980626	00576	EU  	1998	6	26	HEEA0014539      	1	19980604	G	7931	DK44939	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESSURE SYS	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911EB					S812				OIL PRESSURE NR 2 NEEDLE PEGS OUT WHEN POWER APPLIED.						1	G	7	2 	3U				H3EU
1998062600490	19980626	00490		1998	6	26	HEEA0014540      	4	19980604	G	2220	7000992	ACCELEROMETER   			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				ACCELEROMETER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998062600577	19980626	00577	NE  	1998	6	26	HEEA0014541      	2	19980604	G	7261	1742500	OIL FILTER      			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE OIL	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	136AE					7234				OIL FILTER BUTTONS DO NOT STAY IN.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998062600491	19980626	00491	SW  	1998	6	26	HEEA0014542      	1	19980604	G	2823	233565	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				FUEL SYSTEM VALVE INOPERATIVE.						1	G	7	2 	4U				H4SW
1998062600492	19980626	00492	SW  	1998	6	26	HEEA0014543      	1	19980604	G	2842	206364601101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				TRANSMITTER HAS ERRATIC INDICATION.						1	G	7	1 	3U				H2SW
1998062600493	19980626	00493	SW  	1998	6	26	HEEA0014544      	1	19980604	G	7921	8543909	OIL COOLER      			BELL  	206   	206L3       	1182108	SW  										ENGINE	LEAKS           	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6610C					51425				OIL COOLER LEAKING.						1	G	7	1 	3U				H2SW
1998062600494	19980626	00494	SW  	1998	6	26	HEEA0014545      	1	19980604	G	7921	8543909	OIL COOLER      			BELL  	206   	206L3       	1182108	SW  										ENGINE	LEAKS           	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	92MT					51175				OIL COOLER LEAKING.						1	G	7	1 	3U				H2SW
1998062600495	19980626	00495	SW  	1998	6	26	HEEA0014546      	1	19980604	G	7810	206064300005	EXHAUST         			BELL  	206   	206L1       	1182107	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1077A					45382				CRACK IN REAR OF STACK.						1	G	7	1 	3U				H2SW
1998062600496	19980626	00496	SW  	1998	6	26	HEEA0014547      	1	19980604	G	7810	206064300005	EXHAUST         			BELL  	206   	206L3       	1182108	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA					51542				EXHAUST CRACKED.						1	G	7	1 	3U				H2SW
1998062600497	19980626	00497	SW  	1998	6	26	HEEA0014548      	1	19980604	G	6710	206062721007	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					M/R CONTROL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	92MT					51175				MAIN ROTOR CONTROL ACTUATOR INOPERABLE.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600498	19980626	00498	SW  	1998	6	26	HEEA0014549      	1	19980604	G	6710	206062721103	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					M/R	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3178K					45765				ACTUATOR INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600499	19980626	00499	SW  	1998	6	26	HEEA0014550      	1	19980604	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					DROOP COMP	INOPRATIVE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				ACTUATOR INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998062600396	19980626	00396	NE  	1998	6	26	HEEA0014551      	1	19980604	G	3510	50C002412	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	706AE					760275				LOX INDICATOR VERY ERRATIC.						1	G	7	2 	3U				H1NE
1998062600397	19980626	00397		1998	6	26	HEEA0014552      	4	19980604	G	3452	4018368902	MODE SELECTOR   			BEECH 	200   	200CBEECH   	1152926	CE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	500PH					BL29				ALTITUDE SELECT FUNCTION IS INOPERATIVE.						1	L	7	2 	4T				A24CE
1998062600398	19980626	00398	CE  	1998	6	26	HEEA0014553      	1	19980604	G	7714	503800343	INDICATOR       			BEECH 	200   	200CBEECH   	1152926	CE  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH					BL3				TACHOMETER STICKS AT 10-15 PERCENT ON SHUT DOWN.						1	L	7	2 	4T				A24CE
1998062600399	19980626	00399		1998	6	26	HEEA0014554      	4	19980604	G	2210	7611122	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										PITCH SLICE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				NR 1 PITCH AFCS CHANNEL KICKING IN- FLIGHT.						1	G	7	2 	3U				H1NE
1998062600500	19980626	00500	SW  	1998	6	26	HEEA0014555      	1	19980604	G	7714	206075681101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2249Z					45753				TURBINE NEEDLE WILL NOT COME UP.						1	G	7	1 	3U				H2SW
1998062600501	19980626	00501	SW  	1998	6	26	HEEA0014556      	1	19980604	G	3340	7028521	LIGHT           			BELL  	412   	412         	1182202	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				LIGHT INOPERABLE.						1	G	7	2 	4U				H4SW
1998062600502	19980626	00502	SW  	1998	6	26	HEEA0014557      	1	19980604	G	2841	206063633001	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007N					45184				INDICATOR STICKING, LOW OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW
1998062600503	19980626	00503	SW  	1998	6	26	HEEA0014558      	1	19980604	G	2841	206063633001	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										FUEL QUANTITY	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50034					45169				FUEL QUANTITY INDICATOR READS LOW THROUGHOUT SCALE.						1	G	7	1 	3U				H2SW
1998062600504	19980626	00504	SW  	1998	6	26	HEEA0014559      	1	19980604	G	2931	124043	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	UNSERVICABLE    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				HYDRAULIC PRESSURE SIDE MARKINGS FADED.						1	G	7	2 	4U				H4SW
1998062600505	19980626	00505	SW  	1998	6	26	HEEA0014560      	1	19980604	G	2822	206063610003	BOOST PUMP      			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5017G					45228				LEFT BOOST PUMP INOPERATIVE.						1	G	7	1 	3U				H2SW
1998062600578	19980626	00578	EU  	1998	6	26	HEEA0014561      	1	19980604	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				MAST MOMENT UNIT FAILED SELF-TEST.						1	G	7	2 	3U				H3EU
1998062600579	19980626	00579	EU  	1998	6	26	HEEA0014562      	1	19980604	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				MAST MOMENT UNIT FAILED SELF-TEST.						1	G	7	2 	3U				H3EU
1998062600580	19980626	00580	EU  	1998	6	26	HEEA0014563      	1	19980604	G	2424	51565000R	REGULATOR       			BOLKMS	105   	BO105S      	5626006	EU  										AC REGULATOR	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				REGULATOR WILL NOT ADJUST.						1	G	7	2 	3U				H3EU
1998062600506	19980626	00506		1998	6	26	HEEA0014564      	4	19980604	G	3424	214075244001	GYROSCOPE       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RATE OF TURN NEEDLES TO THE RIGHT.						1	G	7	2 	4U				H4SW
1998062600507	19980626	00507	SW  	1998	6	26	HEEA0014565      	1	19980604	G	6240	206075681003	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078G					45398				ROTOR NEEDLE READS HIGH OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW
1998062600508	19980626	00508		1998	6	26	HEEA0014566      	4	19980604	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				RT FLAG WILL NOT PULL.						1	G	7	2 	4U				H4SW
1998062600509	19980626	00509		1998	6	26	HEEA0014567      	4	19980604	G	3422	103002201	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				GYRO ROTOR WILL NOT SPIN.						1	G	7	1 	3U				H2SW
1998062600510	19980626	00510		1998	6	26	HEEA0014568      	4	19980604	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RATE OF TURN NEEDLES TO THE RIGHT.  (REMOVED FROM A/C YV0CVG12).						1	G	7	2 	4U				H4SW
1998062600511	19980626	00511	SW  	1998	6	26	HEEA0014569      	1	19980604	G	2424	214175153105	REGULATOR       			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				CANNOT ADJUST AC REGULATOR.						2	G	7	2 	4U				H10SW
1998062600400	19980626	00400	EA  	1998	6	26	HEEA0014570      	2	19980604	G	7532	310092205	BLEED VALVE     			BEECH 	200   	200BEECH    	1152920	CE  	PWA   	PT6   	PT6A41      	52043	EA  					ENGINE COMP	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	789DS					BB478				BLEED VALVE POPPING AT HIGH TORQUE.						1	L	7	2 	4T	4	T		A24CE   	E4EA
1998062600581	19980626	00581	EU  	1998	6	26	HEEA0014571      	1	19980604	G	3310	SPL2501024	POWER SUPPLY    			BOLKMS	117   	BK117B1     	5626012	EU  										LIGHTING SYSTEM	BURNED OUT      	E			HEEA	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	911TL					7198				LIGHT SYSTEM POWER SUPPLY UNIT SMOKED.						1	G	7	2 	3U				H13EU
1998062600582	19980626	00582	EU  	1998	6	26	HEEA0014572      	1	19980604	G	7933	646600251	TEMP PROBE      			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE OIL SYS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				OIL TEMPERATURE PROBE INOPERATIVE.						1	G	7	1 	3U				H9EU
1998062600512	19980626	00512	SW  	1998	6	26	HEEA0014573      	1	19980604	G	6330	206033503001	LINK ASSEMBLY   			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2249Z					45753				M/R GEARBOX ELASTOMERIC IS WORN.						1	G	7	1 	3U				H2SW
1998062600513	19980626	00513	SW  	1998	6	26	HEEA0014574      	1	19980604	G	2842	BSE20630G	TRANSDUCER      			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y					45192				FUEL SYSTEM TRANSDUCER GIVES INTERMITTENT READINGS.						1	G	7	1 	3U				H2SW
1998062600583	19980626	00583	EU  	1998	6	26	HEEA0014575      	1	19980604	G	7712	G555674	TRANSDUCER      			BOLKMS	117   	BK117B2     	5626013	EU  										ENGINE TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	136AE					7234				TORQUE DROPPED OFF 20 PERCENT, THEN WENT HIGH BY 20 PERCENT.  UNIT WOULD NOT REMAIN CALIBRATED.						1	G	7	2 	3U			NC	H13EU
1998062600401	19980626	00401	NE  	1998	6	26	HEEA0014576      	1	19980604	G	2435	7655009006105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				GENERATOR WILL NOT COME ON LINE.						1	G	7	2 	3U				H1NE
1998062600402	19980626	00402	NE  	1998	6	26	HEEA0014577      	1	19980604	G	2435	51530006A	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				GENERATOR WILL NOT COME ON LINE.						1	G	7	2 	3U				H1NE
1998062600514	19980626	00514	SW  	1998	6	26	HEEA0014578      	1	19980604	G	2437	209070264003	DUAL AMMETER    			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				DUAL AMMETER NR 2 NEEDLE IS STICKING.						1	G	7	1 	4U				H4SW
1998062600515	19980626	00515	SW  	1998	6	26	HEEA0014579      	1	19980604	G	2436	51539002N	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										GENERATOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				GENERATOR CONTROL UNIT INOPERATIVE.						1	G	7	2 	4U				H4SW
1998062600516	19980626	00516	SW  	1998	6	26	HEEA0014580      	1	19980604	G	7714	65013008	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										GAS PRODUCER	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5006F					45181				GP TACH NEEDLE STICKING BETWEEN 5-12 PERCENT.						1	G	7	1 	3U				H2SW
1998062600403	19980626	00403		1998	6	26	HEEA0014581      	4	19980604	G	2210	7611113	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										YAW SLICE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				YAW CHANNEL KICKING.						1	G	7	2 	3U				H1NE
1998062600404	19980626	00404	NE  	1998	6	26	HEEA0014582      	1	19980604	G	6240	7690001881103	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										VIB ABSORBER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				VTA INOPERATIVE.						1	G	7	2 	3U				H1NE
1998062600517	19980626	00517	SW  	1998	6	26	HEEA0014583      	1	19980604	G	6220	206011154107	STRAP           			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WIRE STICKING OUT OF M/R PROTECTIVE COATING.						1	G	7	1 	3U				H2SW
1998062600519	19980626	00519		1998	6	26	HEEA0014585      	4	19980604	G	2210	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				PITCH CHANNEL WILL NOT ENGAGE.  AARS WILL NOT COMPLETE TEST.						2	G	7	2 	4U				H10SW
1998062600521	19980626	00521	SW  	1998	6	26	HEEA0014587      	1	19980604	G	6320	206040531105	CASE            		206040004107	BELL  	206   	206L3       	1182108	SW  										M/ROTOR GEARBOX	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5842	4499 			B51733	51466				M/R CASE IS CRACKED AT SEVERAL PLACES AROUND THE CASE WEBBING.						1	G	7	1 	3U				H2SW
1998062600522	19980626	00522		1998	6	26	HEEA0014588      	1	19980604	G	5530	206020113223A	VERTICAL FIN    																	FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										VERTICAL FIN UNIT RECEIVED IN UNSERVICEABLE CONDITION.
1998062600523	19980626	00523		1998	6	26	HEEA0014589      	4	19980604	G	3416	212070238007	ALTIMETER       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				ALTIMETER FAILED FRICTION ERROR TEST.						1	G	7	1 	4U				H4SW
1998062600524	19980626	00524	SW  	1998	6	26	HEEA0014590      	1	19980604	G	6730	7001482	ACTUATOR        			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				T/R CONTROL NR 2 SIDE IS STUCK.						1	G	7	2 	4U				H4SW
1998062600405	19980626	00405	NE  	1998	6	26	HEEA0014591      	1	19980604	G	2841	7645001078103	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										FUEL QUANTITY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X					760050				NR 2 FLUCTUATES AND WILL NOT CALIBRATE.						1	G	7	2 	3U				H1NE
1998062600525	19980626	00525	SW  	1998	6	26	HEEA0014592      	1	19980604	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20J     	03013	GL  					DROOP COMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2275Y					3626				ACTUATOR STICKS ON HIGH SIDE.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998062600526	19980626	00526	SW  	1998	6	26	HEEA0014593      	1	19980604	G	2436	51509002R	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				STARTER GENERATOR WILL NOT COME ON LINE.						1	G	7	1 	4U				H4SW
1998062600527	19980626	00527		1998	6	26	HEEA0014594      	4	19980604	G	3457	1624820	ANTENNA         			BELL  	206   	206B3       	1181506	SW  										GPS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G					3610				GPS ANTENNA IS INOPERATIVE.  FOUND ANTENNA TO CAUSE ANTENNA FAULT MESSAGE ON GPS UNIT.						1	G	7	1 	3U				H2SW
1998062600528	19980626	00528	SW  	1998	6	26	HEEA0014595      	1	19980604	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P	9848 				33012				FRETTING AND PAD UNBONDED ON UPPER SURFACE.  THE TIP OF THE BLADE IS HEAVY.						1	G	7	2 	4U				H4SW
1998062600584	19980626	00584	EU  	1998	6	26	HEEA0014596      	1	19980604	G	7714	DL40438	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070					S145				NR 1 NEEDLE STICKS AND STAYS 2 PERCENT HIGHER THAN OTHER NEEDLES.						1	G	7	2 	3U				H3EU
1998062600529	19980626	00529		1998	6	26	HEEA0014597      	4	19980604	G	3457	81439000232	RECEIVER        			BELL  	412   	412         	1182202	SW  										GPS SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				GPS FLAG SHOWS  AT ALL TIMES.   PERFORMED PRELIMINARY INSPECTION AND FOUND NEEDLE DEFLECTION INCORRECT.						1	G	7	2 	4U				H4SW
1998062600585	19980626	00585		1998	6	26	HEEA0014598      	4	19980604	G	3457	0845000000	GPS             		SKYNAV5000  	BOLKMS	117   	BK117B1     	5626012	EU  										COCIPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL					7198				GPS LOSES FIX, CASE LOOSE, BONDING TAB BROKEN.						1	G	7	2 	3U				H13EU
1998062600530	19980626	00530		1998	6	26	HEEA0014599      	4	19980604	G	3444	066305401	INDICATOR       			BELL  	407   	407         		SW  										RADIO ALTIMETER	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	405PH					53207				RADIO ALTIMETER TEST FUNCTION INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998062600531	19980626	00531		1998	6	26	HEEA0014600      	4	19980604	G	3422	2891ESR	GYROSCOPE       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50182					45242				DIRECTIONAL GYRO SLAVES BACKWARDS.						1	G	7	1 	3U				H2SW
1998062600532	19980626	00532	SW  	1998	6	26	HEEA0014601      	1	19980605	G	5320	206023119109S	SUPPORT         			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SUPPORT MARKED -109; BUT ARE -110S.  MISIDENTIFIED PARTS.						1	G	7	1 	3U			 	H2SW
1998062600533	19980626	00533	SW  	1998	6	26	HEEA0014602      	1	19980605	G	5260	212075418105	ACTUATOR STEP   			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				STEP ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998062600534	19980626	00534		1998	6	26	HEEA0014603      	4	19980605	G	2220	214074104101	SENSOR DUALRATE 			BELL  	214   	214ST       	1182106	SW  										SCAS SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				SCAS SENSOR ROLL WILL NOT STAY ON LINE.						2	G	7	2 	4U				H10SW
1998062600535	19980626	00535		1998	6	26	HEEA0014604      	4	19980605	G	3400	222375019107	CONNECTOR       			BELL  	214   	214ST       	1182106	SW  										TRANSMITTER	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				CONNECTOR BROKEN.						2	G	7	2 	4U				H10SW
1998062600536	19980626	00536	SW  	1998	6	26	HEEA0014605      	1	19980605	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				M/R ACTUATOR ONLY MOVED AFT.						1	G	7	2 	4U				H4SW
1998062600586	19980626	00586	EU  	1998	6	26	HEEA0014606      	1	19980605	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										EXHAUST TEMP	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	9190Y					S669				TOT INDICATOR HAS EXCESSIVE FRICTION ERROR.  TIME SINCE REPAIR 24:00 HOURS.						1	G	7	2 	3U				H3EU
1998062600537	19980626	00537	SW  	1998	6	26	HEEA0014607      	1	19980605	G	7810	206064300005	BASE            			BELL  	206   	206L1       	1182107	SW  										ENGINE EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	83MT					45492				EXHAUST CRACKED AROUND BASE.						1	G	7	1 	3U				H2SW
1998062600538	19980626	00538	SW  	1998	6	26	HEEA0014608      	1	19980605	G	2810	205061632002	BAFFLE          			BELL  	212   	212         	1181420	SW  										FUEL CELL	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				FUEL CELL UNBONDED IN BAFFLE.						1	G	7	1 	4U				H4SW
1998062600539	19980626	00539	SW  	1998	6	26	HEEA0014609      	1	19980605	G	6330	206033506101	BEARING         			BELL  	206   	206L1       	1182107	SW  										TRANS RESTRAINT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2249Z					45753				TRANSMISSION RESTRA9INT BEARI8NG WORN.						1	G	7	1 	3U				H2SW
1998062600540	19980626	00540	SW  	1998	6	26	HEEA0014610      	1	19980605	G	2810	206031100703	PANEL           			BELL  	206   	206B3       	1181506	SW  										FUEL CELL TUB	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22751					3627				FUEL CELL CORRODED BEYOND REPAIR.						1	G	7	1 	3U				H2SW
1998062600541	19980626	00541	SW  	1998	6	26	HEEA0014611      	1	19980605	G	5330	206031201287	SHELL ASSEMBLY  			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22751					3627				FUSELAGE SHELL CORRODED BEYOND REPAIR.						1	G	7	1 	3U				H2SW
1998062600587	19980626	00587	EU  	1998	6	26	HEEA0014612      	1	19980605	G	5321	10522341	FLOOR PANEL     			BOLKMS	105   	BO105S      	5626006	EU  										CABIN FLOOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070					S145				FLOOR PANEL CORRODED AND SEPARATED.						1	G	7	2 	3U				H3EU
1998062600542	19980626	00542	SW  	1998	6	26	HEEA0014613      	1	19980605	G	2822	9A1746	CARTRIDGE       			BELL  	214   	214ST       	1182106	SW  										FUEL PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				CARTRIDGE INOPERATIVE.						2	G	7	2 	4U				H10SW
1998062600588	19980626	00588	EU  	1998	6	26	HEEA0014614      	1	19980605	G	3340	A413AHDACF1428	POWER SUPPLY    			BOLKMS	105   	BO105S      	5626006	EU  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3071K					S859				STROBE POWER SUPPLY INOPERATIVE.						1	G	7	2 	3U				H3EU
1998062600543	19980626	00543	SW  	1998	6	26	HEEA0014615      	1	19980605	G	3213	412030437103	CAP             			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				RUBBER WORN ON CAP.						1	G	7	2 	4U				H4SW
1998062600544	19980626	00544		1998	6	26	HEEA0014616      	4	19980605	G	3423	CB2100T6D	COMPASS         			BELL  	412   	412         	1182202	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				READINGS ARE OFF 20 DEGREES OFF.   ADJUSTMENTS DO NOT HELP.						1	G	7	2 	4U				H4SW
1998062600545	19980626	00545	SW  	1998	6	26	HEEA0014617      	1	19980605	G	6330	206030539003	MOUNT           			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	103PH					3000				M/R TRANSMISSION RUBBER SEPARATION AT MOUNT.						1	G	7	1 	3U				H2SW
1998062600546	19980626	00546	SW  	1998	6	26	HEEA0014618      	1	19980605	G	3340	A490ATSDF	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6161A					51611				STROBE POWER SUPPLY HAS NO OUTPUT.						1	G	7	1 	3U				H2SW
1998070300190	19980703	00190	SW  	1998	7	3	HEEA0014619      	1	19980608	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y					45192				AIRSPEED NEEDLE RISES 45-50 DEGREES WHEN VHF IS KEYED.						1	G	7	1 	3U				H2SW
1998070300162	19980703	00162		1998	7	3	HEEA0014620      	4	19980608	G	3414	7645000801101	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AIRSPEED COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				ALTIMETER NEEDLE STICKS BETWEEN ZERO AND 20 KNOTS.						1	G	7	2 	3U				H1NE
1998070300191	19980703	00191		1998	7	3	HEEA0014621      	4	19980608	G	3416	10220011850	ALTIMETER       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				TOT INDICATOR NEEDLE STICKS.  ENCODER OUT OF TOLERANCE.						2	G	7	2 	4U				H10SW
1998070300192	19980703	00192	SW  	1998	7	3	HEEA0014622      	1	19980608	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				INDICATOR INTERMITTENTLY STICKS AT ZERO.						1	G	7	1 	3U				H2SW
1998070300193	19980703	00193	SW  	1998	7	3	HEEA0014623      	1	19980608	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5017G					45228				NEEDLE STICKS AT ZERO.						1	G	7	1 	3U				H2SW
1998070300194	19980703	00194	SW  	1998	7	3	HEEA0014624      	1	19980608	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y					45192				INDICATOR INTERMITTENTLY STICKS AT 200 DEGREES.						1	G	7	1 	3U				H2SW
1998070300195	19980703	00195	SW  	1998	7	3	HEEA0014625      	1	19980608	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10761					45381				INDICATOR STICKS AT 200 DEGREES INTERMITTENTLY AND NO OVERTEMP LIGHT.						1	G	7	1 	3U				H2SW
1998070300196	19980703	00196	SW  	1998	7	3	HEEA0014626      	1	19980608	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT TORQUE	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				TORQUE INDICATOR'S NR 1 NEEDLE STICKS AT ZERO.						1	G	7	2 	4U				H4SW
1998070300197	19980703	00197	SW  	1998	7	3	HEEA0014627      	1	19980608	G	2430	206075447007	REGULATOR       			BELL  	206   	206L3       	1182108	SW  										DC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	129MR					51129				GENERATOR WILL NOT COME ON LINE.						1	G	7	1 	3U				H2SW
1998070300198	19980703	00198		1998	7	3	HEEA0014628      	4	19980608	G	3422	5050017904	GYRO            			BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3181Y					3772				DIRECTIONAL GYROSCOPE PRECESSES.						1	G	7	1 	3U				H2SW
1998070300163	19980703	00163		1998	7	3	HEEA0014629      	4	19980608	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT VG	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3122G					760232				ATTITUDE FLAG WILL NOT STAY AFTER 10 MINUTES.  (CAT EYE ERRATIC).						1	G	7	2 	3U				H1NE
1998070300199	19980703	00199		1998	7	3	HEEA0014630      	4	19980608	G	3424	214075244001	RATE GYRO       			BELL  	412   	412         	1182202	SW  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				RATE GYRO TURN NEEDLE OSCILLATES.						1	G	7	2 	4U				H4SW
1998070300164	19980703	00164		1998	7	3	HEEA0014631      	4	19980608	G	3416	5035P2P42	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31217					760229				ALTIMETER GIVES INVALID READOUT AT 5500 FEET.						1	G	7	2 	3U				H1NE
1998070300200	19980703	00200	SW  	1998	7	3	HEEA0014632      	1	19980608	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	206   	206B3       	1181506	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181J					3771				STROBE HAS NO OUTPUT.						1	G	7	1 	3U				H2SW
1998070300201	19980703	00201	SW  	1998	7	3	HEEA0014633      	1	19980608	G	2820	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q					45187				FUEL SYSTEM HAS LOW PRESSURE OUTPUT.						1	G	7	1 	3U				H2SW
1998070300297	19980703	00297	EU  	1998	7	3	HEEA0014634      	1	19980608	G	7712	G555672	TRANSDUCER      			BOLKMS	117   	BK117A4     	5626017	EU  										TORQUE	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				TORQUE TRANSDUCER FLUCTUATES.						1	G	7	2 	3U				H13EU
1998070300202	19980703	00202	SW  	1998	7	3	HEEA0014635      	1	19980608	G	3340	A413A	POWER SUPPLY    			BELL  	206   	206B3       	1181506	SW  										STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2275Y					3626				STROBE LIGHT IS OUT.						1	G	7	1 	3U				H2SW
1998070300165	19980703	00165	NE  	1998	7	3	HEEA0014636      	1	19980608	G	2822	399A106	MOTOR           			SKRSKY	S76   	S76A        	8143006	NE  										BOOST PUMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				BOOST PUMP MOTOR HAS INTERMITTENT OPERATION.						1	G	7	2 	3U				H1NE
1998070300298	19980703	00298		1998	7	3	HEEA0014637      	4	19980608	G	3423	KCA0105W	COMPASS         			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	131AE					S787				MAG COMPASS UNIT LEAKS AND BULB COVER IS MISSING.						1	G	7	2 	3U				H3EU
1998070300203	19980703	00203		1998	7	3	HEEA0014638      	4	19980608	G	3414	412075009105	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3893N					33010				AIRSPEED INDICATOR HAS EXCESSIVE CASE LEAKAGE INDICATES OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998070300204	19980703	00204	SW  	1998	7	3	HEEA0014639      	1	19980608	G	2430	51539002N	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				DC CONTROL UNIT WILL NOT COME ON LINE.						1	G	7	2 	4U				H4SW
1998070300299	19980703	00299	NE  	1998	7	3	HEEA0014640      	2	19980608	G	7261	1742500	FILTER          			BOLKMS	117   	BK117A3     	5626015	EU  	LYC   	LTS101	LTS101650B1 	41560	NE  					ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				ENGINE OIL FILTER'S BYPASS BUTTON POPS AFTER ENGINE OPERATION.						1	G	7	2 	3U	3	U		H13EU   	E5NE
1998070300205	19980703	00205	SW  	1998	7	3	HEEA0014641      	1	19980608	G	7933	206075187003	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE OIL TEMP	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				OIL TEMPERATURE INDICATOR READS HIGH FIRST FEW MINUTES AFTER START-UP.						1	G	7	1 	3U				H2SW
1998070300206	19980703	00206	SW  	1998	7	3	HEEA0014642      	1	19980608	G	3340	7028521	LIGHT           			BELL  	412   	412         	1182202	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				STROBE LIGHT IS INOPERATIVE.						1	G	7	2 	4U				H4SW
1998070300207	19980703	00207		1998	7	3	HEEA0014643      	4	19980608	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										HSI	FLAG STICKING   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				NAVIGATION FLAG STICKS.						1	G	7	2 	4U				H4SW
1998070300208	19980703	00208		1998	7	3	HEEA0014644      	4	19980608	G	2330	066105552	AUDIO PANEL     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206LS					51070				PA DOES NOT TRANSMIT.						1	G	7	1 	3U				H2SW
1998070300300	19980703	00300	EU  	1998	7	3	HEEA0014645      	1	19980608	G	7712	DK50440	TORQUEMETER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				TORQUEMETER NR 2 NEEDLE STAYS AT ZERO WHILE RUNNING.						1	G	7	2 	3U				H3EU
1998070300209	19980703	00209	SW  	1998	7	3	HEEA0014646      	1	19980608	G	7330	206075676117	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	11027					45411				FUEL INDICATOR NEEDLE DROPS TO ZERO THEN GOES BACK UP.						1	G	7	1 	3U				H2SW
1998070300210	19980703	00210	SW  	1998	7	3	HEEA0014647      	1	19980608	G	7714	214175251107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				TRIPLE TACHOMETER'S NR 1 NEEDLE IS INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300211	19980703	00211	SW  	1998	7	3	HEEA0014648      	1	19980608	G	3340	01077028521	LIGHT           			BELL  	412   	412         	1182202	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				STROBE LIGHT UNIT IS INOPERATIVE.						1	G	7	2 	4U				H4SW
1998070300212	19980703	00212	SW  	1998	7	3	HEEA0014649      	1	19980608	G	2820	214066226103	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				NO LIGHT INDICATION ON CAUTION PANEL.  VALVE FAULTY.						1	G	7	2 	4U				H4SW
1998070300213	19980703	00213	SW  	1998	7	3	HEEA0014650      	1	19980608	G	2822	2C273	CARTRIDGE       			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				PUMP WILL NOT COME ON WHEN POWER IS APPLIED.						1	G	7	2 	4U				H4SW
1998070300214	19980703	00214		1998	7	3	HEEA0014651      	4	19980608	G	3416	D120P2T	ENCODER         			BELL  	407   	407         		SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				ENCODER NOT REPORTING PROPERLY.						1	G	7	1 	3U			O	H2SW
1998070300215	19980703	00215	SW  	1998	7	3	HEEA0014652      	1	19980608	G	3340	7028501	LIGHT           			BELL  	214   	214ST       	1182106	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				STROBE LIGHT IS INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300166	19980703	00166	GL  	1998	7	3	HEEA0014653      	2	19980608	G	7412	9580113800	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				IGNITION GENERATOR INTERMITTENT.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998070300216	19980703	00216	SW  	1998	7	3	HEEA0014654      	1	19980608	G	6320	204040386001	CASE            			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				MAIN ROTOR GEARBOX HAS CORROSION ON FLANGE AREA.						1	G	7	2 	4U				H4SW
1998070300217	19980703	00217	SW  	1998	7	3	HEEA0014655      	1	19980608	G	6320	205040231009	GEAR            			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				MAIN ROTOR GEARBOX HAS CORROSION ON FLANGE AREA.						1	G	7	2 	4U				H4SW
1998070300167	19980703	00167	NE  	1998	7	3	HEEA0014656      	1	19980608	G	6220	RMLH2577054	BARREL NUT      			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NO THREADS ON MAIN ROTOR BARREL NUT.						1	G	7	2 	3U				H1NE
1998070300301	19980703	00301	EU  	1998	7	3	HEEA0014657      	1	19980608	G	6420	10531738101	INNER SLEEVE    			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	217UC	1809 				7152				TAIL ROTOR BEARING JOURNAL IS CORRODED AND COATING ID FLAKING OFF.						1	G	7	2 	3U				H13EU
1998070300218	19980703	00218	SW  	1998	7	3	HEEA0014658      	1	19980608	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										CYCLIC	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	7128R					36007				CYCLIC ACTUATOR DRAGS OR STICKS INTERMITTENTLY.						1	G	7	2 	4U				H4SW
1998070300219	19980703	00219		1998	7	3	HEEA0014659      	4	19980608	G	3416	5035P2P44	ENCODER         			BELL  	212   	212         	1181420	SW  										ALTIMETER	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				ENCODER NEEDLE STICKS AND ENCODER READS OUT OF TOLERANCE.						1	G	7	1 	4U				H4SW
1998070300220	19980703	00220		1998	7	3	HEEA0014660      	4	19980608	G	3416	5035P2P44	ENCODER         			BELL  	412   	412         	1182202	SW  										ALTIMETER	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				ENCODER NEEDLE STICKS AND ENCODER INDICATES OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998070300302	19980703	00302	EU  	1998	7	3	HEEA0014661      	1	19980608	G	7931	6607190	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESSURE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070					S145				OIL PRESSURE SWITCH UNIT WOULD NOT COME ON WITH BATTERY SWITCH.						1	G	7	2 	3U				H3EU
1998070300221	19980703	00221	SW  	1998	7	3	HEEA0014662      	1	19980608	G	3340	A413A	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	515KA					51048				STROBE LIGHT WILL NOT FLASH.						1	G	7	1 	3U				H2SW
1998070300303	19980703	00303		1998	7	3	HEEA0014663      	4	19980608	G	2312	40001452502	TRANSCEIVER     			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	134AE					7237				POWER OUT, HESITATING AND UNIT WOULD NOT RECEIVE 138-139 MHZ RANGE.						1	G	7	2 	3U			NC	H13EU
1998070300304	19980703	00304	EU  	1998	7	3	HEEA0014664      	1	19980608	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466	1550 				3004				UNABLE TO BE BALANCE TAIL ROTOR BLADE BELOW .4 IPS.						1	G	7	1 	3U				H9EU
1998070300305	19980703	00305	EU  	1998	7	3	HEEA0014665      	1	19980608	G	2435	150SG122Q	GENERATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	1234 				2771				STARTER GENERATOR INOPERATIVE - WILL NOT START ENGINE.						1	G	7	1 	3U				H9EU
1998070300306	19980703	00306	EU  	1998	7	3	HEEA0014666      	1	19980608	G	7931	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE OIL	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				ENGINE OIL INDICATOR INTERMITTENTLY GOES TO ZERO.						1	G	7	1 	3U				H9EU
1998070300307	19980703	00307	EU  	1998	7	3	HEEA0014667      	1	19980609	G	5330	355A1305200302	SKIN            			SNIAS 	350   	AS350B2     	8680813	EU  										STABILIZER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				STABILIZER CENTER SKIN CRACKED ON TRAILING EDGE BOTTOM LT HAND AT LAST RIVET IN CENTER ROW.						1	G	7	1 	3U				H9EU
1998070300168	19980703	00168	NE  	1998	7	3	HEEA0014668      	1	19980609	G	6210	7615009043050	TIP CAP         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E					760155				MAIN ROTOR TIP CAP OUTER DOUBLER SEPARATED WITH FIBERGLASS BROKEN BETWEEN THE DOUBLER.						1	G	7	2 	3U				H1NE
1998070300222	19980703	00222	SW  	1998	7	3	HEEA0014669      	1	19980609	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608	10502				33075				MAIN ROTOR BLADE WILL NOT TRACK.						1	G	7	2 	4U				H4SW
1998070300223	19980703	00223	SW  	1998	7	3	HEEA0014670      	1	19980609	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608	11014				33075				MAIN ROTOR BLADE WILL NOT TRACK.						1	G	7	2 	4U				H4SW
1998070300224	19980703	00224	SW  	1998	7	3	HEEA0014671      	1	19980609	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P	7617 				33012				COULD NOT BALANCE MAIN ROTOR BLADE.  TIP HEAVY.  (SUSPECT WATER IN THE CORE).						1	G	7	2 	4U				H4SW
1998070300225	19980703	00225		1998	7	3	HEEA0014672      	4	19980609	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT VHF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				TRANSCEIVER TRANSMITS CONSTANTLY.						1	G	7	2 	4U				H4SW
1998070300226	19980703	00226		1998	7	3	HEEA0014673      	4	19980609	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT VHF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				TRANSMISSIONS WEAK.  PERFORMED PRELIMINARY INSPECTION AND TESTED UNIT.  ADJUSTED C/N SQUELCH.  FOUND TRANSMIT POWER OUT 	TOO HIGH.  ALIGNED TRANSMITTER.  NO HELP.					1	G	7	2 	4U				H4SW
1998070300308	19980703	00308	EU  	1998	7	3	HEEA0014674      	1	19980609	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										BOOST PUMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				BOOST PUMP INOPERATIVE.						1	G	7	1 	3U				H9EU
1998070300227	19980703	00227	SW  	1998	7	3	HEEA0014675      	1	19980610	G	3213	206324003	SKID TUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2245Y					45751				SKID TUBE ASSY HAS CRACKS AT SEVERAL INSERTS AS MARKED.						1	G	7	1 	3U				H2SW
1998070300228	19980703	00228	SW  	1998	7	3	HEEA0014676      	1	19980610	G	2435	200SGL132Q	GENERATOR       			BELL  	206   	206L1       	1182107	SW  										STARTER/GEN	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10814	462  				45415				GENERATOR HAS INTERMITTENT OPERATION.						1	G	7	1 	3U				H2SW
1998070300229	19980703	00229	SW  	1998	7	3	HEEA0014677      	1	19980610	G	2912	2111328	FILTER          			BELL  	206   	206L1       	1182107	SW  										HYD SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2759U					45272				INSTALLED TSI 0:00 FILTER IN HYDRAULIC FILTER HOUSING, PRESSURED SYSTEM WITH HYDRAULIC MULE, MOVED CONTROLS AND FILTER B	YPASS BUTTON POPPED UP.  RESET SEVERAL TIMES AND BYPASS KEPT POPPING. REPLACED HYDRAULIC FILTER AND RECHECKED FOR BYPASS	 AND NO BYPASS HAS OCCURRED.				1	G	7	1 	3U				H2SW
1998070300309	19980703	00309	EU  	1998	7	3	HEEA0014678      	1	19980610	G	7722	50061051	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE TOT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B					S673				FOUND ENGINE TOT UNIT TO READ OUT OF TOLERANCE THROUGHOUT SCALE.						1	G	7	2 	3U				H3EU
1998070300230	19980703	00230	SW  	1998	7	3	HEEA0014679      	1	19980610	G	3150	214175122105	CAUTION PANEL   			BELL  	214   	214ST       	1182106	SW  										COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59805					28141				ANTI-ICE LIGHT WILL NOT COME ON FOR NR 1 ENGINE.						2	G	7	2 	4U				H10SW
1998070300231	19980703	00231	SW  	1998	7	3	HEEA0014680      	1	19980610	G	6710	206001062003	WASHER          			BELL  	206   	206L3       	1182108	SW  										M/R CONTROL	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				MAIN ROTOR CONTROL WASHER'S TEFLON COATING IS BAD.  REPLACED WITH SERVICEABLE WASHER.						1	G	7	1 	3U				H2SW
1998070300169	19980703	00169		1998	7	3	HEEA0014681      	4	19980610	G	2312	064101902	LOCKING MECH    			BELL  	206   	206L3       	1182108	SW  										VHF TRANSCEIVER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										LOCKING MECHANISM WORK-BENT.  THIS CAUSED UNIT NOT TO PROPERLY LOCK IN RACK.  RADIO CAN MOVE SIDE TO SIDE, CAUSES INTERM	ITTENT PROBLEMS.  REPLACED TOP COVER, REPAIRED PROBLEM.  BENCH  CHECK GOOD.					1	G	7	1 	3U				H2SW
1998070300232	19980703	00232	SW  	1998	7	3	HEEA0014682      	1	19980610	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				WATER IN FLOAT BOTTLE PRESSURE GAUGE.  REPLACED WITH SERVICEABLE GAUGE.						1	G	7	1 	3U			O	H2SW
1998070300233	19980703	00233	SW  	1998	7	3	HEEA0014683      	1	19980610	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA	1530 				53016				GAUGE ON RIGHT FLOAT BOTTLE READS INACCURATE.  REPLACED WITH SERVICEABLE GAUGE.						1	G	7	1 	3U			O	H2SW
1998070300170	19980703	00170		1998	7	3	HEEA0014684      	4	19980610	G	3442	MI5851345	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										RADAR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217					760229				RADAR COMES ON MOMENTARILY, THEN SHUTS DOWN.  PERFORMED PRELIMINARY INSPECTION AND VERIFIED CAUSES ANTENNA NOT TO SCAN. 	 TROUBLESHOT AND REPLACED U66, P/N 3718361-604 (INTEGRATED CIRCUIT), REPAIRED.  BENCH CHECK GOOD.					1	G	7	2 	3U				H1NE
1998070300310	19980703	00310	EU  	1998	7	3	HEEA0014685      	1	19980610	G	6210	10515141	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	DEBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H	8469 				S833				LEADING EDGE OF MAIN ROTOR BLADE HAS SEPARATION BEYOND LIMITS ON THE OUTBOARD END OF THE TWO INBOARD STRIPS.						1	G	7	2 	3U				H3EU
1998070300234	19980703	00234		1998	7	3	HEEA0014686      	4	19980610	G	3457	0845000000	GPS             		SKYNAV5000  	BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				GPS UNIT WILL NOT RECEIVE ANY SATELLITES.  COOKED UNIT ON BENCH.   UNIT LOCKED ON TO 3D.   FUNCTION CHECK GOOD.						1	G	7	1 	4U				H4SW
1998070300171	19980703	00171		1998	7	3	HEEA0014688      	4	19980610	G	3421	7660002113102	GYRO            			SKRSKY	S76   	S76A        	8143006	NE  										COPILOT VG	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				COPILOT'S HORIZON IS UNREADABLE.						1	G	7	2 	3U				H1NE
1998070300235	19980703	00235	SW  	1998	7	3	HEEA0014690      	1	19980610	G	2820	214066226103	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				FUEL SYSTEM VALVE FAULTY, CAUTION LIGHT FUNCTIONS INTERMITTENTLY.						1	G	7	2 	4U				H4SW
1998070300236	19980703	00236	SW  	1998	7	3	HEEA0014692      	1	19980610	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				STEP WILL NOT COME UP.						1	G	7	2 	4U				H4SW
1998070300237	19980703	00237		1998	7	3	HEEA0014693      	4	19980610	G	3417	214175421101	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT AIR DATA	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	59806					28140				COMPUTER DOES NOT COUNT DOWN AS FUEL BURNS.						2	G	7	2 	4U				H10SW
1998070300238	19980703	00238	SW  	1998	7	3	HEEA0014694      	1	19980610	G	7921	8538100	OIL COOLER      			BELL  	212   	212         	1181420	SW  										OIL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5736J					31140				OIL COOLER LEAKING IN FIN AREA.						1	G	7	1 	4U				H4SW
1998070300311	19980703	00311	EU  	1998	7	3	HEEA0014695      	1	19980610	G	3340	A413AHDADF28V	POWER SUPPLY    			BOLKMS	105   	BO105S      	5626006	EU  										STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				STROBE INOPERATIVE.						1	G	7	2 	3U				H3EU
1998070300239	19980703	00239	SW  	1998	7	3	HEEA0014696      	1	19980610	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Z					51610				STROBE INOPERATIVE.						1	G	7	1 	3U				H2SW
1998070300240	19980703	00240	SW  	1998	7	3	HEEA0014697      	1	19980610	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Z					51610				STROBE INOPERATIVE.						1	G	7	1 	3U				H2SW
1998070300241	19980703	00241	SW  	1998	7	3	HEEA0014698      	1	19980610	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										DUAL TORQUE	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				DUAL TORQUE'S NR 1 NEEDLE READS LOW.  TIME SINCE REPAIR 42:25 HOURS.						1	G	7	2 	4U				H4SW
1998070300312	19980703	00312	EU  	1998	7	3	HEEA0014699      	1	19980610	G	2840	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESSURE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				FUEL PRESSURE TRANSMITTER PEGS OUT INTERMITTENTLY.						1	G	7	2 	3U				H3EU
1998070300242	19980703	00242		1998	7	3	HEEA0014700      	4	19980610	G	3422	102005403	GYROSCOPE       			BELL  	412   	412         	1182202	SW  										HORIZON	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA									HORIZONTAL GYRO WILL NOT ERECT AND NO CURRENT DRAWN.						1	G	7	2 	4U				H4SW
1998070300243	19980703	00243		1998	7	3	HEEA0014701      	4	19980610	G	3424	214075244001	RATE GYRO       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				TURN INDICATOR WOULD NOT OPEN.						1	G	7	2 	4U				H4SW
1998070300244	19980703	00244		1998	7	3	HEEA0014702      	4	19980610	G	2210	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				SCAS AMPLIFIER TRIPS A/C CIRCUIT BREAKER.						2	G	7	2 	4U				H10SW
1998070300245	19980703	00245		1998	7	3	HEEA0014703      	4	19980610	G	2210	214074301105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										SCAS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				AMPLIFIER UNIT WILL NOT EXCHANGE.						2	G	7	2 	4U				H10SW
1998070300246	19980703	00246	SW  	1998	7	3	HEEA0014704      	1	19980610	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				GENERATOR WOULD NOT COME ON.						1	G	7	2 	4U				H4SW
1998070300247	19980703	00247		1998	7	3	HEEA0014705      	4	19980610	G	2210	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				COMPUTER STICKS, DOES NOT FOLLOW APF'S.						1	G	7	2 	4U				H4SW
1998070300313	19980703	00313	EU  	1998	7	3	HEEA0014706      	1	19980610	G	7330	90321022	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131AE					S787				MAIN AND SUPPLY NEEDLES FLUCTUATES.						1	G	7	2 	3U				H3EU
1998070300248	19980703	00248	SW  	1998	7	3	HEEA0014707      	1	19980610	G	7720	214175248103	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				MGT INDICATOR INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300249	19980703	00249	SW  	1998	7	3	HEEA0014708      	1	19980610	G	7714	214175249101	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8045T	580  				28101				RPM INDICATOR FAILED IN FLIGHT.						2	G	7	2 	4U				H10SW
1998070300250	19980703	00250		1998	7	3	HEEA0014709      	4	19980610	G	3416	61031004	ALTIMETER       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2772A					45311				NO LIGHT WITH ALTIMETER.						1	G	7	1 	3U				H2SW
1998070300314	19980703	00314	EU  	1998	7	3	HEEA0014710      	1	19980610	G	6340	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			CR	CRUISE         	1			SW	03	911DD					S830				MAIN ROTOR RPM, LOW SIDE WARNING INTERMITTENTLY IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998070300251	19980703	00251	SW  	1998	7	3	HEEA0014711      	1	19980610	G	2841	393008047	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				FUEL QUANTITY INDICATOR ERRATIC.						1	G	7	2 	4U				H4SW
1998070300252	19980703	00252	SW  	1998	7	3	HEEA0014712      	1	19980610	G	2842	20037000001	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FUEL CELL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FUEL QUANTITY TRANSMITTER READS HIGH CAPACITANCE.						1	G	7	2 	4U				H4SW
1998070300253	19980703	00253	SW  	1998	7	3	HEEA0014713      	1	19980610	G	3040	214073932109	CONVERTER       			BELL  	214   	214ST       	1182106	SW  										LT WIPER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				LEFT WIPER CONVERTER INOPERATIVE						2	G	7	2 	4U				H10SW
1998070300254	19980703	00254	SW  	1998	7	3	HEEA0014714      	1	19980610	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA									STEP ACTUATOR 'S INTERNAL GEAR SEEMS TO BE STRIPPED.						1	G	7	2 	4U				H4SW
1998070300172	19980703	00172	GL  	1998	7	3	HEEA0014715      	2	19980610	G	7412	106149501	IGNITER BOX     			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE IGN	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				DAMAGED THREADS ON IGNITER LEAD POST.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998070300315	19980703	00315	EU  	1998	7	3	HEEA0014716      	1	19980610	G	6320	1171264801	FILTER ASSY     			BOLKMS	117   	BK117B2     	5626013	EU  										M/R GEARBOX	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	136AE					7234				MAIN ROTOR GEARBOX FILTER'S BYPASS BUTTON STAYS PARTIALLY EXTENDED.						1	G	7	2 	3U			NC	H13EU
1998070300255	19980703	00255	SW  	1998	7	3	HEEA0014717      	1	19980610	G	6240	206076373001	GENERATOR       			BELL  	206   	206L1       	1182107	SW  										TRIPLE TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745N					45489				TRIPLE TACHOMETER'S ROTOR NEEDLE DOES NOT MOVE FROM  ZERO.						1	G	7	1 	3U				H2SW
1998070300173	19980703	00173	NE  	1998	7	3	HEEA0014718      	1	19980610	G	3230	4608	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										MLG	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5435V					760158				SEEPS THROUGH HOLE INSIDE OF BODY.						1	G	7	2 	3U				H1NE
1998070300174	19980703	00174	NE  	1998	7	3	HEEA0014719      	1	19980610	G	2121	7650007901103	BLOWER          			SKRSKY	S76   	S76A        	8143006	NE  										COOLING SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				BLOWER WILL NOT MOTOR.						1	G	7	2 	3U				H1NE
1998070300316	19980703	00316	EU  	1998	7	3	HEEA0014720      	1	19980610	G	2435	230321825	STATOR          			BOLKMS	117   	BK117B2     	5626013	EU  										START/GEN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		3578 								STATOR CAUSES VERY HIGH FIELD CURRENT AND BRUSH LEADS ARE TOO LONG.   REWOUND  ON 11-29-97.   INSTALLED ON 3-25-98 AND F	AILED ON TEST.					1	G	7	2 	3U			NC	H13EU
1998070300256	19980703	00256	SW  	1998	7	3	HEEA0014721      	1	19980610	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										M/R CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				AFCS WILL NOT FOLLOW BEEP MOTOR LEFT OR RIGHT.						1	G	7	2 	4U				H4SW
1998070300317	19980703	00317	EU  	1998	7	3	HEEA0014722      	1	19980610	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117A3     	5626015	EU  										INST LIGHTS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				COPILOT INSTRUMENT LIGHT PROBLEM.						1	G	7	2 	3U				H13EU
1998070300257	19980703	00257		1998	7	3	HEEA0014723      	4	19980610	G	2210	214074301105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										SCAS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				SCAS SYSTEM WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW
1998070300175	19980703	00175		1998	7	3	HEEA0014724      	4	19980610	G	2210	7690001805101	SWITCH          			SKRSKY	S76   	S76A        	8143006	NE  										AIRSPEED	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				AIRSPEED SWITCH INOPERATIVE.						1	G	7	2 	3U				H1NE
1998070300176	19980703	00176	NE  	1998	7	3	HEEA0014725      	1	19980610	G	7331	PC820101	SIGNAL COND     			SKRSKY	S76   	S76A        	8143006	NE  										FUEL FLOW	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	31217					760229				FUEL FLOW SIGNAL CONDITIONER INOPERATIVE.						1	G	7	2 	3U				H1NE
1998070300318	19980703	00318	EU  	1998	7	3	HEEA0014726      	1	19980611	G	6520	4619210902	BEVEL GEAR      		4619002003  	BOLKMS	105   	BO105S      	5626006	EU  										T/R GEARBOX	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4294R				1254	S860				METAL IN OIL.  FOUND BEVEL GEAR SET SPALDING AND ROLLOVER ON ALL BEARINGS.  REPLACED WITH NEW GEAR SET.						1	G	7	2 	3U				H3EU
1998070300258	19980703	00258		1998	7	3	HEEA0014727      	4	19980611	G	3421	5040017901	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT ATTITUDE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA									ATTITUDE INDICATOR PRECESSES 1 DEGREE A MINUTE.  REBALANCED STATIC AND DYNAMIC.   RECALIBRATED ROLL AND PITCH ERECTIONS.	   UNIT BENCH CHECKS GOOD.					1	G	7	2 	4U				H4SW
1998070300259	19980703	00259	SW  	1998	7	3	HEEA0014728      	1	19980611	G	6340	214074280107	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				RPM LIMIT DETECTOR HAS LOW AUDIO VOLUME.						1	G	7	2 	4U				H4SW
1998070300260	19980703	00260		1998	7	3	HEEA0014729      	4	19980611	G	3416	D120P2T	ENCODER         			BELL  	206   	206L1       	1182107	SW  										INST PANEL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ENCODER DOES NOT HAVE VALID OUTPUT.						1	G	7	1 	3U				H2SW
1998070300261	19980703	00261		1998	7	3	HEEA0014730      	4	19980611	G	3416	D120P2T	ENCODER         			BELL  	206   	206L4       	1182110	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7074W					52033				ENCODER ALTITUDE NOT RECEIVED BY ATC.						1	G	7	1 	3U			NC	H2SW
1998070300262	19980703	00262	SW  	1998	7	3	HEEA0014731      	1	19980611	G	3340	214175127103	POWER SUPPLY    			BELL  	214   	214ST       	1182106	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				STROBE LIGHT INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300319	19980703	00319	EU  	1998	7	3	HEEA0014732      	1	19980611	G	2422	SS120	STATIC INVERTER 			BOLKMS	117   	BK117B1     	5626012	EU  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL					7198				A/C INVERTER INOPERATIVE.						1	G	7	2 	3U				H13EU
1998070300263	19980703	00263		1998	7	3	HEEA0014733      	4	19980611	G	3422	206075606103	GYRO            			BELL  	206   	206L1       	1182107	SW  										DIRECTIONAL GYRO	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y					45192				DG ROTOR WILL NOT SPIN.  TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW
1998070300264	19980703	00264	SW  	1998	7	3	HEEA0014734      	1	19980611	G	7714	206070265101	INDICTOR        			BELL  	206   	206L1       	1182107	SW  										DUAL TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745N					45489				DUAL TACHOMETER'S ROTOR AND TURBINE NEEDLE INOPERATIVE.						1	G	7	1 	3U				H2SW
1998070300265	19980703	00265	SW  	1998	7	3	HEEA0014735      	1	19980611	G	7931	206075187003	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y					45192				OIL PRESSURE NEEDLE STICKS DURING START.						1	G	7	1 	3U				H2SW
1998070300177	19980703	00177	NE  	1998	7	3	HEEA0014736      	1	19980611	G	2822	399A106	MOTOR           			SKRSKY	S76   	S76A        	8143006	NE  										BOOST PUMP	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				BOOST PUMP MOTOR FUNCTIONS INTERMITTENTLY.						1	G	7	2 	3U				H1NE
1998070300320	19980703	00320	EU  	1998	7	3	HEEA0014737      	1	19980611	G	6340	KDW02	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				ROTOR RPM WARNING HORN LIGHT CAME ON.						1	G	7	2 	3U				H3EU
1998070300266	19980703	00266	SW  	1998	7	3	HEEA0014738      	1	19980611	G	7933	206075187003	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22425					45743				OIL TEMPERATURE NEEDLE STICKS AND PSI NEEDLE HAS FUNCTION ERROR.						1	G	7	1 	3U				H2SW
1998070300178	19980703	00178	NE  	1998	7	3	HEEA0014739      	1	19980611	G	7931	7645001078101	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE OIL	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X					760050				OIL TEMPERATURE SIDE READS LOW.						1	G	7	2 	3U				H1NE
1998070300179	19980703	00179	SW  	1998	7	3	HEEA0014740      	1	19980611	G	7712	206075185001	GAUGE           			BELL  	206   	206B3       	1181506	SW  										ENGINE TORQUE	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181Y					3772				ENGINE TORQUE GAUGE HAS FLUID ON FACE, NEEDLE STICKS AT 100 PERCENT.						1	G	7	1 	3U				H2SW
1998070300267	19980703	00267	SW  	1998	7	3	HEEA0014741      	1	19980611	G	3340	7028521	LIGHT           			BELL  	214   	214ST       	1182106	SW  										STROBE SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				STROBE LIGHT WILL NOT FLASH.						2	G	7	2 	4U				H10SW
1998070300268	19980703	00268	SW  	1998	7	3	HEEA0014742      	1	19980611	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3905B					45598				TOT INDICATOR READS HIGH AFTER WARM-UPS.						1	G	7	1 	3U				H2SW
1998070300269	19980703	00269	SW  	1998	7	3	HEEA0014743      	1	19980611	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3892R					45594				TOT INDICATOR INTERMITTENTLY STICKS ON START UP.						1	G	7	1 	3U				H2SW
1998070300270	19980703	00270	SW  	1998	7	3	HEEA0014744      	1	19980611	G	7712	206075739103	TORQUEMETER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		213  								TORQUE NEEDLE STICKS THROUGHOUT; DOES NOT RETURN TO ZERO.						1	G	7	1 	3U				H2SW
1998070300271	19980703	00271		1998	7	3	HEEA0014745      	4	19980611	G	2210	7000299901	CONTROLER       			BELL  	412   	412         	1182202	SW  										AUTOPILOT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				HP AND CPL SWITCHES WILL NOT ENGAGE.						1	G	7	2 	4U				H4SW
1998070300272	19980703	00272	SW  	1998	7	3	HEEA0014746      	1	19980611	G	2436	214175153105	REGULATOR       			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				GENERATOR WOULD NOT STAY ON LINE.						2	G	7	2 	4U				H10SW
1998070300273	19980703	00273	SW  	1998	7	3	HEEA0014747      	1	19980611	G	7930	35712519131	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				OIL INDICATOR WILL NOT INDICATE.						1	G	7	2 	4U				H4SW
1998070300180	19980703	00180		1998	7	3	HEEA0014748      	4	19980611	G	3416	8140B35	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT ENCODER	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				OUTPUT ON ALTIMETER IS INTERMITTENT AND INCORRECT.						1	G	7	2 	3U				H1NE
1998070300181	19980703	00181		1998	7	3	HEEA0014749      	4	19980611	G	2210	7611132	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										ROLL SLICE	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911MJ					760231				NR 1 ROLL ACTUATOR HARD OVER TO THE LEFT.						1	G	7	2 	3U				H1NE
1998070300274	19980703	00274		1998	7	3	HEEA0014750      	4	19980611	G	2211	4033089901	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59806					28140				PITCH MODE IN SCAS INDICATOR KICKS OFF IN DESCENT.						2	G	7	2 	4U				H10SW
1998070300275	19980703	00275	SW  	1998	7	3	HEEA0014751      	1	19980611	G	3210	214031839101	STRAP ASSY      			BELL  	214   	214ST       	1182106	SW  										MLG	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				RUBBER IS UNBONDED ON STRAP ASSY.						2	G	7	2 	4U				H10SW
1998070300182	19980703	00182	NE  	1998	7	3	HEEA0014752      	1	19980611	G	6200	7665001802102	VTA ACTUATOR    			SKRSKY	S76   	S76A        	8143006	NE  										M/R SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1547D					760077				RIGHT POTENTIOMETER IS LEAKING AND SOLENOID IS INOPERATIVE.						1	G	7	2 	3U				H1NE
1998070300276	19980703	00276	SW  	1998	7	3	HEEA0014753      	1	19980611	G	7160	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ENGINE INTAKE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				ENGINE INTAKE UNIT INOPERATIVE.  TAPPING ON UNIT FREED THE MOTOR FOR A SHORT TIME.						1	G	7	2 	4U				H4SW
1998070300277	19980703	00277	SW  	1998	7	3	HEEA0014754      	1	19980611	G	6320	206040530101	INPUT LINE      			BELL  	206   	206L4       	1182110	SW  										CASE ASSEMBLY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077B					52037				GEARBOX INPUT LINE IS WORN.						1	G	7	1 	3U			NC	H2SW
1998070300183	19980703	00183	NE  	1998	7	3	HEEA0014755      	1	19980611	G	3230	7665002802104	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										MLG	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				MAIN LANDING GEAR VALVE ALLOWS AIR INTO HYDRAULIC SYSTEM.						1	G	7	2 	3U				H1NE
1998070300278	19980703	00278	SW  	1998	7	3	HEEA0014756      	1	19980611	G	5610	M206R3116	CHIN BUBBLE     			BELL  	206   	206B3       	1181506	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CHIN BUBBLE DOES NOT HAVE ENOUGH EDGE TO FIT OPENINGS.  (TOO SHORT)  .						1	G	7	1 	3U				H2SW
1998070300279	19980703	00279	SW  	1998	7	3	HEEA0014757      	1	19980611	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				ACTUATOR DOES NOT WORK FORE AND AFT.						1	G	7	2 	4U				H4SW
1998070300184	19980703	00184		1998	7	3	HEEA0014758      	4	19980611	G	2210	7690001805102	SWITCH          			SKRSKY	S76   	S76A        	8143006	NE  										AUTOFLIGHT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5128					760181				AFCS SWITCH INTERMITTENT.						1	G	7	2 	3U				H1NE
1998070300280	19980703	00280	SW  	1998	7	3	HEEA0014759      	1	19980611	G	3213	212030436007	CAP ASSEMBLY    			BELL  	412   	412         	1182202	SW  										CROSS TUBE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				CROSSTUBE RUBBER ON CAP ASSY IS CRACKING AND DEFORMED.						1	G	7	2 	4U				H4SW
1998070300281	19980703	00281	SW  	1998	7	3	HEEA0014760      	1	19980611	G	2932	205076044009	SWITCH          			BELL  	214   	214ST       	1182106	SW  										HYD PRESSURE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6957Y					28139				SWITCH LEAKING HYDRAULIC OIL.						2	G	7	2 	4U				H10SW
1998070300185	19980703	00185	GL  	1998	7	3	HEEA0014761      	2	19980611	G	7320	7630103901102	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X				263	760050				ACTUATOR MOTOR ROUTES TOO LONG BEFORE SHAFT TURNS.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998070300186	19980703	00186	GL  	1998	7	3	HEEA0014762      	2	19980611	G	7320	7630103901102	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X				185	760050				MOTOR ROTATES TOO LONG BEFORE SHAFT MOVES.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998070300321	19980703	00321		1998	7	3	HEEA0014763      	4	19980611	G	3421	5040017901	SCREW           			SNIAS 	350   	AS350B2     	8680813	EU  										ATTITUDE IND	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				ATTITUDE INDICATOR HAS SCREW LOOSE INSIDE OF UNIT.						1	G	7	1 	3U				H9EU
1998070300322	19980703	00322	EU  	1998	7	3	HEEA0014764      	1	19980611	G	2435	23032022	ARMATURE        			BOLKMS	117   	BK117A4     	5626017	EU  										START/GEN	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ	9901 				7092				STARTER/GENERATOR ARMATURE IS BAD.  INSTALL P/N N1828-1 LONG WEAR BRUSHES.						1	G	7	2 	3U				H13EU
1998070300282	19980703	00282	SW  	1998	7	3	HEEA0014765      	1	19980611	G	2437	214175250103	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				DC INDICATOR'S NR 2 NEEDLE DOES NOT INDICATE.						2	G	7	2 	4U				H10SW
1998070300283	19980703	00283		1998	7	3	HEEA0014766      	4	19980611	G	3416	1003511424	ALTIMETER       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	DRAGGING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				ALTIMETER NEEDLE HAS EXCESSIVE DRAG.						2	G	7	2 	4U				H10SW
1998070300284	19980703	00284		1998	7	3	HEEA0014767      	4	19980611	G	3416	10220011850	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				ENCODER READS OUT OF TOLERANCE ON DOWN-SCALE CHECK.						1	G	7	2 	4U				H4SW
1998070300285	19980703	00285	SW  	1998	7	3	HEEA0014768      	1	19980611	G	7810	206064300005	EXHAUST         			BELL  	206   	206L1       	1182107	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2764F					45279				EXHAUST ASSY CRACKED.						1	G	7	1 	3U				H2SW
1998070300323	19980703	00323		1998	7	3	HEEA0014769      	4	19980611	G	3416	A30	ENCODER         			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				ENCODER DOES NOT HOLD CALIBRATION SLOW TO RESPOND.						1	G	7	2 	3U				H3EU
1998070300286	19980703	00286	SW  	1998	7	3	HEEA0014770      	1	19980611	G	7332	APTE138100G	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				FUEL PRESSURE TRANSMITTER CAUSES INDICATOR TO PEG OUT.						1	G	7	2 	4U				H4SW
1998070300187	19980703	00187	NE  	1998	7	3	HEEA0014771      	1	19980611	G	7810	7630507003044	EJECTOR         			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				ENGINE EXHAUST HAS EXCESSIVE CRACKING.						1	G	7	2 	3U				H1NE
1998070300287	19980703	00287		1998	7	3	HEEA0014772      	4	19980611	G	3414	214175299107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				AIRSPEED NEEDLE DOESN'T RETURN TO ZERO.						2	G	7	2 	4U				H10SW
1998070300288	19980703	00288	SW  	1998	7	3	HEEA0014773      	1	19980611	G	2424	214175153105	REGULATOR       			BELL  	214   	214ST       	1182106	SW  										AC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				GENERATOR WOULD NOT STAY ON LINE.						2	G	7	2 	4U				H10SW
1998070300324	19980703	00324		1998	7	3	HEEA0014774      	4	19980611	G	3416	A30	ENCODER         			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT ALT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				ENCODER GIVES NO VALID OUTPUT.						1	G	7	2 	3U				H3EU
1998070300289	19980703	00289		1998	7	3	HEEA0014775      	4	19980611	G	3416	D120P2T	ENCODER         			BELL  	206   	206L1       	1182107	SW  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	HCBXL					45219				ENCODER ALTIMETER HAS EXCESSIVE CASE LEAKAGE.						1	G	7	1 	3U				H2SW
1998070300325	19980703	00325		1998	7	3	HEEA0014776      	4	19980611	G	2562	ELT1104	ELT             			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				ELT WILL NOT TURN OFF.						1	G	7	2 	3U				H13EU
1998070300290	19980703	00290	SW  	1998	7	3	HEEA0014777      	1	19980611	G	6320	204040324005	SHAFT           			BELL  	212   	212         	1181420	SW  										TRANSMISSION	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				TRANSMISSION SHAFT IS CORRODED AND FRETTED ON MOUNTING SURFACE.						1	G	7	1 	4U				H4SW
1998070300291	19980703	00291	SW  	1998	7	3	HEEA0014778      	1	19980611	G	6320	204040701103	GEAR            			BELL  	212   	212         	1181420	SW  										M/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MAIN ROTOR GEARBOX GEAR ORRODED AND FRETTED ON MOUNTING SURFACE.						1	G	7	1 	4U				H4SW
1998070300292	19980703	00292		1998	7	3	HEEA0014779      	4	19980611	G	2210	214074104101	SENSOR          			BELL  	214   	214ST       	1182106	SW  										SCAS SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				DUAL RATE SENSOR CAUSES FEEDBACK IN CYCLIC STICK.						2	G	7	2 	4U				H10SW
1998070300293	19980703	00293		1998	7	3	HEEA0014780      	4	19980611	G	2210	214074104101	SENSOR          			BELL  	214   	214ST       	1182106	SW  										SCAS SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				DUAL RATE SENSOR CAUSES SCAS SYSTEM TO DISENGAGE WHEN MOVED.						2	G	7	2 	4U				H10SW
1998070300188	19980703	00188	NE  	1998	7	3	HEEA0014781      	2	19980611	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING G/BOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	107X	12873				33113				COMBINING GEARBOX MAKING METAL.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998070300189	19980703	00189	NE  	1998	7	3	HEEA0014782      	2	19980611	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING G/BOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N	7597 				33010				COMBINING GEARBOX MAKING  METAL.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998070300294	19980703	00294	SW  	1998	7	3	HEEA0014783      	1	19980611	G	3340	212075962001	POWER SUPPLY    			BELL  	412   	412         	1182202	SW  										STROBE SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				STROBE LIGHT INOPERATIVE AFTER 3 MINUTES.						1	G	7	2 	4U				H4SW
1998070300295	19980703	00295		1998	7	3	HEEA0014784      	4	19980611	G	3421	RCA26BK12	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8591X					51495				HORIZONTNAL GYRO PRECESSES 10 DEGREES IN DIVE, ERRATIC ERECTION RATES.						1	G	7	1 	3U				H2SW
1998070300296	19980703	00296	SW  	1998	7	3	HEEA0014785      	1	19980611	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										START/GEN	BURNED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	889  			96335	53114				AIRCRAFT WOULD NOT START.  FOUND STARTER/GENERATOR BRUSHES HANGING UP AND ONE BRUSH BOX WAS BURNT.						1	G	7	1 	3U			O	H2SW
1998070300330	19980703	00330	SW  	1998	7	3	HEEA0014786      	1	19980617	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER/GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	578  			97222	53198				AIRCRAFT WILL NOT START.  FOUND STARTER/GENERATOR BRUSHES EXCESSIVELY WORN AND HANGING UP.  REPLACED BRUSHES.						1	G	7	1 	3U			O	H2SW
1998070300332	19980703	00332	SW  	1998	7	3	HEEA0014789      	1	19980617	G	6710	204001109001	TUBE            			BELL  	212   	212         	1181420	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	5736J					31140				TUBE IS PART OF COLLECTIVE SYSTEM.  MUST BE DRILLED IN A FIXTURE.  THIS NEW TUBE HAS NO HOLES.						1	G	7	1 	4U			 	H4SW
1998070300333	19980703	00333	SW  	1998	7	3	HEEA0014790      	1	19980617	G	5313	212030128163S	LONGERON        			BELL  	212   	212         	1181420	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										LONGERON MISMANUFACTURED AND MISIDENTIFIED.  RIVETS INSTALLED AT BOTTOM OF SPLICES WHICH DOES NOT ALLOW US TO PICK UP RI	VET PATTERN FROM CEILING PANEL.  RIVETS ARE NOT INSTALLED, TOP OF SPLICES OF LONGERON.					1	G	7	1 	4U			 	H4SW
1998070300334	19980703	00334	SW  	1998	7	3	HEEA0014792      	1	19980617	G	6520	406040072105	ADAPTER         			BELL  	407   	407         		SW  										T/ROTOR SPLINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				TAIL ROTOR SPLINE'S ADAPTER IS INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998070300359	19980703	00359	EU  	1998	7	3	HEEA0014793      	1	19980617	G	7722	56375600010	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4034Q					2918				T-4 INDICATOR FAILED, WILL NOT INDICATE.						1	G	7	1 	3U				H9EU
1998070300360	19980703	00360	EU  	1998	7	3	HEEA0014794      	1	19980617	G	7933	642790041	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										OIL TEMP	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				OIL TEMPERATURE GAUGE ERRATIC.						1	G	7	1 	3U				H9EU
1998070300335	19980703	00335	SW  	1998	7	3	HEEA0014795      	1	19980617	G	6320	214040806003	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				MAIN ROTOR GEARBOX INDICATOR LIGHT FLICKERS.						1	G	7	1 	3U			O	H2SW
1998070300336	19980703	00336	SW  	1998	7	3	HEEA0014796      	1	19980617	G	3212	8226003	FUSIBLE PLUG    			BELL  	407   	407         		SW  										FLOAT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				PLUG BLEW OUT RELEASING FLOAT BOTTLE PRESSURE.						1	G	7	1 	3U			O	H2SW
1998070300337	19980703	00337	SW  	1998	7	3	HEEA0014797      	1	19980617	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	407   	407         		SW  										ANTI COLL LIGHT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				ANTI-COLLISION LIGHT WILL NOT FLASH.						1	G	7	1 	3U			O	H2SW
1998070300338	19980703	00338	SW  	1998	7	3	HEEA0014798      	1	19980617	G	7933	407375005101	INDICATOR       			BELL  	407   	407         		SW  										OIL TEMP SYS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				OIL TEMPERATURE SIDE OF INDICATOR INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998070300339	19980703	00339	SW  	1998	7	3	HEEA0014799      	1	19980617	G	7931	407375004001	INDICATOR       			BELL  	407   	407         		SW  										OIL PRESSURE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				ENGINE OIL PRESSURE LCD NOT ILLUMINATING OR TESTING.						1	G	7	1 	3U			O	H2SW
1998070300340	19980703	00340	SW  	1998	7	3	HEEA0014800      	1	19980617	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										FUEL QTY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				INDICATION SHOWED INTERMITTENT INDICATIONS DURING FLIGHT.						1	G	7	1 	3U			O	H2SW
1998070300361	19980703	00361	EU  	1998	7	3	HEEA0014801      	1	19980617	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B2     	8680813	EU  										STROBE SYS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				STROBE WILL NOT FLASH LIGHT.						1	G	7	1 	3U				H9EU
1998070300341	19980703	00341	SW  	1998	7	3	HEEA0014802      	1	19980617	G	7714	407375002103	INDICATOR       			BELL  	407   	407         		SW  										ENG NG	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH	264  				53228				INDICATOR GOES THROUGH TEST OK THEN TO ZERO BUT WILL NOT GO UP.						1	G	7	1 	3U			O	H2SW
1998070300342	19980703	00342	SW  	1998	7	3	HEEA0014803      	1	19980617	G	3212	407350301101	FLOAT BAG       			BELL  	407   	407         		SW  										FLOAT SYS	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				FLOAT BAG FAILED 6 MONTH INSPECTION.  LEAK AT FORWARD END AT BOTTOM.						1	G	7	1 	3U			O	H2SW
1998070300343	19980703	00343	SW  	1998	7	3	HEEA0014804      	1	19980617	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	447PH	1059 				53114				OIL COOLER LEAKING.						1	G	7	1 	3U			O	H2SW
1998070300344	19980703	00344	SW  	1998	7	3	HEEA0014805      	1	19980617	G	7720	407375001103	INDICATOR       			BELL  	407   	407         		SW  										MGT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				MGT INDICATOR GOES BLANK IN-FLIGHT.						1	G	7	1 	3U			O	H2SW
1998070300326	19980703	00326		1998	7	3	HEEA0014806      	4	19980617	G	3416	212070238003	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				INDICATOR INDICATES 1500 FEET AT 29.92 HG.  EXCESSIVE ERROR.						1	G	7	2 	3U				H1NE
1998070300345	19980703	00345	SW  	1998	7	3	HEEA0014807      	1	19980617	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				TRIPLE TACHOMETER'S NR  1 NEEDLE STUCK, UNIT FUNCTION CHECKED BAD, NEEDLES ARE ERRATIC AND HAVE AT LEAST 2 DEGREES SPLIT	 BETWEEN THEM.  TIME SINCE REPAIR 118:25 HOURS.					1	G	7	2 	4U				H4SW
1998070300362	19980703	00362	EU  	1998	7	3	HEEA0014808      	1	19980617	G	6720	116488P	BEARING         			BOLKMS	117   	BK117B2     	5626013	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	134AE					7237				BEARING HAS EXCESSIVE WEAR TO THE POINT OF NEAR FAILURE AND POSSIBLE LOSS OF TAIL ROTOR CONTROL.  REPLACED WITH SERVICEA	BLE LINK.					1	G	7	2 	3U			NC	H13EU
1998070300346	19980703	00346	SW  	1998	7	3	HEEA0014809      	1	19980617	G	6710	206001906001	BELLCRANK       			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				MAIN ROTOR BELLCRANK HAS CORROSION DAMAGE BEYOND LIMITS.  SCRAPPED PART, REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW
1998070300347	19980703	00347	SW  	1998	7	3	HEEA0014810      	1	19980617	G	6710	206001330001	SUPPORT         			BELL  	206   	206L1       	1182107	SW  										M/R CYCLIC	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				MAIN ROTOR CYCLIC HAS CORROSION DAMAGE BEYOND LIMITS.  SCRAPPED PART, REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW
1998070300348	19980703	00348	SW  	1998	7	3	HEEA0014811      	1	19980617	G	6710	206001342001	TUBE ASSY       			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				MAIN ROTOR TUBE ASSY HAS MECHANICAL DAMAGE (NICKS, SCRATCHES) AROUND THE UPPER SLOT.  DAMAGE BEYOND LIMITS.  SCRAPPED PA	RT, REPLACED WITH SERVICEABLE PART.					1	G	7	1 	3U				H2SW
1998070300349	19980703	00349	SW  	1998	7	3	HEEA0014812      	1	19980617	G	6220	206001713101	SUPPORT         			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				MAIN ROTOR SUPPORT HAS EXCESSIVELY CORRODED ON BOTTOM.  CORROSION BEYOND LIMITS.  SCRAPPED PART, REPLACED WITH SERVICEAB	LE PART.					1	G	7	1 	3U				H2SW
1998070300327	19980703	00327	NE  	1998	7	3	HEEA0014813      	1	19980617	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219	10980				760230				TAIL ROTOR PADDLE 'B' HAS SOME FOREIGN OBJECT DAMAGE.  THERE IS A HOLE ON LEADING EDGE STRIP AND A GOUGE IN THE AIRFOIL 	REGION.  ON PADDLE 'A' THERE ARE CUTS INTO PRIMARY RUBBER.					1	G	7	2 	3U				H1NE
1998070300350	19980703	00350	SW  	1998	7	3	HEEA0014814      	1	19980617	G	7714	214175251107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				COPILOT TRIPLE TACH PEGS OUT OCCASIONALLY.						2	G	7	2 	4U				H10SW
1998070300351	19980703	00351	SW  	1998	7	3	HEEA0014815      	1	19980617	G	6220	222010154111	TRUNNION        			BELL  	222   	222         	1182122	SW  										M/R HUB	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		4452 								BLUE EPOXY COATING FLAKING.  REMOVED FROM CUSTOMER AIRCRAFT.  RENEWED BLUE EPOXY COATING ,						1	G	7	2 	3U				H9SW
1998070300352	19980703	00352	SW  	1998	7	3	HEEA0014816      	1	19980617	G	5510	206023119151	STABILIZER      			BELL  	206   	206L1       	1182107	SW  										HORIZ STAB	MISLOCATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										HORIZONTAL STABI8LIZER HAS TWO EACH INSERTS LOCATED WRONG PLACE AND THEN FILLED.						1	G	7	1 	3U				H2SW
1998070300353	19980703	00353	SW  	1998	7	3	HEEA0014817      	1	19980617	G	5311	206032308103S	FRAME           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										THE LOWER FLANGE OF THE FRAME, WHERE IT ATTACHES TO THE FUSELAGE AFT FAIRING (P/N 206-032-310-XXX), DOES NOT HAVE SUFFIC	IENT FLANGE WIDTH TO MAINTAIN PROPER EDGE DISTANCE.  THE FLANGE OF THE AFT FAIRING HAS ENOUGH ROOM TO ACCEPT A FLANGE OF	.625 INCH, BUT THE FRAME IS ONLY APPROXIMATELY .375 INCH WIDE.				1	G	7	1 	3U				H2SW
1998070300328	19980703	00328		1998	7	3	HEEA0014818      	4	19980617	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D	7910 				760077				AFCS ACTUATOR CHATTERS.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND POTENTIOMETERS CHECKED BAD ON STRIP CHART.						1	G	7	2 	3U				H1NE
1998070300363	19980703	00363	EU  	1998	7	3	HEEA0014819      	1	19980618	G	7714	AG44A	TACH GENERATOR  			BOLKMS	105   	BO105S      	5626006	EU  										NR 1 ENGINE	MISINSTALLED    	E			HEEA	K				NONE                    				O			OTHER                     			HO	HOVERING       	1			SW	03	8197X					S808				WHEN AIRCRAFT PICKED UP TO A HOVER, N2 NR 1 ENGINE DROPPED TO ZERO.  FOUND GROUNDING STAR WASHER FELL OUT DURING INSTALL	ATION CAUSING GROUND TERMINAL TO HAVE AN INTERMITTENT GROUND.  INSTRUCTED TECHNICIAN ON AN IMPROVED METHOD FOR INSTALLAT	ION OF THIS STAR WASHER TO ASSURE IT REMAINS IN PLACE DURING INSTALLATION.  REPAIRED TACH GENERATOR AND RETURNED TO SERV	ICE.			1	G	7	2 	3U				H3EU
1998070300354	19980703	00354		1998	7	3	HEEA0014821      	4	19980618	G	3452	066106200	TRANSPONER      			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22743					3624				TRANSPONDER NOT TRANSMITTING AND WILL NOT IDENT.  FOUND IDENT REPLY LIGHT BLINKING ON AND OFF.						1	G	7	1 	3U				H2SW
1998070300355	19980703	00355		1998	7	3	HEEA0014822      	4	19980618	G	3457	13824120234	RECEIVER        			BELL  	206   	206B3       	1181506	SW  										GPS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	104PH					3622				GPS RECEIVER WILL NOT COME ON.  PERFORMED PRELIMINARY INSPECTION AND FOUND BURNED COMPONENT ON IOP/POWER SUPPLY BOARD.						1	G	7	1 	3U				H2SW
1998070300356	19980703	00356		1998	7	3	HEEA0014823      	4	19980618	G	3442	40005040301	DRIVE ASSEMBLY  			BELL  	214   	214ST       	1182106	SW  										RADAR ANNTENA	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			NR	NOT REPORTED   	1			SW	03	59806					28140				RADAR INDICATOR DISPLAYS ANTENNA FAULT.						2	G	7	2 	4U				H10SW
1998070300357	19980703	00357		1998	7	3	HEEA0014824      	4	19980618	G	3442	40008310105	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										RADAR SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	59806					28140				RADAR INDICATOR DISPLAYS ANTENNA FAULT IN ON POSITION AND TRANSMITS INTERMITTENTLY.						2	G	7	2 	4U				H10SW
1998070300358	19980703	00358		1998	7	3	HEEA0014825      	4	19980618	G	3442	40005040301	DRIVE ASSEMBLY  			BELL  	214   	214ST       	1182106	SW  										RADAR SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				N			FALSE WARNING             			IN	INSP/MAINT     	1			SW	03	59806					28140				RADAR INTERMITTENT.  R/T FAULT ON INDICATOR IN ON POSITION.						2	G	7	2 	4U				H10SW
1998070300364	19980703	00364		1998	7	3	HEEA0014826      	4	19980618	G	2312	064101902	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4294R					S860				TRANSCEIVER UNIT HAS WEAK OUTPUT WHEN WARMED UP.  FOUND UNIT TO HAVE WEAK RECEIVER SENSITIVITY AND UNIT IS NOT TRANSMITT	ING CORRECT FREQUENCY FROM 118.00-128.00 MHZ.					1	G	7	2 	3U				H3EU
1998070300329	19980703	00329		1998	7	3	HEEA0014827      	4	19980618	G	2312	071101218	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				UPON INSTALLATION, TRANSCEIVER WOULD NOT TEST NOR RECEIVE AUDIO.  PERFORMED PRELIMINARY INSPECTION.  TROUBLESHOT AND FOU	ND S4 (SWITCH) BAD.  SCRAPPED PART.					1	G	7	2 	3U				H1NE
1998070300365	19980703	00365	EU  	1998	7	3	HEEA0014828      	1	19980619	G	6520	350A33215300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	459  				2820				RUBBER SEPARATION AT TAIL ROTOR.						1	G	7	1 	3U				H9EU
1998070300754	19980703	00754	SW  	1998	7	3	HEEA0014831      	1	19980622	G	2435	206062200123	BRUSHES         			BELL  	407   	407         		SW  										START/GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	397  				53003				STARTER/GENERATOR FAILED 300 HOUR INSPECTION, FOUND BRUSHES WERE EXCESSIVELY WORN.  REPAIRED.						1	G	7	1 	3U			O	H2SW
1998070300755	19980703	00755	SW  	1998	7	3	HEEA0014832      	1	19980622	G	6710	214001423109	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										M/R	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				STEP MOTOR IS INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300894	19980703	00894	EU  	1998	7	3	HEEA0014833      	1	19980622	G	8010	2520M	RELAY           			BOLKMS	105   	BO105S      	5626006	EU  										STARTER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4294R					S860				LOCKOUT CONTACTOR STUCK, CAUSING THE OPPOSITE ENGINE STARTER NOT TO ENGAGE.						1	G	7	2 	3U				H3EU
1998070300756	19980703	00756	SW  	1998	7	3	HEEA0014834      	1	19980622	G	2140	205072277009	VALVE           			BELL  	412   	412         	1182202	SW  										HEATER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				HEATER IS INOPERATIVE AND VALVE THREADS ARE DAMAGED.						1	G	7	2 	4U				H4SW
1998070300757	19980703	00757	SW  	1998	7	3	HEEA0014835      	1	19980622	G	2823	L88010501	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				VALVE INOPERATIVE, MOTOR DOES NOT TURN.						1	G	7	2 	4U				H4SW
1998070300758	19980703	00758	SW  	1998	7	3	HEEA0014836      	1	19980622	G	6710	214001423109	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				ACTUATOR SLOW, CAUSING CIRCUIT BREAKER TO TRIP.						2	G	7	2 	4U				H10SW
1998070300759	19980703	00759	SW  	1998	7	3	HEEA0014837      	1	19980622	G	3340	A490A	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3207Q					51540				STROBE LIGHT POWER SUPPLY HAS NO POWER OUTPUT.						1	G	7	1 	3U				H2SW
1998070300760	19980703	00760	EA  	1998	7	3	HEEA0014838      	1	19980622	G	6710	204060762103	ACTUATOR        			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3208H					31304				MOTOR WILL NOT ACTUATE.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998070300729	19980703	00729		1998	7	3	HEEA0014839      	4	19980622	G	2210	7690001812102	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AUTOFLIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				ACTUATOR WILL NOT RELEASE.						1	G	7	2 	3U				H1NE
1998070300895	19980703	00895	EU  	1998	7	3	HEEA0014840      	1	19980622	G	6240	117945641	INDICATOR       			BOLKMS	117   	BK117B2     	5626013	EU  										MAST MOMENT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE					7238				TEST FUNCTION WORKS INTERMITTENTLY ON MAST MOMENT INDICATOR.						1	G	7	2 	3U			NC	H13EU
1998070300896	19980703	00896	EU  	1998	7	3	HEEA0014841      	1	19980622	G	6240	10594575	TRANSMITTER     			BOLKMS	117   	BK117B2     	5626013	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE					7238				TEST FUNCTION WORKS INTERMITTENTLY ON MAST MOMENT INDICATOR.						1	G	7	2 	3U			NC	H13EU
1998070300761	19980703	00761	SW  	1998	7	3	HEEA0014842      	1	19980622	G	2422	ASH4501	INVERTER        			BELL  	412   	412         	1182202	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				AC SYSTEM INVERTER HAS LOW OUTPUT.						1	G	7	2 	4U				H4SW
1998070300762	19980703	00762	SW  	1998	7	3	HEEA0014843      	1	19980622	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				NR 2 NEEDLE ON TRIPLE TACHOMETER HAS INTERMITTENT OPERATION STATUS.						1	G	7	2 	4U				H4SW
1998070300897	19980703	00897		1998	7	3	HEEA0014844      	4	19980622	G	2210	117884141	COMPUTER        			BOLKMS	117   	BK117B2     	5626013	EU  										YAW CSAS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE					7238				POWER TEST 3A GYRO BAD.						1	G	7	2 	3U			NC	H13EU
1998070300763	19980703	00763	SW  	1998	7	3	HEEA0014845      	1	19980622	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										XMSN	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				TEMPERATURE NEEDLE FLUCTUATES WHEN VIBRATED.						1	G	7	2 	4U				H4SW
1998070300764	19980703	00764		1998	7	3	HEEA0014846      	4	19980622	G	3425	1113025	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				COURSE DIGITIZER OUT OF ALIGNMENT.						1	G	7	1 	4U				H4SW
1998070300898	19980703	00898		1998	7	3	HEEA0014847      	4	19980622	G	3454	066302440	SWITCH          			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT COMPASS	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911NC					7026				ADF/VOR SWITCH IS LOOSE AND NO ADF INDICATION.						1	G	7	2 	3U				H13EU
1998070300765	19980703	00765	SW  	1998	7	3	HEEA0014848      	1	19980622	G	6710	204060762103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										M/R CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				AFTER BEEPING TO FULL DECREASE RPM, RPM WILL GRADUALLY INCREASE.						1	G	7	2 	4U				H4SW
1998070300766	19980703	00766	SW  	1998	7	3	HEEA0014849      	1	19980622	G	6240	214074280103	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893P					33012				NO AUDIO ON PILOT'S SIDE.  RPM LIMIT DETECTOR MALFUNCTION.						1	G	7	2 	4U				H4SW
1998070300730	19980703	00730	NE  	1998	7	3	HEEA0014850      	1	19980622	G	2421	7655009005108	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										GENERATOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				GCU WILL NOT COME ON ABOVE 96 PERCENT.						1	G	7	2 	3U				H1NE
1998070300731	19980703	00731	EA  	1998	7	3	HEEA0014851      	2	19980622	G	7532	312320201	VALVE           			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					BLEED AIR SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BLEED VALVE NOT READING CORRECTLY.  TIME SINCE REPAIR 0:00.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998070300767	19980703	00767	SW  	1998	7	3	HEEA0014852      	1	19980622	G	2435	200SGL10081	COMMUTATOR      			BELL  	206   	206L1       	1182107	SW  										STARTER/GEN	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50182	475  				45242				EXCESSIVE CORROSION FOUND ON END BELL DURING FIRST 500 HOUR INSPECTION.						1	G	7	1 	3U				H2SW
1998070300768	19980703	00768	SW  	1998	7	3	HEEA0014853      	1	19980622	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				DROOP COMP WILL NOT ACTUATE.						1	G	7	1 	3U				H2SW
1998070300769	19980703	00769	GL  	1998	7	3	HEEA0014854      	2	19980622	G	7412	106149501	IGNITER BOX     			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE IGNITION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21240					45647				ENGINE DELAYED STARTS, WEAK IGNITERS.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998070300770	19980703	00770	SW  	1998	7	3	HEEA0014855      	1	19980622	G	6240	214074280105	DETECTOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				RPM WARNING DETECTOR WILL NOT MUTE.						2	G	7	2 	4U				H10SW
1998070300771	19980703	00771	SW  	1998	7	3	HEEA0014856      	1	19980622	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										FLIGHT CONTROL	BINDING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ACTUATOR BINDING IN-FLIGHT.						1	G	7	2 	4U				H4SW
1998070300772	19980703	00772	SW  	1998	7	3	HEEA0014857      	1	19980622	G	7712	212075037101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3208H					31304				TORQUE INDICATOR NEEDLE STICKS AND FLUCTUATES.						1	G	7	1 	4U				H4SW
1998070300773	19980703	00773	SW  	1998	7	3	HEEA0014858      	1	19980622	G	7712	212075037101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3208H					31304				TORQUE NEEDLE ON INDICATOR STICKS AND READS LOW.						1	G	7	1 	4U				H4SW
1998070300774	19980703	00774	SW  	1998	7	3	HEEA0014859      	1	19980622	G	7722	212075037105	INDICATOR       			BELL  	212   	212         	1181420	SW  										GAS PRODUCER	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3208H					31304				INDICATOR FOR GAS PRODUCER NEEDLE STICKS AND FLUCTUATES.						1	G	7	1 	4U				H4SW
1998070300775	19980703	00775	SW  	1998	7	3	HEEA0014860      	1	19980622	G	7714	206070266009	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT RPM	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	HCBXL					45219				RPM INDICATOR READS LOW AND NEEDLE STICKING.						1	G	7	1 	3U				H2SW
1998070300732	19980703	00732		1998	7	3	HEEA0014861      	4	19980622	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				VERTICAL GYRO SLOW TO DIRECT.						1	G	7	2 	3U				H1NE
1998070300776	19980703	00776		1998	7	3	HEEA0014862      	4	19980622	G	2210	214074300107	AFCS            			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				AFCS LIGHT WILL NOT COME ON.						2	G	7	2 	4U				H10SW
1998070300777	19980703	00777		1998	7	3	HEEA0014863      	4	19980622	G	2210	214074300107	AFCS            			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				AFCS WILL NOT COME ON.						2	G	7	2 	4U				H10SW
1998070300778	19980703	00778	SW  	1998	7	3	HEEA0014864      	1	19980622	G	2842	206063656001	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										FUEL QUANTITY	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	5745S					45491				FUEL QUANTITY TRANSMITTER WILL NOT TEST.						1	G	7	1 	3U				H2SW
1998070300779	19980703	00779		1998	7	3	HEEA0014865      	4	19980622	G	3422	2594484	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FLUX VALVE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				FLUX VALVE FREQUENCY BETWEEN F AND B AND F AND C IS HIGH ON TRANSMITTER.						1	G	7	2 	4U				H4SW
1998070300780	19980703	00780	SW  	1998	7	3	HEEA0014866      	1	19980622	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										FLIGHT CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893S					33022				ACTUATOR WILL NOT TEST IN LATERAL MODE.						1	G	7	2 	4U				H4SW
1998070300781	19980703	00781	SW  	1998	7	3	HEEA0014867      	1	19980622	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										FLIGHT CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				FORCE TURN RELEASES ON ITS OWN.						1	G	7	2 	4U				H4SW
1998070300733	19980703	00733	NE  	1998	7	3	HEEA0014868      	1	19980622	G	7330	PC820101	SIGNAL COND     			SKRSKY	S76   	S76A        	8143006	NE  										FUEL FLOW	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				SIGNAL COND INTERMITTENT.  FAST TOTALIZER INDICATION.						1	G	7	2 	3U				H1NE
1998070300782	19980703	00782	SW  	1998	7	3	HEEA0014869      	1	19980622	G	6710	214001423105	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				ACTUATOR INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300783	19980703	00783	SW  	1998	7	3	HEEA0014870      	1	19980622	G	2435	200SGL10081	COMMUTATOR      			BELL  	206   	206L1       	1182107	SW  										STARTER/GEN	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		491  								WHILE PERFORMING BRUSH INSPECTION, FOUND END BELL WAS EXCESSIVELY CORRODED.  BEAD BLASTED INNER PART OF END BELL AND FOU	ND EXCESSIVE PITTING AND CORROSION THROUGH SCREW HOLE AREA.					1	G	7	1 	3U				H2SW
1998070300784	19980703	00784	SW  	1998	7	3	HEEA0014871      	1	19980622	G	2434	230321827	ARMATURE        			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										ARMATURE WILL NOT FIT IN STATOR ASSY.  IT HITS FIELD SHOES (I.D. IS TOO SMALL.)						1	G	7	1 	3U			 	H2SW
1998070300785	19980703	00785		1998	7	3	HEEA0014872      	4	19980622	G	2211	4033089901	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										AUTO FLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				AUTOFLIGHT COMPUTER PRODUCES 5 ERRORS ON CDI WHEN CAP TO GPS OR VOR.						2	G	7	2 	4U				H10SW
1998070300786	19980703	00786	SW  	1998	7	3	HEEA0014873      	1	19980622	G	6320	406040056101	CENTER CASE     			BELL  	206   	206L4       	1182110	SW  										BOLT HOLES	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7077B					52037				MAIN ROTOR GEARBOX HAS CORROSION IN BOLT HOLES.						1	G	7	1 	3U			NC	H2SW
1998070300787	19980703	00787	SW  	1998	7	3	HEEA0014874      	1	19980622	G	2822	164A1681	FUEL BOOST PUMP 			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	PRESSURE LOSS   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				BOOST PUMP HAS INTERMITTENT PRESSURE LOSS.						1	G	7	2 	4U				H4SW
1998070300788	19980703	00788	SW  	1998	7	3	HEEA0014875      	1	19980622	G	2435	230321827	GENERATOR       			BELL  	206   	206L1       	1182107	SW  										START / GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										WHILE TESTING STARTER/GENERATOR ON MINIMUM SPEED, STARTER/GENERATOR HAD EXCESSIVE VOLTAGE DROP AND FIELD CURRENT RESISTA	NCE WAS VERY LOW.					1	G	7	1 	3U				H2SW
1998070300734	19980703	00734	NE  	1998	7	3	HEEA0014876      	1	19980622	G	2842	AT2062	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										FUEL TOTALIZER	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				FUEL TOTALIZER HAS ERRATIC READINGS.						1	G	7	2 	3U				H1NE
1998070300899	19980703	00899		1998	7	3	HEEA0014877      	4	19980622	G	2312	6223101011	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										VHF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				NR 2 VHF POSITION TRANSMITS; WILL NOT RECEIVE.						1	G	7	2 	3U				H3EU
1998070300735	19980703	00735		1998	7	3	HEEA0014878      	4	19980622	G	2211	4018369905	COMPUTER        			KING A														AUTOPILOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	500PH					BL29				DESCENDS BEYOND THE SELECTED ALTITUDE OVER CORRECTING IN BANK.  TIME SINCE REPAIR 308:00 HOURS.
1998070300736	19980703	00736		1998	7	3	HEEA0014879      	1	19980622	G	3710	1013810009	VALVE           			KING A														WING	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	500PH					BL29				VACUUM SYSTEM VALVE INOPERATIVE.
1998070300789	19980703	00789		1998	7	3	HEEA0014880      	4	19980622	G	3417	1201F2A1A1A	TRANSDUCER      			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				TRANSDUCER CAUSES FAIL 6 ON ADC.						2	G	7	2 	4U				H10SW
1998070300790	19980703	00790	SW  	1998	7	3	HEEA0014881      	1	19980622	G	6320	204040324005	SHAFT           			BELL  	412   	412         	1182202	SW  										TRANSMISSION	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				SHAFT CORROSION FRETTING ON GEAR MOUNTING SURFACE.						1	G	7	2 	4U				H4SW
1998070300791	19980703	00791	SW  	1998	7	3	HEEA0014882      	1	19980622	G	6320	204040324005	SHAFT           			BELL  	412   	412         	1182202	SW  										TRANSMISSION	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				SHAFT CORROSION FRETTING ON MOUNTING FACE.						1	G	7	2 	4U				H4SW
1998070300792	19980703	00792	SW  	1998	7	3	HEEA0014883      	1	19980622	G	6320	204040701101	BEVEL GEAR      			BELL  	412   	412         	1182202	SW  										TRANSMISSION	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				BEVEL GEAR CORROSION FRETTING ON MOUNTING FACE.						1	G	7	2 	4U				H4SW
1998070300737	19980703	00737	NE  	1998	7	3	HEEA0014884      	1	19980622	G	5350	7660002110102	RADOME          			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1545K					760047				HOLES ON RADOME WILL NOT LINE UP.						1	G	7	2 	3U			 	H1NE
1998070300900	19980703	00900	EU  	1998	7	3	HEEA0014885      	1	19980622	G	2841	1178913101	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										FUEL QUANTITY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	191BK					7146				FUEL QUANTITY INDICATOR CANNOT CALIBRATE.						1	G	7	2 	3U				H13EU
1998070300793	19980703	00793		1998	7	3	HEEA0014886      	4	19980622	G	2312	7001840913	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				TRANSCEIVER INDICATES 15 ON GROUND.  INCONSISTENT TEST OPERATION.						1	G	7	2 	4U				H4SW
1998070300794	19980703	00794	SW  	1998	7	3	HEEA0014887      	1	19980622	G	6240	214074280105	DETECTOR        			BELL  	214   	214ST       	1182106	SW  										COCKPIT M/R RPM	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				RPM WARNING AUDIO TOO LOUD.						2	G	7	2 	4U				H10SW
1998070300795	19980703	00795	SW  	1998	7	3	HEEA0014888      	1	19980622	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				STEP ACTUATOR TRIPS CIRCUIT BREAKER.						1	G	7	2 	4U				H4SW
1998070300796	19980703	00796	SW  	1998	7	3	HEEA0014889      	1	19980622	G	6710	214001423109	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				MOTOR DOESN'T FULLY EXTEND.						2	G	7	2 	4U				H10SW
1998070300797	19980703	00797	SW  	1998	7	3	HEEA0014890      	1	19980622	G	6320	206040190005	HOUSING         			BELL  	206   	206L1       	1182107	SW  										M/R GEARBOX	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MAIN ROTOR GEARBOX HELICOIL PULLED OUT AND HOUSING CRACKED.						1	G	7	1 	3U				H2SW
1998070300798	19980703	00798	SW  	1998	7	3	HEEA0014891      	1	19980622	G	6220	412030437103	CAP ASSEMBLY    			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				RUBBER TORN AND DETERIORATED ON M/R CAP ASSY.						1	G	7	2 	4U				H4SW
1998070300799	19980703	00799	SW  	1998	7	3	HEEA0014892      	1	19980622	G	6220	412030437103	CAP ASSEMBLY    			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				RUBBER DETERIORATED ON M/R CAP ASSY.						1	G	7	2 	4U				H4SW
1998070300738	19980703	00738		1998	7	3	HEEA0014893      	1	19980622	G	2824	1013640867	VALVE           			KING A														FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH					BL3				OUT CROSSFEED ON VALVE INOPERATIVE RIGHT TO LEFT.
1998070300739	19980703	00739	NE  	1998	7	3	HEEA0014894      	1	19980622	G	2400	8241631	POTENTIOMETER   			SKRSKY	S76   	S76A        	8143006	NE  										ELECTRICAL SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		349  								POTENTIONMETER CHECKS BAD IN NULL POSITION.						1	G	7	2 	3U				H1NE
1998070300800	19980703	00800	SW  	1998	7	3	HEEA0014895      	1	19980622	G	6730	206076062003	CYLINDER        			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2249Z	22916				45753				MAIN ROTOR SERVO CYLINDER HAS EXCESSIVE LEAKAGE.						1	G	7	1 	3U				H2SW
1998070300801	19980703	00801	SW  	1998	7	3	HEEA0014896      	1	19980622	G	2422	ASH5845	INVERTER        			BELL  	212   	212         	1181420	SW  										AC SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				CIRCUIT BREAKER TRIPS ON AC SYSTEM.						1	G	7	1 	4U				H4SW
1998070300901	19980703	00901		1998	7	3	HEEA0014897      	4	19980622	G	2340	AMS44	ICS             			BOLKMS	105   	BO105S      	5626006	EU  										DUAL CHANNEL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J					S826				ICS INOPERATIVE-PERFORMED TEST AND ALIGNMENT.						1	G	7	2 	3U				H3EU
1998070300802	19980703	00802	SW  	1998	7	3	HEEA0014898      	1	19980622	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				CONTROL UNIT HAS NO OUTPUT.						1	G	7	2 	4U				H4SW
1998070300902	19980703	00902		1998	7	3	HEEA0014899      	4	19980622	G	2350	066105571	MIC SWITCH      			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT AUDIO	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				MIC SWITCH INTERMITTENT.						1	G	7	1 	3U				H9EU
1998070300803	19980703	00803		1998	7	3	HEEA0014900      	4	19980622	G	2200	2593996333	TARSYN          			BELL  	412   	412         	1182202	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				PITCH AXIS KICKING IN ATT MODE ONLY.						1	G	7	2 	4U				H4SW
1998070300903	19980703	00903	EU  	1998	7	3	HEEA0014901      	1	19980622	G	6240	KDW021A	AUDIO LIGHT     			BOLKMS	105   	BO105S      	5626006	EU  										WARNING BOX	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81832					S828				WARNING BOX AUDIO LIGHT INTERMITTENT.						1	G	7	2 	3U				H3EU
1998070300804	19980703	00804		1998	7	3	HEEA0014902      	4	19980622	G	2200	4020936903	GYRO            			BELL  	412   	412         	1182202	SW  										TARSYN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				GYRO CAUSED PITCH AFCS TO PORPOISE.						1	G	7	2 	4U				H4SW
1998070300740	19980703	00740		1998	7	3	HEEA0014903      	1	19980622	G	2130	10138001313	VALVE           			KING A														CABIN PRESSURE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	39PH					BL3				VALVE WOULD NOT HOLD CABIN ALTITUDE WITH NR 2 FLOWPACK CUT OFF.
1998070300805	19980703	00805		1998	7	3	HEEA0014904      	4	19980622	G	3453	4530093	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										LORAN	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3108E					51498				BUTTONS ON LORAN RECEIVER INTERMITTENT, DIM WILL NOT DIM FOR BRIGHT.						1	G	7	1 	3U				H2SW
1998070300741	19980703	00741		1998	7	3	HEEA0014905      	4	19980622	G	3444	6223201001	RADIO ALTIMETER 			KING A														COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	39PH					BL3				ALTIMETER INTERMITTENT FLAG 2,000 FEET.
1998070300806	19980703	00806		1998	7	3	HEEA0014906      	4	19980622	G	2210	214074303115	AMPLIFIER ASSY  			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				PITCH WILL NOT ENGAGE ON AUTOFLIGHT AMPLIFIER ASSY.						2	G	7	2 	4U				H10SW
1998070300807	19980703	00807		1998	7	3	HEEA0014907      	4	19980622	G	2210	214074303115	AMPLIFIER ASSY  			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				PITCH WILL NOT ENGAGE ON AUTOFLIGHT AMPLIFIER ASSY.						2	G	7	2 	4U				H10SW
1998070300808	19980703	00808	SW  	1998	7	3	HEEA0014908      	1	19980622	G	2841	384178091	SELECTOR        			BELL  	412   	412         	1182202	SW  										FUEL QTY	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				FUEL QUANTITY SELECTOR CAPACITANCE READS HIGH OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998070300809	19980703	00809	SW  	1998	7	3	HEEA0014909      	1	19980622	G	2430	51509002R	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  										DC CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				CONTROL UNIT DOES NOT COME ON LINE.						1	G	7	1 	4U				H4SW
1998070300810	19980703	00810	SW  	1998	7	3	HEEA0014910      	1	19980622	G	2435	2CM272B1	CLUTCH          			BELL  	214   	214ST       	1182106	SW  										START/GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y	233  				28139				CLUTCH HAS EXCESSIVE END PLAY .018 INCH LIMITS ARE .004 INCH TO .010 INCH.						2	G	7	2 	4U				H10SW
1998070300811	19980703	00811	SW  	1998	7	3	HEEA0014911      	1	19980622	G	2842	214066212107	PROBE           			BELL  	214   	214ST       	1182106	SW  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				PROBE CAUSES FUEL FLUCTUATION.						2	G	7	2 	4U				H10SW
1998070300742	19980703	00742	EA  	1998	7	3	HEEA0014912      	2	19980622	G	7210	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COMBINING	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1082G	6610 				31109				COMBINING GEARBOX HAS METAL CONTAMINATION ON NR 2 SIDE.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998070300812	19980703	00812	SW  	1998	7	3	HEEA0014913      	1	19980622	G	2842	214066212107	PROBE           			BELL  	214   	214ST       	1182106	SW  										FUEL SYSTEM	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										INSTALLED PROBE CAUSING FUEL QUANTITY INDICATION OSCILLATION.  REMOVED AND INSTALLED PROBE, S/N 0116F.   FUEL INDICATION	 READS ZERO AND BELOW ON ANALOG NEEDLE.  TIME SINCE REPAIR 0:00.					2	G	7	2 	4U			 	H10SW
1998070300813	19980703	00813	GL  	1998	7	3	HEEA0014914      	2	19980622	G	7314	23068651	SEAL            			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					FUEL PUMP	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	447PH	111  				53114				FUEL PUMP SEAL DRAIN LEAKING.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998070300814	19980703	00814	GL  	1998	7	3	HEEA0014915      	2	19980622	G	7314	23069251	SEAL            			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					FUEL PUMP	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	447PH	310  				53114				FUEL PUMP SEAL DRAIN LEAKING.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998070300904	19980703	00904	EU  	1998	7	3	HEEA0014916      	1	19980622	G	3340	A490A	POWER SUPPLY    			SNIAS 	350   	AS350B2     	8680813	EU  										STROBE SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				POWER SUPPLY BURNS FLASH TUBES OUT EARLY.						1	G	7	1 	3U				H9EU
1998070300815	19980703	00815	SW  	1998	7	3	HEEA0014917      	1	19980622	G	7722	212075067113	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT ITT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				AT 1,000 DEGREE CELSIUS, NEEDLE INTERMITTENTLY FLUCTUATES AFTER UNIT WARMS UP ON INDICATOR OF COCKPIT RPM.						1	G	7	2 	4U				H4SW
1998070300743	19980703	00743		1998	7	3	HEEA0014918      	1	19980622	G	7714	8DJ131LAV1	INDICATOR       																	TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRIPLE TACHOMETER HAS EXCESSIVE NEEDLE SPLIT AND ROTOR INOPERATIVE.
1998070300816	19980703	00816	SW  	1998	7	3	HEEA0014919      	1	19980622	G	7712	212070160101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NR 1 AND NR 2 TORQUE NEEDLE STICKING AT 70 PERCENT.						1	G	7	1 	4U				H4SW
1998070300817	19980703	00817	SW  	1998	7	3	HEEA0014920      	1	19980622	G	7712	212075037101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NEEDLE STICKING ON TORQUE INDICATOR.						1	G	7	1 	4U				H4SW
1998070300818	19980703	00818	SW  	1998	7	3	HEEA0014921      	1	19980622	G	7160	209062214001	ACTUATOR        			BELL  	212   	212         	1181420	SW  										INTAKE	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INTAKE ACTUATOR MICROSWITCH STICKING.						1	G	7	1 	4U				H4SW
1998070300819	19980703	00819		1998	7	3	HEEA0014922      	4	19980622	G	3414	214175271103	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										AIRSPEED COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										AIRSPEED INDICATOR INOPERATIVE.						2	G	7	2 	4U				H10SW
1998070300744	19980703	00744		1998	7	3	HEEA0014923      	4	19980622	G	3457	0845000000	GPS             																	COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										GPS UNIT LOSES MEMORY AFTER BEING OFF AWHILE.
1998070300745	19980703	00745		1998	7	3	HEEA0014924      	4	19980622	G	3416	D120P2T	ENCODER         																	COCKPIT ALT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ENCODER HAS NO VALID OUTPUT.
1998070300746	19980703	00746		1998	7	3	HEEA0014926      	1	19980622	G	2844	124044	INDICATOR       																	FUEL PRESSURE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FUEL PRESSURE INDICATOR READS HIGH AND GLASS IS LOOSE.
1998070300820	19980703	00820	SW  	1998	7	3	HEEA0014927      	1	19980622	G	2437	209070264003	DUAL AMMETER    			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NR 1 AMMETER STICKS AT FULL RANGE AND NR 2 READS HIGH.						1	G	7	1 	3U				H2SW
1998070300821	19980703	00821		1998	7	3	HEEA0014928      	4	19980622	G	3413	212070239001	INDICATOR       			BELL  	212   	212         	1181420	SW  										RATE OF CLIMB	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RATE OF CLIMB INDICATOR HAS EXCESSIVE FRICTION ERROR.						1	G	7	1 	4U				H4SW
1998070300822	19980703	00822	SW  	1998	7	3	HEEA0014929      	1	19980622	G	7933	209070262101	INDICATOR       			BELL  	212   	212         	1181420	SW  										OIL TEMP COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PSI READS HIGH AND NEEDLE FLUCTUATES ON OIL TEMP COOLER INDICATOR.						1	G	7	1 	4U				H4SW
1998070300747	19980703	00747		1998	7	3	HEEA0014930      	1	19980622	G	2930	124043	INDICATOR       																	HYDRALIC SYS	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										HYDRAULIC SYSTEM'S TEMPERATURE NEEDLE STICKS IN INDICATOR.
1998070300823	19980703	00823	GL  	1998	7	3	HEEA0014931      	2	19980622	G	7320	23068651	HMU             			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	904  				53159				FUEL METERING VALVE RATE FAULT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998070300748	19980703	00748		1998	7	3	HEEA0014932      	4	19980622	G	2312	4000113000	TRANSCEIVER     																	VHF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03										VHF HAS NO POWER OUT, TRANSMITS ON WRONG FREQUENCY.
1998070300824	19980703	00824		1998	7	3	HEEA0014933      	4	19980622	G	2213	214074300105	SWITCH          			BELL  	214   	214ST       	1182106	SW  										SCAS	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										SCAS ENGAGE SWITCH INTERMITTENT.						2	G	7	2 	4U				H10SW
1998070300825	19980703	00825	GL  	1998	7	3	HEEA0014934      	2	19980622	G	7320	23068651	HMU             			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH	797  				53177				FADEC FAILURE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998070300826	19980703	00826	GL  	1998	7	3	HEEA0014935      	2	19980622	G	7321	23070254	CONTROLLER      			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH	529  				53177				DECELLERATION IN-FLIGHT.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998070300905	19980703	00905	EU  	1998	7	3	HEEA0014936      	1	19980622	G	7712	9580113720	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE TORQUE	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				TORQUE GAUGE FLUCTUATION.						1	G	7	1 	3U				H9EU
1998070300749	19980703	00749	NE  	1998	7	3	HEEA0014937      	2	19980622	G	7230	3017600	ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					POWER SECTION	STALLS          	E			HEEA	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	108X	16721				33115				COMPRESSOR STALLS.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998070300750	19980703	00750	NE  	1998	7	3	HEEA0014938      	2	19980622	G	7230	3017600	ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMPR  SECTION	STALLS          	E			HEEA	K				NONE                    				R			PARTIAL RPM/PWR LOSS      			IN	INSP/MAINT     	1			SW	03	3893P	13424				33012				COMPRESSOR STALLS.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998070300751	19980703	00751		1998	7	3	HEEA0014939      	4	19980622	G	3416	212070238007	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1547D					760077				ALTIMETER OFF 75 FEET HIGH.						1	G	7	2 	3U				H1NE
1998070300827	19980703	00827	SW  	1998	7	3	HEEA0014940      	1	19980622	G	2430	206075447007	REGULATOR       			BELL  	206   	206L3       	1182108	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				GENERATOR FAILED.  LIGHT BATTERY WILL NOT CHARGE.						1	G	7	1 	3U				H2SW
1998070300828	19980703	00828	SW  	1998	7	3	HEEA0014941      	1	19980622	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRANSMISSION OIL	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				TRANSMISSION TEMPERATURE NEEDLE FLUCTUATES WHEN VIBRATED.						1	G	7	2 	4U				H4SW
1998070300829	19980703	00829	SW  	1998	7	3	HEEA0014942      	1	19980622	G	6720	7001484	ACTUATOR        			BELL  	412   	412         	1182202	SW  										YAW CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				ACTUATOR FROZEN UP.  INOPERATIVE.						1	G	7	2 	4U				H4SW
1998070300830	19980703	00830	SW  	1998	7	3	HEEA0014943      	1	19980622	G	6240	206075681109	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										DUAL TACH	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007N					45184				ROTOR NEEDLE DROPS OFF TO ZERO PERCENT AT 35 PERCENT RPM.						1	G	7	1 	3U				H2SW
1998070300831	19980703	00831	SW  	1998	7	3	HEEA0014944      	1	19980622	G	7714	206075681105	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										DUAL TACH	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1072T					45385				BOUNCING TURBINE INDICATOR NEEDLE GOES TO ZERO.						1	G	7	1 	3U				H2SW
1998070300752	19980703	00752		1998	7	3	HEEA0014945      	4	19980622	G	2200	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D	1366 				760077				NR 1 ROLL AFCS CHANNEL CHATTERS.						1	G	7	2 	3U				H1NE
1998070300832	19980703	00832	SW  	1998	7	3	HEEA0014946      	1	19980622	G	7722	206375007103	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2761N					45277				TOT INDICATOR HAS NO INDICATION ON LIGHT-OFF.						1	G	7	1 	3U				H2SW
1998070300833	19980703	00833		1998	7	3	HEEA0014947      	4	19980622	G	2210	7000299901	CONTROLLER      			BELL  	412   	412         	1182202	SW  										AUTOFLIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				HP AND CPL SWITCHES WILL NOT ENGAGE ON CONTROLLER.						1	G	7	2 	4U				H4SW
1998070300834	19980703	00834	SW  	1998	7	3	HEEA0014948      	1	19980623	G	6420	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH	582  			A219	53147				FEATHERING BEARINGS WORN AND MOVING IN BORE OF YOKE ASSY.						1	G	7	1 	3U			O	H2SW
1998070300835	19980703	00835	SW  	1998	7	3	HEEA0014949      	1	19980623	G	6320	71X7023	SEAL            			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407PH					53003				LEAKING OIL FROM GEARBOX TO INSIDE BOOT.  ALSO FOUND SEALS P/N B56-40 LEAKING; BEARINGS P/N MS27641-4 AND -5, 2 EACH ROU	GH; BOOT P/N 406-312-106-101 DETERIORATED; AND SPINDLES ON TRUNNION ASSY P/N 206-011-726-005 WORN BEYOND LIMITS. REPLACE	D PARTS.				1	G	7	1 	3U			O	H2SW
1998070300836	19980703	00836	SW  	1998	7	3	HEEA0014950      	1	19980623	G	6420	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416				53058	53070				FEATHERING BEARING WORN.						1	G	7	1 	3U			O	H2SW
1998070300837	19980703	00837	SW  	1998	7	3	HEEA0014951      	1	19980623	G	6520	406040339105	BEARING         		406040320101	BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	573  			AFS922	53207				ROUGH TAIL ROTOR BEARINGS.  SERIAL NUMBERS REMOVED ARE M96-1203 AND M96-1395.						1	G	7	1 	3U			O	H2SW
1998070300838	19980703	00838	SW  	1998	7	3	HEEA0014952      	1	19980623	G	2435	206062200113	STARTER         			BELL  	407   	407         		SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				STARTER/GENERATOR WILL NOT CRANK; FOUND BRUSHES WORN BEYOND 1/4 LIFE AND FAN COVER RIVET WASHER CAME LOOSE AND JAMMED AR	MATURE. REPAIRED STARTER GENERATOR.					1	G	7	1 	3U			O	H2SW
1998070300906	19980703	00906		1998	7	3	HEEA0014953      	4	19980623	G	3120	B1894522282A	CLOCK           			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	STOPPED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				CLOCK STOPPED KEEPING TIME.						1	G	7	1 	3U				H9EU
1998070300907	19980703	00907	EU  	1998	7	3	HEEA0014957      	1	19980623	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				BOOST PUMP BLOWS FUSE WHEN SWITCH IS TURNED ON.						1	G	7	1 	3U				H9EU
1998070300908	19980703	00908	EU  	1998	7	3	HEEA0014958      	1	19980623	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				TACHOMETER NR NEEDLE STICKS AT ZERO, THEN ABRUPTLY JUMPS TO NORMAL INDICATION.						1	G	7	1 	3U				H9EU
1998070300909	19980703	00909	EU  	1998	7	3	HEEA0014959      	1	19980623	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				GAUGE READS 410 NR AT FLAT PITCH AND 430 IN FLIGHT.  SOMETIMES PEGS OUT ON HIGH SIDE.						1	G	7	1 	3U				H9EU
1998070300910	19980703	00910	EU  	1998	7	3	HEEA0014960      	1	19980623	G	6220	350A31177000	PIN             			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR BLADE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				MAIN ROTOR PIN CORRODED AND PITTED.						1	G	7	1 	3U				H9EU
1998070300911	19980703	00911	EU  	1998	7	3	HEEA0014961      	1	19980623	G	2435	150SG122Q	GENERATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4034Q	380  				2918				GENERATOR HAS DEAD SPOT, INTERMITTENTLY INOPERATIVE--BRUSHES HAVE 1/8 LIFE LEFT.						1	G	7	1 	3U				H9EU
1998070300912	19980703	00912	EU  	1998	7	3	HEEA0014962      	1	19980623	G	2435	150SG122Q	STARTER         			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				GENERATOR WOULD NOT MOTOR ENGINE.						1	G	7	1 	3U				H9EU
1998070300913	19980703	00913	EU  	1998	7	3	HEEA0014963      	1	19980623	G	2435	150SG122Q	STARTER         			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	1221 				2820				STARTER/GENERATOR WOULD NOT MOTOR ENGINE; NO SPIN.						1	G	7	1 	3U				H9EU
1998070300914	19980703	00914	EU  	1998	7	3	HEEA0014971      	1	19980623	G	5610	04011650990	WINDOW          			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				I			FLT. ATTITUDE INST.       			IN	INSP/MAINT     	1			SW	03	60951					2771				BLACK PLASTIC TRACK ON WINDOW IS CRACKED.						1	G	7	1 	3U				H9EU
1998070300915	19980703	00915	EU  	1998	7	3	HEEA0014972      	1	19980623	G	7921	1184961	COOLER          			SNIAS 	350   	AS350B2     	8680813	EU  										OIL SYSTEM	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				OIL SYSTEM COOLER MAKING METAL.						1	G	7	1 	3U				H9EU
1998070300839	19980703	00839	SW  	1998	7	3	HEEA0014973      	1	19980624	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1472 				53060				STARTER BRUSHES WORN.						1	G	7	1 	3U			O	H2SW
1998070300840	19980703	00840	SW  	1998	7	3	HEEA0014975      	1	19980624	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				PRESSURE GAUGE DIAL FACE ROTATES FREELY.						1	G	7	1 	3U			O	H2SW
1998070300841	19980703	00841	SW  	1998	7	3	HEEA0014976      	1	19980624	G	6220	407010150103	FRAHM ASSEMBLY  			BELL  	407   	407         		SW  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH	804  				53177				INTERNAL RUBBER UNBONDED ON FRAHM ASSY.						1	G	7	1 	3U			O	H2SW
1998070300842	19980703	00842	SW  	1998	7	3	HEEA0014977      	1	19980624	G	7910	206061505115	TANK            			BELL  	407   	407         		SW  										ENG OIL TANK	STRIPPED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH	804  				53177				UPON REMOVAL OF OUTLET FITTING P/N AN837-12D FROM ENGINE OIL TANK FOR THE FIRST TIME, FOUND THREADS IN TANK WERE STRIPPE	D.					1	G	7	1 	3U			O	H2SW
1998070300843	19980703	00843	SW  	1998	7	3	HEEA0014978      	1	19980624	G	6310	406040500123	FREEWHEEL UNIT  			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH	589  				53147				LEAKING AT FORWARD SEAL.						1	G	7	1 	3U			O	H2SW
1998070300844	19980703	00844		1998	7	3	HEEA0014979      	4	19980624	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         		SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				CLOCK WILL NOT MAINTAIN TIME WHEN AIRCRAFT BATTERY IS TURNED OFF.						1	G	7	1 	3U			O	H2SW
1998070300845	19980703	00845	SW  	1998	7	3	HEEA0014980      	1	19980624	G	6520	406040453101	SEAL            			BELL  	407   	407         		SW  										TAIL ROTOR G/BOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	437PH					53072				TAIL ROTOR GEARBOX INPUT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW
1998070300846	19980703	00846	SW  	1998	7	3	HEEA0014981      	1	19980624	G	6320	407040006107	TRANSMISSION    			BELL  	407   	407         		SW  										MAIN ROTOR G/BOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	1863 				53070				MAIN ROTOR TRANSMISSION MAKING METAL.						1	G	7	1 	3U			O	H2SW
1998070300847	19980703	00847	SW  	1998	7	3	HEEA0014982      	1	19980624	G	6322	206061432116	BLOWER HOUSING  			BELL  	407   	407         		SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				WORKING RIVETS ON END CAPS AND FLANGE MOUNTS.						1	G	7	1 	3U			O	H2SW
1998070300848	19980703	00848	SW  	1998	7	3	HEEA0014984      	1	19980624	G	3110	407375038101	GUARD           			BELL  	407   	407         		SW  										INSTRUMENT PANEL	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				START/DISENGAGE GUARD BROKEN OFF						1	G	7	1 	3U			O	H2SW
1998070300849	19980703	00849	SW  	1998	7	3	HEEA0014985      	1	19980624	G	2842	407375016101	TRANSMITTER     			BELL  	407   	407         		SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				FUEL QUANTITY GAUGE WOULD GO BLANK (NUMBERS AND BAR GRAPH).						1	G	7	1 	3U			O	H2SW
1998070300850	19980703	00850	SW  	1998	7	3	HEEA0014988      	1	19980624	G	6220	222310504101	BEARING         			BELL  	230   	230         	1182149	SW  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				METAL SLIDER ON BEARING PAD CAME UNBONDED ON LEFT AFT AND RIGHT AFT SIDE OF NODAL BEAM.  SERIAL NUMBERS REMOVED ARE 0042	 AND BR146.					1	G	7	2 	3U			NC	H9SW
1998070300851	19980703	00851	SW  	1998	7	3	HEEA0014989      	1	19980624	G	5311	206032308103S	FRAME           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SHORT ON EDGE DISTANCE ON FLANGE AREA OF PERIMETER.  (1 EACH).						1	G	7	1 	3U			 	H2SW
1998070300852	19980703	00852	SW  	1998	7	3	HEEA0014990      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR DRIVE COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300853	19980703	00853	SW  	1998	7	3	HEEA0014991      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         	       	SW  										T/R DRIVE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	457PH					53147				PER AD 97-24-17 (PART A), TAIL ROTOR DRIVE BOLT TORQUE BELOW MINIMUM.						1	G	7	1 	3U			O	H2SW
1998070300854	19980703	00854	SW  	1998	7	3	HEEA0014992      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				TAIL ROTOR DRIVE COUPLING CRACKED AND RUSTY.						1	G	7	1 	3U			O	H2SW
1998070300855	19980703	00855	SW  	1998	7	3	HEEA0014993      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	55   				53070				FOUND NR 2 DISC COUPLING CRACKED DURING COMPLIANCE OF AD 97-24-17, PARTS A, B, AND E.						1	G	7	1 	3U			O	H2SW
1998070300856	19980703	00856	SW  	1998	7	3	HEEA0014994      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				TAIL ROTOR DRIVE COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300857	19980703	00857	SW  	1998	7	3	HEEA0014995      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR DRIVE COUPLING PITTED AND CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300858	19980703	00858	SW  	1998	7	3	HEEA0014996      	1	19980624	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR DRIVE COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300859	19980703	00859	SW  	1998	7	3	HEEA0014997      	1	19980624	G	3212	8226003	FUSIBLE PLUG    			BELL  	407   	407         		SW  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	510PH					53209				FLOAT PLUG LEAKING.						1	G	7	1 	3U			O	H2SW
1998070300860	19980703	00860	SW  	1998	7	3	HEEA0014998      	1	19980624	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										OIL SYSTEM	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				OIL SYSTEM COOLER HAS METAL CONTAMINATION.						1	G	7	1 	3U			O	H2SW
1998070300861	19980703	00861	SW  	1998	7	3	HEEA0014999      	1	19980624	G	6310	406040500123	SEAL            			BELL  	407   	407         		SW  										F/WHEEL M/R	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	427PH	1394 				53059				MAIN ROTOR FREEWHEEL FRONT SEAL LEAKING.						1	G	7	1 	3U			O	H2SW
1998070300862	19980703	00862	SW  	1998	7	3	HEEA0015001      	1	19980624	G	6300	406010417101	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MAIN ROTOR BEARING HAS PLAY.  SERIAL NUMBERS REMOVED ARE A1566 AND A1598.						1	G	7	1 	3U			O	H2SW
1998070300863	19980703	00863	SW  	1998	7	3	HEEA0015002      	1	19980624	G	6420	407012101107	BEARING         			BELL  	407   	407         		SW  										T/R HUB	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	1749 				53070				TAIL ROTOR FEATHERING BEARING INNER LINER COMING OUT.						1	G	7	1 	3U			O	H2SW
1998070300864	19980703	00864	SW  	1998	7	3	HEEA0015003      	1	19980624	G	6330	406010425107	LEVER ASSEMBLY  			BELL  	407   	407         		SW  										MAIN  ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	1907 				53003				MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS.  SERIAL NUMBERS REMOVED ARE A1721 AND A1702.						1	G	7	1 	3U			O	H2SW
1998070300865	19980703	00865	SW  	1998	7	3	HEEA0015004      	1	19980624	G	6330	406010425107	LEVER ASSEMBLY  			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1315 				53114				MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS.  SERIAL NUMBERS REMOVED ARE A1962 AND A1967.						1	G	7	1 	3U			O	H2SW
1998070300866	19980703	00866	SW  	1998	7	3	HEEA0015005      	1	19980624	G	6330	406010425107	LEVER ASSEMBLY  			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	581  				53207				MAIN ROTOR LEVER ASSY HAS WORN BUSHINGS.  SERIAL NUMBERS REMOVED ARE A2111 AND A2119.						1	G	7	1 	3U			O	H2SW
1998070300867	19980703	00867	SW  	1998	7	3	HEEA0015006      	1	19980624	G	3310	SM20ACD300A21	RELAY           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				LIGHTING RELAY WOULD NOT FULLY CLOSE.						1	G	7	1 	3U			O	H2SW
1998070300868	19980703	00868	SW  	1998	7	3	HEEA0015007      	1	19980624	G	6720	230312001101	LINK            			BELL  	230   	230         	1182149	SW  										T/R	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				T/R P/C LINKS BEARINGS WORN.						1	G	7	2 	3U			NC	H9SW
1998070300869	19980703	00869	SW  	1998	7	3	HEEA0015013      	1	19980624	G	3212	206050247131	FLOAT COVER ASSY			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FLOAT COVER WORN.						1	G	7	1 	3U			O	H2SW
1998070300870	19980703	00870	SW  	1998	7	3	HEEA0015014      	1	19980624	G	3212	206050247131	FLOAT COVER ASSY			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				FLOAT COVER WORN.						1	G	7	1 	3U			O	H2SW
1998070300871	19980703	00871	SW  	1998	7	3	HEEA0015015      	1	19980624	G	3212	206050247131	FLOAT COVER ASSY			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW
1998070300872	19980703	00872	SW  	1998	7	3	HEEA0015016      	1	19980624	G	6220	406010428109	HUB BUSHING     			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	2783 				53003				MAIN ROTOR HUB BUSHINGS WORN.						1	G	7	1 	3U			O	H2SW
1998070300873	19980703	00873	SW  	1998	7	3	HEEA0015017      	1	19980624	G	6321	406010429101	PIN             			BELL  	407   	407         		SW  										M/ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MAIN ROTOR BRAKE BOLT HOLES ELONGATED.						1	G	7	1 	3U			O	H2SW
1998070300874	19980703	00874	SW  	1998	7	3	HEEA0015018      	1	19980624	G	6321	406010429101	PIN             			BELL  	407   	407         		SW  										M/ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				MAIN ROTOR BRAKE PIN WORN.						1	G	7	1 	3U			O	H2SW
1998070300875	19980703	00875	SW  	1998	7	3	HEEA0015019      	1	19980624	G	6230	406010428109	HUB BUSHING     			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1315 				53114				HUB BUSHINGS WORN.						1	G	7	1 	3U			O	H2SW
1998070300876	19980703	00876	SW  	1998	7	3	HEEA0015020      	1	19980624	G	7714	407375008103	INDICATOR       			BELL  	407   	407         		SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	407PH					53003				DUAL TACHOMETER FAILED SELF-TEST, NEEDLE SPLITS, WILL NOT ZERO.						1	G	7	1 	3U			O	H2SW
1998070300877	19980703	00877	SW  	1998	7	3	HEEA0015021      	1	19980624	G	6321	206340301103	ROTOR BRAKE     			BELL  	407   	407         		SW  										M/ROTOR	MISSING PARTS   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH	1394 				53059				MAIN ROTOR BRAKE PADS MISSING.						1	G	7	1 	3U			O	H2SW
1998070300878	19980703	00878	SW  	1998	7	3	HEEA0015022      	1	19980624	G	6321	206340301103	ROTOR BRAKE     			BELL  	407   	407         		SW  										M/ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	427PH	677  				53059				MAIN ROTOR BRAKE IS OIL SOAKED AND LEAKING.						1	G	7	1 	3U			O	H2SW
1998070300879	19980703	00879	SW  	1998	7	3	HEEA0015023      	1	19980624	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         		SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				ENGINE EXHAUST STACK IS CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300880	19980703	00880	SW  	1998	7	3	HEEA0015024      	1	19980625	G	6410	206016201131	BLADE           			BELL  	206   	206L3       	1182108	SW  										T/ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										TAIL ROTOR BLADE TOO LIGHT--- CANNOT BALANCE.						1	G	7	1 	3U			 	H2SW
1998070300881	19980703	00881	SW  	1998	7	3	HEEA0015025      	1	19980626	G	6420	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										T/ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH				53057	53059				TAIL ROTOR BEARING EXCESSIVELY WORN.						1	G	7	1 	3U			O	H2SW
1998070300882	19980703	00882	SW  	1998	7	3	HEEA0015026      	1	19980626	G	6420	NAS5784B	RETAINER        		407012101105	BELL  	407   	407         	       	SW  										T/ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	427PH				53057	53059				TAIL ROTOR RETAINER WOULD NOT FIT ON NUT P/N NAS577B4A.						1	G	7	1 	3U			O	H2SW
1998070300883	19980703	00883	SW  	1998	7	3	HEEA0015027      	1	19980626	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				FOUND CRACKED DISC IN COUPLING BETWEEN HORIZONTAL STABILIZER AND T/R GEARBOX.						1	G	7	1 	3U			O	H2SW
1998070300884	19980703	00884	SW  	1998	7	3	HEEA0015028      	1	19980626	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				TAIL ROTOR COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300885	19980703	00885	SW  	1998	7	3	HEEA0015029      	1	19980626	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				TAIL ROTOR COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300886	19980703	00886	SW  	1998	7	3	HEEA0015030      	1	19980626	G	6510	406040340101	COUPLING        			BELL  	407   	407         		SW  										T/ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998070300887	19980703	00887	SW  	1998	7	3	HEEA0015031      	1	19980626	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	141MA	1017 				53016				ENGINE OIL COOLER LEAKING.						1	G	7	1 	3U			O	H2SW
1998070300888	19980703	00888	SW  	1998	7	3	HEEA0015032      	1	19980626	G	2844	407375007103	TRANSMITTER     			BELL  	407   	407         		SW  										FUEL PRESS	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	1144 				53070				AMMETER GOES FROM MAX TO ZERO AND BACK REPEATEDLY WITH NO GENERATOR LIGHT OR CHANGE IN VOLTMETER.						1	G	7	1 	3U			O	H2SW
1998070300889	19980703	00889	SW  	1998	7	3	HEEA0015033      	1	19980626	G	7922	724155	REGULATOR       			BELL  	407   	407         		SW  										OIL TEMP	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				ENGINE OIL TEMPERATURE EXCEEDED 120 DEGREES.						1	G	7	1 	3U			O	H2SW
1998070300890	19980703	00890	SW  	1998	7	3	HEEA0015034      	1	19980626	G	7714	407375002103	INDICATOR       			BELL  	407   	407         		SW  										ENGINE NG	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				ENGINE NG LCD DISPLAY ERRATIC.						1	G	7	1 	3U			O	H2SW
1998070300891	19980703	00891	GL  	1998	7	3	HEEA0015035      	2	19980626	G	7320	VSB628CP	FADEC HORN      			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					COCKPIT	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				FADEC HORN WEAK AND INAUDIBLE WITH ENGINE RUNNING.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998070300892	19980703	00892	SW  	1998	7	3	HEEA0015036      	1	19980626	G	6220	407010150103	FRAHM ASSEMBLY  			BELL  	407   	407         		SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				M/R VIBRATION.						1	G	7	1 	3U			O	H2SW
1998070300893	19980703	00893	SW  	1998	7	3	HEEA0015037      	1	19980626	G	6340	407375017101	TRANSMITTER     			BELL  	407   	407         		SW  										M/ROTOR	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				ERRATIC M/R INDICATIONS.						1	G	7	1 	3U			O	H2SW
1998070300916	19980703	00916	EU  	1998	7	3	HEEA0015038      	1	19980626	G	6520	350A33200403	SPIDER          			SNIAS 	350   	AS350B2     	8680813	EU  										T/ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				TAIL ROTOR BEARING, SEAL AND GUIDE WORN.						1	G	7	1 	3U				H9EU
1998070300917	19980703	00917	EU  	1998	7	3	HEEA0015039      	1	19980626	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				ENGINE RPM NEEDLE STICKS THEN JUMPS UP TO NORMAL INDICATION.						1	G	7	1 	3U				H9EU
1998070300918	19980703	00918	EU  	1998	7	3	HEEA0015040      	1	19980626	G	7714	614764021	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				ENGINE TACHOMETER STICKS AT ABOUT ZERO 300 NR.						1	G	7	1 	3U				H9EU
1998070300919	19980703	00919	EU  	1998	7	3	HEEA0015041      	1	19980626	G	3340	31031	LIGHT           			SNIAS 	350   	AS350B2     	8680813	EU  										POSITION LIGHT	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										MISMANUFACTURED.  LIGHT SOCKET MISMADE.						1	G	7	1 	3U			 	H9EU
1998070300920	19980703	00920	EU  	1998	7	3	HEEA0015042      	1	19980626	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										BOOST PUMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	312  				2771				BOOST PUMP WILL NOT WORK.						1	G	7	1 	3U				H9EU
1998070300753	19980703	00753	GL  	1998	7	3	HEEA0015043      	2	19980626	G	7260	23063413	GEAR            		6894171     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	PITTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8197X				CAG38881	S808	CAE835215			RECEIVING INSPECTION REVEALED:  PITS BEYOND SERVICEABLE LIMITS ON A/O SEP. GEAR TEETH. INSTALLED A NEW A/O SEP. GEAR.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998071400445	19980714	00445	SW  	1998	7	14	HEEA0015044      	1	19980629	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				STEP ACTUATOR OPERATED ONCE THEN FAILED TO OPERATE AFTER THAT.						1	G	7	2 	4U				H4SW
1998071400446	19980714	00446		1998	7	14	HEEA0015046      	4	19980629	G	3422	103002201	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	4282Z					51499				FLAG WILL NOT PULL.  POWER FAILURE FLAG ADJUSTMENT IS SET TOO HIGH (24.1 VOLTS).  POWER FAILURE FLAG SHOULD BE SET AT 22	.5 VOLTS.					1	G	7	1 	3U			 	H2SW
1998071400421	19980714	00421	NE  	1998	7	14	HEEA0015047      	1	19980630	G	6730	7630103902102	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										SERVO SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				INSTALLED ACTUATOR ON NR 2 SIDE.  ACTUATOR RUNS CONSTANTLY.  CONNECTED TO NR 1 SIDE.  STILL RUNS CONSTANTLY.						1	G	7	2 	3U				H1NE
1998071400447	19980714	00447		1998	7	14	HEEA0015048      	4	19980630	G	2312	069102404	TRANSCEIVER     			BELL  	206   	206L4       	1182110	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	CFVEF					52071				TRANSCEIVER WILL NOT POWER UP.						1	G	7	1 	3U			NC	H2SW
1998071400422	19980714	00422	NE  	1998	7	14	HEEA0015049      	1	19980630	G	5630	7620710009192	WINDOW          			SKRSKY	S76   	S76A        	8143006	NE  										DOOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	3122H					760233				WINDOW SCREW HOLE WILL NOT LINE UP WITH SCREW HOLE ON WINDOW FRAME.						1	G	7	2 	3U			 	H1NE
1998071400507	19980714	00507	EU  	1998	7	14	HEEA0015050      	1	19980630	G	6320	4638304001	SUN GEAR        		4638001004  	BOLKMS	105   	BO105S      	5626006	EU  										TRANSMISSION	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB	426  			229	S756				TRANSMISSION CAME IN DUE TO METAL IN OIL.  REPLACED SUN GEAR.						1	G	7	2 	3U				H3EU
1998071400508	19980714	00508	EU  	1998	7	14	HEEA0015051      	1	19980630	G	6230	4638205005	ROTOR MAST      		4638001004  	BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB	7192 			229	S756				CORROSION IN BORES BEYOND LIMITS.  REPLACED MAST ASSY.						1	G	7	2 	3U				H3EU
1998071400448	19980714	00448	SW  	1998	7	14	HEEA0015052      	1	19980630	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X	10659				33113				HOLES IN THE OUTBOARD LEADING EDGE ABRASION STRIP.						1	G	7	2 	4U				H4SW
1998071400449	19980714	00449	SW  	1998	7	14	HEEA0015053      	1	19980630	G	6210	412015300109	EROSION SHIELD  			BELL  	412   	412         	1182202	SW  										M/R BLADE	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X	9141 				33113				SEPARATION ON THE EROSION SHIELD ON THE M/R BLADE INBOARD END.						1	G	7	2 	4U				H4SW
1998071400450	19980714	00450	SW  	1998	7	14	HEEA0015057      	1	19980630	G	5330	206033172105	PANEL           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	513EH					45421				NOT ENOUGH METAL PROTRUDING BEYOND FUSELAGE TRANSITION ON PANEL.						1	G	7	1 	3U			 	H2SW
1998071400509	19980714	00509	EU  	1998	7	14	HEEA0015058      	1	19980630	G	6320	4619210902	BEVEL GEAR SET  		4619002003  	BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B				340	S673				SPALLING OF M/R GEARBOX GEAR TEETH.  SCRAPPED PARTS AND REPLACED WITH NEW PARTS.						1	G	7	2 	3U				H3EU
1998071400451	19980714	00451		1998	7	14	HEEA0015059      	4	19980630	G	3421	5040017901	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				GYRO ROTATES 360 DEGREES DURING FLIGHT.  REPLACED BEARINGS, BALANCED, BENCH CHECK GOOD.						1	G	7	1 	3U				H2SW
1998071400423	19980714	00423	NE  	1998	7	14	HEEA0015060      	1	19980630	G	7714	7645001076101	TACHOMETER      			SKRSKY	S76   	S76A        	8143006	NE  										N1 TACH	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				TACHOMETER NEEDLE READS 15 PERCENT LOWER THAN READ OUT.						1	G	7	2 	3U				H1NE
1998071400510	19980714	00510	EU  	1998	7	14	HEEA0015061      	1	19980630	G	6320	DK040	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										XMSN LUBE TORQUE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				TRANSDUCER PEGGING OUT, FUNCTION CHECK BAD, OUT OF TOLERANCE ON INCREASING PRESSURE.						1	G	7	2 	3U				H3EU
1998071400511	19980714	00511	EU  	1998	7	14	HEEA0015062      	1	19980630	G	7714	DL40438	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				NR 2 NEEDLE FLUCTUATES, FUNCTION CHECK BAD, ALSO FOUND NEEDLES TO HAVE SEVERE SPLIT BETWEEN THEM.						1	G	7	2 	3U				H3EU
1998071400452	19980714	00452	SW  	1998	7	14	HEEA0015063      	1	19980630	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				TRIPLE TACHOMETER'S NR 2 NEEDLE INDICATES 5 PERCENT HIGH, UNIT FUNCTION CHECK BAD, ALSO FOUND NR 2 NEEDLE TO HAVE EXCESS	IVE FRICTION.					1	G	7	2 	4U				H4SW
1998071400453	19980714	00453		1998	7	14	HEEA0015065      	4	19980630	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	33008					36004				VHF'S TRANSMIT AND RECEIVE GARBLED.						1	G	7	2 	4U				H4SW
1998071400454	19980714	00454		1998	7	14	HEEA0015066      	4	19980630	G	3455	066104701	RECEIVER        			BELL  	212   	212         	1181420	SW  										ADF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				ADF RECEIVER WILL NOT COME ON WHEN POWER IS APPLIED.						1	G	7	1 	4U				H4SW
1998071400424	19980714	00424		1998	7	14	HEEA0015067      	4	19980630	G	3451	066106901	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				DME INDICATOR WILL NOT COME UP ON LINE.  PERFORMED PRELIMINARY INSPECTION.  FOUND FRONT PLATE AND COVER HAD STRIPPED SCR	EW HOLES.  REPLACED FRONT PLATE AND COVER.  BEGAN BENCH CHECK AND FOUND UNIT DOES NOT TURN OFF.					1	G	7	2 	3U				H1NE
1998071400455	19980714	00455		1998	7	14	HEEA0015068      	4	19980630	G	3457	13824120234	RECEIVER        			BELL  	206   	206B3       	1181506	SW  										COCKPIT GPS	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2753F					2729				GPS RECEIVER INTERMITTENTLY LOCKING ON TO SATELLITES.						1	G	7	1 	3U				H2SW
1998071400456	19980714	00456		1998	7	14	HEEA0015069      	4	19980630	G	3457	13824120234	RECEIVER        			BELL  	206   	206L3       	1182108	SW  										COCKPIT GPS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4282Z					51499				WARNING COMES UP, BATTERY LOW AND GPS UNRELIABLE.						1	G	7	1 	3U				H2SW
1998071400425	19980714	00425		1998	7	14	HEEA0015070      	4	19980630	G	3421	40016702511	GYRO            																	COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FOUND INDICATOR HAD NO ROLL FUNCTION.
1998071400457	19980714	00457		1998	7	14	HEEA0015071      	4	19980630	G	3460	5205160006	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22608					33075				TO-FROM FLAG WILL NOT PULL.						1	G	7	2 	4U				H4SW
1998071400458	19980714	00458	SW  	1998	7	14	HEEA0015072      	1	19980630	G	6321	206340301103	BRAKE           			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH	552  				53207				MAIN ROTOR BRAKE WEAK AND WORN.						1	G	7	1 	3U			O	H2SW
1998071400459	19980714	00459	SW  	1998	7	14	HEEA0015073      	1	19980701	G	5313	206031314083	LONGERON        			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2245Y					45751				WHEN LONGERON IS INSTALLED, NO EDGE DISTANCE ON FASTENER HOLES--LONGERON IS TOO WIDE.						1	G	7	1 	3U			 	H2SW
1998071400460	19980714	00460	SW  	1998	7	14	HEEA0015074      	1	19980701	G	7120	209062105001	BEARING         			BELL  	212   	212         	1181420	SW  										ENGINE MOUNT	SCARRED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEARING ON ENGINE MOUNT IS SCARRED.						1	G	7	1 	4U				H4SW
1998071400426	19980714	00426	GL  	1998	7	14	HEEA0015075      	2	19980701	G	7313	23031866	NOZZLE          		23033185    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	BLISTERED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5012V				CAT70486	45200	CAE860248			DURING MACHINING NOTED:  BLISTERED COATING BEYOND SERVICEABLE LIMITS ON NR 2 NOZZLE, NR 2 TIP PATH.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998071400427	19980714	00427	GL  	1998	7	14	HEEA0015076      	2	19980701	G	7313	23055430	NOZZLE          		23033185    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	5012V				CAT70486	45200	CAE860248			RECEIVING INSPECTION REVEALED:  COATING LIFTING ON NR 2 NOZZLE 2ND STAGE TIP PATH.						1	G	7	1 	3U	3	U	 	H2SW    	E1GL
1998071400428	19980714	00428	GL  	1998	7	14	HEEA0015077      	2	19980701	G	7313	23055430	NOZZLE          		23033185    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	FLAKING         	E			HEEA	K				NONE                    				J			WARNING INDICATION        			IN	INSP/MAINT     	1			SW	03	5745S				CAT70404	45491	CAE860697			ENGINE REMOVED DUE TO OIL OVERTEMP.  UPON INSPECTION OF TURBINE PARTS NOTED:  COATING FLAKING ON NR 2 NOZZLE, NR 1 AND N	R 2 TIP PATHS.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998071400461	19980714	00461	SW  	1998	7	14	HEEA0015078      	1	19980701	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										DROOP COMP	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107PH					2789				DROOP COMP ACTUATOR STICKS.						1	G	7	1 	3U				H2SW
1998071400512	19980714	00512	EU  	1998	7	14	HEEA0015079      	1	19980701	G	6720	10531782	BELLCRANK       			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				BELLCRANK ASSY HAS WORN BEARING BORE HOLE.						1	G	7	2 	3U				H3EU
1998071400429	19980714	00429		1998	7	14	HEEA0015080      	4	19980701	G	3421	1113034	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				COPILOT'S ATTITUDE INDICATOR PRECESSING.						1	G	7	2 	3U				H1NE
1998071400462	19980714	00462	SW  	1998	7	14	HEEA0015081      	1	19980701	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				DROOP COMP WILL NOT MOVE.						1	G	7	1 	3U				H2SW
1998071400463	19980714	00463	SW  	1998	7	14	HEEA0015082      	1	19980701	G	6320	204040324005	SHAFT           			BELL  	412   	412         	1182202	SW  										TRANSMISSION	FRETTING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				MAIN ROTOR TRANSMISSION SHAFT HAS FRETTING ON FLANGE.						1	G	7	2 	4U				H4SW
1998071400464	19980714	00464	SW  	1998	7	14	HEEA0015083      	1	19980701	G	6320	204040701101	BEVEL GEAR      			BELL  	412   	412         	1182202	SW  										TRANSMISSION	FRETTING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				MAIN ROTOR TRANSMISSION BEVEL GEAR HAS FRETTING ON MATING SURFACE.						1	G	7	2 	4U				H4SW
1998071400465	19980714	00465	SW  	1998	7	14	HEEA0015084      	1	19980701	G	6320	206040530001	CASE ASSY       			BELL  	206   	206L3       	1182108	SW  										M/R GEARBOX	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6161A					51611				MAIN ROTOR GEARBOX  HAS WORN INPUT QUILL LINER.						1	G	7	1 	3U				H2SW
1998071400466	19980714	00466		1998	7	14	HEEA0015085      	4	19980701	G	3417	214175421101	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT AIR DATA	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				AIR DATA COMPUTER WILL NOT SHOW PANEL CHECKS.						2	G	7	2 	4U				H10SW
1998071400430	19980714	00430		1998	7	14	HEEA0015086      	4	19980701	G	3421	125780	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				ADI INDICATOR PRECESSES IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998071400467	19980714	00467		1998	7	14	HEEA0015087      	4	19980701	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				COCKPIT ATTITUDE INDICATOR TRIPS CIRCUIT BREAKER.						1	G	7	2 	4U				H4SW
1998071400468	19980714	00468		1998	7	14	HEEA0015088      	4	19980701	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				HSI COMPASS CARD STICKS.						1	G	7	2 	4U				H4SW
1998071400513	19980714	00513	EU  	1998	7	14	HEEA0015089      	1	19980701	G	7714	DL40438	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4294R					S860				TRIPLE TACHOMETER'S NR 1 NEEDLE STICKS AT 98 PERCENT AND ALL OTHER NEEDLES EXHIBIT  OPERATION THROUGHOUT SCALE.						1	G	7	2 	3U				H3EU
1998071400469	19980714	00469	SW  	1998	7	14	HEEA0015090      	1	19980701	G	2841	214175257103	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										FUEL QUANTITY	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				FUEL QUANTITY INDICATOR DIGITS REPORTED INOPERATIVE.						2	G	7	2 	4U				H10SW
1998071400431	19980714	00431		1998	7	14	HEEA0015091      	4	19980701	G	2312	6221879001	TRANSCEIVER     			BEECH 	200   	200BEECH    	1152920	CE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	789DS					BB478				VHF WILL NOT TRANSMIT.						1	L	7	2 	4T				A24CE
1998071400432	19980714	00432		1998	7	14	HEEA0015092      	4	19980701	G	2312	6221879001	TRANSCEIVER     			BEECH 	200   	200BEECH    	1152920	CE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	789DS					BB478				COCKPIT VHF WEAK ON TRANSMIT.						1	L	7	2 	4T				A24CE
1998071400470	19980714	00470	SW  	1998	7	14	HEEA0015093      	1	19980701	G	2842	206364601101	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										FUEL QTY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				FUEL QUANTITY HAS INACCURATE READINGS.						1	G	7	1 	3U				H2SW
1998071400471	19980714	00471		1998	7	14	HEEA0015094      	4	19980701	G	2312	064101900	TRANSCEIVER     			BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39122					3312				TRANSCEIVER'S MODULATION DISTORTED AT 85 PERCENT MODULATION.						1	G	7	1 	3U				H2SW
1998071400514	19980714	00514	EU  	1998	7	14	HEEA0015095      	1	19980701	G	7930	6607190A	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  										OIL PRESSURE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070					S145				TRANSMISSION PRESSURE LIGHT WILL NOT GO OUT.						1	G	7	2 	3U				H3EU
1998071400472	19980714	00472	SW  	1998	7	14	HEEA0015096      	1	19980701	G	2823	212076015001	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				VALVE IN FUEL SYSTEM IS LEAKING.						1	G	7	2 	4U				H4SW
1998071400473	19980714	00473	SW  	1998	7	14	HEEA0015097      	1	19980701	G	6240	206076373001	TACH GEN        			BELL  	206   	206L3       	1182108	SW  										RPM WARNING	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8588X					51486				RPM WARNING HAS INTERMITTENT OPERATION.						1	G	7	1 	3U				H2SW
1998071400474	19980714	00474	SW  	1998	7	14	HEEA0015098      	1	19980701	G	5522	206023119151	SKIN            			BELL  	206   	206L1       	1182107	SW  										HORIZ STAB	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2245Y					45751				EXCESSIVE DENTS ON OUTER STAB SKIN.						1	G	7	1 	3U				H2SW
1998071400475	19980714	00475	SW  	1998	7	14	HEEA0015099      	1	19980701	G	6320	212040190101	ADAPTER         			BELL  	412   	412         	1182202	SW  										SEAL RIDE	PITTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				MAIN ROTOR  GEARBOX ADAPTER HAS PITTING ON SEAL RIDE.						1	G	7	2 	4U				H4SW
1998071400515	19980714	00515		1998	7	14	HEEA0015100      	4	19980701	G	3453	4530103	LORAN           			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721MB					S752				MEMORY ON LORAN IS NOT HOLDING.						1	G	7	2 	3U				H3EU
1998071400476	19980714	00476		1998	7	14	HEEA0015101      	4	19980701	G	3453	4530103	LORAN           			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2770Y					45291				LORAN WILL NOT FUNCTION IN NAV MODE.						1	G	7	1 	3U				H2SW
1998071400433	19980714	00433		1998	7	14	HEEA0015102      	4	19980701	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K	7036 				760047				AFCS ACTUATOR HAS NOISY OPERATION.						1	G	7	2 	3U				H1NE
1998071400477	19980714	00477		1998	7	14	HEEA0015103      	4	19980701	G	2340	A3016W	SWITCH          			BELL  	412   	412         	1182202	SW  										INTERPHONE BOX	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				INTERPHONE SELECTOR SWITCH HARD TO TURN AND DISPLAY PANEL WORN.						1	G	7	2 	4U				H4SW
1998071400478	19980714	00478		1998	7	14	HEEA0015104      	4	19980701	G	3422	2891ESR	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2772A					45311				DIRECTIONAL GYRO PRECESSES EXCESSIVELY IN UNSLAVE MODE.						1	G	7	1 	3U				H2SW
1998071400516	19980714	00516	EU  	1998	7	14	HEEA0015105      	1	19980701	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT EGT/TIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4294R					S860				EGT/TIT INDICATOR READS LOW AT 800 DEGREES.						1	G	7	2 	3U				H3EU
1998071400517	19980714	00517	EU  	1998	7	14	HEEA0015106      	1	19980701	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT EGT/TIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911EB					S812				EGT/TIT INDICATOR READS HIGH AND FLUCTUATES AT 900 DEGREES WHEN VIBRATING.						1	G	7	2 	3U				H3EU
1998071400434	19980714	00434		1998	7	14	HEEA0015107      	4	19980701	G	3425	1258103	SELECTOR        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				COURSE SELECTOR KNOB ROTATES CONTINUOUSLY WITH POWER ON.						1	G	7	2 	3U				H1NE
1998071400479	19980714	00479	SW  	1998	7	14	HEEA0015108      	1	19980701	G	6340	214074280107	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				NR 2 ENGINE RPM LIMIT OUT LIGHT REMAINS ON WITH ENGINE ON LINE.						1	G	7	2 	4U				H4SW
1998071400480	19980714	00480	SW  	1998	7	14	HEEA0015109      	1	19980701	G	6710	214001970111	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				ACTUATOR WILL NOT MONITOR TEST AND WILL NOT WORK WITH OTHER ACTUATORS.						2	G	7	2 	4U				H10SW
1998071400481	19980714	00481		1998	7	14	HEEA0015110      	4	19980701	G	3424	214075244001	RATE GYRO       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				AVI TURN NEEDLE IS INOPERATIVE ON GYRO.						1	G	7	2 	4U				H4SW
1998071400518	19980714	00518	EU  	1998	7	14	HEEA0015111      	1	19980701	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT EGT/TIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										EGT/TIT INDICATOR INTERMITTENTLY FLUCTUATES WHEN VIBRATED AT 800 DEGREES.						1	G	7	2 	3U				H3EU
1998071400435	19980714	00435		1998	7	14	HEEA0015112      	1	19980701	G	2435	230481031	ARMATURE        																	START/GEN	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STARTER/GENERATOR CAUSING EXCESSIVE BRUSH ARCHING.
1998071400436	19980714	00436		1998	7	14	HEEA0015113      	1	19980701	G	2435	23046311	FIELD ASSEMBLY  																	START/GEN	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FIELD ASSY IS CAUSING STARTER GENERATOR TO RUN VERY HOT AND WOULD NOT PASS TEST.
1998071400437	19980714	00437		1998	7	14	HEEA0015114      	1	19980701	G	2435	230481031	ARMATURE        																	START/GEN	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STARTER/GENERATOR CAUSING EXCESSIVE BRUSH ARCHING.
1998071400519	19980714	00519	EU  	1998	7	14	HEEA0015115      	1	19980701	G	7923	209072433101	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										OIL SYSTEM	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				VALVE STICKS IN OPEN POSITION.						1	G	7	2 	3U				H3EU
1998071400438	19980714	00438	NE  	1998	7	14	HEEA0015116      	1	19980701	G	2421	7655009005108	CONTROLLER      			SKRSKY	S76   	S76A        	8143006	NE  										AC GENERATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				GENERATOR WOULD NOT COME ON LINE.						1	G	7	2 	3U				H1NE
1998071400439	19980714	00439	NE  	1998	7	14	HEEA0015117      	1	19980701	G	3230	4608	PRIORITY VALVE  			SKRSKY	S76   	S76A        	8143006	NE  										MLG	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				LANDING GEAR TAKES TOO LONG TO EXTEND AND RETRACT.						1	G	7	2 	3U				H1NE
1998071400482	19980714	00482	SW  	1998	7	14	HEEA0015118      	1	19980701	G	7332	BSE20630G	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										FUEL PRESS	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2759U					45272				FUEL PRESSURE READING STUCK AT 8 PSI.						1	G	7	1 	3U				H2SW
1998071400520	19980714	00520	EU  	1998	7	14	HEEA0015119      	1	19980701	G	7332	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESS	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	133AE					S800				FUEL PRESSURE TRANSMITTER HAS FLUCTUATION.						1	G	7	2 	3U				H3EU
1998071400483	19980714	00483	SW  	1998	7	14	HEEA0015120      	1	19980701	G	2430	214175132103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806				CG45530	28140				RELAY IS BURNED AND PITTED.						2	G	7	2 	4U				H10SW
1998071400521	19980714	00521	EU  	1998	7	14	HEEA0015121      	1	19980701	G	7332	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESS IND	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM					S683				FUEL PRESSURE INDICATOR FLUCTUATES THROUGHOUT SCALE.						1	G	7	2 	3U				H3EU
1998071400484	19980714	00484	SW  	1998	7	14	HEEA0015122      	1	19980701	G	2430	214175131103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806				CG61548	28140				RELAY IS BURNED AND PITTED.						2	G	7	2 	4U				H10SW
1998071400440	19980714	00440		1998	7	14	HEEA0015123      	4	19980701	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				AFCS WILL NOT PULL ADI FLAG.  TIME SINCE REPAIR 8:05 HOURS.						1	G	7	2 	3U				H1NE
1998071400485	19980714	00485	SW  	1998	7	14	HEEA0015124      	1	19980701	G	5530	206020113127	FIN             			BELL  	206   	206B3       	1181506	SW  										TAILBOOM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181Y					3772				VERTICAL FIN CORRODED AND SEPARATED NEAR OUTBOARD MOUNTING HOLES.  SCREWS SHEARED OFF IN UPPER CAP AREA.						1	G	7	1 	3U				H2SW
1998071400441	19980714	00441		1998	7	14	HEEA0015125      	4	19980701	G	2312	4000106010	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										VHF COMM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				CANNOT LOAD FREQUENCIES INTO VHF COMM MEMORY.						1	G	7	2 	3U				H1NE
1998071400486	19980714	00486		1998	7	14	HEEA0015126      	4	19980701	G	3414	214074152101	TRANSPONDER     			BELL  	214   	214ST       	1182106	SW  										AIRSPEED	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				AIRSPEED TRANSPONDER CAUSING FAIL 5 CODE.						2	G	7	2 	4U				H10SW
1998071400487	19980714	00487	SW  	1998	7	14	HEEA0015127      	1	19980701	G	2430	214175171103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	PITTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806				CE80478	28140				RELAY HAS PITTED CONTACTS.						2	G	7	2 	4U				H10SW
1998071400488	19980714	00488	NE  	1998	7	14	HEEA0015128      	1	19980701	G	6710	204060762103	ACTUATOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				DROOP COMP INTERNAL STOPS SEEMS BROKEN.  MOTOR INTERMITTENT.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998071400442	19980714	00442	NE  	1998	7	14	HEEA0015129      	2	19980701	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING BOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	21498	14672				36003				COMBINING BOX IS TRANSFERRING OIL TO NR 1 ENGINE.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998071400489	19980714	00489		1998	7	14	HEEA0015130      	4	19980701	G	2210	2593996333	TARSYN          			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				TARSYN FAILED PITCH AND ROLL TEST SST BENCH.						1	G	7	2 	4U				H4SW
1998071400443	19980714	00443		1998	7	14	HEEA0015131      	4	19980701	G	3414	8502CS20LW	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				AIR SPEED INDICATOR DOES NOT INDICATE, AND ZERO STOP MISSING.						1	G	7	2 	3U				H1NE
1998071400490	19980714	00490	SW  	1998	7	14	HEEA0015132      	1	19980701	G	7722	206375007101	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										TOT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				TOT INDICATOR INTERMITTENTLY STICKS AT ZERO.						1	G	7	1 	3U				H2SW
1998071400444	19980714	00444		1998	7	14	HEEA0015133      	4	19980701	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				VERTICAL GYRO PRECESSING 30 DEGREES ON FLIGHT.						1	G	7	2 	3U				H1NE
1998071400491	19980714	00491		1998	7	14	HEEA0015134      	4	19980701	G	2312	064101900	TRANSCEIVER     		KY196       	BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22743					3624				TRANSCEIVER BREAKS SQUELCH HIGH END.						1	G	7	1 	3U				H2SW
1998071400522	19980714	00522		1998	7	14	HEEA0015135      	4	19980701	G	2312	064101900	TRANSCEIVER     		KY196       	BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4294R					S860				TRANSCEIVER WILL NOT STORE FREQUENCIES.						1	G	7	2 	3U				H3EU
1998071400492	19980714	00492		1998	7	14	HEEA0015136      	4	19980701	G	3453	066104100	LORAN           			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				LORAN HAS NO RELAY AND CODING PULSES BAD.						1	G	7	2 	4U				H4SW
1998071400493	19980714	00493		1998	7	14	HEEA0015137      	4	19980701	G	3416	066104800	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				ALTIMETER INDICATOR INDICATED 150 FEET AT 1,000 AND 2,000 FEET.  INOPERATIVE.						1	G	7	1 	4U				H4SW
1998071400494	19980714	00494	SW  	1998	7	14	HEEA0015138      	1	19980701	G	2841	214175257105	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				FUEL QUANTITY INDICATOR'S RIGHT NEEDLE STICKS.						2	G	7	2 	4U				H10SW
1998071400495	19980714	00495	SW  	1998	7	14	HEEA0015139      	1	19980701	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805	102  				28141				STARTER/GENERATOR BURNT.						2	G	7	2 	4U				H10SW
1998071400496	19980714	00496	SW  	1998	7	14	HEEA0015140      	1	19980701	G	2424	206075447007	REGULATOR       			BELL  	206   	206L3       	1182108	SW  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Y					51609				REGULATOR INOPERATIVE, FALLS OFF LINE.						1	G	7	1 	3U				H2SW
1998071400497	19980714	00497	SW  	1998	7	14	HEEA0015141      	1	19980701	G	7712	214175428101	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				INDICATOR CANNOT MATCH TORQUES ON ENGINE.						2	G	7	2 	4U				H10SW
1998071400498	19980714	00498	SW  	1998	7	14	HEEA0015142      	1	19980701	G	6320	412040111103	SEAL            			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1202T					33112				MAIN ROTOR SEAL IS LEAKING.						1	G	7	2 	4U				H4SW
1998071400499	19980714	00499	SW  	1998	7	14	HEEA0015143      	1	19980701	G	6320	412040111103	SEAL            			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3893N					33010				MAIN ROTOR SEAL IS LEAKING.						1	G	7	2 	4U				H4SW
1998071400500	19980714	00500	SW  	1998	7	14	HEEA0015144      	1	19980701	G	6320	412040111103	SEAL            			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2261D					33076				MAIN ROTOR SEAL IS LEAKING.						1	G	7	2 	4U				H4SW
1998071400501	19980714	00501	SW  	1998	7	14	HEEA0015145      	1	19980701	G	2842	391046199	PROBE           			BELL  	212   	212         	1181420	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				FUEL SYSTEM PROBE DID NOT PASS CAPACITANCE TEST.						1	G	7	1 	4U				H4SW
1998071400502	19980714	00502	SW  	1998	7	14	HEEA0015146      	1	19980701	G	6320	412040111103	SEAL            			BELL  	412   	412         	1182202	SW  										M/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3893S					33022				MAIN ROTOR SEAL IS LEAKING.						1	G	7	2 	4U				H4SW
1998071400523	19980714	00523		1998	7	14	HEEA0015147      	4	19980701	G	3422	206075606103	GYRO            			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				DIRECTIONAL GYRO PRECESSES EXCESSIVELY.						1	G	7	2 	3U				H3EU
1998071400524	19980714	00524		1998	7	14	HEEA0015148      	4	19980701	G	3422	40205773	GYRO            			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE					7238				DIRECTIONAL GYRO IS INOPERATIVE.						1	G	7	2 	3U			NC	H13EU
1998071400503	19980714	00503	SW  	1998	7	14	HEEA0015149      	1	19980701	G	7714	212075037101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				AIRSPEED INDICATOR NEEDLE STUCK AT ZERO.						1	G	7	1 	4U				H4SW
1998071400525	19980714	00525	EU  	1998	7	14	HEEA0015150      	1	19980701	G	2424	51565000R	REGULATOR       			BOLKMS	105   	BO105S      	5626006	EU  										AC SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911DD					S830				VOLTAGE REGULATOR WILL NOT ADJUST.						1	G	7	2 	3U				H3EU
1998071400526	19980714	00526		1998	7	14	HEEA0015151      	4	19980701	G	3422	5208130004	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911EB					S812				COURSE POINTER ON INDICATOR IS INOPERATIVE.						1	G	7	2 	3U				H3EU
1998071400504	19980714	00504	SW  	1998	7	14	HEEA0015152      	1	19980701	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										NR 1 GENERATOR	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				KICKS OFF LINE AND POSITIVE TACK DISTORTED.						1	G	7	2 	4U				H4SW
1998071400505	19980714	00505		1998	7	14	HEEA0015153      	4	19980701	G	3413	VM4506LP	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				VSI INDICATOR INDICATES HIGH OUT OF TOLERANCE, AND NEEDLE STICKS.						1	G	7	1 	3U				H2SW
1998071400506	19980714	00506	GL  	1998	7	14	HEEA0015154      	2	19980701	G	7421	099192204	IGNITER         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014Y					45219				VSI RELEASE RELAY DOES NOT WORK, AND DIODE IS BURNED.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998073100645	19980731	00645	GL  	1998	7	31	HEEA0015155      	2	19980713	G	7250	6886407	WHEEL           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	50293	556  			CAT40303	S677	CAE835254			ENGINE REMOVED DUE TO COMPRESSOR OVERHAUL.   TURBINE DISASSEMBLED DUE TO LOW POWER ON TEST CELL.  UPON INSPECTION OF TUR	BINE PARTS NOTED:   MEASURED .006 INCH OVER BLUEPRINT SPECS (6.190-6.191) ON NR 1 WHEEL OUTSIDE DIAMETER.  INSTALLED A N	EW NR 1 WHEEL.				1	G	7	2 	3U	3	U	 	H3EU    	E4CE
1998073100648	19980731	00648	SW  	1998	7	31	HEEA0015156      	1	19980713	G	5330	212030099071S	SKIN            			BELL  	212   	212         	1181420	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SKIN MISMANUFACTURED.  TOOLING HOLES AT OPENING FOR AFT POSITION LIGHT ARE DRILLED TO .4375 INCH.  THESE HOLES ARE SUPPO	SED TO ALIGN TO EXISTING .1875 INCH HOLES WHERE 10-32 NUT PLATES ARE INSTALLED.					1	G	7	1 	4U			 	H4SW
1998073100649	19980731	00649	SW  	1998	7	31	HEEA0015157      	1	19980713	G	5330	212030099071S	SKIN            			BELL  	212   	212         	1181420	SW  										FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										DEEP SANDING MARKS ON FORWARD LOWER RIGHT SIDE OF SKIN.						1	G	7	1 	4U			 	H4SW
1998073100650	19980731	00650	SW  	1998	7	31	HEEA0015158      	1	19980713	G	6240	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				ROTOR NEEDLE INOPERATIVE.  TIME SINCE REPAIR 23:25 HOURS.						1	G	7	2 	4U				H4SW
1998073100651	19980731	00651	SW  	1998	7	31	HEEA0015159      	1	19980713	G	6322	406040339105	BEARING         		406040320101	BELL  	407   	407         		SW  										T/R DRIVE	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH				AFS973	53228				ROUGH BEARINGS.  SERIAL NUMBERS REMOVED ARE G97-1595 AND G97-1570.  REPLACEMENT PART SERIAL NUMBERS ARE E98-2393 AND E98	-2415.					1	G	7	1 	3U			O	H2SW
1998073100652	19980731	00652	SW  	1998	7	31	HEEA0015161      	1	19980713	G	6420	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA	1482 			53025	53016				ROTOR BEARINGS WORN.						1	G	7	1 	3U			O	H2SW
1998073100653	19980731	00653	SW  	1998	7	31	HEEA0015162      	1	19980713	G	6210	407015001117	BLADE           			BELL  	407   	407         		SW  										MAIN ROTOR	VOID            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH	774  				53142				VOID AT STATION 144 ON UPPER SURFACE.						1	G	7	1 	3U			O	H2SW
1998073100654	19980731	00654	SW  	1998	7	31	HEEA0015163      	1	19980713	G	6410	212010750105	BLADE           		212011701101	BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008	58   			A355	36004				TIP CAP IS SEPARATION ON END SECTION.						1	G	7	2 	4U				H4SW
1998073100700	19980731	00700	EU  	1998	7	31	HEEA0015164      	1	19980713	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH CONT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				PITCH CONTROL ROD WORN BEYOND LIMITS.  SERIAL NUMBERS REMOVED ARE S1317 AND S11117.						1	G	7	1 	3U				H9EU
1998073100701	19980731	00701	EU  	1998	7	31	HEEA0015165      	1	19980713	G	7160	350A54108421	SEAL            			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE INTAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				SEAL WORN.  PARTS SCRAPPED LOCALLY.						1	G	7	1 	3U				H9EU
1998073100702	19980731	00702	EU  	1998	7	31	HEEA0015166      	1	19980713	G	3340	356H2802	POWER SUPPLY    			SNIAS 	350   	AS350B2     	8680813	EU  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				STROBE POWER SUPPLY BLOWS FIRE.						1	G	7	1 	3U				H9EU
1998073100703	19980731	00703	EU  	1998	7	31	HEEA0015167      	1	19980713	G	6510	350A34021006	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R DRIVE SHAFT	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R	4311 				2862				FORWARD BEARING CAME LOOSE.						1	G	7	1 	3U				H9EU
1998073100704	19980731	00704	EU  	1998	7	31	HEEA0015168      	1	19980713	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH CONT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				PITCH CONTROL ROD,  WEAR IN BEARING.						1	G	7	1 	3U				H9EU
1998073100705	19980731	00705	EU  	1998	7	31	HEEA0015169      	1	19980713	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				PITCH CONTROL ROD HEAVILY WORN.						1	G	7	1 	3U				H9EU
1998073100706	19980731	00706	EU  	1998	7	31	HEEA0015170      	1	19980713	G	6420	350A33200405	SPIDER          			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				TAIL ROTOR SPIDER WORN.						1	G	7	1 	3U				H9EU
1998073100707	19980731	00707	EU  	1998	7	31	HEEA0015171      	1	19980713	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH CONT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				PITCH CONTROL ROD BEARINGS WORN.						1	G	7	1 	3U				H9EU
1998073100708	19980731	00708	EU  	1998	7	31	HEEA0015172      	1	19980713	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH CONT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				PITCH CONTROL ROD HAS WORN BEARINGS.						1	G	7	1 	3U				H9EU
1998073100655	19980731	00655	SW  	1998	7	31	HEEA0015173      	1	19980713	G	6320	407375005101	INDICATOR       			BELL  	407   	407         		SW  										XMSN OIL TEMP	FLUCTUATING     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				TRANS OIL PRESSURE INDICATOR FLUCTUATES DOWN TO ZERO AND BACK UP.						1	G	7	1 	3U			O	H2SW
1998073100656	19980731	00656		1998	7	31	HEEA0015174      	4	19980713	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				CLOCK WILL NOT STAY READABLE.						1	G	7	1 	3U			O	H2SW
1998073100657	19980731	00657	SW  	1998	7	31	HEEA0015175      	1	19980713	G	7714	407375008101	INDICATOR       			BELL  	407   	407         		SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				ROTOR TACHOMETER FAILED.						1	G	7	1 	3U			O	H2SW
1998073100658	19980731	00658	SW  	1998	7	31	HEEA0015176      	1	19980713	G	6420	J123131	MOUNT           			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				RUBBER ON MOUNT COMING LOOSE.						1	G	7	1 	3U			O	H2SW
1998073100659	19980731	00659	SW  	1998	7	31	HEEA0015177      	1	19980713	G	6320	214040806003	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				PRESSURE SWITCH STICKS IN OPEN POSITION.						1	G	7	1 	3U			O	H2SW
1998073100660	19980731	00660	SW  	1998	7	31	HEEA0015178      	1	19980713	G	6300	407010201101	BEAM            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH	804  				53177				BEAM ASSY CHAFED BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW
1998073100662	19980731	00662	SW  	1998	7	31	HEEA0015180      	1	19980713	G	6410	406312100101	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH	582  				53147				TAIL ROTOR BEARING WORN.						1	G	7	1 	3U			O	H2SW
1998073100663	19980731	00663	SW  	1998	7	31	HEEA0015182      	1	19980713	G	7921	406360500101	OIL COOLER      			BELL  	407   	407         		SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	467PH					53142				OIL COOLER CORE LEAKING.						1	G	7	1 	3U			O	H2SW
1998073100664	19980731	00664	SW  	1998	7	31	HEEA0015183      	1	19980713	G	1100	23081018	I D PLATE       			BELL  	407   	407         		SW  										STARTER	MISSING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH	585  				53188				STARTER/GENERATOR REMOVED FOR 300 HOUR INSPECTION.  FOUND THERE WAS NO BELL HELICOPTER PART NUMBER 206-062-200-112 ON TH	E I.D. PLATE.  AS PER BELL, PART NUMBER 23081-018 ALONE IS NOT AUTHORIZED FOR THEIR 407 AIRCRAFT.					1	G	7	1 	3U			O	H2SW
1998073100665	19980731	00665	SW  	1998	7	31	HEEA0015184      	1	19980713	G	6720	206011728001	TRUNNION        			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1375 				53114				TRUNNION WORN, ALSO SEAL P/N B56-40-2 LEAKING AND BOOT P/N 406-312-106-101 DETERIORATED DUE TO OIL SATURATION.						1	G	7	1 	3U			O	H2SW
1998073100666	19980731	00666	SW  	1998	7	31	HEEA0015185      	1	19980713	G	7920	70037A090000	LINE            			BELL  	407   	407         		SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				MAIN OIL LINE TO ENGINE LEAKING.						1	G	7	1 	3U			O	H2SW
1998073100667	19980731	00667	SW  	1998	7	31	HEEA0015186      	1	19980713	G	6510	406040340101	PACK DISK       			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				CRACKED TAIL ROTOR DRIVE SHAFT COUPLING PACK DISK.						1	G	7	1 	3U			O	H2SW
1998073100668	19980731	00668	SW  	1998	7	31	HEEA0015187      	1	19980713	G	6500	406040339111	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				TAIL ROTOR BEARINGS ROUGH.						1	G	7	1 	3U			O	H2SW
1998073100669	19980731	00669	SW  	1998	7	31	HEEA0015188      	1	19980713	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998073100670	19980731	00670	SW  	1998	7	31	HEEA0015189      	1	19980713	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										M/R DRIVE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				MGT INDICATOR ERRATIC, THEN WENT TO ZERO DEGREES.						1	G	7	1 	3U			O	H2SW
1998073100671	19980731	00671	SW  	1998	7	31	HEEA0015190      	1	19980713	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998073100672	19980731	00672	SW  	1998	7	31	HEEA0015191      	1	19980713	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998073100673	19980731	00673	SW  	1998	7	31	HEEA0015193      	1	19980717	G	5330	206033100019	SKIN            			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SKIN TOO SHORT.						1	G	7	1 	3U			 	H2SW
1998073100674	19980731	00674	SW  	1998	7	31	HEEA0015194      	1	19980717	G	5313	206031314083S	CHANNEL         			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										CHANNEL NOT FORMED CORRECTLY.						1	G	7	1 	3U			 	H2SW
1998073100675	19980731	00675	SW  	1998	7	31	HEEA0015195      	1	19980717	G	6510	204040603011	COUPLING        			BELL  	212   	212         	1181420	SW  										TAIL ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										COUPLING MISMANUFACTURED - SLOT ON END OPPOSITE TEETH NOT MACHINED.						1	G	7	1 	4U			 	H4SW
1998073100676	19980731	00676	SW  	1998	7	31	HEEA0015198      	1	19980717	G	3340	407362005103	SWITCH          			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	405PH					53207				LOW LEVEL LIGHT ON SWITCH STAYS ON.						1	G	7	1 	3U			O	H2SW
1998073100709	19980731	00709	EU  	1998	7	31	HEEA0015200      	1	19980717	G	6720	350A33214300	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONT ROD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				SPHERICAL BEARING HAS WEAR IN IT.						1	G	7	1 	3U				H9EU
1998073100710	19980731	00710	EU  	1998	7	31	HEEA0015201      	1	19980717	G	6520	4619211003	COVER           		4619003003  	BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	818SH				1361	S753				CORROSION IN THREADED BOLT HOLES.  REPLACED WITH SERVICEABLE COVER.						1	G	7	2 	3U				H3EU
1998073100677	19980731	00677	SW  	1998	7	31	HEEA0015202      	1	19980721	G	6710	206001053005	BEARING         			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										WHEN INSTALLING THESE NEW BEARINGS, NOTICED THE BEARINGS INNER RACE SEEMED TIGHT AND THE PROTECTIVE COATING DID NOT APPE	AR THE SAME AS THE OTHER BEARINGS.  TEFLON COATING SEEMS TO FLAKE OFF WHEN THE BEARING RACE IS MOVED.   (DEFECTIVE LOT N	R 110375).				1	G	7	1 	3U			 	H2SW
1998073100678	19980731	00678	SW  	1998	7	31	HEEA0015203      	1	19980721	G	5320	206031307103S	ANGLE           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	513EH					45421				ANGLE MISMANUFACTURED.  THERE IS NO EDGE DISTANCE AT THE TOP PART OF THE ANGLE AT THE LOWER INBOARD RIVET.						1	G	7	1 	3U			 	H2SW
1998073100679	19980731	00679	SW  	1998	7	31	HEEA0015204      	1	19980721	G	5320	206031403005P	FITTING         			BELL  	206   	206L4       	1182110	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										FITTING MISMANUFACTURED.  FORWARD CORNERS OF FITTING WHERE FITTING CONTACTS FORWARD TAILBOOM BULKHEAD FRAME.  THE AFT EN	D OF THE FITTING IS RADIUSED AND IS NOT REQUIRED TO BE.					1	G	7	1 	3U			NC	H2SW
1998073100680	19980731	00680	SW  	1998	7	31	HEEA0015205      	1	19980721	G	5347	214031277129S	TRACK           			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	825H					28137				LOWER OUTBOARD FLANGE TOO NARROW TO PICK UP FASTENERS.						2	G	7	2 	4U			 	H10SW
1998073100681	19980731	00681	SW  	1998	7	31	HEEA0015206      	1	19980721	G	5320	214031703333	STIFFENER       			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	825H					28137				STIFFENER MISMANUFACTURED.   PART DOESN'T FIT THE POSITION ON THE AIRFRAME.						2	G	7	2 	4U			 	H10SW
1998073100682	19980731	00682	SW  	1998	7	31	HEEA0015207      	1	19980721	G	6700	206001343001S	ELBOW           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	5745S					45491				WHEN LOCATING LOWER HOLE TO MOUNT TO TUBE ASSY, FOUND EDGE DISTANCE TO BE .3125 INCH TO CENTER OF HOLE AND REQUIRED .437	5 INCH.					1	G	7	1 	3U			 	H2SW
1998073100683	19980731	00683	SW  	1998	7	31	HEEA0015208      	1	19980721	G	5320	206033410021S	INTERCOSTAL     			BELL  	206   	206L4       	1182110	SW  										FUSELAGE	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										INTERCOSTAL MISMARKED.  PART SERVICEABLE.  VENDOR MISPACKAGED P/N 206-033-410-021S WAS ORDERED,  THE BHT PICK TICKET HAS	 -021S P/N ON IT; BUT A -025S INTERCOSTAL WAS SENT.					1	G	7	1 	3U			NC	H2SW
1998073100684	19980731	00684	SW  	1998	7	31	HEEA0015209      	1	19980721	G	5320	206033103037S	SPLICE          			BELL  	206   	206L4       	1182110	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										AFT FLANGE OF T-ANGLE SPLICE IS TRIMMED TOO SHORT TO PROVIDE PROPER EDGE DISTANCE FOR .1562 INCH RIVETS.  THE AREA WHICH	 IS TRIMMED TOO SHORT IS ON THE SIDE OF PART, JUST INBOARD OF WHERE THE CURVE BEGINS TO MATCH THE SHELL CONTOUR.					1	G	7	1 	3U			NC	H2SW
1998073100685	19980731	00685	SW  	1998	7	31	HEEA0015210      	1	19980721	G	5330	206033100019	SKIN            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	IMPROPER PART   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	8592X					51508				INCORRECT PARTS SHIPPED (SKIN).  MISMANUFACTURED AND NOT MADE PER BELL DRAWINGS.						1	G	7	1 	3U			 	H2SW
1998073100686	19980731	00686	SW  	1998	7	31	HEEA0015211      	1	19980721	G	5330	206033100020	SKIN            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	IMPROPER PART   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	8592X					51508				INCORRECT PARTS SHIPPED (SKIN).  MISMANUFACTURED AND NOT MADE PER BELL DRAWINGS.						1	G	7	1 	3U			 	H2SW
1998073100687	19980731	00687	SW  	1998	7	31	HEEA0015212      	1	19980721	G	5330	206033100313	SKIN            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	IMPROPER PART   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	8592X					51508				INCORRECT PARTS SHIPPED (SKIN).  MISMANUFACTURED AND NOT MADE PER BELL DRAWINGS.						1	G	7	1 	3U			 	H2SW
1998073100688	19980731	00688	SW  	1998	7	31	HEEA0015213      	1	19980721	G	5330	206033100314	SKIN            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	IMPROPER PART   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	8592X					51508				INCORRECT PARTS SHIPPED (SKIN).  MISMANUFACTURED AND NOT MADE PER BELL DRAWINGS.						1	G	7	1 	3U			 	H2SW
1998073100646	19980731	00646	GL  	1998	7	31	HEEA0015214      	2	19980722	G	7230	230052711	SPLINE ADAPTER  								ALLSN 	250C  	250C30S     	03013	GL  					COMPRESSOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					68260					RECEIVING INSPECTION REVEALED:  MEASURED .0005 INCH BELOW SPECS (.9855 INCH - .9860 INCH) ON SPLINE ADAPTER OUTSIDE DIAM	ETER.										3	U			E1GL
1998073100647	19980731	00647	GL  	1998	7	31	HEEA0015215      	2	19980722	G	7230	230052711	SPLINE ADAPTER  			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMPRESSOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	3116P				68262	51530				RECEIVING INSPECTION REVEALED:  MEASURED .0005 INCH BELOW SPECS (.9855 INCH - .9860 INCH) ON SPLINE ADAPTER OUTSIDE DIAM	ETER.					1	G	7	1 	3U	3	U	 	H2SW    	E1GL
1998073100689	19980731	00689	SW  	1998	7	31	HEEA0015216      	1	19980722	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR LINK WORN.						1	G	7	1 	3U			O	H2SW
1998073100690	19980731	00690	SW  	1998	7	31	HEEA0015217      	1	19980722	G	6410	406312100101	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1522 				53060				BEARING WORN AND CORRODED.						1	G	7	1 	3U			O	H2SW
1998073100691	19980731	00691	SW  	1998	7	31	HEEA0015218      	1	19980722	G	3212	407350300101	VALVE           			BELL  	407   	407         		SW  										FLOAT BAG	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	2079 				53070				CHECK VALVE LEAKING.						1	G	7	1 	3U			O	H2SW
1998073100692	19980731	00692	SW  	1998	7	31	HEEA0015219      	1	19980722	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				DISK COUPLING HAS CORROSION.						1	G	7	1 	3U			O	H2SW
1998073100693	19980731	00693	SW  	1998	7	31	HEEA0015220      	1	19980722	G	7810	407063001101	STACK           			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				EXHAUST STACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998073100694	19980731	00694		1998	7	31	HEEA0015221      	4	19980722	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         		SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				OUTSIDE AIR TEMPERATURE READS HIGH.						1	G	7	1 	3U			O	H2SW
1998073100695	19980731	00695	SW  	1998	7	31	HEEA0015222      	1	19980722	G	7714	407375008101	INDICATOR       			BELL  	407   	407         		SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				NR FAILED TO TEST.						1	G	7	1 	3U			O	H2SW
1998073100696	19980731	00696	SW  	1998	7	31	HEEA0015226      	1	19980722	G	6720	406312103101	BEARING         			BELL  	407   	407         		SW  										T/R LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				WORN BEARINGS ON TAIL ROTOR LINK.						1	G	7	1 	3U			O	H2SW
1998073100697	19980731	00697	SW  	1998	7	31	HEEA0015227      	1	19980722	G	6720	406312103101	BEARING         			BELL  	407   	407         		SW  										T/R LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				WORN BEARINGS ON TAIL ROTOR LINK.						1	G	7	1 	3U			O	H2SW
1998073100698	19980731	00698	SW  	1998	7	31	HEEA0015228      	1	19980722	G	7714	407375008101	INDICATOR       			BELL  	407   	407         		SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				TURBINE NEEDLE WOULD NOT MOVE.						1	G	7	1 	3U			O	H2SW
1998073100711	19980731	00711	EU  	1998	7	31	HEEA0015230      	1	19980722	G	6330	704A3363310951	STOP ASSY       			SNIAS 	350   	AS350B2     	8680813	EU  										TRANSMISSION	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S	897  				2777				SEPARATED.  SERIAL NUMBERS REMOVED 11624, 11641, AND 11640.  REPLACEMENT PART SERIAL NUMBERS ARE 12668, 12795, AND 12797	.					1	G	7	1 	3U				H9EU
1998073100712	19980731	00712	EU  	1998	7	31	HEEA0015231      	1	19980722	G	7931	S1120021090	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				PRESSURE SWITCH WILL NOT INDICATE.						1	G	7	1 	3U				H9EU
1998073100713	19980731	00713	EU  	1998	7	31	HEEA0015232      	1	19980722	G	7931	1130021089	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				LIGHT WILL NOT COME ON.						1	G	7	1 	3U				H9EU
1998073100714	19980731	00714	EU  	1998	7	31	HEEA0015233      	1	19980722	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				FUEL PUMP DOES NOT PUMP.						1	G	7	1 	3U				H9EU
1998073100715	19980731	00715	EU  	1998	7	31	HEEA0015234      	1	19980722	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				FUEL PUMP WENT DEAD AFTER APPROXIMATELY 1 MINUTE, BLEW FUSE FIRST THEN WENT DEAD.						1	G	7	1 	3U				H9EU
1998073100699	19980731	00699	SW  	1998	7	31	HEEA0015236      	1	19980724	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT PRESSURE	DESTROYED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				PRESSURE GAUGE SCRAPPED (PARTS IN PIECES).						1	G	7	1 	3U			O	H2SW
1998081400640	19980814	00640	GL  	1998	8	14	HEEA0015237      	2	19980727	G	7322	2537739	VALVE SLEEVE    		252464429   	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR				334872	S719				FOUND DEFECTIVE METERING VALVE SLEEVE (UNBONDED).  REPLACED METERING VALVE SLEEVE.   UNIT TESTED SATISFACTORY PER TEST C	ALIBRATION SPECS NR 12529-01.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998081400496	19980814	00496	SW  	1998	8	14	HEEA0015238      	1	19980727	G	6330	214031614127	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										M/R TRANSMISSION	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					LK0854					CRACK FOUND IN NMAIN ROTOR GEARBOX PLATE ASSEMBLY.						2	G	7	2 	4U				H10SW
1998081400641	19980814	00641	EU  	1998	8	14	HEEA0015239      	1	19980727	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5029H				688	S670				EXHAUST TEMPERATURE INDICATOR UNIT READS 20 PERCENT HIGH AT 600, UNIT FUNCTION CHECKED BAD AND CANNOT BE CALIBRATED.						1	G	7	2 	3U				H3EU
1998081400642	19980814	00642	GL  	1998	8	14	HEEA0015240      	2	19980727	G	7320	1564T1005	SERVO MOTOR     			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			CL	CLIMB          	1			SW	03	7170D				52598	S840				NR STARTED TO DROOP AFTER TAKEOFF AND WOULD NOT BEEP UP.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998081400497	19980814	00497	SW  	1998	8	14	HEEA0015241      	1	19980727	G	7921	8543909	COOLER          			BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N				10270	45267				INSTALLED OIL COOLER FROM STOCK AND RAN AIRCRAFT.  ENGINE OIL TEMP WAS HIGH.						1	G	7	1 	3U				H2SW
1998081400498	19980814	00498	SW  	1998	8	14	HEEA0015242      	1	19980727	G	7921	8543909	COOLER          			BELL  	206   	206L3       	1182108	SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8589X				10237	51487				RECEIVED OIL COOLER FROM STOCK.  INSTALLED ON AIRCRAFT AND ENGINE OIL TEMP WAS VERY HIGH AT RED LINE.  COOLER APPEARS CL	OGGED AND DIRTY AND ALSO CORRODED.					1	G	7	1 	3U				H2SW
1998081400499	19980814	00499		1998	8	14	HEEA0015246      	4	19980727	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498				P1142	36003				BENCH CHECK AND 2 YEAR INSPECTION.  PERFORMED PRELIMINARY INSPECTION.  FOUND TRANSMIT POWER OUT FLUCTUATING AND MODULATI	ON DISTORTED INTERMITTENTLY.  SWAPPED OUT Q109 AND Q110 TRANSISTORS.  NO HELP.  ALSO FOUND C529 CAPACITOR BROKEN.					1	G	7	2 	4U				H4SW
1998081400500	19980814	00500		1998	8	14	HEEA0015249      	4	19980727	G	3457	0110005400	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41128				81550060	51134				TAKES EXCESSIVE TIME TO INITIATE SATELLITES.						1	G	7	1 	3U				H2SW
1998081400643	19980814	00643		1998	8	14	HEEA0015250      	4	19980727	G	3457	0110005400	GPS             			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81992				81508853	S827				TWO YEAR INSPECTION.  PERFORMED PRELIMINARY INSPECTION AND FOUND LOW BATTERY VOLTAGE AND ALSO FOUND CLR AND DIRECT TO BU	TTONS BECOMING UNREADABLE.					1	G	7	2 	3U				H3EU
1998081400501	19980814	00501		1998	8	14	HEEA0015251      	4	19980727	G	2312	063100700	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014Y				1108	45219				TRANSCEIVER WILL NOT TRANSMIT.						1	G	7	1 	3U				H2SW
1998081900061	19980819	00061	SW  	1998	8	19	HEEA0015252      	1	19980727	G	3212	20077115	MOUNT           			BELL  	206   	206L1       	1182107	SW  										FLOAT	MISLOCATED      	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	3905B				010	45598				MOUNTING SKIRTS ON FLOAT BAG MISLOCATED.						1	G	7	1 	3U			 	H2SW
1998081900062	19980819	00062	SW  	1998	8	19	HEEA0015253      	1	19980727	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	107PH				2611	2789				ACTUATOR BAD FROM STOCK - FOUND BAD WIRES.  REPAIRED WIRES AND UNIT STILL DID NOT WORK.						1	G	7	1 	3U			 	H2SW
1998081400502	19980814	00502	SW  	1998	8	14	HEEA0015254      	1	19980727	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1073W				140	45386				TOT INDICATOR INTERMITTENTLY STICKS AT ZERO.						1	G	7	1 	3U				H2SW
1998081400503	19980814	00503	SW  	1998	8	14	HEEA0015255      	1	19980727	G	2432	G641	BATTERY         			BELL  	206   	206B3       	1181506	SW  										BATTERY COMPT	DISCHARGED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					G01721854					ACTIVATED BATTERY WITH ELECTROLYTE.  CHARGED BATTERY FOR 36 HOURS, SPECIFIC GRAVITY OF THE ELECTROLYTE READ BELOW REQUIR	ED 1.285 AND 1.295.					1	G	7	1 	3U				H2SW
1998081400504	19980814	00504		1998	8	14	HEEA0015257      	4	19980727	G	2312	40008310103	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D					31135				TRANSCEIVER UNIT TRANSMITS INTERMITTENTLY AFTER WARM-UP.						1	G	7	1 	4U				H4SW
1998081400505	19980814	00505		1998	8	14	HEEA0015258      	4	19980727	G	2312	40008310103	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y				2033	28139				TRANSCEIVER HAS WAVY DISPLAY AND DOES NOT TEST PROPERLY - RT FAULT.						2	G	7	2 	4U				H10SW
1998081400506	19980814	00506		1998	8	14	HEEA0015259      	4	19980727	G	3442	40016702501	RADAR UNIT      			BELL  	212   	212         	1181420	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D				1020	31135				RADAR UNIT BUTTON STICKING ON FACEPLATE, DISPLAY SPIKES AFTER WARM-UP.						1	G	7	1 	4U				H4SW
1998081400507	19980814	00507		1998	8	14	HEEA0015260      	4	19980727	G	2312	064102300	TRANSCIEVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N				1648	28106				VHF TRANSCEIVER HAS NO SQUELCH; EXCESSIVE CORROSION.						2	G	7	2 	4U				H10SW
1998081400508	19980814	00508		1998	8	14	HEEA0015261      	4	19980727	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R				5519	36007				VHF TRANSCEIVER TRANSMITS ARE GARBLED.  SIDETONE FADES.  PERFORMED PRELIMINARY INSPECTION.  REMOVED CORROSION FROM UNIT.	  ADJUSTED CARRIER SQUELCH, MIC GAIN, SIDETONE AND COMPRESSOR.  AFTER FURTHER TESTING, UNIT STOPPED TRANSMITTING.					1	G	7	2 	4U				H4SW
1998081400509	19980814	00509		1998	8	14	HEEA0015262      	4	19980727	G	3431	066400700	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT VOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N				7495	33002				NAVIGATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998081400510	19980814	00510	SW  	1998	8	14	HEEA0015263      	1	19980727	G	7931	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608				90021468	33075				ENGINE OIL PRESSURE INDICATOR INOPERATIVE.  PRESSURE SIDE ONLY.						1	G	7	2 	4U				H4SW
1998081400511	19980814	00511		1998	8	14	HEEA0015264      	4	19980727	G	2210	2593996333	TARSYN 333      			BELL  	412   	412         	1182202	SW  										AUTO FLIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023				7713250	33080				CO-PILOT'S HSI WILL NOT WORK, UNIT FUNCTION CHECK BAD, FAILED TEST 1.1 ON SST BENCH.  D.G. WILL NOT COME VALID.						1	G	7	2 	4U				H4SW
1998081400644	19980814	00644		1998	8	14	HEEA0015265      	4	19980727	G	3451	066107001	TRANSCEIVER     			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT DME	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	134AE				3811	7237				TRANSCEIVER INOPERATIVE.  NO DISPLAY OR RECEIVE.						1	G	7	2 	3U			NC	H13EU
1998081400645	19980814	00645		1998	8	14	HEEA0015266      	4	19980727	G	2312	069102525	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT VHF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070				P11138	S145				TRANSCEIVER CAN'T RECEIVE OR TRANSMIT.						1	G	7	2 	3U				H3EU
1998081400646	19980814	00646		1998	8	14	HEEA0015267      	4	19980727	G	2312	069102525	TRANSCEIVER     			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT VHF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE				48525	7238				BOTH DISPLAYS ON TRANSCEIVER INOPERATIVE. PERFORMED PRELIMINARY INSPECTION.  SWAPPED DISPLAYS AND DISPLAYS WORKED FOR 1-	2 MINUTES AND THEN WENT OUT.					1	G	7	2 	3U			NC	H13EU
1998081400647	19980814	00647	EU  	1998	8	14	HEEA0015268      	1	19980727	G	6210	10515141	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8197X	4194 			5946	S808				M/R BLADE HAS SEPARATION ON THE OUTBOARD LEADING EDGE STRIP NEAR THE TIP END.						1	G	7	2 	3U				H3EU
1998081400648	19980814	00648	GL  	1998	8	14	HEEA0015269      	2	19980727	G	7320	1564T1005	SERVO MOTOR     			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7170D				1667	S840				ACTUATOR WOULD NOT BEEP.  FOUND WIRE WORN THROUGH AT BODY.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998081400649	19980814	00649	EU  	1998	8	14	HEEA0015270      	1	19980727	G	2435	23032048	STARTER         			BOLKMS	105   	BO105S      	5626006	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911DD	11562			13287	S830				STARTER/GENERATOR WILL NOT MOTOR ENGINE OVER.						1	G	7	2 	3U				H3EU
1998081400650	19980814	00650		1998	8	14	HEEA0015271      	4	19980727	G	2312	4000106010	CONTROL UNIT    			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G				2317	S853				INTERMITTENT THUMBWHEEL ON CONTROL UNIT.						1	G	7	2 	3U				H3EU
1998081400651	19980814	00651	EU  	1998	8	14	HEEA0015272      	1	19980727	G	2840	DK042	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J				12978	S826				FUEL PRESSURE FLUCTUATES.  FUNCTION CHECK BAD, TRANSMITTER OUTPUT PEGS OUT AT 15 PSI.						1	G	7	2 	3U				H3EU
1998081400459	19980814	00459		1998	8	14	HEEA0015273      	4	19980727	G	3444	066104800	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K				3095	760082				ALTIMETER INOPERATIVE.  PERFORMED PRELIMINARY INSPECTION, FOUND UNIT INACCURATE.						1	G	7	2 	3U				H1NE
1998081400460	19980814	00460	NE  	1998	8	14	HEEA0015274      	1	19980727	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H	8820 			A13700571	760233				PRIMARY POLY STRIP ON BOTH PADDLES IS WORN THROUGH TO THE GLASS ON TAIL ROTOR BLADE.						1	G	7	2 	3U				H1NE
1998081400461	19980814	00461		1998	8	14	HEEA0015275      	4	19980727	G	2200		POTENTIOMETER   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342				81082018	760096				POTENTIOMETER CAUSING ACTUATOR NOT TO STAY CENTERED IN FLIGHT.   FOUND POTENTIOMETERS TO CHECK BAD IN NULL POSITION.						1	G	7	2 	3U				H1NE
1998081400512	19980814	00512		1998	8	14	HEEA0015276      	4	19980727	G	3421	5040017901	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA				10362B					ATTITUDE INDICATOR LIGHTS INOPERATIVE.  REPLACED 5-VOLT LIGHTS.						1	G	7	2 	4U				H4SW
1998081400513	19980814	00513	SW  	1998	8	14	HEEA0015277      	1	19980727	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T	8459 			A1072	33112				OUTBOARD LEADING EDGE ABRASION STRIP HAS CRACKS WITH MULTIPLE BRANCH.						1	G	7	2 	4U				H4SW
1998081400514	19980814	00514	SW  	1998	8	14	HEEA0015278      	1	19980727	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2251Z				171	45756				INDICATOR INTERMITTENTLY STICKS AT ZERO.						1	G	7	1 	3U				H2SW
1998081400462	19980814	00462	EA  	1998	8	14	HEEA0015279      	2	19980727	G	7321	32447066	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1082G				C11103	31109				NR 2 SIDE HAS INTERNAL AIR LEAK THAT PREVENTS NR 2 ENGINE FROM TOPPING.  (BOTH SERVO VALVES LEAK).						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998081400652	19980814	00652		1998	8	14	HEEA0015280      	4	19980727	G	3455	066107200	RECEIVER        			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT ADF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL				22617	7198				BFO INOPERATIVE AND STRIPPED SCREW HOLE ON FRAME. PERFORMED PRELIMINARY INSPECTION AND FOUND PHOTOCELL INOPERATIVE, REPL	ACED PHOTOCELL, FOUND BFO INOPERATIVE AND STRIPPED SCREW HOLE ON FRAME.					1	G	7	2 	3U				H13EU
1998081400515	19980814	00515		1998	8	14	HEEA0015281      	4	19980727	G	2312	063100700	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT VHF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2135V				1926	45657				TRANSCEIVER INOPERATIVE.						1	G	7	1 	3U				H2SW
1998081400653	19980814	00653		1998	8	14	HEEA0015284      	4	19980727	G	3455	066107200	RECEIVER        			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT ADF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL				8266	7198				ADF RADIO INOPERATIVE. PERFORMED PRELIMINARY INSPECTION, FOUND BLOWN FUSE.  INSTALLED CIRCUIT BREAKER (1 AMP) TO TROUBLE	SHOOT.  WHEN TURNED ON, SMOKE CAME FROM UNIT.  UNIT OPERATION WAS FAULTY.					1	G	7	2 	3U				H13EU
1998081400516	19980814	00516	SW  	1998	8	14	HEEA0015285      	1	19980727	G	5260	206301109	STEP            			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3107N					51512				STEP CORRODED BEYOND LIMITS.						1	G	7	1 	3U				H2SW
1998081400517	19980814	00517	SW  	1998	8	14	HEEA0015286      	1	19980727	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T	6137 			A663	33112				CANNOT TRACK OR BALANCE.  SUSPECT WATER IN THE BLADE CORE.						1	G	7	2 	4U				H4SW
1998081400463	19980814	00463		1998	8	14	HEEA0015287      	4	19980727	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		3194 			86101610					ACTUATOR MOTOR INTERMITTENTLY BINDS UP (LIKE SOMETHING CATCHES INSIDE GEARBOX).						1	G	7	2 	3U				H1NE
1998081900057	19980819	00057	NE  	1998	8	19	HEEA0015288      	1	19980727	G	6220	7640002900104	ARM             			SKRSKY	S76   	S76A        	8143006	NE  										VISCOUS DAMPER	MISINSTALLED    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1545K				069	760047				DAMPER ARM IMPROPERLY INSTALLED.						1	G	7	2 	3U			 	H1NE
1998081400518	19980814	00518	SW  	1998	8	14	HEEA0015289      	1	19980727	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608	9434 			A913	33075				CANNOT TRACK OR BALANCE.  SUSPECT WATER IN THE BLADE CORE.						1	G	7	2 	4U				H4SW
1998081400519	19980814	00519		1998	8	14	HEEA0015290      	4	19980727	G	3422	5050031904	GYRO            			BELL  	407   	407         		SW  										COCKPIT	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH	6    			25584	53266				DIAL SCREW BACKED OUT OF CENTER DIAL SHAFT AND IS WEDGED BETWEEN DIAL AND FLAG IN DIRECTIONAL GYRO.						1	G	7	1 	3U			O	H2SW
1998081400520	19980814	00520		1998	8	14	HEEA0015291      	4	19980727	G	3421	5040017901	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	92MT				129	51175				ATTITUDE INDICATOR INOPERATIVE.  OVERHAULED UNIT.  REPLACED ALL BEARINGS AND ROTOR.  STATIC AND DYNAMIC BALANCED.  UNIT 	REPAIRED AND BENCH CHECK GOOD.					1	G	7	1 	3U				H2SW
1998081400521	19980814	00521		1998	8	14	HEEA0015292      	4	19980727	G	2312	069102404	TRANSCEIVER     			BELL  	206   	206L4       	1182110	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	CFVEF				38879	52071				ON FIRST FLIGHT, VHF TRANSMITTED GARBLED.						1	G	7	1 	3U			NC	H2SW
1998081400522	19980814	00522		1998	8	14	HEEA0015293      	4	19980727	G	2312	066106200	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10761				37285	45381				TRANSCEIVER OUTPUT WEAK.						1	G	7	1 	3U				H2SW
1998081400464	19980814	00464		1998	8	14	HEEA0015294      	4	19980727	G	3444	066104800	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K				3082	760082				SIGNAL THRESHOLD WILL NOT UNLOCK.  PERFORMED PRELIMINARY INSPECTION.  FOUND ALTIMETER UNIT INACCURATE.						1	G	7	2 	3U				H1NE
1998081400523	19980814	00523		1998	8	14	HEEA0015295      	4	19980727	G	2312	071127401	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5000K				3874	45167				CHANNEL MEMORY ON TRANSCEIVER WILL NOT HOLD FREQUENCY.						1	G	7	1 	3U				H2SW
1998081400654	19980814	00654		1998	8	14	HEEA0015296      	4	19980727	G	2312	069102525	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT VHF	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911PF				47074	S718				TRANSCEIVER TRANSMITS AND RECEIVES WEAK.						1	G	7	2 	3U				H3EU
1998081400524	19980814	00524		1998	8	14	HEEA0015297      	4	19980727	G	2312	069102409	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT VHF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251Y				P35296	51556				TRANSCEIVER INTERMITTENT, ON/OFF KNOB.  WILL NOT WORK PROPERLY.						1	G	7	1 	3U				H2SW
1998081400525	19980814	00525	SW  	1998	8	14	HEEA0015298      	1	19980727	G	2435	200SGL132Q	STARTER         			BELL  	206   	206L1       	1182107	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5742H	487  			3098	45476				STARTER/GENERATOR ARCHING AND GENERATOR WILL NOT COME ON LINE.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND BRUSHES E	XCESSIVELY WORN AND COMMUTATOR BURNED AND PITTED.					1	G	7	1 	3U				H2SW
1998081900063	19980819	00063	SW  	1998	8	19	HEEA0015299      	1	19980727	G	5520	206023119157	ELEVATOR        			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										ELEVATOR IS TOO WIDE (4.6875 INCHES WIDE).  SHOULD BE 4.3750 INCHES WIDE.						1	G	7	1 	3U			 	H2SW
1998081400655	19980814	00655		1998	8	14	HEEA0015300      	4	19980727	G	2312	4000106010	CONTROL UNIT    			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911PF				1641	S718				FREQUENCY SELECTED ON THUMBWHEEL IS NOT PROPERLY DISPLAYED.  REPLACED THUMBWHEEL S1.   FOUND ONE NUMBER ON THUMBWHEEL TO	 STILL BE INTERMITTENT.					1	G	7	2 	3U				H3EU
1998081400526	19980814	00526		1998	8	14	HEEA0015301      	4	19980727	G	3457	0845000000	GPS             			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S				4E000240	30953				SKYNAV 5000 WILL NOT FIND ITSELF.  FOUND UNIT SLOW TO LOCK ON, ALSO BUTTONS ARE DIRTY AND INTERMITTENT.						1	G	7	1 	4U				H4SW
1998081400527	19980814	00527	SW  	1998	8	14	HEEA0015302      	1	19980727	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K				81021043	36001				UNIT FUNCTION CHECK BAD, NR 1 NEEDLE STICKS AT ZERO ON TRIPLE TACHOMETER INDICATOR..						1	G	7	2 	4U				H4SW
1998081400528	19980814	00528		1998	8	14	HEEA0015303      	4	19980727	G	2211	4033089901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AUTO FLIGHT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH				83110732	33150				COMPUTER INOPERATIVE.  FUNCTION CHECKED BAD.  FAILS LAMP DRIVERS TEST 2.2, 2.3, 3.1, AND 4.3 ON SST.  TIME SINCE REPAIR 	97:35 HOURS.					1	G	7	2 	4U				H4SW
1998081400529	19980814	00529	SW  	1998	8	14	HEEA0015306      	1	19980727	G	7810	212061201011	EJECTOR         			BELL  	412   	412         	1182202	SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P				13000492	33012				EJECTOR OUTER SHROUD CRACKED AND FLANGE CRACKED ON EJECTOR ASSEMBLY..						1	G	7	2 	4U				H4SW
1998081900064	19980819	00064	SW  	1998	8	19	HEEA0015307      	1	19980727	G	6210	206015001107	DOUBLER         			BELL  	206   	206L1       	1182107	SW  										M/R BLADE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					A2985					BLADE DOUBLER CUT TOO SHORT.  SUBMITTER STATED UNACCEPTABLE FOR PHI USE.						1	G	7	1 	3U			 	H2SW
1998081900058	19980819	00058	GL  	1998	8	19	HEEA0015308      	2	19980729	G	7250	23034775	SUPPORT         		23035128    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					GP SECTION	DEFECTIVE       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1545X				FX16410	760050	CAE890670S			RECEIVING INSPECTION REVEALED:  EXCESSIVE RUNOUT .013 INCH BEYOND SERVICEABLE LIMITS ON G.P. SUPPORT FORWARD FLANGE.  IN	STALLED A DALLAS AIRMOTIVE OVERHAULED G.P. SUPPORT.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL
1998081900059	19980819	00059	GL  	1998	8	19	HEEA0015309      	2	19980729	G	7250	23033111	COLLECTOR RING  		23035128    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					TURBINE SECTION	DEFECTIVE       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1545X				29720	760050	CAE890670S			RECEIVING INSPECTION REVEALED:  EXCESSIVE RUNOUT .010 INCH BEYOND SERVICEABLE LIMITS ON EXHAUST COLLECTOR.  FORWARD PILO	T AND VENT ORIFICE TUBE OUT OF ROUND.  INSTALLED A DALLAS AIRMOTIVE OVERHAULED EXHAUST COLLECTOR.					1	G	7	2 	3U	3	U	 	H1NE    	E1GL
1998081400530	19980814	00530	SW  	1998	8	14	HEEA0015310      	1	19980729	G	5320	206175203	TUBE            			BELL  	206   	206B3       	1181506	SW  										MIRROR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22751					3627				TUBE CRACKED WHERE MIRROR MOUNTS TO TUBE ASSY.						1	G	7	1 	3U				H2SW
1998081400531	19980814	00531	SW  	1998	8	14	HEEA0015316      	1	19980729	G	3213	206053203101	CROSSTUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745S				A1010	45491				CORROSION PITS BEYOND LIMITS.  SCRAPPED CROSSTUBE AND REPLACED WITH SERVICEABLE CROSSTUBE.						1	G	7	1 	3U				H2SW
1998081400532	19980814	00532	SW  	1998	8	14	HEEA0015317      	1	19980729	G	2840	206075676003	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										DUAL FUEL	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078D				128	45397				LOADMETER NEEDLE BROKEN, GIVES FLUCTUATING INDICATIONS WITHOUT BEING PLUGGED IN.						1	G	7	1 	3U				H2SW
1998081400533	19980814	00533		1998	8	14	HEEA0015318      	4	19980729	G	2210	2593996444	TARSYN          			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F				4022002	30936				DIRECTIONAL GYRO HAS NO SYNCHRO HEADING OUTPUT.  TIME SINCE REPAIR, 7:15 HOURS.						1	G	7	1 	4U				H4SW
1998081400534	19980814	00534		1998	8	14	HEEA0015319      	4	19980729	G	2350	AMS44	AUDIO SELECTOR  			BELL  	407   	407         		SW  										DUAL CHANNEL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH	648  			1829	53142				RADIO TRANSMISSION WEAK AND DISTORTED.						1	G	7	1 	3U			O	H2SW
1998081400535	19980814	00535		1998	8	14	HEEA0015320      	4	19980729	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S				7137	33022				TRANSCEIVER WEAK AND GARBLED.  REPAIRED AND FUNCTION CHECKED GOOD.						1	G	7	2 	4U				H4SW
1998081400536	19980814	00536		1998	8	14	HEEA0015321      	4	19980729	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L				V001	33023				HSI DOES NOT SLAVE WHEN OTHER HSI IS IN COMMAND.						1	G	7	2 	4U				H4SW
1998081400537	19980814	00537		1998	8	14	HEEA0015322      	4	19980729	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T				806108	33112				PART WAS INSTALLED AND FUNCTION CHECK GOOD ON GROUND.  ON NEXT DAY, AFTER APPROX, 30 MINUTES OF FLIGHT TIME, NOW COMPASS	 CARD SPINS CONSTANTLY. REPLACED WITH SERVICEABLE HSI.					1	G	7	2 	4U				H4SW
1998081400538	19980814	00538	NE  	1998	8	14	HEEA0015323      	2	19980729	G	7532	318320201	VALVE           			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					BLEED AIR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498				A9852	36003				WHEN INSTALLED IN AIRCRAFT BLEED VALVE CAUSED COMPRESSOR STALL.  REPLACED WITH SERVICEABLE BLEED VALVE.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998081400656	19980814	00656	GL  	1998	8	14	HEEA0015324      	2	19980729	G	7320	1564T1005	SERVO MOTOR     			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G				195	S853				SERVOMOTOR INTERMITTENTLY INOPERATIVE.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998081400465	19980814	00465		1998	8	14	HEEA0015325      	4	19980729	G	3421	500DCF288	GYRO            			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217				3766	760229				WHEN BANKING LEFT OR RIGHT, POINTER BAR CLIMBS OR DIVES 20 DEGREES.						1	G	7	2 	3U				H1NE
1998081400466	19980814	00466	NE  	1998	8	14	HEEA0015326      	1	19980729	G	2430	UC2814	DC CONVERTER    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE				952	760275				DC CONVERTER INOPERATIVE.						1	G	7	2 	3U				H1NE
1998081400657	19980814	00657	EU  	1998	8	14	HEEA0015327      	1	19980729	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T				1864	S539				MAST MOMENT INDICATOR GIVES ERRONEOUS READINGS.						1	G	7	2 	3U				H3EU
1998081400658	19980814	00658	EU  	1998	8	14	HEEA0015328      	1	19980729	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T				1030	S539				TORQUE TRANSMITTER GIVES ERRONEOUS READINGS.						1	G	7	2 	3U				H3EU
1998081400539	19980814	00539	SW  	1998	8	14	HEEA0015329      	1	19980729	G	2842	214066212107	PROBE           			BELL  	214   	214ST       	1182106	SW  										FUEL SYSTEM	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N				0116F	28106				INSTALLED PROBE CAUSING FUEL QUANTITY INDICATION OSCILLATIONS.  FUEL INDICATOR READ ZERO AND BELOW ON ANALOG NEEDLE.						2	G	7	2 	4U				H10SW
1998081400540	19980814	00540		1998	8	14	HEEA0015330      	4	19980729	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608				4539	33075				INDICATOR BALL ROTATES SLOW AND RATCHETS IN CLIMB AND DRIVE.						1	G	7	2 	4U				H4SW
1998081400541	19980814	00541		1998	8	14	HEEA0015331      	4	19980729	G	3414	214074152101	TRANSDUCER      			BELL  	214   	214ST       	1182106	SW  										AIRSPEED	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T				27	28101				TRANSDUCER FAILED 5 ON ADC.						2	G	7	2 	4U				H10SW
1998081400542	19980814	00542	SW  	1998	8	14	HEEA0015332      	1	19980729	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R				8111505	36007				NR 1 NEEDLE STICKS ON TRIPLE TACHOMETER.						1	G	7	2 	4U				H4SW
1998081400659	19980814	00659		1998	8	14	HEEA0015333      	4	19980729	G	3421	060001500	GYRO            			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J				24998	S826				CIRCUIT BREAKER TRIPS ON GYRO.						1	G	7	2 	3U				H3EU
1998081400543	19980814	00543		1998	8	14	HEEA0015334      	4	19980729	G	3416	D120P2T	ENCODER         			BELL  	206   	206B3       	1181506	SW  										ALTIMETER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G				74661	3610				ENCODER HAS NO OUTPUT.						1	G	7	1 	3U				H2SW
1998081400544	19980814	00544		1998	8	14	HEEA0015335      	4	19980729	G	2312	40008310103	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806				2384	28140				TRANSCEIVER WILL NOT TURN ON.  TIME SINCE REPAIR,  27:15 HOURS.						2	G	7	2 	4U				H10SW
1998081400545	19980814	00545	SW  	1998	8	14	HEEA0015336      	1	19980729	G	2430	206075447007	REGULATOR       			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22425				430	45743				AMMETER DEFLECTS NEGATIVE WHENEVER VHF IS KEYED.						1	G	7	1 	3U				H2SW
1998081400546	19980814	00546		1998	8	14	HEEA0015337      	4	19980729	G	3417	214175421101	COMPUTER        			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608				113	33075				AIR DATA COMPUTER WILL NOT SHOW FUEL BURN AND ON OCCASION POWER CHECK.						1	G	7	2 	4U				H4SW
1998081400547	19980814	00547	SW  	1998	8	14	HEEA0015338      	1	19980729	G	2841	206063623001	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10761				878	45381				FUEL QUANTITY INDICATOR HAS ERRATIC READING, UNIT READS HIGH OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW
1998081400660	19980814	00660	EU  	1998	8	14	HEEA0015339      	1	19980729	G	2435	23032048	STARTER         			BOLKMS	105   	BO105S      	5626006	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J				13194	S826				STARTER/GENERATOR INTERMITTENTLY WILL NOT ENGAGE ON START.						1	G	7	2 	3U				H3EU
1998081400548	19980814	00548	SW  	1998	8	14	HEEA0015340      	1	19980729	G	2435	23081018	STARTER         			BELL  	206   	206L3       	1182108	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					1328					SCREEN NOT ATTACHED ON STARTER/GENERATOR..						1	G	7	1 	3U				H2SW
1998081400549	19980814	00549	NE  	1998	8	14	HEEA0015341      	2	19980729	G	7412	103815501	EXCITER         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH				88192515	33197				EXCITER HAS SLOW SPARK RATE.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998081400550	19980814	00550	SW  	1998	8	14	HEEA0015342      	1	19980729	G	7810	212061202009	DUCT            			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				FLANGE CRACKED ON DUCT ASSEMBLY.						1	G	7	2 	4U				H4SW
1998081400551	19980814	00551	SW  	1998	8	14	HEEA0015343      	1	19980729	G	5260	SYLC502281	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K				1682	36001				STEP ACTUATOR EXCESSIVELY SLOW.						1	G	7	2 	4U				H4SW
1998081400552	19980814	00552	SW  	1998	8	14	HEEA0015344      	1	19980729	G	6330	206030539003	MOUNT           			BELL  	206   	206B3       	1181506	SW  										TRANSMISSION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2269A				LK0578	3608				CAUSED YELLOW TEMP INDICATOR ON INPUT SHAFT TO TURN BLACK.						1	G	7	1 	3U				H2SW
1998081400553	19980814	00553	SW  	1998	8	14	HEEA0015345      	1	19980729	G	3350	CC15AHX05	POWER SUPPLY    			BELL  	214   	214ST       	1182106	SW  										CABIN	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T				166343	28101				POWER SUPPLY FAILED 5 CODES, INOPERATIVE.						2	G	7	2 	4U				H10SW
1998081400554	19980814	00554	SW  	1998	8	14	HEEA0015346      	1	19980729	G	6710	214001423105	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T				109	28101				ACTUATOR WILL NOT ROTATE.						2	G	7	2 	4U				H10SW
1998081400661	19980814	00661	EU  	1998	8	14	HEEA0015347      	1	19980729	G	7714	6505A3053	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL				488	7198				NR 2 N2 NEEDLE ON TRIPLE TACHOMETER FLUCTUATING AT 100 PERCENT.						1	G	7	2 	3U				H13EU
1998081400555	19980814	00555		1998	8	14	HEEA0015348      	4	19980729	G	2312	064102300	TRANSCIEVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N				5579	28106				VHF TRANSCEIVER'S BREAKING SQUELCH MAKES NOISE.						2	G	7	2 	4U				H10SW
1998081400467	19980814	00467		1998	8	14	HEEA0015349      	4	19980729	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K				80043059	760082				NR 2 YAW SYSTEM INOPERATIVE.						1	G	7	2 	3U				H1NE
1998081400468	19980814	00468		1998	8	14	HEEA0015350      	4	19980729	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219	5560 			8401762	760230				AFCS ACTUATOR CHATTERING AND RATCHETY.						1	G	7	2 	3U				H1NE
1998081400556	19980814	00556	SW  	1998	8	14	HEEA0015351      	1	19980729	G	7722	206375007103	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3904L				5127AB	45597				NEEDLE STICKS AT ZERO ON TOT INDICATOR.						1	G	7	1 	3U				H2SW
1998081400469	19980814	00469		1998	8	14	HEEA0015352      	4	19980729	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S				80C6024	760035				AFCS ACTUATOR ONLY EXTENDS HALF WAY.						1	G	7	2 	3U				H1NE
1998081400470	19980814	00470	NE  	1998	8	14	HEEA0015353      	1	19980729	G	6700	7690001822103	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										CYCLIC TRIM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K				811106	760047				CANNOT ADJUST TRIM ACTUATOR TO PROPER SETTINGS.						1	G	7	2 	3U				H1NE
1998081400557	19980814	00557	SW  	1998	8	14	HEEA0015354      	1	19980729	G	2844	124044	INDICATOR       			BELL  	212   	212         	1181420	SW  										FUEL PRESSURE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S				79M0500	30953				FUEL PRESSURE INDICATOR HAS EXCESSIVE FRICTION ERROR.						1	G	7	1 	4U				H4SW
1998081400558	19980814	00558	SW  	1998	8	14	HEEA0015355      	1	19980729	G	7931	206075677103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE OIL	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116L				91060767	51529				STICKS AND PRESSURE READS HIGH AT HIGH END.						1	G	7	1 	3U				H2SW
1998081400559	19980814	00559		1998	8	14	HEEA0015356      	4	19980729	G	3413	843676R	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH	804  			3182B	53177				CLIMB RATE INDICATOR NEEDLE STICKS EXCESSIVELY.						1	G	7	1 	3U			O	H2SW
1998081400560	19980814	00560	SW  	1998	8	14	HEEA0015357      	1	19980729	G	2420	206075447007	REGULATOR       			BELL  	206   	206L1       	1182107	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27702				AL1445	45300				GENERATOR DROPPING OFF LINE.						1	G	7	1 	3U				H2SW
1998081400561	19980814	00561	SW  	1998	8	14	HEEA0015358      	1	19980729	G	2822	164A199	PUMP            			BELL  	206   	206L1       	1182107	SW  										FUEL BOOST	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	10778				218	45391				BOOST PUMP FAILED IN FLIGHT.						1	G	7	1 	3U				H2SW
1998081400562	19980814	00562		1998	8	14	HEEA0015359      	4	19980729	G	3416	D120P2T	ENCODER         			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH				75096	53038				ENCODER READS HIGH OUT OF TOLERANCE.						1	G	7	1 	3U			O	H2SW
1998081400563	19980814	00563	SW  	1998	8	14	HEEA0015360      	1	19980729	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1077A				117	45382				TOT INDICATOR HAS NO NEEDLE MOVEMENT, STUCK AT ZERO.						1	G	7	1 	3U				H2SW
1998081400471	19980814	00471		1998	8	14	HEEA0015361      	4	19980729	G	2211	4008519916	COMPUTER        			BEECH 	200   	200BEECH    	1152920	CE  										AUTOPILOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	789DS				81123133	BB478				AUTOPILOT OSCILLATES IN ROLL.  TIME SINCE REPAIR, 95:05 HOURS.						1	L	7	2 	4T				A24CE
1998081400564	19980814	00564	SW  	1998	8	14	HEEA0015362      	1	19980729	G	2434	51539002N	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  										NR 2 GENERATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1082G				6596	31109				NR 2 GENERATOR INOPERATIVE.						1	G	7	1 	4U				H4SW
1998081400565	19980814	00565	SW  	1998	8	14	HEEA0015363      	1	19980729	G	5512	206023119151	SKIN            			BELL  	206   	206L1       	1182107	SW  										STAB ASSY	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2764F				PH116	45279				STABILIZER ASSEMBLY SEPARATED AND DELAMINATED ON LOWER SIDE.						1	G	7	1 	3U				H2SW
1998081400566	19980814	00566	SW  	1998	8	14	HEEA0015364      	1	19980729	G	2435	2CM272B1	STARTER         			BELL  	214   	214ST       	1182106	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T	168  			98A1380	28101				STARTER KICKS OUT IN START, INTERMITTENT WILL NOT MOTOR.						2	G	7	2 	4U				H10SW
1998081400472	19980814	00472	NE  	1998	8	14	HEEA0015365      	1	19980729	G	2840	23356	SWITCH          			SKRSKY	S76   	S76A        	8143006	NE  										FUEL PRESSURE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S				1622	760035				SWITCH MALFUNCTION CAUSING FUEL PRESSURE LIGHT TO FLICKER.						1	G	7	2 	3U				H1NE
1998081400473	19980814	00473		1998	8	14	HEEA0015366      	4	19980729	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ				78125916	760231				AFCS ACTUATOR CHATTERS EXCESSIVELY.						1	G	7	2 	3U				H1NE
1998081400567	19980814	00567		1998	8	14	HEEA0015367      	4	19980729	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N				7137	33002				TRANSCEIVER WILL NOT TEST AND RECEIVE.						1	G	7	2 	4U				H4SW
1998081400568	19980814	00568		1998	8	14	HEEA0015368      	4	19980729	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N				4293	33002				TRANSCEIVER WILL NOT TRANSMIT.						1	G	7	2 	4U				H4SW
1998081400569	19980814	00569		1998	8	14	HEEA0015369      	4	19980729	G	3423	CB2100T6D	COMPASS         			BELL  	412   	412         	1182202	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH				B7419	33150				COMPASS HAS INCORRECT READINGS.						1	G	7	2 	4U				H4SW
1998081400662	19980814	00662	EU  	1998	8	14	HEEA0015370      	1	19980729	G	7100	4545005	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE COMPART	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8197X				1232	S808				VALVE STICKS, SOLENOID INOPERATIVE.						1	G	7	2 	3U				H3EU
1998081400663	19980814	00663	EU  	1998	8	14	HEEA0015371      	1	19980729	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH				0700	7050				CONROL UNIT HAS INTERMITTENT LIGHT SURGES.						1	G	7	2 	3U				H13EU
1998081400570	19980814	00570	SW  	1998	8	14	HEEA0015372      	1	19980729	G	2913	206076373001	PUMP            			BELL  	206   	206L1       	1182107	SW  										HYD	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Q				4928	45187				HYDRAULIC PUMP DRIVE SHAFT STUCK IN TACH GEN AND SPLINES WORN.						1	G	7	1 	3U				H2SW
1998081400571	19980814	00571	SW  	1998	8	14	HEEA0015373      	1	19980729	G	7722	35712519131	INDICATOR       			BELL  	412   	412         	1182202	SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N				1205A	33002				ITT GAUGE UNIT WILL NOT INDICATE.						1	G	7	2 	4U				H4SW
1998081400572	19980814	00572		1998	8	14	HEEA0015374      	4	19980729	G	2312	6222078001	TRANSCEIVER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	515KA				17483	51048				VHF DOES NOT TRANSMIT OR RECEIVE.						1	G	7	1 	3U				H2SW
1998081400573	19980814	00573	SW  	1998	8	14	HEEA0015375      	1	19980729	G	7722	3030083	COMPENSATOR     			BELL  	212   	212         	1181420	SW  										ENGINE TIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U				6697010	31122				TRIM COMPENSATOR WILL NOT BRING TEMPERATURE ANY LOWER THAN 75 CHANGE.						1	G	7	1 	4U				H4SW
1998081400574	19980814	00574	SW  	1998	8	14	HEEA0015376      	1	19980729	G	6240	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N				174	33002				TRIPLE TACHOMETER HAS ERRATIC MOVEMENT ON ALL NEEDLES.						1	G	7	2 	4U				H4SW
1998081400575	19980814	00575		1998	8	14	HEEA0015377      	4	19980729	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008				4537	36004				INDICATOR'S TURN NEEDLE STAYS DEFLECTED.						1	G	7	2 	4U				H4SW
1998081400576	19980814	00576		1998	8	14	HEEA0015378      	4	19980729	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	OUT OF ADJUST   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008				81914	36004				ADI CHATTERS AND IS VERY LOOSE IN ADJUSTMENT.						1	G	7	2 	4U				H4SW
1998081400474	19980814	00474	NE  	1998	8	14	HEEA0015379      	1	19980729	G	3150	7655001001103	CAUTION PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219				078	760230				CANNOT CANCEL MASTER CAUTION LIGHT ON NR 5 PACK.						1	G	7	2 	3U				H1NE
1998081400475	19980814	00475	NE  	1998	8	14	HEEA0015380      	1	19980729	G	3150	7655001001103	CAUTION PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ				367	760231				MASTER CAUTION LIGHT WILL NOT ILLUMINATE ON CONTROL PANEL.						1	G	7	2 	3U				H1NE
1998081400577	19980814	00577	SW  	1998	8	14	HEEA0015381      	1	19980729	G	2913	212076011001	PUMP            			BELL  	412   	412         	1182202	SW  										HYD SYSTEM	VIBRATING       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH	8553 			AU30D14244E	33150				HYDRAULIC PUMP CAUSING HIGH FREQUENCY VIBRATION.						1	G	7	2 	4U				H4SW
1998081400578	19980814	00578	SW  	1998	8	14	HEEA0015382      	1	19980729	G	2913	214075334101	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYD SYSTEM	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806				MX403343	28140				METAL CONTAMINATION IN FILTERS IN HYDRAULIC PUMP.						2	G	7	2 	4U				H10SW
1998081400579	19980814	00579	SW  	1998	8	14	HEEA0015383      	1	19980729	G	6240	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z				8108105	36019				ROTOR TACH INOPERATIVE.  UNIT FUNCTION CHECKED BAD, ROTOR NEEDLE STUCK.						1	G	7	2 	4U				H4SW
1998081400664	19980814	00664	EU  	1998	8	14	HEEA0015384      	1	19980729	G	7714	DL41240	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E				1147	S806				NEEDLES NOT MOVING, NO INDICATION ON RPM INDICATOR.						1	G	7	2 	3U				H3EU
1998081400476	19980814	00476		1998	8	14	HEEA0015385      	4	19980729	G	3455	6222362001	RECEIVER        			KING A														COCKPIT ADF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	30PH				14893	BB635				RECEIVER INDICATOR WILL NOT POINT.
1998081400580	19980814	00580		1998	8	14	HEEA0015386      	4	19980729	G	3423	CB2100T6D	COMPASS         			BELL  	222   	222U        	1182140	SW  										COCKPIT	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6992				B1040	47521				COMPASS, AIR BUBBLE IN 10 ERROR.						1	G	7	2 	3U				H9SW
1998081400581	19980814	00581		1998	8	14	HEEA0015387      	4	19980729	G	3416	6221205004	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T				323	33112				ALTIMETER NEEDLE WILL NOT SHOW ABOVE 2000.						1	G	7	2 	4U				H4SW
1998081400477	19980814	00477		1998	8	14	HEEA0015388      	4	19980729	G	3421	7660002113102	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U				1375	760167				VERTICAL GYRO PRECESSES IN FLIGHT.						1	G	7	2 	3U				H1NE
1998081400478	19980814	00478		1998	8	14	HEEA0015389      	4	19980729	G	3416	212070238003	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S				C502	760035				ALTIMETER INDICATOR DEFECTIVE.  EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H1NE
1998081400665	19980814	00665	EU  	1998	8	14	HEEA0015390      	1	19980729	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117B1     	5626012	EU  										ENGINE N1	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL				220	7198				GAUGE STICKING AT ZERO ON N1 INDICATOR WHEN POWER SHUT OFF.						1	G	7	2 	3U				H13EU
1998081400582	19980814	00582		1998	8	14	HEEA0015391      	4	19980729	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L				25190	33023				HSI INDICATOR CARD STICKS DURING TURNS.						1	G	7	2 	4U				H4SW
1998081400479	19980814	00479	NE  	1998	8	14	HEEA0015392      	1	19980729	G	2430	7655009006105	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U				9079A	760167				DC CONTROL UNIT WILL NOT BRING GENERATOR ON LINE.						1	G	7	2 	3U				H1NE
1998081400583	19980814	00583		1998	8	14	HEEA0015393      	4	19980729	G	2562	ELT910	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										ELT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	42EA				11774	51542				ELT WILL NOT RESET.						1	G	7	1 	3U				H2SW
1998081400584	19980814	00584	SW  	1998	8	14	HEEA0015394      	1	19980729	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N				270BA	45267				TOT INDICATOR INTERMITTENT.						1	G	7	1 	3U				H2SW
1998081400480	19980814	00480		1998	8	14	HEEA0015395      	4	19980729	G	3416	212070238007	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V				C12	760158				INDICATOR HAS EXCESSIVE FRICTION AND KNOB IS HARD TO TURN.						1	G	7	2 	3U				H1NE
1998081400481	19980814	00481		1998	8	14	HEEA0015396      	4	19980729	G	2210	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342				1159M	760096				NR 2 PITCH KICKS ON VERTICAL GYRO.						1	G	7	2 	3U				H1NE
1998081400585	19980814	00585	SW  	1998	8	14	HEEA0015397      	1	19980729	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT TOT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N				205	45267				TOT INDICATOR INTERMITTENT AND GLASS FACE CRACKED.						1	G	7	1 	3U				H2SW
1998081400666	19980814	00666	EU  	1998	8	14	HEEA0015398      	1	19980729	G	2913	4002001	SPLINE          			BOLKMS	105   	BO105S      	5626006	EU  										HYD PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G				AZ67	S853				SPLINE WORN ON HYDRAULIC PUMP.						1	G	7	2 	3U				H3EU
1998081400586	19980814	00586		1998	8	14	HEEA0015399      	4	19980729	G	2211	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F				81060381	33073				NR 2 AFCS WOULD NOT LATCH.						1	G	7	2 	4U				H4SW
1998081400482	19980814	00482	NE  	1998	8	14	HEEA0015400      	1	19980729	G	2160	7650007903102	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										AIR SHUTOFF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217				P204	760229				CIRCUIT BREAKER TRIPPED ON SHUT-OFF VALVE.						1	G	7	2 	3U				H1NE
1998081400483	19980814	00483		1998	8	14	HEEA0015401      	4	19980729	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ				1073M	760231				ADI INOPERATIVE.						1	G	7	2 	3U				H1NE
1998081400587	19980814	00587	SW  	1998	8	14	HEEA0015402      	1	19980729	G	6240	206075681117	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8593X				0500	51509				DUAL TACHOMETER, ONE-HALF NEEDLE WIDTH SPLIT AT 100 PERCENT.						1	G	7	1 	3U				H2SW
1998081400484	19980814	00484	NE  	1998	8	14	HEEA0015403      	1	19980729	G	6220	7610608000049	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1547D				A06101468	760077				MAIN ROTOR DAMPER LEAKING.						1	G	7	2 	3U				H1NE
1998081400485	19980814	00485	NE  	1998	8	14	HEEA0015404      	1	19980729	G	2160	7650007903102	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										AIR SHUTOFF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217	482  			1593	760229				SHUT-OFF VALVE WILL NOT CLOSE.						1	G	7	2 	3U				H1NE
1998081400667	19980814	00667	EU  	1998	8	14	HEEA0015412      	1	19980730	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH ROD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				WORN BEARINGS FOUND ON ROD, PITCH CONTROL.						1	G	7	1 	3U				H9EU
1998081900065	19980819	00065	SW  	1998	8	19	HEEA0015413      	1	19980730	G	5347	214031277129S	TRACK           			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	825H					28137				LOWER OUTBOARD FLANGE TOO NARROW TO PICK UP FASTENERS.						2	G	7	2 	4U			 	H10SW
1998081400486	19980814	00486		1998	8	14	HEEA0015414      	3	19980730	G	6140	503890571	TACH GEN        			KING A														PROPELLER	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH				11659	BL3				AT 200 TO 250 RPM, PROP FLUCTUATES, INDICATION ONLY.
1998081400588	19980814	00588	SW  	1998	8	14	HEEA0015415      	1	19980730	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498				2577263	36003				ENGINE RUNNING HOT HIGH ITT.						1	G	7	2 	4U				H4SW
1998081400589	19980814	00589	SW  	1998	8	14	HEEA0015416      	1	19980730	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023				98900	33080				ITT FLUCTUATES AND CANNOT ADJUST BIAS. S						1	G	7	2 	4U				H4SW
1998081400590	19980814	00590	SW  	1998	8	14	HEEA0015417      	1	19980730	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										DROOP COMP	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22751				H98174	3627				SCREW AT SPLIT BROKEN.						1	G	7	1 	3U				H2SW
1998081400591	19980814	00591		1998	8	14	HEEA0015418      	4	19980730	G	3414	214074152101	TRANSDUCER      			BELL  	214   	214ST       	1182106	SW  										AIRSPEED	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y				154	28139				AIRSPEED 3 FAILS.						2	G	7	2 	4U				H10SW
1998081400592	19980814	00592		1998	8	14	HEEA0015419      	4	19980730	G	3416	214175278101	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT ALTIM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008				142568	36004				ALTIMETER INDICATOR READS 10,000 FEET OFF AND LOOSE PARTS INSIDE.						1	G	7	2 	4U				H4SW
1998081400593	19980814	00593	SW  	1998	8	14	HEEA0015420      	1	19980730	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5005B				1566	45175				ACTUATOR WILL NOT RUN.						1	G	7	1 	3U				H2SW
1998081400594	19980814	00594	SW  	1998	8	14	HEEA0015422      	1	19980730	G	6320	412040111105	SEAL            			BELL  	412   	412         	1182202	SW  										M/R DRIVE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				MAIN ROTOR DRIVE SEAL LEAKING.						1	G	7	2 	4U				H4SW
1998081400595	19980814	00595	SW  	1998	8	14	HEEA0015423      	1	19980730	G	6320	412040111105	SEAL            			BELL  	412   	412         	1182202	SW  										M/R DRIVE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				MAIN ROTOR DRIVE SEAL LEAKING.						1	G	7	2 	4U				H4SW
1998081400487	19980814	00487	EA  	1998	8	14	HEEA0015424      	2	19980730	G	7210	3024780	GEARBOX         			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					COMBINING BOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805	9516 			CPGB2126	31106				GEARBOX HAS METAL ON NR 1 SIDE.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998081400596	19980814	00596		1998	8	14	HEEA0015425      	4	19980730	G	3416	6221205004	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T				676	33112				ALTIMETER HAS INTERMITTENT OPERATION.						1	G	7	2 	4U				H4SW
1998081400597	19980814	00597	SW  	1998	8	14	HEEA0015426      	1	19980730	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										M/R CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L				H8905	33006				ACTUATOR WILL NOT MOTOR IN FOR AND AFTER TEST.						1	G	7	2 	4U				H4SW
1998081400598	19980814	00598	SW  	1998	8	14	HEEA0015429      	1	19980730	G	2844	BSE20630G	TRANSDUCER      			BELL  	206   	206L3       	1182108	SW  										FUEL PRESSURE	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X				2781371	51508				TRANSDUCER READS LOW OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW
1998081400488	19980814	00488	NE  	1998	8	14	HEEA0015430      	1	19980730	G	2430	6153A	TRANSFORMER     			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V				1445	760158				TRANSFORMER WILL NOT COME ON LINE.						1	G	7	2 	3U				H1NE
1998081400489	19980814	00489	NE  	1998	8	14	HEEA0015432      	1	19980730	G	2430	7655009006105	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X				4477A	760050				GENERATOR WILL NOT RESET WHEN TESTING FOR GROUND FAULT OR OVER VOLTAGE.						1	G	7	2 	3U				H1NE
1998081400599	19980814	00599		1998	8	14	HEEA0015433      	4	19980730	G	2210	4020936903	TARSYN 333      			BELL  	412   	412         	1182202	SW  										3 AXIS	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608				82060170	33075				ADI PRECESSING AND INTERMITTENT FLAG.  VG BECOMES INVALID.						1	G	7	2 	4U				H4SW
1998081400600	19980814	00600		1998	8	14	HEEA0015434      	4	19980730	G	2562	ELT910	TRANSMITTER     			BELL  	206   	206B3       	1181506	SW  										ELT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22751				11778	3627				ELT TRANSMITTER COMES ON AT TIMES.						1	G	7	1 	3U				H2SW
1998081400668	19980814	00668		1998	8	14	HEEA0015435      	4	19980730	G	2562	ELT1104	ELT             			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S				54176	2777				G-SWITCH INOPERATIVE ON ELT.						1	G	7	1 	3U				H9EU
1998081400490	19980814	00490		1998	8	14	HEEA0015436      	4	19980730	G	3424	7690001808102	RATE GYRO       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ				80A4607	760231				NR 1 TEST NO INDICATION ON GYRO.						1	G	7	2 	3U				H1NE
1998081400601	19980814	00601		1998	8	14	HEEA0015437      	4	19980730	G	2370	9806019001	RECORDER        			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N	4590 			276	33002				CVR WILL NOT TEST.						1	G	7	2 	4U				H4SW
1998081400602	19980814	00602		1998	8	14	HEEA0015438      	4	19980730	G	3444	7001840903	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH				83050911	33150				RADAR ALT. INOPERATIVE OVER 100 FEET.						1	G	7	2 	4U				H4SW
1998081400603	19980814	00603	SW  	1998	8	14	HEEA0015439      	1	19980730	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										ENGINE	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z				1344001	36019				ITT READING TOO HIGH.						1	G	7	2 	4U				H4SW
1998081400604	19980814	00604		1998	8	14	HEEA0015440      	4	19980730	G	3421	1113034	INDICATOR       			BELL  	212   	212         	1181420	SW  										ATTITUDE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S				0615	30953				ATTITUDE INDICATOR SHOWS CONSTANT RIGHT HAND TURN.						1	G	7	1 	4U				H4SW
1998081400605	19980814	00605		1998	8	14	HEEA0015441      	4	19980730	G	3416	8503S20LW	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805				1325	31106				ALTIMETER INDICATOR HAS EXCESSIVE FRICTION ERROR.						1	G	7	1 	4U				H4SW
1998081400606	19980814	00606	SW  	1998	8	14	HEEA0015442      	1	19980730	G	6320	206075188005	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5012V				934	45200				PRESSURE GAUGE READS APPROXIMATELY 181 POUNDS.  TOO LOW, LEAKS.						1	G	7	1 	3U				H2SW
1998081400491	19980814	00491		1998	8	14	HEEA0015443      	4	19980730	G	3413	RC30VIL	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1546G				0304642	760076				RATE OF CLIMB HAS EXCESSIVE CASE LEAKAGE.						1	G	7	2 	3U				H1NE
1998081400607	19980814	00607	SW  	1998	8	14	HEEA0015444      	1	19980730	G	7931	206075188005	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1072T				507	45385				LOW PRESSURE READING WHEN OIL BECOMES HOT.						1	G	7	1 	3U				H2SW
1998081400608	19980814	00608	SW  	1998	8	14	HEEA0015445      	1	19980730	G	7810	212061201011	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498				41621	36003				EJECTOR ASSEMBLY CRACKED AND BRACKET BROKEN.						1	G	7	2 	4U				H4SW
1998081400609	19980814	00609	SW  	1998	8	14	HEEA0015446      	1	19980730	G	6320	212075036101	INDICATOR       			BELL  	412   	412         	1182202	SW  										G/B OIL PRESS	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T				80G0260	33112				GEARBOX OIL PRESSURE NEEDLE FLUCTUATES.   TIME SINCE REPAIR, 42:40 HOURS.						1	G	7	2 	4U				H4SW
1998081400610	19980814	00610	SW  	1998	8	14	HEEA0015447      	1	19980730	G	3213	412050015109	SKIDTUBE        			BELL  	412   	412         	1182202	SW  										MLG	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				SKID TUBE CRACKED.						1	G	7	2 	4U				H4SW
1998081400611	19980814	00611	SW  	1998	8	14	HEEA0015448      	1	19980730	G	2842	EA4703709	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G				597	3610				TANK UNIT HAS CRACKED INSULATORS AND NOT READING CORRECTLY.						1	G	7	1 	3U				H2SW
1998081400612	19980814	00612	SW  	1998	8	14	HEEA0015449      	1	19980730	G	6330	214031614128	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										M/R TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T				LK1053	28101				TRANSMISSION PLATE ASSEMBLY HAS WORN RUBBER.						2	G	7	2 	4U				H10SW
1998081400613	19980814	00613	SW  	1998	8	14	HEEA0015450      	1	19980730	G	6330	214031614127	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										M/R TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T				LK1031	28101				TRANSMISSION PLATE ASSEMBLY HAS WORN RUBBER.						2	G	7	2 	4U				H10SW
1998081400614	19980814	00614	SW  	1998	8	14	HEEA0015451      	1	19980730	G	6320	204040102017	PINION ASSY     			BELL  	412   	412         	1182202	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH				A610	33197				TRANSMISSION PINION ASSEMBLY HAS WORN SEAL WEAR SLEEVE BEYOND LIMITS.						1	G	7	2 	4U				H4SW
1998081400615	19980814	00615	SW  	1998	8	14	HEEA0015452      	1	19980730	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6251X				HTS44894	51552				STROBE LIGHT DOES NOT WORK.						1	G	7	1 	3U				H2SW
1998081400669	19980814	00669	EU  	1998	8	14	HEEA0015453      	1	19980730	G	6320	7631955115	OIL PUMP        			BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5029H				414	S670				LOW OIL PRESSURE FOUND ON OIL PUMP.						1	G	7	2 	3U				H3EU
1998081400616	19980814	00616	SW  	1998	8	14	HEEA0015454      	1	19980730	G	2915	212076006007	VALVE ASSY      			BELL  	412   	412         	1182202	SW  										HYD PRESSURE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L				2262	33023				CONTACT PINS ON SOLENOID BROKEN.						1	G	7	2 	4U				H4SW
1998081400670	19980814	00670	EU  	1998	8	14	HEEA0015455      	1	19980730	G	3340	099800003	SEARCH LIGHT    			BOLKMS	105   	BO105S      	5626006	EU  										FUSELAGE	INTERMITTENT    	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	133AE				1895GB	S800				SEARCH LIGHT INTERMITTENT AND STAYS ON WHEN SWITCH IS OFF.						1	G	7	2 	3U				H3EU
1998081400492	19980814	00492		1998	8	14	HEEA0015456      	4	19980730	G	3454	066400700	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K				5747	760082				RECEIVER INOPERATIVE.						1	G	7	2 	3U				H1NE
1998081400493	19980814	00493		1998	8	14	HEEA0015457      	4	19980730	G	2210	7611113	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										YAW SLICE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K				79F7443	760082				NR 1 YAW INOPERATIVE.						1	G	7	2 	3U				H1NE
1998081400617	19980814	00617		1998	8	14	HEEA0015458      	4	19980730	G	3431	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT NAV	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008				1598	36004				WITH NR 2 NAVIGATION SWITCH ON, GREEN HSI POINTERS SHOW 10 DIFFERENCE.						1	G	7	2 	4U				H4SW
1998081900060	19980819	00060	NE  	1998	8	19	HEEA0015459      	1	19980730	G	5350	7660002110102	RADOME          			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03					243					HOLE FOR RADOME MISMANUFACTURED.						1	G	7	2 	3U			 	H1NE
1998081900066	19980819	00066	SW  	1998	8	19	HEEA0015460      	1	19980730	G	5610	M2063401	WINDSHIELD      			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										WINDSHIELD MISMANUFACTURED.  NO EDGE DISTANCE ON LOWER CORNERS, TOO SHORT.						1	G	7	1 	3U			 	H2SW
1998081400494	19980814	00494		1998	8	14	HEEA0015461      	4	19980730	G	2210	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H				1051M	760233				VERTICAL GYRO SLOW TO DIRECT.						1	G	7	2 	3U				H1NE
1998081400495	19980814	00495		1998	8	14	HEEA0015462      	4	19980730	G	3421	125780	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT ADI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U				1110	760167				ADI INDICATION RATCHETY.						1	G	7	2 	3U				H1NE
1998081400618	19980814	00618	SW  	1998	8	14	HEEA0015463      	1	19980730	G	7921	206075677103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										ENGINE OIL	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X				89030299	51495				PRESSURE INDICATOR READS 5 PSI HIGH.						1	G	7	1 	3U				H2SW
1998081400619	19980814	00619		1998	8	14	HEEA0015464      	4	19980730	G	3416	5934D1	ALTIMETER       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078C				6H779	45392				ALTIMETER HAS EXCESSIVE CASE LEAKAGE.						1	G	7	1 	3U				H2SW
1998081400671	19980814	00671		1998	8	14	HEEA0015465      	4	19980730	G	3424	RCA563B	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TURN/BANK	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5029H				880017	S670				TURN AND BACK INDICATOR DOES NOT LIGHT TRAY.						1	G	7	2 	3U				H3EU
1998081400620	19980814	00620	SW  	1998	8	14	HEEA0015466      	1	19980730	G	2437	209070264003	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608				80F0066	33075				NR 1 INDICATOR ON DUAL AMMETER WILL NOT READ.						1	G	7	2 	4U				H4SW
1998081400621	19980814	00621	SW  	1998	8	14	HEEA0015467      	1	19980730	G	6320	206033513001	LINK ASSY       			BELL  	206   	206L1       	1182107	SW  										M/R GEARBOX	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50034				B123500	45169				LINK ASSEMBLY HAS WORN SPINDLE.						1	G	7	1 	3U				H2SW
1998081400622	19980814	00622		1998	8	14	HEEA0015468      	4	19980730	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608				88112227	33075				AFCS COMPUTER KICKING IN PITCH.						1	G	7	2 	4U				H4SW
1998081400623	19980814	00623		1998	8	14	HEEA0015469      	4	19980730	G	2211	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					82070526					NR 1 HELIPILOT KICKS IN ROLL CHANNEL ON AFCS COMPUTER.						1	G	7	2 	4U				H4SW
1998081400624	19980814	00624	SW  	1998	8	14	HEEA0015470      	1	19980730	G	2611	3023131	SMOKE DETECTOR  			BELL  	214   	214ST       	1182106	SW  										CARGO BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N				23521	28106				SMOKE DETECTOR WILL NOT ILLUMINATE BAGGAGE LIGHT.						2	G	7	2 	4U				H10SW
1998081400625	19980814	00625	SW  	1998	8	14	HEEA0015471      	1	19980730	G	7714	206075681105	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										DUAL TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	205FC				KD075	51130				DUAL TACHOMETER TURBINE NEEDLE INTERMITTENTLY FALLS OFF.						1	G	7	1 	3U				H2SW
1998081400626	19980814	00626	SW  	1998	8	14	HEEA0015472      	1	19980730	G	7712	206075739103	TORQUEMETER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2249Z				683A	45753				TORQUE METER NEEDLE STICKS AROUND 40 PERCENT THROUGH UPPER RANGE.						1	G	7	1 	3U				H2SW
1998081400627	19980814	00627	SW  	1998	8	14	HEEA0015473      	1	19980730	G	6320	206075188005	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										XMSN OIL	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	HCBXL				3694	45219				PRESSURE GAUGE STICKS AT 50 PSI.						1	G	7	1 	3U				H2SW
1998081400628	19980814	00628	SW  	1998	8	14	HEEA0015474      	1	19980730	G	2430	206075447007	REGULATOR       			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	83MT				452	45492				WHEN VHF KEYED, LOADMETER GOES TO ZERO.						1	G	7	1 	3U				H2SW
1998081400629	19980814	00629		1998	8	14	HEEA0015475      	4	19980730	G	3160	7003430902	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M				87100997	28102				CRT HAS NO DISPLAY.						2	G	7	2 	4U				H10SW
1998081400630	19980814	00630		1998	8	14	HEEA0015476      	4	19980730	G	2312	069102404	TRANSCEIVER     			BELL  	206   	206L4       	1182110	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	CFVEF				45851	52071				VHF RADIO WILL NOT TURN OFF.						1	G	7	1 	3U			NC	H2SW
1998081400631	19980814	00631	SW  	1998	8	14	HEEA0015477      	1	19980730	G	6322	214076333107	MOTOR           			BELL  	214   	214ST       	1182106	SW  										BLOWER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805				0272	28141				HYDRAULIC MOTOR SLOW TURNING; WILL NOT TURN OUT OIL COOLER CAUTION LIGHT AT GROUND IDLE.						2	G	7	2 	4U				H10SW
1998081400632	19980814	00632		1998	8	14	HEEA0015478      	4	19980730	G	2211	4033089901	COMPUTER        			BELL  	214   	214ST       	1182106	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806				91101204	28140				COMPUTER INTERMITTENTLY UNCOMMANDED GO AROUND MODE CONDITION.						2	G	7	2 	4U				H10SW
1998081400672	19980814	00672		1998	8	14	HEEA0015479      	4	19980730	G	3421	060001500	GYRO            			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5029H				25484	S670				GYRO INTERMITTENTLY SHUTS DOWN.						1	G	7	2 	3U				H3EU
1998081400633	19980814	00633		1998	8	14	HEEA0015480      	4	19980730	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008				89876	36004				ATTITUDE INDICATOR INTERMITTENTLY STICKS IN ROLL.						1	G	7	2 	4U				H4SW
1998081400634	19980814	00634		1998	8	14	HEEA0015481      	4	19980730	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S				81111390	36002				AFCS COMPUTER WILL NOT ENGAGE.						1	G	7	2 	4U				H4SW
1998081400673	19980814	00673	EU  	1998	8	14	HEEA0015482      	1	19980730	G	7714	DL41239	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E				153A	S806				INDICATOR STICKS AT LOW RPM.						1	G	7	2 	3U				H3EU
1998081400635	19980814	00635	SW  	1998	8	14	HEEA0015483      	1	19980730	G	7712	412075008111	INDICATOR       			BELL  	412   	412         	1182202	SW  										DUAL TORQUE	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH				SD3190	33150				NR 1 NEEDLE ON TORQUE INDICATOR STICKS AT 30 PERCENT.						1	G	7	2 	4U				H4SW
1998081400636	19980814	00636	SW  	1998	8	14	HEEA0015484      	1	19980730	G	6240	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T				8105118E	33112				ROTOR NR 1 NEEDLE ON TRIPLE TACHOMETER STICKS AT ZERO.						1	G	7	2 	4U				H4SW
1998081400637	19980814	00637	SW  	1998	8	14	HEEA0015485      	1	19980730	G	7810	212061201012	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S				A468	33022				EJECTOR ASSEMBLY CRACKED.						1	G	7	2 	4U				H4SW
1998081400638	19980814	00638	SW  	1998	8	14	HEEA0015486      	1	19980730	G	7810	212061201011	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S				13000038	33022				EJECTOR ASSY CRACKED.						1	G	7	2 	4U				H4SW
1998081400674	19980814	00674	EU  	1998	8	14	HEEA0015487      	1	19980730	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721MB				069	S752				RPM AUDIO INDICATIONS NOT FUNCTIONING WHEN NR 1 SPLITS 12 PERCENT.						1	G	7	2 	3U				H3EU
1998081400675	19980814	00675	EU  	1998	8	14	HEEA0015488      	1	19980730	G	2510	AFG013176	INERTIA REEL    			BOLKMS	105   	BO105S      	5626006	EU  										HARNESS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131AE					S787				INTERTIA REEL WILL NOT RETRACT AND RELEASE.  CABLE FRAYED.						1	G	7	2 	3U				H3EU
1998081400639	19980814	00639	SW  	1998	8	14	HEEA0015489      	1	19980730	G	5510	206023119151	STAB ASSY       			BELL  	206   	206L1       	1182107	SW  										TAIL BOOM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH				A004079	45421				STABILIZER ASSEMBLY CORRODED BEYOND LIMITS.						1	G	7	1 	3U				H2SW
1998082800348	19980828	00348	SW  	1998	8	28	HEEA0015490      	1	19980813	G	7712	407375003107	INDICATOR       			BELL  	407   	407         		SW  										TORQUE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	57416					53070				AT LEAST HALF OF TORQUE INDICATOR LED LIGHTS BLINK OFF DURING FLIGHT.						1	G	7	1 	3U			O	H2SW
1998082800349	19980828	00349	SW  	1998	8	28	HEEA0015491      	1	19980813	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										M/R DRIVE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	57416					53070				MGT INDICATOR GOES BLANK AND GOES THROUGH LCD TEST MODE INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW
1998082800350	19980828	00350	SW  	1998	8	28	HEEA0015492      	1	19980813	G	7712	407375003107	INDICATOR       			BELL  	407   	407         		SW  										TORQUE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	403PH					53177				TORQUE INDICATOR INTERMITTENTLY INDICATING ZERO, LCD TEST GOOD, INDICATOR CAN SOMETIMES BE RESTROYED BY REMOVING AND RE-	APPLYING POWER.					1	G	7	1 	3U			O	H2SW
1998082800351	19980828	00351	SW  	1998	8	28	HEEA0015493      	1	19980813	G	2420	1820300150	SHUNT           			BELL  	230   	230         	1182149	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	230UN					23009				GENERATOR DROPS OFF LINE WITH HIGH VOLTAGE.						1	G	7	2 	3U			NC	H9SW
1998082800352	19980828	00352	SW  	1998	8	28	HEEA0015496      	1	19980813	G	6310	406040500123	FREEWHEEL       			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			NR	NOT REPORTED   	1			SW	03	141MA	1721 				53016				MAIN ROTOR FREEWHEEL UNIT LEAKING.						1	G	7	1 	3U			O	H2SW
1998082800441	19980828	00441	EU  	1998	8	28	HEEA0015500      	1	19980813	G	2510	350A77125805	SEAT            			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				COCKPIT SEAT CRACKED AT RIGHT SIDE.						1	G	7	1 	3U				H9EU
1998082800335	19980828	00335	SW  	1998	8	28	HEEA0015501      	1	19980813	G	2140	47127	SHUTOFF VALVE   			BELL  	407   	407         		SW  										HEATER SYS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	407MM					53060				SHUT-OFF VALVE INOPERATIVE.  HEATER WOULD NOT TURN ON WHEN POWER WAS DISTRIBUTED.						1	G	7	1 	3U			O	H2SW
1998082800353	19980828	00353	SW  	1998	8	28	HEEA0015502      	1	19980813	G	6500	406040339111	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				TAIL ROTOR HAS ROUGH BEARING.  SERIAL NUMBERS REMOVED ARE A98-0440 AND A98-0512.						1	G	7	1 	3U			O	H2SW
1998082800354	19980828	00354	SW  	1998	8	28	HEEA0015503      	1	19980813	G	6220	407010107103	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	1232 				53159				BEARING SEAT HAS BLUE EPOXY WORN OFF.						1	G	7	1 	3U			O	H2SW
1998082800355	19980828	00355	SW  	1998	8	28	HEEA0015504      	1	19980813	G	6320	214040806003	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				TRANSMISSION PRESSURE LIGHT WILL NOT GO OUT WHEN OIL PRESSURE GOES THROUGH 38 PSI.						1	G	7	1 	3U			O	H2SW
1998082800356	19980828	00356	SW  	1998	8	28	HEEA0015505      	1	19980813	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				EXHAUST DUCT CRACKED CAUSED BY WORKING RIVETS ON BLOWER HOUSING.						1	G	7	1 	3U			O	H2SW
1998082800442	19980828	00442	EU  	1998	8	28	HEEA0015508      	1	19980813	G	2911	704A34240015	ACCUMULATOR     			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				TAIL ROTOR ACCUMULATOR WILL NOT HOLD NITROGEN CHARGE.						1	G	7	1 	3U				H9EU
1998082800357	19980828	00357	SW  	1998	8	28	HEEA0015509      	1	19980813	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				STARTER HAS WORN BRUSHES, FOUND BRUSHES WERE HANGING UP AND EXCESSIVELY WORN.  ALSO FOUND FRICTION RING WORN.  REPAIRED 	BY PHI.					1	G	7	1 	3U			O	H2SW
1998082800358	19980828	00358	SW  	1998	8	28	HEEA0015510      	1	19980813	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH	573  				53209				FOUND STARTER WITH BRUSHES EXCESSIVELY WORN.  REPAIRED BY PHI.						1	G	7	1 	3U			O	H2SW
1998082800359	19980828	00359	SW  	1998	8	28	HEEA0015511      	1	19980813	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MAIN ROTOR BLADE DENT NEAR THE TRAILING EDGE AT STATION 123 ON THE LOWER SIDE.						1	G	7	1 	3U				H2SW
1998082800360	19980828	00360		1998	8	28	HEEA0015512      	4	19980813	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078C					45392				TRANSPONDER HAS WEAK SIGNAL AND FAILED 2 YEAR TRANSPONDER TEST. PERFORMED PRELIMINARY INSPECTION.  FOUND FREQUENCY AND P	ULSE WIDTH OUT OF SPECS, ALSO SHOWS FALSE PULSES.					1	G	7	1 	3U				H2SW
1998082800361	19980828	00361		1998	8	28	HEEA0015513      	4	19980813	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2761X					45283				TRANSPONDER WILL NOT REGISTER ANYTHING ON 60O TEST SET MODE A OR C.						1	G	7	1 	3U				H2SW
1998082800362	19980828	00362		1998	8	28	HEEA0015514      	4	19980813	G	3452	066106200	TRANSPONER      			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50182					45242				TRANSPONDER ALTITUDE REPORTING OFF BY 28,000 FEET.						1	G	7	1 	3U				H2SW
1998082800363	19980828	00363		1998	8	28	HEEA0015515      	4	19980813	G	3457	1624820	ANTENNA         			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1078D					45397				GPS ANTENNA CAUSES ANTENNA FAULT MESSAGE TO BE DISPLAYED ON RECEIVER.						1	G	7	1 	3U				H2SW
1998082800364	19980828	00364	SW  	1998	8	28	HEEA0015516      	1	19980813	G	5312	205032853009	BULKHEAD        			BELL  	212   	212         	1181420	SW  										FUSELAGE	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BULKHEAD DENTS IN RADIUS BEYOND LIMITS.						1	G	7	1 	4U				H4SW
1998082800365	19980828	00365	SW  	1998	8	28	HEEA0015517      	1	19980813	G	5230	206B9301	STRUCTURE       			BELL  	206   	206L1       	1182107	SW  										BAGGAGE DOOR	MISLOCATED      	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BAGGAGE DOOR HAS MISLOCATED LATCH HOLES.						1	G	7	1 	3U			 	H2SW
1998082800366	19980828	00366	SW  	1998	8	28	HEEA0015518      	1	19980813	G	2820	2C271	CARTRIDGE       			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	21497	870  				51518				AFTER INSTALLATION, FOUND CARTRIDGE TO BE LEAKING THROUGH CENTER SNAP RING AREA.						1	G	7	1 	3U				H2SW
1998082800367	19980828	00367	SW  	1998	8	28	HEEA0015519      	1	19980813	G	2820	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				BOOST PUMP NOISY OPERATION AND LOW FLOW.						1	G	7	1 	3U				H2SW
1998082800368	19980828	00368	SW  	1998	8	28	HEEA0015520      	1	19980813	G	6240	212070108007	INDICATOR       			BELL  	212   	212         	1181420	SW  										TRIPLE TACH	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5736J					31140				TRIPLE TACHOMETER , ALL NEEDLES HAVE ERRATIC MOVEMENT.						1	G	7	1 	4U				H4SW
1998082800336	19980828	00336	NE  	1998	8	28	HEEA0015521      	2	19980813	G	7323	25249994	GOVERNOR        			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1202T	14565				33112				ENGINE GOVERNOR INDUCING TORQUE SPLITS.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998082800369	19980828	00369	SW  	1998	8	28	HEEA0015522      	1	19980813	G	6240	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6559Z					36019				TRIPLE TACHOMETER, ALL NEEDLES ARE ERRATIC THROUGHOUT SCALE.						1	G	7	2 	4U				H4SW
1998082800370	19980828	00370		1998	8	28	HEEA0015523      	4	19980813	G	3421	5040017908	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	21498					36003				GYRO INDICATOR LIGHTS DO NOT WORK, ALSO IND. PRECESSES TO THE RIGHT. REPLACED ALL BEARINGS AND CALIBRATED UNIT.  REPAIRE	D 5 VOLTS LIGHTS.  BENCH CHECK GOOD.					1	G	7	2 	4U				H4SW
1998082800371	19980828	00371	SW  	1998	8	28	HEEA0015524      	1	19980813	G	2432	RG380E40	COVER           			BELL  	412   	412         	1182202	SW  										BATTERY	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BATTERY COVER ASSY BROKEN OFF.  SCRAPPED BATTERY.						1	G	7	2 	4U				H4SW
1998082800443	19980828	00443		1998	8	28	HEEA0015525      	4	19980813	G	3457	0845000000	GPS             			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6095S					2777				GPS DUMPS MEMORY AND DISPLAY GOES OUT INTERMITTENTLY.  FOUND NO BACKLIGHTING BEHIND DB BUTTON.						1	G	7	1 	3U				H9EU
1998082800444	19980828	00444		1998	8	28	HEEA0015526      	4	19980813	G	3457	0845000000	GPS             			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	911LK					7068				GPS DISPLAY BECOMES UNREADABLE, LETTERS AND FIGURES ARE SCRAMBLED.  FOUND ENTER BUTTON UNREADABLE.						1	G	7	2 	3U			NC	H13EU
1998082800445	19980828	00445	EU  	1998	8	28	HEEA0015527      	1	19980813	G	3213	10550001	BEARING RING    		1055000126  	BOLKMS	105   	BO105S      	5626006	EU  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				MLG BEARING RING CORRODED BEYOND LIMITS.  REPLACED WITH NEW BEARING RINGS.						1	G	7	2 	3U				H3EU
1998082800446	19980828	00446		1998	8	28	HEEA0015528      	4	19980813	G	2312	4000106010	CONTROL UNIT    			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	217UC					7152				ATTITUDE INDICATOR RADIO WILL SHUT OFF BY ITSELF.  PERFORMED PRELIMINARY INSPECTION.  FOUND BAD PHOTOCELL CAUSING DISPLA	Y TO FADE OUT TO JUST ABOUT UNREADABLE.  REPLACED PHOTOCELL RT1.  REPAIRED PROBLEM.  BENCH CHECK GOOD.					1	G	7	2 	3U				H13EU
1998082800372	19980828	00372		1998	8	28	HEEA0015529      	4	19980813	G	3421	5040017901	INDICATOR       			BELL  	407   	407         		SW  										ATTITUDE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH	746  				53198				SHOWS 5 DEGREE RIGHT TURN AND 3 DEGREE BAR RISE WHEN SETTLING.						1	G	7	1 	3U			O	H2SW
1998082800373	19980828	00373	GL  	1998	8	28	HEEA0015530      	2	19980813	G	7261	23063144	FILTER          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				FOUND OIL FILTER BYPASS INDICATIONS. SCRAPPED OIL FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998082800374	19980828	00374	GL  	1998	8	28	HEEA0015531      	2	19980813	G	7261	23063144	FILTER          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				SCAVENGE OIL FITLER BYPASS INDICATION.  SCRAPPED OIL FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998082800375	19980828	00375	GL  	1998	8	28	HEEA0015532      	2	19980813	G	7261	23063144	FILTER          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				FOUND OIL FILTER BYPASS BUTTON POPPED ON DAILY INSPECTION.  SCRAPPED OIL FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998082800376	19980828	00376	GL  	1998	8	28	HEEA0015533      	2	19980813	G	7261	23063144	FILTER          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				FILTER BYPASSING.  SCRAPPED OIL FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998082800377	19980828	00377	GL  	1998	8	28	HEEA0015534      	2	19980813	G	7261	23063144	FILTER          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				OIL FILTER BYPASS INDICATED TWO TIMES.  SCRAPPED OIL FILTER.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998082800378	19980828	00378		1998	8	28	HEEA0015535      	4	19980813	G	3421	5040017908	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	293CA									GYRO VALID FLAG WILL NOT PULL.  REPAIRED BY PHI, CALIBRATED, BENCH CHECK GOOD.						1	G	7	2 	4U				H4SW
1998082800379	19980828	00379	SW  	1998	8	28	HEEA0015536      	1	19980813	G	3212	212073533001	B-NUT           			BELL  	412   	412         	1182202	SW  										FLOAT	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				B-NUT CAME OFF TUBE ASSY DURING MANUAL INFLATION OF FLOATS.  REPLACED WITH SERVICEABLE TUBE ASSY.						1	G	7	2 	4U				H4SW
1998082800380	19980828	00380	SW  	1998	8	28	HEEA0015537      	1	19980813	G	6510	327211	DISC SET        			BELL  	206   	206L1       	1182107	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				DISC CORRODED AND PITTED.  REPLACED WITH SERVICEABLE PARTS.						1	G	7	1 	3U				H2SW
1998082800381	19980828	00381	SW  	1998	8	28	HEEA0015538      	1	19980813	G	3213	206053203101	CROSSTUBE       			BELL  	206   	206L1       	1182107	SW  										MLG	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				CORROSION AND PITTING DAMAGE AT SKID TUBE MOUNTING POINT EXCEEDING LIMITS.  SCRAPPED CROSSTUBE.						1	G	7	1 	3U				H2SW
1998082800382	19980828	00382	SW  	1998	8	28	HEEA0015539      	1	19980813	G	6720	206001713001	SUPPORT         			BELL  	206   	206L1       	1182107	SW  										COCKPIT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				SUPPORT HAS CORROSION AND PITTED BEYOND LIMITS.  REPLACED WITH SERVICEABLE SUPPORT.						1	G	7	1 	3U				H2SW
1998082800383	19980828	00383	SW  	1998	8	28	HEEA0015540      	1	19980813	G	6720	206001763001	BELLCRANK       			BELL  	206   	206L1       	1182107	SW  										TAIL ROTOR	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				BELLCRANK CHAFED BEYOND LIMITS.  SCRAPPED BELLCRANK AND REPLACED WITH SERVICEABLE PART.						1	G	7	1 	3U				H2SW
1998082800384	19980828	00384	SW  	1998	8	28	HEEA0015541      	1	19980813	G	6310	406340102101	CARBON SEAL     			BELL  	407   	407         		SW  										M/R DRIVE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03		420  								MAIN ROTOR DRIVE SEAL LEAKING.						1	G	7	1 	3U			O	H2SW
1998082800447	19980828	00447	EU  	1998	8	28	HEEA0015543      	1	19980814	G	7714	DL41240	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5421E					S806				TACHOMETER STICKS AT LOW RPM EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H3EU
1998082800385	19980828	00385		1998	8	28	HEEA0015544      	4	19980814	G	3431	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT NAV	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	142PH					33150				RECEIVER CAUSES THE NR 1 NAVIGATOR POINTER TO JUMP AROUND DURING LOCALIZER TEST.						1	G	7	2 	4U				H4SW
1998082800448	19980828	00448	EU  	1998	8	28	HEEA0015545      	1	19980814	G	3610	209072433103	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										BLEED AIR	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				BLEED AIR VALVE INTERMITTENTLY STICKS IN OPEN POSITION.						1	G	7	2 	3U				H3EU
1998082800386	19980828	00386	SW  	1998	8	28	HEEA0015546      	1	19980814	G	2840	473203003	SIGNAL COND     			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				TRANSFER PUMP LIGHT COMES ON IN DECENT.						1	G	7	2 	4U				H4SW
1998082800387	19980828	00387		1998	8	28	HEEA0015547      	4	19980814	G	3444	6223201001	RADIO ALTIMETER 			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				RADIO ALTIMETER DROPS OFF LINE.						1	G	7	2 	4U				H4SW
1998082800388	19980828	00388	SW  	1998	8	28	HEEA0015548      	1	19980814	G	2840	206063656001	TRANSMITTER     			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27702					45300				FUEL GAUGE READS ZERO.						1	G	7	1 	3U				H2SW
1998082800337	19980828	00337		1998	8	28	HEEA0015549      	4	19980814	G	3416	5035P2P42	ENCODER         			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	792CH					760193				ENCODER FLUCTUATES.						1	G	7	2 	3U				H1NE
1998082800389	19980828	00389	SW  	1998	8	28	HEEA0015550      	1	19980814	G	7722	3030083	COMPENSATOR     			BELL  	412   	412         	1182202	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				TOT COMPENSATOR CHECKS HIGH ABOVE 60 OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998082800338	19980828	00338	NE  	1998	8	28	HEEA0015551      	1	19980814	G	5630	7620710009192	WINDOW          			SKRSKY	S76   	S76A        	8143006	NE  										CABIN	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										WINDOW SCREW HOLE WILL NOT LINE UP WITH SCREW HOLE ON WINDOW FRAME.						1	G	7	2 	3U			 	H1NE
1998082800339	19980828	00339	NE  	1998	8	28	HEEA0015552      	1	19980814	G	5630	7620710009191	WINDOW          			SKRSKY	S76   	S76A        	8143006	NE  										CABIN	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										WINDOW SCREW HOLE WILL NOT LINE UP WITH SCREW HOLE ON WINDOW FRAME.						1	G	7	2 	3U			 	H1NE
1998082800390	19980828	00390	SW  	1998	8	28	HEEA0015553      	1	19980814	G	6410	212010750105	BLADE           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023	2416 				33080				SEPARATION AT TAIL ROTOR BLADE TIP.						1	G	7	2 	4U				H4SW
1998082800391	19980828	00391	SW  	1998	8	28	HEEA0015554      	1	19980814	G	5510	206023119151	STABILIZER      			BELL  	206   	206L1       	1182107	SW  										TAIL	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745S					45491				STABLIZER SEPARATED BEYOND LIMITS.						1	G	7	1 	3U				H2SW
1998082800392	19980828	00392		1998	8	28	HEEA0015555      	4	19980814	G	3454	071121701	NAV UNIT        			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				NAVIGATOR UNIT INOPERATIVE AND MISSING NUT PLATE ON CONNECTOR.						2	G	7	2 	4U				H10SW
1998082800393	19980828	00393		1998	8	28	HEEA0015556      	4	19980814	G	3454	071121701	NAV UNIT        			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				VOR WILL NOT POINT TO STATIONS.						2	G	7	2 	4U				H10SW
1998082800340	19980828	00340	NE  	1998	8	28	HEEA0015557      	2	19980814	G	7200	3017600	ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					POWER SECT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023	9227 				33080				REPAIR DUE TO OIL CONSUMPTION AND HIGH CYCLED COMPRESSOR TURBINE DISC.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998082800394	19980828	00394	SW  	1998	8	28	HEEA0015558      	1	19980814	G	2844	124044	INDICATOR       			BELL  	212   	212         	1181420	SW  										FUEL PRESSURE	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				INDICATOR FLUCTUATES AND DOES NOT RETURN TO ZERO WITH PRESSURE OFF AND POWER ON.						1	G	7	1 	4U				H4SW
1998082800395	19980828	00395	SW  	1998	8	28	HEEA0015559      	1	19980814	G	6240	212070108007	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	27805					31106				TACHOMETER INDICATOR NR 2 AND ROTOR NEEDLE WILL NOT COME UP.						1	G	7	1 	4U				H4SW
1998082800449	19980828	00449	EU  	1998	8	28	HEEA0015560      	1	19980814	G	2844	BSE206150G3	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4573B					S673				NO OUTPUT FROM TRANSDUCER.						1	G	7	2 	3U				H3EU
1998082800396	19980828	00396	SW  	1998	8	28	HEEA0015561      	1	19980814	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										TOT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2124Z					45646				TOT INDICATOR WILL NOT INDICATE.						1	G	7	1 	3U				H2SW
1998082800341	19980828	00341	NE  	1998	8	28	HEEA0015562      	1	19980814	G	7722	7645001076107	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342					760096				TOT NEEDLE STICKING DURING ENGINE START.						1	G	7	2 	3U				H1NE
1998082800397	19980828	00397	SW  	1998	8	28	HEEA0015563      	1	19980814	G	7712	206075739103	TORQUEMETER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	206FS					51506				TORQUE NEEDLE STICKS AT 14 PERCENT WHEN DECREASING PRESSURE.						1	G	7	1 	3U				H2SW
1998082800398	19980828	00398		1998	8	28	HEEA0015564      	4	19980814	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2148K					36001				GYRO TURN NEEDLE DOES NOT MOVE.						1	G	7	2 	4U				H4SW
1998082800399	19980828	00399		1998	8	28	HEEA0015565      	4	19980814	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	33008					36004				GYRO FAILED.  DOES NOT MOVE TURN NEEDLE MAX TO RIGHT.						1	G	7	2 	4U				H4SW
1998082800400	19980828	00400	SW  	1998	8	28	HEEA0015566      	1	19980814	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2135V					45657				DROOP COMPENSATOR ACTUATOR INOPERATIVE.						1	G	7	1 	3U				H2SW
1998082800401	19980828	00401	SW  	1998	8	28	HEEA0015567      	1	19980814	G	6330	214031614127	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										M/R XMSN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				MAIN ROTOR TRANSMISSION RUBBER CRACKED.						2	G	7	2 	4U				H10SW
1998082800402	19980828	00402	SW  	1998	8	28	HEEA0015568      	1	19980814	G	2121	214073917101	BLOWER          			BELL  	214   	214ST       	1182106	SW  										AIR DIST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6957Y					28139				BLOWER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998082800403	19980828	00403	SW  	1998	8	28	HEEA0015569      	1	19980814	G	6220	206011139001	BEARINGS        			BELL  	206   	206B3       	1181506	SW  										M/R ARM	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2285B					3642				WORN BEARINGS.						1	G	7	1 	3U				H2SW
1998082800404	19980828	00404	SW  	1998	8	28	HEEA0015570      	1	19980814	G	3350	214175140103	POWER SUPPLY    			BELL  	214   	214ST       	1182106	SW  										CABIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8045T					28101				POWER SUPPLY WILL NOT HOLD CHARGE.						2	G	7	2 	4U				H10SW
1998082800405	19980828	00405	SW  	1998	8	28	HEEA0015571      	1	19980814	G	2822	2C273	CARTRIDGE       			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				BOOST PUMP INTERNAL FAILURE.						1	G	7	2 	4U				H4SW
1998082800406	19980828	00406	SW  	1998	8	28	HEEA0015572      	1	19980814	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5006F					45181				BOOST PUMP INTERNAL FAILURE.						1	G	7	1 	3U				H2SW
1998082800407	19980828	00407	SW  	1998	8	28	HEEA0015573      	1	19980814	G	2822	2C271	CARTRIDGE       			BELL  	206   	206B3       	1181506	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3181J					3771				BOOST PUMP INTERNAL FAILURE.						1	G	7	1 	3U				H2SW
1998082800408	19980828	00408	SW  	1998	8	28	HEEA0015574      	1	19980814	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5005B					45175				BOOST PUMP INTERNAL FAILURE.						1	G	7	1 	3U				H2SW
1998082800409	19980828	00409	SW  	1998	8	28	HEEA0015575      	1	19980814	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L3       	1182108	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81SP					51029				BOOST PUMP LEAKING WITH AIRCRAFT ON GROUND AND PUMP OFF.						1	G	7	1 	3U				H2SW
1998082800410	19980828	00410	SW  	1998	8	28	HEEA0015576      	1	19980814	G	2822	2C271	CARTRIDGE       			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2777D					45299				BOOST PUMP INTERNAL FAILURE.						1	G	7	1 	3U				H2SW
1998082800411	19980828	00411		1998	8	28	HEEA0015577      	4	19980814	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA									AFCS COMPUTER YAW KICKS.						1	G	7	2 	4U				H4SW
1998082800412	19980828	00412	SW  	1998	8	28	HEEA0015578      	1	19980814	G	6330	214031614127	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										M/R XMSN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				M/R TRANSMISSION PLATE ASSY CRACKED.						2	G	7	2 	4U				H10SW
1998082800413	19980828	00413		1998	8	28	HEEA0015579      	4	19980814	G	2211	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3893N					33010				IN SAS MODE WHEN FORCE TRIM IS RELEASED, AIRCRAFT PITCHES NOSE UP.						1	G	7	2 	4U				H4SW
1998082800414	19980828	00414		1998	8	28	HEEA0015581      	4	19980814	G	3120	811B	DIGITAL CLOCK   			BELL  	412   	412         	1182202	SW  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				DIGITAL CLOCK UPPER LEFT SEGMENT ILLUMINATES VERY WEAK.						1	G	7	2 	4U				H4SW
1998082800415	19980828	00415		1998	8	28	HEEA0015582      	4	19980814	G	3120	811B	DIGITAL CLOCK   			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				DIGITAL CLOCK UPPER RIGHT SEGMENTS HAVE BROKEN FILAMENT.						1	G	7	2 	4U				H4SW
1998082800416	19980828	00416		1998	8	28	HEEA0015583      	4	19980814	G	2562	ELT910	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										ELT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				ELT CASE SEAL BROKEN.						1	G	7	1 	3U				H2SW
1998082800342	19980828	00342	NE  	1998	8	28	HEEA0015584      	1	19980814	G	7600	7690001880106	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E					760155				NR 1 TORQUE INTERMITTENTLY STICKS WHEN PULLING POWER.						1	G	7	2 	3U				H1NE
1998082800417	19980828	00417	SW  	1998	8	28	HEEA0015585      	1	19980814	G	6240	206076373001	SPLINES         			BELL  	206   	206L1       	1182107	SW  										TACH GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2135V					45657				TACHOMETER GENERATOR SPLINES WORN.						1	G	7	1 	3U				H2SW
1998082800418	19980828	00418		1998	8	28	HEEA0015586      	4	19980814	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				AFCS COMPUTER INTERMITTENT, FAILS TEST 10.2 ON SST.						1	G	7	2 	4U				H4SW
1998082800419	19980828	00419		1998	8	28	HEEA0015587      	4	19980814	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				AFCS WILL NOT ENGAGE.						1	G	7	2 	4U				H4SW
1998082800343	19980828	00343		1998	8	28	HEEA0015588      	4	19980814	G	3455	6222363001	ANTENNA LOOP    			SKRSKY	S76   	S76A        	8143006	NE  										ADF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				ADF NEEDLE NOT POINTING TOWARD STATION.  .						1	G	7	2 	3U				H1NE
1998082800420	19980828	00420	NE  	1998	8	28	HEEA0015589      	2	19980814	G	7320	214060326103	FUEL CONTROL    			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT72A       	30030	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				FUEL CONTROL WORN.						2	G	7	2 	4U	4	U		H10SW   	E8NE
1998082800421	19980828	00421		1998	8	28	HEEA0015590      	4	19980814	G	2562	DK100	BEACON          			BELL  	206   	206B3       	1181506	SW  										LOCATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	104PH					3622				BEACON WOULD NOT TEST WHEN INSTALLED IN MOUNT.						1	G	7	1 	3U				H2SW
1998082800422	19980828	00422	SW  	1998	8	28	HEEA0015591      	1	19980814	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				A/C FORCE TRIM INTERMITTENTLY WILL NOT RELEASE.						1	G	7	2 	4U				H4SW
1998082800423	19980828	00423	SW  	1998	8	28	HEEA0015592      	1	19980814	G	5510	206023119151A	STABILIZER      			BELL  	206   	206L3       	1182108	SW  										TAILBOOM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X	5943 				51508				STABILIZER CORRODED UNDER CENTER DOUBLER.						1	G	7	1 	3U				H2SW
1998082800424	19980828	00424	SW  	1998	8	28	HEEA0015593      	1	19980814	G	5330	206031124111	SKIN            			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				SKIN CORRODED AND SEPARATED.						1	G	7	1 	3U				H2SW
1998082800425	19980828	00425	SW  	1998	8	28	HEEA0015594      	1	19980814	G	5300	206032310109	FAIRING ASSY    			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FAIRING ASSY RECEIVED DAMAGED.  TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW
1998082800426	19980828	00426	SW  	1998	8	28	HEEA0015595      	1	19980814	G	7714	206075682107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										GAS PRODUCER	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6160Z					51610				TACHOMETER NEEDLE FLUCTUATES AND DROPS OFF.						1	G	7	1 	3U				H2SW
1998082800427	19980828	00427	SW  	1998	8	28	HEEA0015596      	1	19980814	G	2425	209070263003	INDICATOR       			BELL  	212   	212         	1181420	SW  										DUAL VOLT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				DUAL VOLT A/C NEEDLE HANGS WITH POWER OFF.						1	G	7	1 	4U				H4SW
1998082800428	19980828	00428	SW  	1998	8	28	HEEA0015597      	1	19980814	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRANSMISSION OIL	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				TRANSMISSION O8IL PRESSURE PSI NEEDLE STICKY AT 20 PSI.						1	G	7	2 	4U				H4SW
1998082800429	19980828	00429	SW  	1998	8	28	HEEA0015598      	1	19980814	G	7931	206075677103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116L					51529				INDICATOR STICKS AND PRESSURE READS HIGH AT HIGH END.						1	G	7	1 	3U				H2SW
1998082800430	19980828	00430	SW  	1998	8	28	HEEA0015599      	1	19980814	G	7931	206075677103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				INDICATOR PRESSURE INDICATOR READS 5 PSI HIGH.						1	G	7	1 	3U				H2SW
1998082800431	19980828	00431		1998	8	28	HEEA0015600      	4	19980814	G	3416	214175278101	ENCODER         			BELL  	412   	412         	1182202	SW  										COCKPIT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ENCODER INDICATOR OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998082800432	19980828	00432	SW  	1998	8	28	HEEA0015601      	1	19980814	G	6710	412001303101	ACTUATOR        			BELL  	412   	412         	1182202	SW  										CYCLIC CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				CYCLIC KICK IN PITCH MODE.						1	G	7	2 	4U				H4SW
1998082800433	19980828	00433	SW  	1998	8	28	HEEA0015602      	1	19980814	G	2435	23081018	STARTER         			BELL  	206   	206L1       	1182107	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	20898	14011				45721				STARTER HAS BURNT BRUSHES AND COMMUTER.						1	G	7	1 	3U				H2SW
1998082800344	19980828	00344		1998	8	28	HEEA0015603      	4	19980814	G	2200	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	KICKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U	5600 				760167				NR 1 YAW KICKS.						1	G	7	2 	3U				H1NE
1998082800345	19980828	00345		1998	8	28	HEEA0015604      	4	19980814	G	2200	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546K					760082				AFCS ACTUATOR INOPERATIVE.						1	G	7	2 	3U				H1NE
1998082800346	19980828	00346		1998	8	28	HEEA0015605      	4	19980814	G	2200	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U	11068				760167				ACTUATOR MALFUNCTION.						1	G	7	2 	3U				H1NE
1998082800347	19980828	00347		1998	8	28	HEEA0015606      	4	19980814	G	2200	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342	6739 				760096				AFCS ACTUATOR HARD OVER TO ONE SIDE.  WILL NOT MOVE.						1	G	7	2 	3U				H1NE
1998082800434	19980828	00434		1998	8	28	HEEA0015607      	4	19980814	G	3434	TS4001AL	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1077A					45382				INDICATOR TURN NEEDLE DOES NOT DEFLECT.						1	G	7	1 	3U				H2SW
1998082800435	19980828	00435	SW  	1998	8	28	HEEA0015608      	1	19980814	G	6720	7001482	CONTROL ROD     			BELL  	412   	412         	1182202	SW  										PITCH AXIS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				CYCLIC DOES NOT MOVE AFT WHEN BEEPING AFT.						1	G	7	2 	4U				H4SW
1998082800436	19980828	00436	SW  	1998	8	28	HEEA0015609      	1	19980814	G	6520	212040506005	CASE ASSY       			BELL  	212   	212         	1181420	SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										T/R GEARBOX SIGHT GLASS BORE, MOUNTING HOLE AND SURFACE OF MOUNTING SEAT ARE CORRODED.						1	G	7	1 	4U				H4SW
1998082800438	19980828	00438	SW  	1998	8	28	HEEA0015611      	1	19980814	G	6420	205012710001	BEARING         			BELL  	212   	212         	1181420	SW  										TAIL ROTOR	DEFLECTED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										T/R BEARING HAS DEFLECTED INNER RACE.						1	G	7	1 	4U				H4SW
1998082800450	19980828	00450	EU  	1998	8	28	HEEA0015612      	1	19980814	G	3150	ELT1104	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  										ELT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				ELT G-SWITCH INOPERATIVE.						1	G	7	1 	3U				H9EU
1998082800439	19980828	00439	SW  	1998	8	28	HEEA0015613      	1	19980814	G	2820	206063640101	VALVE           			BELL  	206   	206L1       	1182107	SW  										FUEL SYSTEM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				FUEL SYSTEM VALVE E FITTING BENT.						1	G	7	1 	3U				H2SW
1998082800440	19980828	00440	SW  	1998	8	28	HEEA0015615      	1	19980814	G	6420	NAS5774A	NUT             			BELL  	407   	407         		SW  										T/R  HUB	MISMANUFACTURED 	E			HEEA	K				NONE                    				O	W		OTHER                     	INADEQUATE Q C            		IN	INSP/MAINT     	1			SW	03	417PH	2267 				53038				2 EACH P/N NAS577-4A NUTS AND 2 EACH P/N NAS578-4B RETAINERS MISMANUFACTURED.  HUB, P/N 40702101105.						1	G	7	1 	3U			O	H2SW
1998090400514	19980904	00514	SW  	1998	9	4	HEEA0015617      	1	19980817	G	7930	1740352	INDICATOR       		174083905   	BELL  	206   	206L3       	1182108	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81SP					51029				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	1 	3U				H2SW
1998090400515	19980904	00515	SW  	1998	9	4	HEEA0015618      	1	19980817	G	7930	174035201	INDICATOR       		174000103   	BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2125M				4011	45649				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	1 	3U				H2SW
1998090400516	19980904	00516	SW  	1998	9	4	HEEA0015619      	1	19980817	G	7930	174035201	INDICATOR       		174000103   	BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1076T				487	45373				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	1 	3U				H2SW
1998090400517	19980904	00517	SW  	1998	9	4	HEEA0015620      	1	19980817	G	7930	174035201	INDICATOR       		174000103   	BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50046				4262	45173				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	1 	3U				H2SW
1998090400518	19980904	00518	SW  	1998	9	4	HEEA0015621      	1	19980817	G	7930	174035201	INDICATOR       		174000103   	BELL  	206   	206B3       	1181506	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22751				3990	3627				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	1 	3U				H2SW
1998090400588	19980904	00588	EU  	1998	9	4	HEEA0015622      	1	19980817	G	7930	174035201	INDICATOR       		174000103   	BOLKMS	105   	BO105S      	5626006	EU  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131AE				472	S787				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	2 	3U				H3EU
1998090400519	19980904	00519	SW  	1998	9	4	HEEA0015623      	1	19980817	G	7930	174035201	INDICATOR       		174000103   	BELL  	206   	206L1       	1182107	SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50034				420	45169				INDICATOR WAS REMOVED FROM BOWL AND CLEANED.  INSTALLED INDICATOR BACK ON BOWL, TESTED AND INDICATOR STILL DIDN'T WORK.						1	G	7	1 	3U				H2SW
1998090400498	19980904	00498		1998	9	4	HEEA0015624      	4	19980817	G	3457	81439000232	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT GPS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X	126  				760050				TO/FROM POINTER INOPERATIVE ON NAVIGATOR INDICATOR.						1	G	7	2 	3U				H1NE
1998090400520	19980904	00520		1998	9	4	HEEA0015625      	4	19980817	G	3457	0110005400	GPS             			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22425					45743				GPS WILL NOT SHOW DISTANCE.						1	G	7	1 	3U				H2SW
1998090400521	19980904	00521		1998	9	4	HEEA0015626      	4	19980817	G	2312	066106103	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2245Y					45751				FRONT PLATE BROKEN ON RADAR ALTIMETER.						1	G	7	1 	3U				H2SW
1998090400522	19980904	00522	SW  	1998	9	4	HEEA0015627      	1	19980817	G	5330	214031292160	PANEL           			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	825H					28137				THREE EACH DOUBLER RINGS ON BOTTOM OF PANEL BONDED ON 180 DEGREES OUT - SLOT ON RING NEEDS TO BE FACING OUTBOARD AND AFT	 CENTER ACCESS HOLE SEPARATED.					2	G	7	2 	4U				H10SW
1998090400523	19980904	00523	SW  	1998	9	4	HEEA0015628      	1	19980817	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				NR 1 NEEDLE INOPERATIVE ON INDICATOR.  TIME SINCE REPAIR 417:30 HOURS.						1	G	7	2 	4U				H4SW
1998090400589	19980904	00589		1998	9	4	HEEA0015629      	4	19980817	G	2312	4000102000	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4294R					S860				TRANSCEIVER HAS NO TRANSMIT AND NO SIDETONE.  PERFORMED PRELIMINARY INSPECTION, TROUBLESHOT UNIT AND FOUND WRONG AUDIO B	OARD IN UNIT.					1	G	7	2 	3U				H3EU
1998090400590	19980904	00590	EU  	1998	9	4	HEEA0015630      	1	19980817	G	2840	DK042	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81992					S827				TRANSMITTER FLUCTUATES AND TRANSMITS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H3EU
1998090400499	19980904	00499		1998	9	4	HEEA0015631      	4	19980817	G	2210	7690001802106	AFCS ACTUATOR   			SKRSKY	S76   	S76A        	8143006	NE  										YAW SLICE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U	6001 				760167				ACTUATOR INOPERATIVE.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND POTENTIOMETERS CHECKED BAD ON STRIP CHART.						1	G	7	2 	3U				H1NE
1998090400500	19980904	00500		1998	9	4	HEEA0015632      	4	19980817	G	2210	7683431	POTENTIOMETER   		769000180210	SKRSKY	S76   	S76A        	8143006	NE  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		459  			90051222					POTENTIOMETER CAUSING ACTUATOR TO KICK AND CHATTER.  FOUND POTS WERE BAD IN NULL POSITION.						1	G	7	2 	3U				H1NE
1998090400501	19980904	00501		1998	9	4	HEEA0015634      	1	19980817	G	6730	C4264282	SLEEVE          																	SERVO	MISINSTALLED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INCORRECT PART.  WASHER SUBSTITUTED FOR SLEEVE.
1998090400502	19980904	00502		1998	9	4	HEEA0015635      	1	19980817	G	6730	C4264282	SLEEVE          																	SERVO	MISINSTALLED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INCORRECT PART.  WASHER SUBSTITUTED FOR SLEEVE.
1998090400524	19980904	00524	GL  	1998	9	4	HEEA0015636      	2	19980817	G	7322	25490925	FUEL CONTROL    			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6610Y					51419				AIR LEAKING FROM DERICH ADJUSTMENT.  CAUSING EXCESSIVE ADJUSTMENT ON N2.  INSPECTED UNIT WHEN RECEIVED IN SHOP.  APPLIED	 SHOP AIR TO FUEL CONTROL AND LEAK CHECKED UNIT.  FOUND NO LEAKS AT START DERICH SECTION AS STATED IN DESCRIPTION OF DIF	FICULTY.  NOTE:  ONLY LEAK FOUND WAS AT THE PX BLEED COVER, AIR LEAKING FROM THIS COVER IS NORMAL.  UNIT BENCH TESTED SA	TISFACTORY.			1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400591	19980904	00591	NE  	1998	9	4	HEEA0015637      	2	19980817	G	7530	430110209	ACTUATOR        			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1B    	6OO30	NE  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FOUND PISTON PACKINGS TO BE HARD AND BRITTLE CAUSING PISTON SEALS TO RETRACT AND ALLOW AIR TO SEEP PAST THE PISTON.  REP	LACED PACKINGS AND SEALS WITH NEW PARTS.  UNIT TESTED OK PER TEST SPEC. NR 10809-01.					1	G	7	1 	3U	3	U		H9EU    	E19EU
1998090400525	19980904	00525	SW  	1998	9	4	HEEA0015638      	1	19980817	G	6210	214015357101	TRIM TAB ASSY   			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR BLADE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRIM TAB ASSEMBLY MISMANUFACTURED.  COULD NOT FIT THIS TAB ON M/R BLADE DUE TO IMPROPER BONDING.						2	G	7	2 	4U				H10SW
1998090400526	19980904	00526	SW  	1998	9	4	HEEA0015639      	1	19980817	G	6210	206015001107	BLADE           			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BLADE UNACCEPTABLE FOR PHI USE.  RECEIVED WITH FACTORY DEFECT.						1	G	7	1 	3U				H2SW
1998090400527	19980904	00527	SW  	1998	9	4	HEEA0015641      	1	19980817	G	2913	206076030101	SHAFT           			BELL  	206   	206L1       	1182107	SW  										HYD PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5007Y					45192				DRIVE SHAFT WORN.						1	G	7	1 	3U				H2SW
1998090400503	19980904	00503		1998	9	4	HEEA0015642      	4	19980817	G	3421	503842033	ARTIFICIAL HORIZ			BEECH 	200   	200CBEECH   	1152926	CE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	500PH					BL29				ARTIFICAL HORIZON SLOW TO ERECT.						1	L	7	2 	4T				A24CE
1998090400528	19980904	00528	SW  	1998	9	4	HEEA0015643      	1	19980817	G	7714	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				TRIPLE TACHOMETER'S NR 1 NEEDLE READS LOW AND   SPLITS.  TIME SINCE REPAIR 95:25 HOURS.						1	G	7	2 	4U				H4SW
1998090400529	19980904	00529	SW  	1998	9	4	HEEA0015644      	1	19980817	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				STEP ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400530	19980904	00530	SW  	1998	9	4	HEEA0015645      	1	19980817	G	2913	206076030101	SHAFT           			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				SHAFT SPLINE WORN.						1	G	7	1 	3U				H2SW
1998090400531	19980904	00531	SW  	1998	9	4	HEEA0015646      	1	19980817	G	2913	206076030101	PUMP            			BELL  	206   	206L1       	1182107	SW  										HYD PUMP	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5737T					45454				PUMP LEAKING.						1	G	7	1 	3U				H2SW
1998090400532	19980904	00532	SW  	1998	9	4	HEEA0015647      	1	19980817	G	2913	206076030101	SHAFT           			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251Y					51556				HYDRAULIC PUMP SHAFT WORN.						1	G	7	1 	3U				H2SW
1998090400533	19980904	00533	SW  	1998	9	4	HEEA0015648      	1	19980817	G	2913	206076030101	SHAFT           			BELL  	206   	206L3       	1182108	SW  										HYD PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8587X					51464				HYDRAULIC PUMP SHAFT WORN.						1	G	7	1 	3U				H2SW
1998090400534	19980904	00534	SW  	1998	9	4	HEEA0015649      	1	19980817	G	2913	206076030101	SPLINE          			BELL  	206   	206L1       	1182107	SW  										HYD PUMP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019G					45247				INTERNAL SPLINE WORN ON HYDRAULIC PUMP.						1	G	7	1 	3U				H2SW
1998090400535	19980904	00535	SW  	1998	9	4	HEEA0015650      	1	19980817	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										DROOP COMP	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745S					45491				ACTUATOR CORRODED IN SEVERAL AREAS.						1	G	7	1 	3U				H2SW
1998090400536	19980904	00536	SW  	1998	9	4	HEEA0015651      	1	19980817	G	6240	206076373001	TACH GEN        			BELL  	206   	206L1       	1182107	SW  										FLT CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2124Z					45646				NOISE FROM HYDRAULIC PUMP DRIVE END BEARINGS.						1	G	7	1 	3U				H2SW
1998090400537	19980904	00537	SW  	1998	9	4	HEEA0015652      	1	19980817	G	2432	39563001	BATTERY PACK    			BELL  	412   	412         	1182202	SW  										CABIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21498					36003				BATTERY VOLTAGE BELOW 18 VOLTS.						1	G	7	2 	4U				H4SW
1998090400592	19980904	00592		1998	9	4	HEEA0015653      	4	19980817	G	3416	A30	ENCODER         			BOLKMS	105   	BO105S      	5626006	EU  										ALTIMETER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				ALTIMETER HAS NO ENCODER OUTPUT.						1	G	7	2 	3U				H3EU
1998090400593	19980904	00593	EU  	1998	9	4	HEEA0015654      	1	19980817	G	2913	4002001	PUMP            			BOLKMS	105   	BO105S      	5626006	EU  										OIL SYSTEM	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911DD					S830				HYDRAULIC PUMP HAS WORN BEARING TRUNNIONS.						1	G	7	2 	3U				H3EU
1998090400538	19980904	00538	SW  	1998	9	4	HEEA0015655      	1	19980817	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				STEP ACTUATOR BURNED OUT OR WORN.						1	G	7	2 	4U				H4SW
1998090400539	19980904	00539	SW  	1998	9	4	HEEA0015656      	1	19980817	G	2841	412375001105	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				FUEL INDICATOR STICKS AT DIFFERENT LEVELS NEAR HIGH END.						1	G	7	2 	4U				H4SW
1998090400540	19980904	00540		1998	9	4	HEEA0015657      	4	19980817	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				RATE GYRO INDICATION FOUND TO BE UNRELIABLE, 1 FULL NEEDLE WIDTH OFF IN STRAIGHT AND LEVEL FLIGHT.						1	G	7	2 	4U				H4SW
1998090400594	19980904	00594		1998	9	4	HEEA0015658      	4	19980817	G	3442	78806059602	RADAR           			BOLKMS	117   	BK117A3     	5626015	EU  										E/E BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	911NC					7026				INDICATOR SAYS ERROR WHEN GOING THROUGH TEST MODE.						1	G	7	2 	3U				H13EU
1998090400541	19980904	00541	SW  	1998	9	4	HEEA0015659      	1	19980817	G	2140	209072433105	VALVE           			BELL  	214   	214ST       	1182106	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				VALVE DOES NOT OPEN.						2	G	7	2 	4U				H10SW
1998090400504	19980904	00504	NE  	1998	9	4	HEEA0015660      	1	19980817	G	3040	7655001013103	MOTOR           			SKRSKY	S76   	S76A        	8143006	NE  										WIPER	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				WIPER MOTOR DOESN'T MOTOR.						1	G	7	2 	3U				H1NE
1998090400505	19980904	00505	NE  	1998	9	4	HEEA0015661      	1	19980817	G	7330	PC820101	SIGNAL COND     			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					NR 2 ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				FUEL FLOW HAS NO INDICATION NR 2.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998090400506	19980904	00506	NE  	1998	9	4	HEEA0015662      	1	19980817	G	6210	7615009100042	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		12229								TIP CAP DOES NOT MATCH THE HOLES ON THE TIP RIB OR THE TIP BLOCK.						1	G	7	2 	3U				H1NE
1998090400542	19980904	00542		1998	9	4	HEEA0015663      	4	19980817	G	3416	6221205004	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				ALTIMETER INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400543	19980904	00543		1998	9	4	HEEA0015664      	4	19980817	G	3425	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				CONNECTOR BROKE FREE FROM INDICATOR HOUSING.						1	G	7	2 	4U				H4SW
1998090400544	19980904	00544		1998	9	4	HEEA0015665      	4	19980817	G	3425	1113025	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				HSI INDICATOR FAILS TEST 12.6 AND COURSE DIGITIZER OFFSET.						2	G	7	2 	4U				H10SW
1998090400545	19980904	00545	SW  	1998	9	4	HEEA0015666      	1	19980817	G	3340	A490ATSDF1428	POWER SUPPLY    			BELL  	206   	206L3       	1182108	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				STROBE LIGHT DOES NOT WORK.						1	G	7	1 	3U				H2SW
1998090400546	19980904	00546		1998	9	4	HEEA0015667      	4	19980817	G	3414	214074152101	TRANSDUCER      			BELL  	214   	214ST       	1182106	SW  										AIRSPEED	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				ELEVATOR CAUTION LIGHT COMES ON.						2	G	7	2 	4U				H10SW
1998090400547	19980904	00547	SW  	1998	9	4	HEEA0015668      	1	19980817	G	6330	214031614128	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										MOUNT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				PLATE ASSY CRACKED.						2	G	7	2 	4U				H10SW
1998090400548	19980904	00548	SW  	1998	9	4	HEEA0015669      	1	19980817	G	6330	214031614128	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				TORN RUBBER FOUND ON PLATE ASSEMBLY.						2	G	7	2 	4U				H10SW
1998090400549	19980904	00549	SW  	1998	9	4	HEEA0015670      	1	19980817	G	6330	214031614127	PLATE ASSY      			BELL  	214   	214ST       	1182106	SW  										MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				RUBBER CRACKED ON PLATE ASSY.						2	G	7	2 	4U				H10SW
1998090400550	19980904	00550	GL  	1998	9	4	HEEA0015671      	2	19980819	G	7320	VSB628CP	FADEC  HORN     			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				FADEC FAIL HORN AUDIO EXTREMELY WEAK.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998090400551	19980904	00551	SW  	1998	9	4	HEEA0015672      	1	19980819	G	6240	222375077119	TRANSMITTER     			BELL  	407   	407         		SW  										TORQUE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				TORQUE GAUGE READS ZERO AT ALL TIMES.						1	G	7	1 	3U			O	H2SW
1998090400552	19980904	00552	SW  	1998	9	4	HEEA0015675      	1	19980819	G	7120	407060111101	BIPOD MOUNT     			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				BIPOD MOUNT HAS WORN BEARING.						1	G	7	1 	3U			O	H2SW
1998090400553	19980904	00553	SW  	1998	9	4	HEEA0015676      	1	19980819	G	6300	406010421103	SPACER          			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				SPACERS WORN.						1	G	7	1 	3U			O	H2SW
1998090400554	19980904	00554	SW  	1998	9	4	HEEA0015677      	1	19980819	G	6300	406010417101	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				MAIN ROTOR BEARING WORN.						1	G	7	1 	3U			O	H2SW
1998090400555	19980904	00555	SW  	1998	9	4	HEEA0015678      	1	19980819	G	6300	406010417101	BEARING         			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				MAIN ROTOR BEARING WORN.						1	G	7	1 	3U			O	H2SW
1998090400556	19980904	00556	SW  	1998	9	4	HEEA0015679      	1	19980819	G	6321	406010429101	PIN             			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				DRIVE PIN WORN.						1	G	7	1 	3U			O	H2SW
1998090400557	19980904	00557	SW  	1998	9	4	HEEA0015680      	1	19980819	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				ONE EACH DISC CRACKED ON SECOND PACK FROM TAIL ROTOR GEARBOX.						1	G	7	1 	3U			O	H2SW
1998090400558	19980904	00558	SW  	1998	9	4	HEEA0015681      	1	19980819	G	2432	31908001	BATTERY         			BELL  	407   	407         		SW  										DC SYSTEM	DISCHARGED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				BATTERY HAS LOW VOLTAGE.  FOUND TWO CELLS WERE BURNT.						1	G	7	1 	3U			O	H2SW
1998090400559	19980904	00559	SW  	1998	9	4	HEEA0015682      	1	19980819	G	7930	407375005101	INDICATOR       			BELL  	407   	407         		SW  										XMSN OIL TEMP	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH	711  				53142				LED LIGHTS ON TRANS. OIL PRESSURE SIDE OF GAUGE INTERMITTENTLY GO OUT.  (TEST GOOD, YET WHEN CIRCUIT BREAKER IS PRESSED,	 PSI SIDE BARS LIGHT UP THEN FADE AWAY).					1	G	7	1 	3U			O	H2SW
1998090400560	19980904	00560	SW  	1998	9	4	HEEA0015683      	1	19980819	G	6322	406040320101	SHAFT           			BELL  	407   	407         		SW  										COOLER BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				SHAFT ASSEMBLY HAS WORN SPLINES.						1	G	7	1 	3U			O	H2SW
1998090400561	19980904	00561	SW  	1998	9	4	HEEA0015684      	1	19980819	G	6500	406040339111	BEARING         		406040320101	BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH				AFS755	53114				ROUGH BEARINGS.  SERIAL NUMBERS REMOVED ARE K97-0661 AND K97-0626.						1	G	7	1 	3U			O	H2SW
1998090400562	19980904	00562	SW  	1998	9	4	HEEA0015685      	1	19980819	G	6322	407040303105A	BEARINGS        			BELL  	407   	407         		SW  										COOLER BLOWER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				OIL COOLER BLOWER SHAFT BEARINGS ROUGH SENT TO BELL HELICOPTER TEXTRON FOR CREDIT AGAINST REPLACEMENT PART PURCHASED.						1	G	7	1 	3U			O	H2SW
1998090400507	19980904	00507	EU  	1998	9	4	HEEA0015686      	1	19980819	G	7714	645500051	TRANSMITTER     			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				TACHOMETER TRANSMITTER INTERMITTENT.						1	G	7	1 	3U				H9EU
1998090400595	19980904	00595	EU  	1998	9	4	HEEA0015687      	1	19980819	G	7722	56375600010	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				T4 INDICATOR INTERMITTENT.						1	G	7	1 	3U				H9EU
1998090400596	19980904	00596	EU  	1998	9	4	HEEA0015688      	1	19980819	G	3212	158172	BRACKET         			SNIAS 	350   	AS350B2     	8680813	EU  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				AFT FLOAT BRACKET WORN.						1	G	7	1 	3U				H9EU
1998090400597	19980904	00597	EU  	1998	9	4	HEEA0015689      	1	19980819	G	3212	158173	FLOAT BRACKET   			SNIAS 	350   	AS350B2     	8680813	EU  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				AFT FLOAT BRACKET WORN.						1	G	7	1 	3U				H9EU
1998090400598	19980904	00598	EU  	1998	9	4	HEEA0015690      	1	19980819	G	7110	350A58164301	BRACE ASSY      			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE COWL	BENT            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				BRACE STRUT BENT AND SEPARATING.						1	G	7	1 	3U				H9EU
1998090400563	19980904	00563	SW  	1998	9	4	HEEA0015694      	1	19980819	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				COUPLING HAS CRACKED DISC.						1	G	7	1 	3U			O	H2SW
1998090400564	19980904	00564	SW  	1998	9	4	HEEA0015695      	1	19980819	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				COUPLING HAS CRACKED DISC.						1	G	7	1 	3U			O	H2SW
1998090400565	19980904	00565	SW  	1998	9	4	HEEA0015696      	1	19980819	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW
1998090400566	19980904	00566	SW  	1998	9	4	HEEA0015697      	1	19980819	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				WORKING SHEARED RIVETS - CAUSING HOUSING TO CRACK.						1	G	7	1 	3U			O	H2SW
1998090400567	19980904	00567	SW  	1998	9	4	HEEA0015698      	1	19980819	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BLOWER HOUSING COMING APART.						1	G	7	1 	3U			O	H2SW
1998090400568	19980904	00568	SW  	1998	9	4	HEEA0015701      	1	19980819	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										FUEL QTY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				FUEL QUANTITY INDICATOR WORKS INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW
1998090400569	19980904	00569	SW  	1998	9	4	HEEA0015702      	1	19980819	G	5210	20898415	DOOR LATCH      			BELL  	407   	407         		SW  										FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				REPLACED TEMP REPAIR LATCH ROD.						1	G	7	1 	3U			O	H2SW
1998090400570	19980904	00570	SW  	1998	9	4	HEEA0015703      	1	19980819	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         		SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				EXHAUST STACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998090400571	19980904	00571	SW  	1998	9	4	HEEA0015704      	1	19980819	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				EXHAUST DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1998090400572	19980904	00572	SW  	1998	9	4	HEEA0015705      	1	19980819	G	7712	407375003107	INDICATOR       			BELL  	407   	407         		SW  										TORQUE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				TORQUEMETER STAYS ON ZERO.  TIME SINCE LAST REPAIR 17:00 HOURS.						1	G	7	1 	3U			O	H2SW
1998090400573	19980904	00573	SW  	1998	9	4	HEEA0015707      	1	19980819	G	6320	214040806003	SWITCH          			BELL  	407   	407         		SW  										M/R GEARBOX	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				LIGHT COMES ON INTERMITTENTLY ON PRESSURE SWITCH.						1	G	7	1 	3U			O	H2SW
1998090400574	19980904	00574	SW  	1998	9	4	HEEA0015708      	1	19980819	G	2510	222020763103	SEAT BACK       			BELL  	230   	230         	1182149	SW  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				SEAT BACK BROKEN (CRACKED).						1	G	7	2 	3U			NC	H9SW
1998090400599	19980904	00599	EU  	1998	9	4	HEEA0015709      	1	19980819	G	2821	432B124	FILTER          			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL SYSTEM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				TREADS ON BOWL STRIPPED.						1	G	7	1 	3U				H9EU
1998090400600	19980904	00600	EU  	1998	9	4	HEEA0015710      	1	19980819	G	6240	50071550020	SENSOR          			SNIAS 	350   	AS350B2     	8680813	EU  										ROTOR TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				BROKEN WIRE CONNECTOR ON TACHOMETER.						1	G	7	1 	3U				H9EU
1998090400601	19980904	00601	EU  	1998	9	4	HEEA0015711      	1	19980819	G	2500	350A7713450001	UPHOLSTERING    			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				UPHOLSTERY BROKEN AND CRACKED.						1	G	7	1 	3U				H9EU
1998090400602	19980904	00602	EU  	1998	9	4	HEEA0015712      	1	19980819	G	6220	704A33633109	SPHERICAL STOP  			SNIAS 	350   	AS350B2     	8680813	EU  										M/R HEAD	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R	1044 				2862				WEATHERIZED CRACKING AT SPHERICAL STOP.						1	G	7	1 	3U				H9EU
1998090400603	19980904	00603	EU  	1998	9	4	HEEA0015714      	1	19980819	G	2121	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  										AIR DIST	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				BLOWER INTERMITTENT (DEAD SPOT).						1	G	7	1 	3U				H9EU
1998090400604	19980904	00604	EU  	1998	9	4	HEEA0015715      	1	19980819	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH ROD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				ROD, PITCH CONTROL HAS WORN BEARINGS.						1	G	7	1 	3U				H9EU
1998090400605	19980904	00605	EU  	1998	9	4	HEEA0015716      	1	19980819	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										T/R PITCH ROD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				ROD, PITCH CONTROL HAS WORN BEARINGS.						1	G	7	1 	3U				H9EU
1998090400508	19980904	00508	GL  	1998	9	4	HEEA0015717      	2	19980820	G	7230	23007196	REAR SUPPORT    		23033193    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					MAJOR SEAL	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791				CAC91436	51465	CAE895165			ENGINE REMOVED DUE TO METAL IN OIL.  COMPRESSOR DISASSEMBLED DUE TO N-1 DRAG ON TEST CELL.  DISASSEMBLY INSPECTION REVEA	LED:  LIFTING AND FLAKING BEYOND SERVICEABLE LIMITS ON REAR SUPPORT MAJOR SEAL.  INSTALLED AN H-S TOOL & PARTS, INC. REA	R SUPPORT.				1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400509	19980904	00509	GL  	1998	9	4	HEEA0015718      	2	19980820	G	7313	23031866	NOZZLE          		23033185    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5742H				CAT70171	45476	CAE860128			ENGINE REMOVED DUE TO LOW POWER.  UPON INSPECTION OF TURBINE PARTS NOTED:  COATING LIFTING FROM NR 2 NOZZLE 1ST AND 2ND 	STAGE TIP PATH.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400510	19980904	00510	GL  	1998	9	4	HEEA0015719      	2	19980820	G	7313	23008054	NOZZLE          		23033185    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5742H				CAT70171	45476	CAE860128			ENGINE REMOVED DUE TO LOW POWER.  UPON INSPECTION OF TURBINE PARTS NOTED:  CRACKED BEYOND SERVICEABLE LIMITS ON NR 1 NOZ	ZLE VANES AND OUTER SHROUD.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400575	19980904	00575		1998	9	4	HEEA0015720      	4	19980820	G	3423	2593379001	COMPENSATOR     			BELL  	212   	212         	1181420	SW  										COMPASS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				PILOT COMPENSATOR DRIFTS OFF WHEN LANDING ON A STEEL DECK BY 70, ALSO THE NR 1 FUSE BLOWS.						1	G	7	1 	4U				H4SW
1998090400576	19980904	00576	SW  	1998	9	4	HEEA0015721      	1	19980820	G	5210	206033601118	DOOR            			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				DOOR ASSEMBLY CORRODED AND SEPARATED BEYOND REPAIR AT THIS STATION.						1	G	7	1 	3U				H2SW
1998090400577	19980904	00577		1998	9	4	HEEA0015722      	4	19980820	G	2312	064101900	TRANSCEIVER     			BELL  	206   	206L1       	1182107	SW  										E/E BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				MODULATION DISTORTED AT 85 PERCENT ON TRANSCEIVER.						1	G	7	1 	3U				H2SW
1998090400606	19980904	00606	EU  	1998	9	4	HEEA0015723      	1	19980820	G	2437	BE413	AMMETER         			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				AMMETER HAS INSULATOR CRACKED AND NEEDLE IS ERRATIC.						1	G	7	2 	3U				H3EU
1998090400511	19980904	00511	NE  	1998	9	4	HEEA0015724      	1	19980820	G	6300	L84102993	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				SEPARATION OF ELASTOMERIC BEARING.						1	G	7	2 	3U				H1NE
1998090400578	19980904	00578	SW  	1998	9	4	HEEA0015725      	1	19980820	G	2842	774000381	TANK UNIT       			BELL  	206   	206B3       	1181506	SW  										FUEL SYSTEM	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2269A					3608				TRANSMITTER IN FUEL TANK  TRANSMITS HIGH OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW
1998090400607	19980904	00607		1998	9	4	HEEA0015726      	4	19980820	G	3452	066106200	TRANSPONER      			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721MB					S752				TRANSCEIVER INOPERATIVE.						1	G	7	2 	3U				H3EU
1998090400579	19980904	00579	SW  	1998	9	4	HEEA0015727      	1	19980820	G	2840	473203003	SIGNAL COND     			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				FUEL TRANSFER LIGHT FLICKERS WITH TANKS EMPTY AND SWITCH ON OR OFF POSITION.						1	G	7	2 	4U				H4SW
1998090400580	19980904	00580		1998	9	4	HEEA0015728      	4	19980820	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50034					45169				TRANSPONDER WILL NOT TEST ON REPORT.						1	G	7	1 	3U				H2SW
1998090400581	19980904	00581		1998	9	4	HEEA0015729      	4	19980820	G	2312	7001840913	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				RCVR TRANSMITTER'S OUTPUT IS ERRATIC.						1	G	7	2 	4U				H4SW
1998090400582	19980904	00582		1998	9	4	HEEA0015730      	4	19980820	G	3425	1113025	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT HSI	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INSPECT AND REPAIR HSI INDICATOR, GS AND OFF FLAGS STICK.						1	G	7	1 	4U				H4SW
1998090400583	19980904	00583		1998	9	4	HEEA0015731      	4	19980820	G	3413	212070239001	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				RATE-OF CLIMB INDICATOR NEEDLE IS OFF.						1	G	7	1 	4U				H4SW
1998090400584	19980904	00584	SW  	1998	9	4	HEEA0015732      	1	19980820	G	7330	206075676117	INDICATOR       			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116L					51529				FUEL LOAD METER INOPERATIVE.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400585	19980904	00585	SW  	1998	9	4	HEEA0015733      	1	19980820	G	7722	35712519129	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	513EH					45421				REDLINE AND RED DOT FADED.  CHECK FOR PROPER OPERATION AND PROPER CALIBRATION.						1	G	7	1 	3U				H2SW
1998090400608	19980904	00608	EU  	1998	9	4	HEEA0015734      	1	19980820	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				CONTROL UNIT SHORTED AND TRIPPED CIRCUIT BREAKER.						1	G	7	2 	3U				H13EU
1998090400512	19980904	00512		1998	9	4	HEEA0015735      	4	19980820	G	2312	7001840913	TRANSCEIVER     																	COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVER/TRANSMITTER WILL NOT BECOME VALID.
1998090400513	19980904	00513	NE  	1998	9	4	HEEA0015736      	1	19980820	G	7330	PC820101	SIGNAL COND     			SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				SIGNAL CONDITIONER UNIT CAUSING NR 1 FLOWMETER TO PEG HIGH.						1	G	7	2 	3U	3	U		H1NE    	E1GL
1998090400586	19980904	00586		1998	9	4	HEEA0015737      	4	19980820	G	2370	9806019001	CVR             			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N	4014 				33002				TEST LIGHT ON CVR COMES ON.						1	G	7	2 	4U				H4SW
1998090400587	19980904	00587	SW  	1998	9	4	HEEA0015738      	1	19980821	G	2435	206062200113	STARTER         			BELL  	407   	407         		SW  										STARTER/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	1439 				53038				STARTER/GENERATOR ARCHING BADLY AND SOME TIMES WOULD NOT MOTOR.   INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND BRUSHES	 EXCESSIVELY WORN AND COMMUTATOR PITTED.					1	G	7	1 	3U			O	H2SW
1998090400636	19980904	00636	SW  	1998	9	4	HEEA0015740      	1	19980824	G	5320	206033110239	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	6161A					51611				STIFFENER MISMANUFACTURED.  AFT FLANGE OF EXTRUDED ANGLE TOO NARROW.						1	G	7	1 	3U			 	H2SW
1998090400637	19980904	00637		1998	9	4	HEEA0015741      	4	19980825	G	3452	066106200	TRANSPONER      			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5019F					45244				TRANSCEIVER DOES NOT TRANSMIT.  PERFORMED PRELIMINARY INSPECTION AND FOUND RECEIVER SENSITIVITY WEAK AND REPLY LIGHT BLI	NKS ALL THE TIME.					1	G	7	1 	3U				H2SW
1998090400638	19980904	00638	SW  	1998	9	4	HEEA0015742      	1	19980825	G	5330	206031141039	PANEL           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2758N					45267				PANEL ASSEMBLY MISMANUFACTURED.  PANEL WAS TRIMMED .1250 INCH TOO SMALL, COULD NOT GET GOOD EDGE DISTANCE FOR SCREW HOLE	S.					1	G	7	1 	3U			 	H2SW
1998090400639	19980904	00639	SW  	1998	9	4	HEEA0015743      	1	19980825	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	STUCK           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406EH					45183				TOT NEEDLE STICKS AT ZERO ON START UP, UNIT FUNCTION CHECKED BAD, ALSO STICKS AT 20 PERCENT.  TIME SINCE REPAIR 61:00 HO	URS.					1	G	7	1 	3U				H2SW
1998090400640	19980904	00640	SW  	1998	9	4	HEEA0015744      	1	19980825	G	7722	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8592X					51508				TOT INDICATOR HAS NO READINGS.						1	G	7	1 	3U				H2SW
1998090400641	19980904	00641	SW  	1998	9	4	HEEA0015745      	1	19980825	G	7722	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				TOT INDICATOR HAS NO LIGHTS.  UNIT FUNCTION CHECKED BAD, NEEDLE STICKS AT ZERO WHEN COLD.						1	G	7	1 	3U				H2SW
1998090400642	19980904	00642		1998	9	4	HEEA0015746      	4	19980825	G	3442	40008310105	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				RT FAULT DISPLAYED AND DOES NOT TRANSMIT.  PERFORMED PRELIMINARY INSPECTION.						2	G	7	2 	4U				H10SW
1998090400643	19980904	00643		1998	9	4	HEEA0015747      	4	19980825	G	3442	40008310105	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				TRANSCEIVER WILL NOT PAINT TARGETS AND WILL NOT TRANSMIT.  PERFORMED PRELIMINARY INSPECTION.						2	G	7	2 	4U				H10SW
1998090400644	19980904	00644	SW  	1998	9	4	HEEA0015748      	1	19980825	G	6710	206001191001	TUBE ASSY       			BELL  	206   	206L1       	1182107	SW  										M/R CONTROL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				CRACK IN TUBE P/N 206-001-191-003 AT CLEVIS END (TWO PLACES) .  ONE APPROX. 0.150 INCH LONG AND ONE 0.105 INCH.  REPLACE	D WITH SERVICEABLE TUBE ASSY.					1	G	7	1 	3U				H2SW
1998090400645	19980904	00645	SW  	1998	9	4	HEEA0015749      	1	19980825	G	6322	206061432109	IMPELLER        		206040370013	BELL  	206   	206L1       	1182107	SW  										BLOWER	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745S				PHI63	45491				BLOWER IMPELLER CORRODED.  SCRAPPED ASSY AND REPLACED WITH NEW ASSY.						1	G	7	1 	3U				H2SW
1998090400646	19980904	00646	SW  	1998	9	4	HEEA0015750      	1	19980825	G	6322	206061432109	IMPELLER        		206040370103	BELL  	206   	206L1       	1182107	SW  										BLOWER	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N				BT398	45267				BLOWER IMPELLER EXCESSIVELY CORRODED.  SCRAPPED ASSY AND REPLACED WITH NEW ASSY.						1	G	7	1 	3U				H2SW
1998090400647	19980904	00647		1998	9	4	HEEA0015752      	4	19980825	G	3416	1003511424	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				ALTIMETER READS 140 FEET HIGH AND HAS LOOSE PARTS INSIDE.						1	G	7	2 	4U				H4SW
1998090400648	19980904	00648	SW  	1998	9	4	HEEA0015753      	1	19980825	G	7931	209070262101	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				PRESSURE FLUCTUATES IN-FLIGHT, FUNCTION CHECK BAD, PRESSURE NEEDLE INDICATES HIGH AND FLUCTUATES.						1	G	7	2 	4U				H4SW
1998090400649	19980904	00649	SW  	1998	9	4	HEEA0015754      	1	19980825	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				NR 1 AND NR 2 NEEDLES OSCILLATE.  TIME SINCE REPAIR 239:45 HOURS.						1	G	7	2 	4U				H4SW
1998090400777	19980904	00777		1998	9	4	HEEA0015755      	4	19980825	G	3416	B4553110102	ENCODER         			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				ENCODER GIVES ERRONEOUS READINGS INTERMITTENTLY THROUGHOUT SCALE.						1	G	7	2 	3U				H13EU
1998090400650	19980904	00650		1998	9	4	HEEA0015757      	4	19980825	G	3422	103002201	GYRO            			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				ROTOR WILL NOT SPIN ON DIRECTIONAL GYRO.  TIME SINCE REPAIR 71:00 HOURS.						1	G	7	1 	3U			O	H2SW
1998090400651	19980904	00651		1998	9	4	HEEA0015758      	4	19980825	G	2312	064102300	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				VHF TRANSCEIVER INOPERATIVE - DOES NOT ILLUMINATE CONTROL DISPLAY.  PERFORMED PRELIMINARY INSPECTION.   FOUND ALL POWER 	SUPPLY VOLTAGES BAD.   TROUBLESHOT UNIT AND FOUND LIFTING DIODE CR107 WOULD GET POWER SUPPLY VOLTAGES TO COME UP.   ALSO	 FOUND WRONG DIODE INSTALLED FOR CR107.   REPLACED DIODE CR107.  DID NOT CURE PROBLEM.  ALSO REPLACED TRANSISTORS Q106 A	ND Q107.  NO HELP.			1	G	7	2 	4U				H4SW
1998090400609	19980904	00609		1998	9	4	HEEA0015759      	4	19980825	G	2210	7690001808102	RATE GYRO       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				ADI RT FLAG WILL NOT PULL.						1	G	7	2 	3U				H1NE
1998090400652	19980904	00652		1998	9	4	HEEA0015760      	4	19980825	G	3451	066106602	TRANSPONDER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				TRANSPONDER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998090400653	19980904	00653		1998	9	4	HEEA0015761      	4	19980825	G	3451	066106902	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					3005				INDICATOR TOTALLY INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400654	19980904	00654		1998	9	4	HEEA0015762      	4	19980825	G	3455	066104701	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT ADF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				RECEIVER HAS SCRATCHY RECEPTION.						1	G	7	2 	4U				H4SW
1998090400655	19980904	00655	SW  	1998	9	4	HEEA0015763      	1	19980825	G	6320	90093013	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										XMSN TEMP	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	20898					45721				PRESSURE READS HIGH OUT OF TOLERANCE.						1	G	7	1 	3U				H2SW
1998090400656	19980904	00656		1998	9	4	HEEA0015764      	4	19980825	G	3424	A593002	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2272J					3620				TURN INDICATOR INOPERATIVE.						1	G	7	1 	3U				H2SW
1998090400610	19980904	00610	GL  	1998	9	4	HEEA0015765      	2	19980826	G	7250	6886407	WHEEL           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FIRST STAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U	1212 			CAT37107	S678	CAE821700F			ENGINE REMOVED DUE TO LOW POWER.  UPON INSPECTION OF TURBINE PARTS NOTED:  MINOR SULPHIDATION ON 12 BLADES.  SCRAPPED NR	 1 WHEEL.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998090400657	19980904	00657	NE  	1998	9	4	HEEA0015766      	2	19980826	G	7320	214060326103	FUEL CONTROL    			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT72A       	30030	NE  					ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				FUEL CONTROL ASSEMBLY HAS FLAT SPOTS NEAR CUT OFF.						2	G	7	2 	4U	4	U		H10SW   	E8NE
1998090400658	19980904	00658	SW  	1998	9	4	HEEA0015767      	4	19980826	G	3417	1221L1	ADC             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				ADC SHOWS FAIL 4 AND AIRSPEED 3 FAILS.						2	G	7	2 	4U				H10SW
1998090400659	19980904	00659		1998	9	4	HEEA0015768      	4	19980826	G	3455	066107700	ADF             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				POINTER ON ADF RECEIVER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998090400611	19980904	00611	NE  	1998	9	4	HEEA0015769      	1	19980826	G	7600	7630103901102	ACUTATOR        			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X					760050				ACTUATOR MOTOR STICKS INTERMITTENTLY.						1	G	7	2 	3U				H1NE
1998090400778	19980904	00778		1998	9	4	HEEA0015770      	4	19980826	G	2340	AA95759	AUDIO CONTROL   			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	133AE					S800				AUDIO CONTROL HAS BROKEN SWITCH.						1	G	7	2 	3U				H3EU
1998090400660	19980904	00660		1998	9	4	HEEA0015771      	4	19980826	G	3416		ALTIMETER       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5014V					45217				ALTIMETER HAS EXCESSIVE FRICTION ERROR.						1	G	7	1 	3U				H2SW
1998090400661	19980904	00661	SW  	1998	9	4	HEEA0015772      	1	19980826	G	2430	206075447007	REGULATOR       			BELL  	206   	206L1       	1182107	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50034					45169				GENERATOR WOULD NOT STAY ON LINE AT IDLE.  SENT TO MASCO FOR INSPECTION AND REPAIR.						1	G	7	1 	3U				H2SW
1998090400662	19980904	00662	SW  	1998	9	4	HEEA0015773      	1	19980826	G	3212	D24922117	FLOAT BAG       			BELL  	412   	412         	1182202	SW  										EMERG FLOAT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	23023	470  				33080				FLOAT BAG ASSEMBLY LEAKING - UNBONDED TOP-OFF VALVE.						1	G	7	2 	4U				H4SW
1998090400612	19980904	00612	NE  	1998	9	4	HEEA0015774      	2	19980826	G	7230	3017600	ENGINE          			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					POWER SECT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P	11972				33012				NOISE COMING FROM COMPRESSOR BLADES DURING SPOOL DOWN FROM 10 PERCENT.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998090400779	19980904	00779	EU  	1998	9	4	HEEA0015775      	1	19980826	G	6240	DL43638	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131AE					S787				NR 1 AND NR 2 NEEDLE STICKING, ROTOR NEEDLE INOPERATIVE.						1	G	7	2 	3U				H3EU
1998090400613	19980904	00613		1998	9	4	HEEA0015776      	4	19980826	G	3416	8140BS20LW	ENCODER         			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03										EXCESSIVE LEAKAGE AROUND BARS, KNOB ENCODER READS HIGH OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE
1998090400780	19980904	00780	EU  	1998	9	4	HEEA0015777      	1	19980826	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50293					S677				RPM WARNING LIGHT AND AUDIO ARE INTERMITTENTLY COMING ON.						1	G	7	2 	3U				H3EU
1998090400781	19980904	00781	EU  	1998	9	4	HEEA0015778      	1	19980826	G	7722	TM42739	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT TOT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				EXHAUST TEMPERATURE INDICATOR READS LOW AND WILL NOT CALIBRATE.						1	G	7	2 	3U				H3EU
1998090400782	19980904	00782	EU  	1998	9	4	HEEA0015779      	1	19980826	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				RPM LIGHT AND AUDIO COME ON INTERMITTENTLY.						1	G	7	2 	3U				H3EU
1998090400663	19980904	00663		1998	9	4	HEEA0015780      	4	19980826	G	2210	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				NOISY ROTOR IN VERTICAL GYRO.						1	G	7	2 	4U				H4SW
1998090400664	19980904	00664	SW  	1998	9	4	HEEA0015781      	1	19980826	G	6300	406340102101	CARBON SEAL     		406040500123	BELL  	407   	407         		SW  										M/R DRIVE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	141MA	1721 			A3174	53016				FORWARD CARBON SEAL LEAKING.						1	G	7	1 	3U			O	H2SW
1998090400665	19980904	00665	SW  	1998	9	4	HEEA0015782      	1	19980826	G	6420	406312100101	BEARING         		406012101105	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH				53170	53159				FEATHERING BEARINGS WORN ON TAIL ROTOR.						1	G	7	1 	3U			O	H2SW
1998090400666	19980904	00666	SW  	1998	9	4	HEEA0015783      	1	19980826	G	6300	406340102101	CARBON SEAL     		406040500123	BELL  	407   	407         		SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH	1276 			A3909	53159				CARBON SEAL LEAKING AND WORN.						1	G	7	1 	3U			O	H2SW
1998090400783	19980904	00783		1998	9	4	HEEA0015784      	4	19980826	G	3120	704A47320011	CLOCK           			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				CLOCK INOPERATIVE.						1	G	7	1 	3U				H9EU
1998090400667	19980904	00667	SW  	1998	9	4	HEEA0015785      	1	19980826	G	6710	406010413117	BEARING         			BELL  	407   	407         		SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				PITCH LINK HAS WORN BEARINGS.  P/N 406-010-413-117, S/N A5281, T.T. 0:00, P/N 406-310-405-101, S/N RXFS2261, T.T. 1577:0	0 BEARINGS WORN.					1	G	7	1 	3U			O	H2SW
1998090400668	19980904	00668	SW  	1998	9	4	HEEA0015786      	1	19980826	G	6230	406010401115	SWASHPLATE      			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407MM	1880 				53060				GREASE LEAKING PAST UPPER SEAL.						1	G	7	1 	3U			O	H2SW
1998090400670	19980904	00670	SW  	1998	9	4	HEEA0015788      	1	19980826	G	6710	406010413117	BEARING         			BELL  	407   	407         		SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				PITCH LINK HAS WORN BEARINGS.  P/N 406-040-413-117, S/N A4252, T.T. 0:00 P/N 406-310-405-101, S/N RXFS2200, T.T. 1577:00	 BEARINGS WORN.					1	G	7	1 	3U			O	H2SW
1998090400671	19980904	00671	SW  	1998	9	4	HEEA0015789      	1	19980826	G	6710	406010413117	BEARING         			BELL  	407   	407         		SW  										M/R PITCH LINK	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				PITCH LINK BEARINGS WORN.  P/N 406-040-413-117, S/N A5897, T.T. 0:00 P/N 406-310-405-101, S/N RXFS1945, T.T. 2977:10 BEA	RINGS WORN.					1	G	7	1 	3U			O	H2SW
1998090400672	19980904	00672	SW  	1998	9	4	HEEA0015790      	1	19980826	G	6710	406010413117	PITCH LINK      			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				PITCH LINK BEARINGS WORN.  P/N 406-040-413-117, S/N A6566, T.T. 0:00 P/N 406-310-416-101, S/N DIFS23, T.T. 2932:25 BEARI	NGS WORN, P/N 406-310-405-101, S/N RXFS1836, T.T. 2932:25 BEARINGS WORN.					1	G	7	1 	3U			O	H2SW
1998090400673	19980904	00673	SW  	1998	9	4	HEEA0015791      	1	19980826	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				LEFT BOOST PRESSURE LIGHT WOULD NOT ILLUMINATE.						1	G	7	1 	3U			O	H2SW
1998090400674	19980904	00674	SW  	1998	9	4	HEEA0015793      	1	19980826	G	8011	SM20ACD300A21	RELAY           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				STARTER LIGHT WOULD NOT STAY ON WITH STARTER ENGAGED.						1	G	7	1 	3U			O	H2SW
1998090400675	19980904	00675	SW  	1998	9	4	HEEA0015794      	1	19980826	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				FOUND LINK BEARING WORN.						1	G	7	1 	3U			O	H2SW
1998090400676	19980904	00676	SW  	1998	9	4	HEEA0015795      	1	19980826	G	2932	205076044007	SWITCH          			BELL  	407   	407         		SW  										HYD PRESSURE	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				HYDRAULIC COUNTER LIGHT INTERMITTENT.						1	G	7	1 	3U			O	H2SW
1998090400677	19980904	00677	SW  	1998	9	4	HEEA0015796      	1	19980826	G	6330	406010425107	BUSHING         			BELL  	407   	407         		SW  										M/R LEVER ASSY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1880 				53060				LEVER ASSEMBLY HAS WORN BUSHINGS.  SERIAL NUMBERS REMOVED ARE A1708 AND A1719.						1	G	7	1 	3U			O	H2SW
1998090400678	19980904	00678	SW  	1998	9	4	HEEA0015797      	1	19980826	G	6330	406010426101	LINK ASSY       			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1880 				53060				WORN LINK.  SERIAL NUMBERS REMOVED ARE AFS-1351 AND AFS-1365.						1	G	7	1 	3U			O	H2SW
1998090400679	19980904	00679	SW  	1998	9	4	HEEA0015798      	1	19980826	G	6230	406010427109	GIMBAL RING     			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1880 				53060				RING BUSHINGS ARE WORN.						1	G	7	1 	3U			O	H2SW
1998090400680	19980904	00680	SW  	1998	9	4	HEEA0015799      	1	19980826	G	6310	214040814105	SLEEVE          			BELL  	407   	407         		SW  										FREEWHEEL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA	1721 				53016				REPLACED WORN SLEEVE FROM FREEWHEELING UNIT 406-040-500-123, SN A3174.						1	G	7	1 	3U			O	H2SW
1998090400681	19980904	00681	SW  	1998	9	4	HEEA0015800      	1	19980826	G	7931	407375004101	INDICATOR       			BELL  	407   	407         		SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				ENGINE OIL PRESSURE LCD INOPERATIVE, WILL NOT TEST.						1	G	7	1 	3U			O	H2SW
1998090400682	19980904	00682	SW  	1998	9	4	HEEA0015801      	1	19980826	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         		SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				CRACKED ALONG WELD LINE ON SMALL RADIUS.						1	G	7	1 	3U			O	H2SW
1998090400614	19980904	00614	SW  	1998	9	4	HEEA0015802      	1	19980826	G	7160	4068T96P01	PRESSURE SWITCH 			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				PRESSURE SWITCH WILL NOT ILLUMINATE PARTICLE SEPARATOR LIGHT ON CAUTION PANEL.						2	G	7	2 	4U				H10SW
1998090400615	19980904	00615	SW  	1998	9	4	HEEA0015803      	1	19980826	G	2930	4053T40P01	SIGHT GLASS     			BELL  	214   	214ST       	1182106	SW  										HYDRAULIC SYS	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				GLASS BROKEN ON SIGHT GLASS.						2	G	7	2 	4U				H10SW
1998090400616	19980904	00616	NE  	1998	9	4	HEEA0015804      	2	19980827	G	7261	4052T92P01	CHIP DETECTOR   			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT72A       	30030	NE  					ENGINE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				LEAKS FROM ELECTRIC POST, CRIMPED TO DETECTOR BODY.						2	G	7	2 	4U	4	U		H10SW   	E8NE
1998090400784	19980904	00784	EU  	1998	9	4	HEEA0015808      	1	19980827	G	2822	P94B12209	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466	398  				3004				FUEL PUMP INOPERATIVE.						1	G	7	1 	3U				H9EU
1998090400617	19980904	00617	EU  	1998	9	4	HEEA0015810      	1	19980827	G	2910	030137020	LINE            			SNIAS 	350   	AS350B2     	8680813	EU  										HYDRAULIC SYS	DENTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				DENT IN LINE.						1	G	7	1 	3U				H9EU
1998090400683	19980904	00683		1998	9	4	HEEA0015811      	4	19980827	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				AFCS FAILS TEST 35.3 AND 35 ON SST IN YAW.						1	G	7	2 	4U				H4SW
1998090400684	19980904	00684		1998	9	4	HEEA0015812      	4	19980827	G	3451	066106600	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				TRANSCEIVER CAUSES ATC TRANSPORTATION REPLY LIGHT TO FLICKER CONSTANTLY.						1	G	7	2 	4U				H4SW
1998090400685	19980904	00685		1998	9	4	HEEA0015813      	4	19980827	G	3450	066104100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										COCKPIT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				TRANSPONDER FRAMING OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998090400686	19980904	00686	SW  	1998	9	4	HEEA0015814      	1	19980827	G	7722	9429100135	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	515KA	236  				51048				TOT INDICATOR FLUCTUATES BETWEEN 125 AND 625.						1	G	7	1 	3U				H2SW
1998090400687	19980904	00687	SW  	1998	9	4	HEEA0015815      	1	19980827	G	7722	206075680107	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				TOT INDICATOR FLUCTUATES WITHOUT ASSOCIATED GAUGE INDICATIONS.						1	G	7	1 	3U				H2SW
1998090400688	19980904	00688		1998	9	4	HEEA0015816      	4	19980827	G	3457	0845000000	GPS             			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81671					51301				GPS WILL NOT PRESENT USER WAY POINTS.   FACE WAS BROKEN DUE TO SHEET METAL TRIM NOT INSTALLED PROPERLY.						1	G	7	1 	3U				H2SW
1998090400689	19980904	00689	SW  	1998	9	4	HEEA0015817      	1	19980827	G	2840	473203003	SIGNAL COND     			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				WITH TOTAL FUEL SHOWING ZERO POUNDS, THE MID AND FORWARD TANKS SHOW 10 POUNDS. EACH.  (TANKS EMPTY) .						1	G	7	2 	4U				H4SW
1998090400618	19980904	00618	NE  	1998	9	4	HEEA0015818      	1	19980827	G	6510	7640201162041	SHAFT           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SHAFT RECEIVED WITH NO HOLES.						1	G	7	2 	3U			 	H1NE
1998090400690	19980904	00690		1998	9	4	HEEA0015819      	4	19980827	G	2312	40008310103	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D					31135				AFTER WARM-UP, TRANSCEIVER UNIT TRANSMITS INTERMITTENTLY.						1	G	7	1 	4U				H4SW
1998090400691	19980904	00691		1998	9	4	HEEA0015820      	4	19980827	G	2312	40008310103	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				TRANSCEIVER HAS WAVY DISPLAY AND DOES NOT TEST PROPERLY-RT FAULT.						2	G	7	2 	4U				H10SW
1998090400692	19980904	00692	SW  	1998	9	4	HEEA0015821      	1	19980827	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X					51494				MOTOR RUNS BUT ACTUATOR FROZEN.						1	G	7	1 	3U				H2SW
1998090400693	19980904	00693		1998	9	4	HEEA0015822      	4	19980827	G	2562	ELT10	ELT             			BELL  	212   	212         	1181420	SW  										G-SWITCH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				ELT ACTIVATES IN ARMED POSITION.						1	G	7	1 	4U				H4SW
1998090400694	19980904	00694	SW  	1998	9	4	HEEA0015823      	1	19980827	G	6240	2360016901	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1072T					45385				ROTOR INDICATOR NOISY, BEARINGS WORN.						1	G	7	1 	3U				H2SW
1998090400695	19980904	00695		1998	9	4	HEEA0015824      	4	19980827	G	2211	4033089901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				COMPUTER INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400785	19980904	00785	EU  	1998	9	4	HEEA0015825      	1	19980827	G	6240	117945641	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										MAST MOMENT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				TEST LIGHT ON INDICATOR STAYS ON IN-FLIGHT.						1	G	7	2 	3U				H13EU
1998090400786	19980904	00786	EU  	1998	9	4	HEEA0015826      	1	19980827	G	6240	10594575	TRANSMITTER     			BOLKMS	117   	BK117A4     	5626017	EU  										MAST MOMENT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				TEST LIGHT ON TORQUE TRANSMITTER STAYS ON IN-FLIGHT.						1	G	7	2 	3U				H13EU
1998090400696	19980904	00696	SW  	1998	9	4	HEEA0015827      	1	19980827	G	7722	35712519127	INDICATOR       			BELL  	206   	206B3       	1181506	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2275Q					3625				TOT INDICATOR NEEDLE STICKING AT 300 AND ABOVE.						1	G	7	1 	3U				H2SW
1998090400619	19980904	00619		1998	9	4	HEEA0015828      	4	19980827	G	3425	656767	COMPENSATOR     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT HSI	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				COMPENSATOR CRACKED.						1	G	7	2 	3U				H1NE
1998090400620	19980904	00620	NE  	1998	9	4	HEEA0015829      	1	19980827	G	3150	7645001078112	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				INDICATOR FLUCTUATES, MOISTURE INSIDE.						1	G	7	2 	3U				H1NE
1998090400621	19980904	00621		1998	9	4	HEEA0015830      	4	19980827	G	3422	258719342	GYRO COMPASS    			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				GYRO COMPASS HAS LOOSE HARDWARE IN ASSY.						1	G	7	2 	3U				H1NE
1998090400787	19980904	00787		1998	9	4	HEEA0015831      	4	19980827	G	3452	066106200	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	137AE					S851				INTERMITTENT OUTPUT FUNCTION SELECTOR KNOB ON TRANSCEIVER IS SUSPECTED SOURCE OF PROBLEM.						1	G	7	2 	3U				H3EU
1998090400697	19980904	00697	SW  	1998	9	4	HEEA0015832      	1	19980827	G	2820	AV24B1119B	VALVE           			BELL  	212   	212         	1181420	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S					30953				WORN GEAR IN FUEL VALVE.						1	G	7	1 	4U				H4SW
1998090400698	19980904	00698	SW  	1998	9	4	HEEA0015833      	1	19980827	G	2820	AV24B1119B	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				VALVE INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400699	19980904	00699	SW  	1998	9	4	HEEA0015834      	1	19980827	G	2432	214175379103	BATTERY CHARGER 			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				NR 2 CHARGER CIRCUIT BREAKER TRIPS AT 20 PERCENT NG.						2	G	7	2 	4U				H10SW
1998090400622	19980904	00622		1998	9	4	HEEA0015835      	4	19980827	G	3457	1624820	ANTENNA         																	FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										HOLES DO NOT LINE UP BETWEEN SHELL AND BASE.   PART DEFECTIVE.
1998090400700	19980904	00700	SW  	1998	9	4	HEEA0015836      	1	19980827	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5737T					45454				TOT INDICATOR NEEDLE HAS RATCHETY OPERATION BELOW ZERO DEGREES AFTER SEVERAL HOURS IN OFF POSITION.  NEEDLE RISES.						1	G	7	1 	3U				H2SW
1998090400701	19980904	00701		1998	9	4	HEEA0015837      	4	19980827	G	2210	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				TARYSN ERRATIC IN PITCH.						1	G	7	2 	4U				H4SW
1998090400702	19980904	00702		1998	9	4	HEEA0015838      	4	19980827	G	3457	13824120234	RECEIVER        			BELL  	206   	206L1       	1182107	SW  										COCKPIT GPS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	45RP					45521				GPS RECEIVER WILL LOSE CONTACT WITH SATELLITES INTERMITTENTLY.						1	G	7	1 	3U				H2SW
1998090400703	19980904	00703		1998	9	4	HEEA0015839      	4	19980827	G	2340	A3016W	INTERPHONE      			BELL  	412   	412         	1182202	SW  										COMM SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				VOLUME HAS STATIC WHEN MOVED, ADF COMES ON BY ITSELF.  BLEED OVER BETWEEN RADIOS AND FACEPLATE UNACCEPTABLE FOR NIGHTS.						1	G	7	2 	4U				H4SW
1998090400704	19980904	00704		1998	9	4	HEEA0015840      	4	19980827	G	2340	A3016W	INTERPHONE      			BELL  	214   	214ST       	1182106	SW  										COMM SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				BLEED OVER BETWEEN NR 1 VHF AND NR 2 VHF.						2	G	7	2 	4U				H10SW
1998090400623	19980904	00623		1998	9	4	HEEA0015841      	4	19980827	G	2340	A3016W	INTERPHONE      			SKRSKY	S76   	S76A        	8143006	NE  										COMM SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										FM 1 CHANNEL REPORTED GARBLED WHILE TRANSMITTING.  VOLUME CONTROL SCRATCHY WHILE ROTATING.						1	G	7	2 	3U				H1NE
1998090400705	19980904	00705	SW  	1998	9	4	HEEA0015842      	1	19980827	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										STARTER/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										STARTER WILL NOT STAY ENGAGED.						2	G	7	2 	4U				H10SW
1998090400706	19980904	00706	SW  	1998	9	4	HEEA0015843      	1	19980827	G	2435	23081018	STARTER         			BELL  	206   	206L3       	1182108	SW  										STARTER/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	49EA	5693 				51507				NO VOLTAGE OUTPUT FROM GENERATOR.						1	G	7	1 	3U				H2SW
1998090400624	19980904	00624		1998	9	4	HEEA0015844      	4	19980827	G	3454	071121627	CONTROL UNIT    																	COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										NAVIGATOR CONTROL HAS STATIC.
1998090400707	19980904	00707	SW  	1998	9	4	HEEA0015845      	1	19980827	G	3350	212075962001	POWER SUPPLY    			BELL  	412   	412         	1182202	SW  										CABIN	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				POWER SUPPLY HAS NO OUTPUT.						1	G	7	2 	4U				H4SW
1998090400708	19980904	00708		1998	9	4	HEEA0015846      	4	19980827	G	3421	206075607103	GYRO            			BELL  	412   	412         	1182202	SW  										ATTITUDE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				ATTITUDE GYRO HAS SLOW SLAVE TIMES.						1	G	7	2 	4U				H4SW
1998090400709	19980904	00709	SW  	1998	9	4	HEEA0015847      	1	19980827	G	6710	206062721103	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6603X					51412				ACTUATOR WILL NOT INCREASE OR DECREASE.						1	G	7	1 	3U				H2SW
1998090400625	19980904	00625		1998	9	4	HEEA0015848      	4	19980827	G	3420	2360041906	ATTITUDE IND. RO																	COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ATTITUDE INDICATOR HAS WORN BEARINGS.
1998090400710	19980904	00710	SW  	1998	9	4	HEEA0015849      	1	19980827	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1072T					45385				ACTUATOR WILL NOT INCREASE OR DECREASE.						1	G	7	1 	3U				H2SW
1998090400711	19980904	00711		1998	9	4	HEEA0015850      	4	19980827	G	2312	064102300	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				WITH CONTROLLER OFF AND BLANK, RECEIVE AUDIO IS STILL HEARD.  WILL NOT TURN OFF.						2	G	7	2 	4U				H10SW
1998090400712	19980904	00712	SW  	1998	9	4	HEEA0015851      	1	19980827	G	7921	8543909	OIL COOLER      			BELL  	206   	206L3       	1182108	SW  										ENGINE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21497					51518				OIL COOLER HAS HIGH OIL TEMPERATURE AND FINS ARE CORRODED.						1	G	7	1 	3U				H2SW
1998090400713	19980904	00713	SW  	1998	9	4	HEEA0015852      	1	19980827	G	7921	8543909	OIL COOLER      			BELL  	206   	206L3       	1182108	SW  										ENGINE	CLOGGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4180F					51469				OIL COOLER HAS HIGH OIL TEMPERATURE AND CORES ARE CLOGGED.						1	G	7	1 	3U				H2SW
1998090400714	19980904	00714	SW  	1998	9	4	HEEA0015853      	1	19980827	G	2435	23032048	STARTER         			BELL  	206   	206B3       	1181506	SW  										STARTER/GEN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2285B					3642				STARTER/GENERATOR HAS INTERMITTENT START PROBLEM.						1	G	7	1 	3U				H2SW
1998090400788	19980904	00788	GL  	1998	9	4	HEEA0015854      	2	19980827	G	7314	3865005	PUMP            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	137AE	9632 				S851				BYPASS VALVE NOT SEALING CLOSED.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998090400715	19980904	00715	SW  	1998	9	4	HEEA0015855      	1	19980827	G	2435	230322111	ARMATURE        			BELL  	407   	407         		SW  										STARTER/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				ARMATURE CAUSING EXCESSIVE ARCHING--BURNT SPOTS ON COMMUTATOR.						1	G	7	1 	3U			O	H2SW
1998090400716	19980904	00716	SW  	1998	9	4	HEEA0015856      	1	19980827	G	5510	206023119151	STABILIZER      			BELL  	206   	206L1       	1182107	SW  										TAIL BOOM	DAMAGED         	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										STABILIZER ASSY HAS CONCEALED DAMAGE.  TIME SINCE REPAIR 0:00.						1	G	7	1 	3U			 	H2SW
1998090400717	19980904	00717	SW  	1998	9	4	HEEA0015857      	1	19980827	G	2840	212070122009	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										INDICATOR OUT OF TOLERANCE THROUGHOUT.						1	G	7	1 	4U				H4SW
1998090400718	19980904	00718		1998	9	4	HEEA0015858      	4	19980827	G	3424	214075244001	RATE GYRO       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				NEEDLE DEFLECTS RIGHT ON RATE GYRO.						2	G	7	2 	4U				H10SW
1998090400719	19980904	00719	SW  	1998	9	4	HEEA0015859      	1	19980827	G	2422	412075101101	INVERTER        			BELL  	412   	412         	1182202	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				INVERTER CAUSED VOLTAGE SPIKES.						1	G	7	2 	4U				H4SW
1998090400789	19980904	00789	EU  	1998	9	4	HEEA0015860      	1	19980827	G	7722	TM42739	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT TOT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				READING 20 TO 30 DEGREES HIGH ON EXHAUST TEMPERATURE INDICATOR.						1	G	7	2 	3U				H3EU
1998090400790	19980904	00790	EU  	1998	9	4	HEEA0015861      	1	19980827	G	7930	90321003	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81832					S828				SUPPLY GAUGE ON FUEL INDICATOR ERRATIC AND INDICATOR FLUCTUATES FROM FULL TO EMPTY IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998090400720	19980904	00720	SW  	1998	9	4	HEEA0015862      	1	19980827	G	7714	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				NR 2 ENGINE N2 NEEDLE INOPERATIVE AND OTHERS ARE RISING.						1	G	7	2 	4U				H4SW
1998090400721	19980904	00721	SW  	1998	9	4	HEEA0015863      	1	19980827	G	7722	212075067105	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT ITT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				ITT GAUGE STICKS BETWEEN 500 AND 600 DEGREES ON SHUTDOWN.						1	G	7	2 	4U				H4SW
1998090400791	19980904	00791	EU  	1998	9	4	HEEA0015864      	1	19980827	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										M/R RPM	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				RPM WARNING BOX CAUSES INTERMITTENT RPM LIGHT TO ILLUMINATE WHEN AT 100 PERCENT IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998090400722	19980904	00722	SW  	1998	9	4	HEEA0015865      	1	19980827	G	7712	206075739103	TORQUEMETER     			BELL  	206   	206L3       	1182108	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610Y					51419				TORQUEMETER STICKS AND FLUCTUATES.						1	G	7	1 	3U				H2SW
1998090400723	19980904	00723		1998	9	4	HEEA0015866      	4	19980827	G	2211	4033089901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				COMPUTER INOPERATIVE, SMOKED, FAILED TEST 2.2-2.3-2.4-11.2-13 AND 23.2 DNSS.						1	G	7	2 	4U				H4SW
1998090400724	19980904	00724	SW  	1998	9	4	HEEA0015867      	1	19980827	G	7810	212061201011	EJECTOR         			BELL  	212   	212         	1181420	SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				LEFT EJECTOR ASSEMBLY'S WELDS ARE CRACKED AND HAS LOOSE RIVETS.						1	G	7	1 	4U				H4SW
1998090400725	19980904	00725		1998	9	4	HEEA0015868      	4	19980827	G	3432	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				GLIDESCOPE INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400726	19980904	00726		1998	9	4	HEEA0015869      	4	19980827	G	3434	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				BLUE LIGHT INOPERATIVE ON MARKER BEACON.						1	G	7	2 	4U				H4SW
1998090400727	19980904	00727		1998	9	4	HEEA0015870      	4	19980827	G	3453	066402601	LORAN           			BELL  	230   	230         	1182149	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				RIGHT SIDE OF GLASS CRAZED.  HARD TO SEE FROM PILOT SEAT.						1	G	7	2 	3U			NC	H9SW
1998090400792	19980904	00792		1998	9	4	HEEA0015871      	4	19980827	G	2350	066105571	AUDIO PANEL     			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				AUDIO PANEL RECEIVES ICS AND RADIOS INTERMITTENTLY.						1	G	7	1 	3U				H9EU
1998090400793	19980904	00793		1998	9	4	HEEA0015872      	4	19980827	G	2350	066105552	AUDIO PANEL     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB					S737				AUDIO EXTREMELY WEAK ON AUDIO PANEL.						1	G	7	2 	3U				H3EU
1998090400794	19980904	00794	EU  	1998	9	4	HEEA0015873      	1	19980827	G	6240	6505A1008	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131AE					S787				NR 1 ENGINE'S N2 NEEDLE STICKING.						1	G	7	2 	3U				H3EU
1998090400728	19980904	00728		1998	9	4	HEEA0015874      	4	19980827	G	3422	206075606103	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206LS					51070				DIRECTIONAL GYRO PRECESSES.						1	G	7	1 	3U				H2SW
1998090400795	19980904	00795	EU  	1998	9	4	HEEA0015875      	1	19980827	G	2436	51565000R	REGULATOR       			BOLKMS	105   	BO105S      	5626006	EU  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911FL					S717				VOLTAGE REGULATOR IS OVER VOLTAGE.						1	G	7	2 	3U				H3EU
1998090400729	19980904	00729	SW  	1998	9	4	HEEA0015876      	1	19980827	G	6240	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				ROTOR READS HIGH IN ALL RPM'S.						1	G	7	2 	4U				H4SW
1998090400730	19980904	00730	SW  	1998	9	4	HEEA0015877      	1	19980827	G	7931	214175253103	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										OIL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				OIL TEMPERATURE PEGS OUT HIGH SIDE.  INDICATOR FAILED COMMON MODE TEST.						2	G	7	2 	4U				H10SW
1998090400731	19980904	00731	SW  	1998	9	4	HEEA0015878      	1	19980827	G	7931	214175252101	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										OIL SYSTEM	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				INDICATOR READING LOW PRESSURE,  INDICATOR FAILED COMMON MODE TEST.						2	G	7	2 	4U				H10SW
1998090400732	19980904	00732	SW  	1998	9	4	HEEA0015879      	1	19980827	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L4       	1182110	SW  										DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	CFVEF					52071				ACTUATOR INOPERATIVE.  TRIES TO MOVE ONLY ONE WAY.						1	G	7	1 	3U			NC	H2SW
1998090400734	19980904	00734		1998	9	4	HEEA0015881      	4	19980827	G	2210	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				DIRECTIONAL GYRO NOISY AND PRECESSES.						1	G	7	2 	4U				H4SW
1998090400735	19980904	00735	SW  	1998	9	4	HEEA0015882      	1	19980827	G	7921	8543909	OIL COOLER      			BELL  	206   	206L3       	1182108	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31801					51074				OIL COOLER HAS HIGH OIL TEMPERATURE, CORES CLOGGED.						1	G	7	1 	3U				H2SW
1998090400736	19980904	00736		1998	9	4	HEEA0015883      	4	19980827	G	3460	5205160006	INDICATOR       			BELL  	412   	412         	1182202	SW  										FLIGHT MANAGE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				KNOB STICKS ON INDICATOR COURSE SELECTOR.						1	G	7	2 	4U				H4SW
1998090400737	19980904	00737	SW  	1998	9	4	HEEA0015884      	1	19980827	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				STEP ACTUATOR RUNS 1 CYCLE THEN QUITS.						1	G	7	2 	4U				H4SW
1998090400738	19980904	00738	SW  	1998	9	4	HEEA0015885      	1	19980827	G	2840	214066254101	SWITCH          			BELL  	214   	214ST       	1182106	SW  										INST PANEL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				FUEL SWITCH CAUSES LIGHT TO FLICKER.						2	G	7	2 	4U				H10SW
1998090400739	19980904	00739	SW  	1998	9	4	HEEA0015886      	1	19980827	G	6320	206040530001	MAIN CASE       			BELL  	206   	206L1       	1182107	SW  										M/R GEARBOX	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										MAIN CASE ASSEMBLY HAS WORN I/P LINER AND 4 EACH STUD HOLES AT UPPER MATING SURFACE HAVE CORROSION.						1	G	7	1 	3U				H2SW
1998090400740	19980904	00740		1998	9	4	HEEA0015887      	4	19980827	G	2562	DK100	BEACON          			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										BEACON HAS LOW VOLTAGE.  TIME SINCE REPAIR 0:00.						1	G	7	1 	3U				H2SW
1998090400741	19980904	00741	SW  	1998	9	4	HEEA0015888      	1	19980827	G	5260	SYLC502281	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				STEP ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400742	19980904	00742	SW  	1998	9	4	HEEA0015889      	1	19980827	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				STEP ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400743	19980904	00743	SW  	1998	9	4	HEEA0015890      	1	19980827	G	6710	206062721113	ACTUATOR        			BELL  	206   	206B3       	1181506	SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	104PH					3622				ACTUATOR INTERMITTENTLY STICKS IN EXTENDED POSITION.						1	G	7	1 	3U				H2SW
1998090400744	19980904	00744	GL  	1998	9	4	HEEA0015891      	2	19980827	G	7320	206062721109	ACTUATOR        			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					DROOP COMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31821					51076				ACTUATOR WILL NOT RETRACT.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998090400626	19980904	00626	NE  	1998	9	4	HEEA0015892      	1	19980827	G	2420	7655009005108	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				AC GENERATOR DROPS OFF LINE WHEN AIR CONDITIONER IS TURNED ON.						1	G	7	2 	3U				H1NE
1998090400627	19980904	00627		1998	9	4	HEEA0015893      	4	19980827	G	3455	066104701	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT ADF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				ADF SLOW TO RESPOND, KA135 CABLE BROKEN.						1	G	7	2 	3U				H1NE
1998090400628	19980904	00628		1998	9	4	HEEA0015894      	4	19980827	G	3431	066400700	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT VOR	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				VOR RECEIVER HAS WEAK RECEIVE, CAN BE OFF BY UP TO 7 POINTER.						1	G	7	2 	3U				H1NE
1998090400745	19980904	00745		1998	9	4	HEEA0015895      	4	19980827	G	3431	066400700	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT VOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				VOR RECEIVER HAS INOPERATIVE LOCALIZER.						1	G	7	2 	4U				H4SW
1998090400746	19980904	00746		1998	9	4	HEEA0015896      	4	19980827	G	3452	066104100	TRANSPONDER     			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				TRANSPONDER A/C CODE STAYS AT 0000.						1	G	7	1 	4U				H4SW
1998090400747	19980904	00747		1998	9	4	HEEA0015897      	4	19980827	G	3452	066106200	TRANSPONDER     			BELL  	407   	407         		SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				TRANSPONDER INOPERATIVE AND NO POWER OUT.						1	G	7	1 	3U			O	H2SW
1998090400748	19980904	00748		1998	9	4	HEEA0015898      	4	19980828	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				AMP WILL NOT STAY ON LINE.  TIME SINCE REPAIR 0:00.						2	G	7	2 	4U				H10SW
1998090400749	19980904	00749	SW  	1998	9	4	HEEA0015899      	1	19980828	G	3212	214052200107	FLOAT           			BELL  	214   	214ST       	1182106	SW  										EMERG FLOAT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03		2481 								AFT FLOAT FOUND LEAKING DURING TEST.						2	G	7	2 	4U				H10SW
1998090400750	19980904	00750	GL  	1998	9	4	HEEA0015900      	2	19980828	G	7320	23069551	HMU             			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH	1253 				53228				HMU WOULD NOT GO TO IDLE.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998090400751	19980904	00751	SW  	1998	9	4	HEEA0015901      	1	19980828	G	7712	412075008113	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				NR 2 NEEDLE ON TORQUE INDICATOR WILL NOT OPERATE AT ALL TIMES.						1	G	7	2 	4U				H4SW
1998090400629	19980904	00629		1998	9	4	HEEA0015902      	4	19980828	G	3455	6222362001	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT ADF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				ADF WILL NOT TEST, RECEIVED SIGNAL AND NEEDLE WILL NOT POINT.						1	G	7	2 	3U				H1NE
1998090400752	19980904	00752	SW  	1998	9	4	HEEA0015903      	1	19980828	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										XMSN OIL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				INDICATOR STICKS AT 30 PERCENT PRESSURE SIDE.						1	G	7	2 	4U				H4SW
1998090400630	19980904	00630		1998	9	4	HEEA0015904      	4	19980828	G	3414	8502CS20LW	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				DURING TAKEOFF, AIRSPEED INDICATES NEGATIVE AIRSPEED UNTIL 60 KNOTS.  READS CORRECTLY AFTER TAKEOFF AND CRUISE FLIGHT.						1	G	7	2 	3U				H1NE
1998090400796	19980904	00796		1998	9	4	HEEA0015905      	4	19980828	G	3425	066304605	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT HSI	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				HSI CONTROL INTERMITTENTLY INOPERATIVE, G/S NEEDLE STICKS.						1	G	7	2 	3U				H13EU
1998090400753	19980904	00753	SW  	1998	9	4	HEEA0015906      	1	19980828	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				STEP ACTUATOR WILL NOT RAISE IF ANY RESISTANCE IS PUT ON ACTUATOR, WORKS OK IF NOT LOADED DOWN.						1	G	7	2 	4U				H4SW
1998090400754	19980904	00754	SW  	1998	9	4	HEEA0015907      	1	19980828	G	6330	206033506101	RESTRAINT       			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745S					45491				RESTRAINT BEARING AXIAL PLAY IS BEYOND LIMITS.						1	G	7	1 	3U				H2SW
1998090400797	19980904	00797	EU  	1998	9	4	HEEA0015908      	1	19980828	G	7930	6607190A	SWITCH          			BOLKMS	105   	BO105S      	5626006	EU  										OIL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	54191					S804				OIL LIGHT WOULD NOT ILLUMINATE WHEN BATTERY SWITCHED TO ON POSITION.						1	G	7	2 	3U				H3EU
1998090400755	19980904	00755		1998	9	4	HEEA0015909      	4	19980828	G	3452	066106200	TRANSPONDER     			BELL  	206   	206L3       	1182108	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3116P					51530				TRANSPONDER HAS BROKEN KNOB.						1	G	7	1 	3U				H2SW
1998090400756	19980904	00756	SW  	1998	9	4	HEEA0015910      	1	19980828	G	7714	8DJ81WBS4	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										GAS PRODUCER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50046					45173				GAUGE STICKS BETWEEN 0-15 PERCENT AND FLUCTUATES.						1	G	7	1 	3U				H2SW
1998090400757	19980904	00757	SW  	1998	9	4	HEEA0015911      	1	19980828	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				TOT NEEDLE STICKS ON START-UP.						1	G	7	1 	3U				H2SW
1998090400758	19980904	00758	SW  	1998	9	4	HEEA0015912      	1	19980828	G	7722	206375006101	INDICATOR       			BELL  	206   	206L1       	1182107	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2758N					45267				TOT INDICATOR READS 10 PERCENT HIGH ABOVE 500 AFTER UNIT IS WARM.						1	G	7	1 	3U				H2SW
1998090400759	19980904	00759	SW  	1998	9	4	HEEA0015913      	1	19980828	G	6240	214074280103	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				RPM LIMIT INDICATOR HAS NO LOW RPM TONE.						1	G	7	2 	4U				H4SW
1998090400631	19980904	00631	CE  	1998	9	4	HEEA0015914      	1	19980828	G	2422	PC17	INVERTER        			BEECH 	200   	200CBEECH   	1152926	CE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	39PH					BL3				INVERTER DROPS OFF LINE THEN COMES BACK ON IN-FLIGHT.						1	L	7	2 	4T				A24CE
1998090400760	19980904	00760		1998	9	4	HEEA0015915      	4	19980828	G	3425	071107600	AMPLIFIER       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				AMP CAUSED POINTER TO MOVE SLOWLY DURING THE TO/FROM PORTION OF THE NAVIGATION SYSTEM TEST.						1	G	7	2 	4U				H4SW
1998090400798	19980904	00798	EU  	1998	9	4	HEEA0015916      	1	19980828	G	2840	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESSURE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				FUEL PRESSURE TRANSMITTER READS HIGH DURING PUMP OPERATION.						1	G	7	2 	3U				H3EU
1998090400799	19980904	00799	EU  	1998	9	4	HEEA0015917      	1	19980828	G	2844	BSE206150G3	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	624MB					S751				NO OIL PRESSURE READING ON ENGINE.						1	G	7	2 	3U				H3EU
1998090400761	19980904	00761	SW  	1998	9	4	HEEA0015918      	1	19980828	G	7722	212075067109	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT ITT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				READING ON ITT INDICATOR ERRATIC AND STICKS.						1	G	7	2 	4U				H4SW
1998090400762	19980904	00762		1998	9	4	HEEA0015919      	4	19980828	G	3420	060001500	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT HSI	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	92MT					51175				GYRO PRECESSES IN-FLIGHT SLOW TO ACQUIRE.						1	G	7	1 	3U				H2SW
1998090400763	19980904	00763		1998	9	4	HEEA0015920      	4	19980828	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				RATE GYRO INOPERATIVE, NO NEEDLE MOVEMENT, FLAG DOES NOT PULL.						1	G	7	2 	4U				H4SW
1998090400764	19980904	00764	SW  	1998	9	4	HEEA0015921      	1	19980828	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				PUMP TRIPS CIRCUIT BREAKER.						1	G	7	2 	4U				H4SW
1998090400765	19980904	00765	SW  	1998	9	4	HEEA0015922      	1	19980828	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				PUMP TRIPS CIRCUIT BREAKER.						1	G	7	2 	4U				H4SW
1998090400766	19980904	00766		1998	9	4	HEEA0015923      	4	19980828	G	2312	4004512	ANTENNA         			BELL  	212   	212         	1181420	SW  										FUSELAGE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ANTENNA HAS CORROSION.  REMOVED FROM AIRCRAFT HK4121X (212).						1	G	7	1 	4U				H4SW
1998090400767	19980904	00767		1998	9	4	HEEA0015924      	4	19980828	G	3421	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				RATE GYRO'S NEEDLE INOPERATIVE.						1	G	7	2 	4U				H4SW
1998090400768	19980904	00768	SW  	1998	9	4	HEEA0015925      	1	19980828	G	2422	214175104101	INVERTER        			BELL  	214   	214ST       	1182106	SW  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				INVERTER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998090400769	19980904	00769		1998	9	4	HEEA0015926      	4	19980828	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				ROLL CHANNEL INOPERATIVE AND HANDLE MISSING.						1	G	7	2 	4U				H4SW
1998090400800	19980904	00800	EU  	1998	9	4	HEEA0015927      	1	19980828	G	6240	2202A1002	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										RPM WARNING	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5029H					S670				RPM WARNING INOPERATIVE.						1	G	7	2 	3U				H3EU
1998090400632	19980904	00632		1998	9	4	HEEA0015928      	4	19980828	G	3421	1113034	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				RT FLAG ATTITUDE INDICATOR WILL NOT PULL.						1	G	7	2 	3U				H1NE
1998090400633	19980904	00633	NE  	1998	9	4	HEEA0015929      	1	19980828	G	2430	7655009006105	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				GENERATOR WOULD NOT RESET.						1	G	7	2 	3U				H1NE
1998090400801	19980904	00801		1998	9	4	HEEA0015930      	4	19980828	G	2562	ELT910	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										ELT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				ELT CAME ON AND WOULD NOT GO OFF.  TIME SINCE REPAIR 0:00.						1	G	7	2 	3U				H3EU
1998090400770	19980904	00770		1998	9	4	HEEA0015931      	4	19980828	G	2562	ELT910	TRANSMITTER     			BELL  	206   	206L3       	1182108	SW  										ELT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6251X					51552				ELT STAYS ON.  TIME SINCE REPAIR 128:35 HOURS.						1	G	7	1 	3U				H2SW
1998090400634	19980904	00634	NE  	1998	9	4	HEEA0015932      	1	19980828	G	3150	7655001001103	CAUTION PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5128					760181				SPARE SEGMENT ON CAUTION PANEL DOES NOT ILLUMINATE.						1	G	7	2 	3U				H1NE
1998090400802	19980904	00802	GL  	1998	9	4	HEEA0015933      	2	19980828	G	7320	1564T1005	SERVOMOTOR      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B					S673				SERVO MOTOR WILL NOT ACTUATE, FILTER SHORTED TO GROUND.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998090400803	19980904	00803	GL  	1998	9	4	HEEA0015934      	2	19980828	G	7320	1564T1005	SERVOMOTOR      			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB					S737				SERVO MOTOR WILL NOT ACTUATE UP OR DOWN, BRAKE STICKING.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998090400635	19980904	00635		1998	9	4	HEEA0015935      	4	19980828	G	3416	066306401	ENCODER         			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				NEEDLE STICKS THROUGHOUT SCALE AND ENCODER READS OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE
1998090400771	19980904	00771	SW  	1998	9	4	HEEA0015936      	1	19980828	G	7714	214175251107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				TACHOMETER INDICATOR INOPERATIVE.						2	G	7	2 	4U				H10SW
1998090400772	19980904	00772		1998	9	4	HEEA0015937      	4	19980828	G	2211	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				AFCS COMPUTER WILL NOT RECOVER, FAILS TEST.						1	G	7	2 	4U				H4SW
1998090400773	19980904	00773	SW  	1998	9	4	HEEA0015938      	1	19980828	G	2432	39563001	BATTERY         			BELL  	412   	412         	1182202	SW  										CABIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893S	2860 				33022				BATTERY PACK READS ZERO VOLTS.						1	G	7	2 	4U				H4SW
1998090400774	19980904	00774	SW  	1998	9	4	HEEA0015939      	1	19980828	G	2432	39563001	BATTERY         			BELL  	412   	412         	1182202	SW  										CABIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6559Z					36019				BATTERY 18 VOLTS LOW.						1	G	7	2 	4U				H4SW
1998090400775	19980904	00775	SW  	1998	9	4	HEEA0015940      	1	19980828	G	2432	39563001	BATTERY         			BELL  	412   	412         	1182202	SW  										CABIN	DISCHARGED      	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893S	2042 				33022				BATTERY VOLTAGE READS 13 VOLTS.						1	G	7	2 	4U				H4SW
1998090400776	19980904	00776		1998	9	4	HEEA0015941      	4	19980828	G	3455	066104701	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT ADF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				RECEIVER HAS NO AUDIO.						1	G	7	2 	4U				H4SW
1998091100201	19980911	00201	SW  	1998	9	11	HEEA0015942      	1	19980901	G	6520	206040439001	SHAFT           			BELL  	206   	206L1       	1182107	SW  										TAIL ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										MISMANUFACTURED.  CANNOT INSTALL TAIL ROTOR RETENTION NUT, THREADS DEFECTIVE.  SUSPECT THREADS NOT CUT DEEP ENOUGH.						1	G	7	1 	3U				H2SW
1998091100202	19980911	00202	SW  	1998	9	11	HEEA0015943      	1	19980901	G	6230	289053499	SEAL            		407040011101	BELL  	407   	407         		SW  										M/R MAST	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	402PH	1232 			53159	53159				MAIN ROTOR MAST, SEAL LEAKING.						1	G	7	1 	3U			O	H2SW
1998091100203	19980911	00203	SW  	1998	9	11	HEEA0015944      	1	19980902	G	5300	206023119053	PIN             			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5745S					45491				MISMANUFACTURED.  THREADED PORTION OF PIN TOO LONG (BOTTOMS OUT) AND SHANK TOO SHORT.						1	G	7	1 	3U				H2SW
1998091100192	19980911	00192	GL  	1998	9	11	HEEA0015945      	2	19980903	G	7250	6886407	WHEEL           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					1ST STAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	50293	556  			CAT40303	S677	CAE835254			ENGINE REMOVED DUE TO COMPRESSOR OVERHAUL.    TURBINE DISASSEMBLED DUE TO LOW POWER ON TEST CELL.  UPON INSPECTION OF TU	RBINE PARTS NOTED:    MEASURED .006 INCH OVER BLUE PRINT SPECS.  (6.190 INCH - 6.191 INCH) ON NR 1 WHEEL OUTSIDE DIAMETE	R.  INSTALLED A NEW NR 1 WHEEL.				1	G	7	2 	3U	3	U		H3EU    	E4CE
1998091100193	19980911	00193	GL  	1998	9	11	HEEA0015947      	1	19980903	G	7500	6876294	LINE            		6890550     	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					BLEED VALVE	MISALIGNED      	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	107PH				CAC30400F	2789	CAE834648			RECEIVING INSPECTION REVEALED:  MISALIGNMENT OF TUBE ASSEMBLY.  INSTALLED A NEW TUBE ASSY.						1	G	7	1 	3U	3	U		H2SW    	E4CE
1998091100194	19980911	00194	NE  	1998	9	11	HEEA0015948      	1	19980903	G	2400	8241631	POTENTIOMETER   		769000180210	SKRSKY	S76   	S76A        	8143006	NE  										ELECTRICAL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	2743E	131  			8107111	760155				CAUSED ACTUATOR TO BE INOPERATIVE.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND POTS CAUSED ACTUATOR TO TEST OUT OF L	IMITS ON TEST POINTS 9(Q) 3 & 5 (MECHANICAL CENTER OUT OF LIMITS AFTER SETTING ELECTRICAL CENTER) AND STRIP CHART INDICA	TED BADAREAS IN NULL POSITION.				1	G	7	2 	3U				H1NE
1998091100195	19980911	00195	NE  	1998	9	11	HEEA0015949      	1	19980903	G	2400	8241631	POTENTIOMETER   			SKRSKY	S76   	S76A        	8143006	NE  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		349  								POTENTIOMETER CHECKS BAD IN NULL POSITION.						1	G	7	2 	3U				H1NE
1998091100196	19980911	00196	NE  	1998	9	11	HEEA0015950      	1	19980903	G	2400	8241631	POTENTIOMETER   			SKRSKY	S76   	S76A        	8143006	NE  										ELECTRICAL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		288  								CAUSING ACTUATOR NOT TO OPERATE.  FOUND POTS CHECKED BAD IN NULL POSITION.						1	G	7	2 	3U				H1NE
1998091100204	19980911	00204	SW  	1998	9	11	HEEA0015951      	1	19980903	G	6420	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM	1522 			53069	53060				BEARINGS ON TAIL ROTOR ARE WORN AND CORRODED.						1	G	7	1 	3U			O	H2SW
1998091100197	19980911	00197	GL  	1998	9	11	HEEA0015952      	2	19980904	G	7260	23039794	PUMP ASSY       								ALLSN 	250C  	250C30P     	03013	GL  					ENGINE OIL	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  DEEP CASTING FLAWS BEYOND SERVICEABLE LIMITS IN OIL PUMP ASSY SCAVENGE PORT.											3	U			E1GL
1998091100205	19980911	00205	SW  	1998	9	11	HEEA0015953      	1	19980904	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				ONE EACH DISC CRACKED ON COUPLING DISC PACK - NR 3 FROM T/R GEARBOX.						1	G	7	1 	3U			O	H2SW
1998091100206	19980911	00206	SW  	1998	9	11	HEEA0015954      	1	19980904	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										T/R DRIVE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				LOW TORQUE ON BOLTS.						1	G	7	1 	3U			O	H2SW
1998091100207	19980911	00207	SW  	1998	9	11	HEEA0015955      	1	19980904	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				ENGINE OIL COOLER HAS HIGH OIL TEMPERATURE.						1	G	7	1 	3U			O	H2SW
1998091100208	19980911	00208	SW  	1998	9	11	HEEA0015956      	1	19980904	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	720PH					53277				OIL COOLER LEAKING THROUGH FINS.						1	G	7	1 	3U			O	H2SW
1998091100209	19980911	00209	SW  	1998	9	11	HEEA0015957      	1	19980904	G	6710	406010413117	PITCH LINK      			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				BEARINGS WORN.   BELL WAS UNABLE TO SUPPLY TRUNNION BEARING P/N 406-310-405-101, SO PHI ORDERED THE PITCH LINK ASSY P/N 	406-010-413-117 INSTEAD.  PHI THEN ROBBED THE BEARING OFF OF THE SERVICEABLE PITCH LINK.  THE UNSERVICEABLE BEARING WAS 	INSTALLED ON THE SERVICEABLE LINK ASSY, WHICH NOW RENDERS THE LINK ASSY UNSERVICEABLE.				1	G	7	1 	3U			O	H2SW
1998091100210	19980911	00210	SW  	1998	9	11	HEEA0015958      	1	19980904	G	6300	406010413117	PITCH LINK      			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				BEARINGS WORN.  BELL WAS UNABLE TO SUPPLY TRUNNION BEARING P/N 406-310-405-101, SO PHI ORDERED THE PITCH LINK ASSY P/N 4	06-010-413-117 INSTEAD.  PHI THEN ROBBED THE BEARING OFF OF THE SERVICEABLE PITCH LINK.  THE UNSERVICEABLE BEARING WAS I	NSTALLED ON THE SERVICEABLE LINK ASSY, WHICH NOW RENDERS THE LINK ASSY UNSERVICEABLE.				1	G	7	1 	3U			O	H2SW
1998091100211	19980911	00211	SW  	1998	9	11	HEEA0015962      	1	19980904	G	3212	407350302101	FLOAT BAG       			BELL  	407   	407         		SW  										FUSELAGE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				FLOAT BAG LEAKS.						1	G	7	1 	3U			O	H2SW
1998091100212	19980911	00212	SW  	1998	9	11	HEEA0015965      	1	19980904	G	2910	206076036105	VALVE           			BELL  	407   	407         		SW  										HYDRAULIC SYS	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	17   				53198				HYDRAULIC VALVE STICKS.						1	G	7	1 	3U			O	H2SW
1998091100213	19980911	00213	SW  	1998	9	11	HEEA0015966      	1	19980904	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										MGB TACH	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	783  				53198				MGT INDICATOR, INTERMITTENT; ERRATIC.						1	G	7	1 	3U			O	H2SW
1998091100215	19980911	00215	SW  	1998	9	11	HEEA0015968      	1	19980904	G	2820	206064520103	HOSE            			BELL  	407   	407         		SW  										FUEL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				HOSE CHAFED ON HARD PART OF FUEL LINE.						1	G	7	1 	3U			O	H2SW
1998091100216	19980911	00216	SW  	1998	9	11	HEEA0015969      	1	19980904	G	3212	206050247137	FLOAT COVER     			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				FLOAT COVER HAS TORN CAP.						1	G	7	1 	3U			O	H2SW
1998091100217	19980911	00217	SW  	1998	9	11	HEEA0015970      	1	19980904	G	6720	406010431109	LINK            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	1753 				53003				WORN BEARINGS ON LINK.						1	G	7	1 	3U			O	H2SW
1998091100218	19980911	00218	SW  	1998	9	11	HEEA0015971      	1	19980904	G	6720	406010432101	LINK            			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	1753 				53003				WORN BEARINGS ON LINK.						1	G	7	1 	3U			O	H2SW
1998091100219	19980911	00219	SW  	1998	9	11	HEEA0015972      	1	19980904	G	6510	407040316101	FLYWHEEL        			BELL  	407   	407         		SW  										TAIL ROTOR	OUT OF ADJUST   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				3.0 IPS MEASURED ON FORWARD BLOWER HANGER.						1	G	7	1 	3U			O	H2SW
1998091100220	19980911	00220	SW  	1998	9	11	HEEA0015973      	1	19980904	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				WORN BEARINGS ON TAIL ROTOR LINK.						1	G	7	1 	3U			O	H2SW
1998091100221	19980911	00221	SW  	1998	9	11	HEEA0015974      	1	19980904	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				WORN BEARINGS ON TAIL ROTOR LINK.						1	G	7	1 	3U			O	H2SW
1998091100222	19980911	00222	SW  	1998	9	11	HEEA0015975      	1	19980904	G	6520	406040453101	SEAL            			BELL  	407   	407         		SW  										T/R GEARBOX	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	403PH					53177				SEAL LEAKING ON TAIL ROTOR GEARBOX.						1	G	7	1 	3U			O	H2SW
1998091100223	19980911	00223	SW  	1998	9	11	HEEA0015976      	1	19980904	G	2820	407076010101	TUBE ASSEMBLY   			BELL  	407   	407         		SW  										FUEL SYSTEM	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				FUEL SYSTEM TUBE ASSY CHAFED.						1	G	7	1 	3U			O	H2SW
1998091100224	19980911	00224	SW  	1998	9	11	HEEA0015977      	1	19980904	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				RELAY CAUSING GENERATOR TO DROP OFF LINE IN-FLIGHT.						1	G	7	1 	3U			O	H2SW
1998091100225	19980911	00225	EU  	1998	9	11	HEEA0015978      	1	19980904	G	2435	150SG122Q	GENERATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				ACFT HAD TOTAL ELECTRIC FAILURE, NO OUTPUT FROM GENERATOR.						1	G	7	1 	3U				H9EU
1998091100226	19980911	00226		1998	9	11	HEEA0015979      	4	19980904	G	3414	3839949002	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				INDICATOR GIVES ERRATIC INDICATIONS.						1	G	7	1 	3U				H9EU
1998091100227	19980911	00227	EU  	1998	9	11	HEEA0015980      	1	19980904	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	34   				2820				COULD NOT BALANCE TAIL ROTOR. BLADE.						1	G	7	1 	3U				H9EU
1998091100198	19980911	00198	EU  	1998	9	11	HEEA0015981      	1	19980904	G	2460	9550168600	HARNESS         			SNIAS 	350   	AS350B2     	8680813	EU  										DC SYSTEM	FRAYED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				FRAYED WIRING HARNESS NEAR B-NUT.						1	G	7	1 	3U				H9EU
1998091100199	19980911	00199	NE  	1998	9	11	HEEA0015982      	2	19980904	G	7532	5044T08P11	BLEED VALVE     			BELL  	214   	214ST       	1182106	SW  	GE    	CT7TS 	CT72A       	30030	NE  					ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				LOW POWER ENGINE BLEED VALVE MALFUNCTIONED.						2	G	7	2 	4U	4	U		H10SW   	E8NE
1998091100228	19980911	00228	EU  	1998	9	11	HEEA0015984      	1	19980904	G	7712	305731365	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				COCKPIT INDICATOR HAS BEARING WEAR.						1	G	7	1 	3U				H9EU
1998091100229	19980911	00229	EU  	1998	9	11	HEEA0015986      	1	19980904	G	6320	18373	CHIP DETECTOR   			SNIAS 	350   	AS350B2     	8680813	EU  										TRANSMISSION	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				HEAD ROUNDED OFF ON CHIP DETECTOR.						1	G	7	1 	3U				H9EU
1998091100230	19980911	00230	NE  	1998	9	11	HEEA0015987      	2	19980904	G	7220	350A58160702	SCREEN          			SNIAS 	350   	AS350B2     	8680813	EU  	TMECA 	ARRIEL	ARRIEL1D    		NE  					INTAKE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				INTAKE SCREEN HAS SEVERAL BROKEN WIRES AND CHAFING.						1	G	7	1 	3U	3	U		H9EU    	E19EU
1998091100231	19980911	00231	EU  	1998	9	11	HEEA0015988      	1	19980904	G	6420	350A33200405	SPIDER          			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				DUPLEX BEARING FEELS ROUGH AND PC STAKED BEARING WORN.						1	G	7	1 	3U				H9EU
1998091100232	19980911	00232	EU  	1998	9	11	HEEA0015989      	1	19980904	G	6520	350A33020005	GEARBOX         			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	1963 				2820				TAIL ROTOR GEARBOX MAKING METAL.						1	G	7	1 	3U				H9EU
1998091100233	19980911	00233	EU  	1998	9	11	HEEA0015990      	1	19980904	G	6730	SC5084	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6095S	624  				2777				MAIN ROTOR SERVO LEAKING.						1	G	7	1 	3U				H9EU
1998091100200	19980911	00200	SW  	1998	9	11	HEEA0015991      	1	19980904	G	6322	6038T59P02	SHAFT           			BELL  	214   	214ST       	1182106	SW  										BLOWER ASSY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805	2228 				28141				BLOWER SHAFT SHEARED.						2	G	7	2 	4U				H10SW
1998091800406	19980918	00406	GL  	1998	9	18	HEEA0015996      	2	19980909	G	7240	23051644	HOUSING         		23051643    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					COMB FLANGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	5014V				CAC91731	45217	CAE895682			RECEIVING INSPECTION REVEALED:  UNABLE TO OBTAIN IMPELLER TO SHROUD HOUSING THROAT CLEARANCE.   TRIED SHROUD HOUSING ON 	SEVERAL IMPELLERS.  INSTALLED A DALLAS AIRMOTIVE OVERHAULED SHROUD HOUSING.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998091800412	19980918	00412	SW  	1998	9	18	HEEA0015997      	1	19980909	G	7714	214175251111FM	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3897N					28106				TRIPLE TACHOMETER UNRELIABLE, NEEDLE FLUCTUATES AND READS HIGH.						2	G	7	2 	4U				H10SW
1998091800413	19980918	00413	EU  	1998	9	18	HEEA0015998      	1	19980909	G	7714	22A690	TACH GENERATOR  			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	8197X	221  				S808				TACHOMETER GENERATOR IS INOPERATIVE.						1	G	7	2 	3U				H3EU
1998091800414	19980918	00414	SW  	1998	9	18	HEEA0015999      	1	19980909	G	6410	406312100101	BEARING         		407012101105	BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	978  			53038	53003				FEATHERING BEARINGS WORN ON TAIL ROTOR BLADE.  REPLACED WORN BEARINGS.						1	G	7	1 	3U			O	H2SW
1998091800415	19980918	00415	SW  	1998	9	18	HEEA0016000      	1	19980909	G	6520	PHI407112	BOOT            			BELL  	407   	407         		SW  										TAIL ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				BOOT DETERIORATED, LINERS LOOSE ON TRUNNION AND BEARINGS WORN.  REPAIRED.						1	G	7	1 	3U			O	H2SW
1998091800416	19980918	00416	SW  	1998	9	18	HEEA0016001      	1	19980909	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				TWO EACH DISCS CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800417	19980918	00417	SW  	1998	9	18	HEEA0016002      	1	19980909	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				TWENTY-FIVE HOUR ASB/AD NUTS TURNED DURING TORQUE CHECK.						1	G	7	1 	3U			O	H2SW
1998091800418	19980918	00418	SW  	1998	9	18	HEEA0016003      	1	19980909	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800419	19980918	00419	SW  	1998	9	18	HEEA0016004      	1	19980909	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1998091800420	19980918	00420	SW  	1998	9	18	HEEA0016005      	1	19980909	G	3212	206050247135	COVER           			BELL  	407   	407         		SW  										RT & LT FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				LEFT AND RIGHT MIDDLE FLOAT COVERS TORN.						1	G	7	1 	3U			O	H2SW
1998091800421	19980918	00421	SW  	1998	9	18	HEEA0016006      	1	19980909	G	3212	206050247137	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW
1998091800422	19980918	00422	SW  	1998	9	18	HEEA0016007      	1	19980909	G	3212	206050247138	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW
1998091800423	19980918	00423	SW  	1998	9	18	HEEA0016008      	1	19980909	G	6510	206061432121	RIVETS          			BELL  	407   	407         		SW  										BLOWER HOUSING	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				BLOWER HOUSING HAS LOOSE RIVETS.						1	G	7	1 	3U			O	H2SW
1998091800424	19980918	00424		1998	9	18	HEEA0016011      	4	19980909	G	3414	206075725103	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	1928 				53070				AIRSPEED INDICATOR READS LOW.						1	G	7	1 	3U			O	H2SW
1998091800425	19980918	00425	SW  	1998	9	18	HEEA0016012      	1	19980909	G	2420	SM20ACD300A21	RELAY           			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				RELAY CAUSED GENERATOR NOT TO COME ON LINE.						1	G	7	1 	3U			O	H2SW
1998091800426	19980918	00426	SW  	1998	9	18	HEEA0016013      	1	19980909	G	2430	206075447101	REGULATOR       			BELL  	407   	407         		SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				NO POWER FROM PIN M ON VOLTAGE REGULATOR TO TERMINAL ON STARTER/GENERATOR.						1	G	7	1 	3U			O	H2SW
1998091800427	19980918	00427	SW  	1998	9	18	HEEA0016014      	1	19980909	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										M/R DRIVE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				MGT INDICATOR READS 4 DEGREES HIGH.						1	G	7	1 	3U			O	H2SW
1998091800444	19980918	00444	EU  	1998	9	18	HEEA0016015      	1	19980909	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CNTL ROD	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				BEARINGS WORN ON PITCH CONTROL.   SERIAL NUMBERS REMOVED ARE S2294 AND M210.						1	G	7	1 	3U				H9EU
1998091800428	19980918	00428	SW  	1998	9	18	HEEA0016016      	1	19980909	G	6230	214010413105	DRIVE PLATE     			BELL  	214   	214ST       	1182106	SW  										M/R MAST	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										DRIVE PLATE MISMANUFACTURED.  BOTH HOLES NOT SPACED PROPERLY.						2	G	7	2 	4U				H10SW
1998091800445	19980918	00445	EU  	1998	9	18	HEEA0016017      	1	19980911	G	2121	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  										AIR DIST	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				BLOWER MOTOR FAILED.						1	G	7	1 	3U				H9EU
1998091800429	19980918	00429	SW  	1998	9	18	HEEA0016018      	1	19980911	G	6500	406040339111	BEARING         		406040320101	BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM				AFS1138	53060				TAIL ROTOR HAS ROUGH BEARING.  SERIAL NUMBERS REMOVED ARE B98-1155 AND B98-1148.						1	G	7	1 	3U			O	H2SW
1998091800430	19980918	00430		1998	9	18	HEEA0016019      	4	19980911	G	3421	206075606103	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	206LS					51070				POWER FLAG INTERMITTENTLY WILL NOT PULL ON GYRO.						1	G	7	1 	3U				H2SW
1998091800407	19980918	00407		1998	9	18	HEEA0016020      	1	19980911	G	2434	230321825	STATOR          																	DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CAUSED STARTER/GENERATOR TO FAIL TEST POINT C (5) EXTERNAL FIELD CURRENT RESISTANCE WAS TOO LOW.
1998091800431	19980918	00431		1998	9	18	HEEA0016021      	4	19980911	G	3422	2891ESR	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1078G					45398				DIRECTIONAL GYRO INTERMITTENTLY PRECESSES IN SLAVE MODE.						1	G	7	1 	3U				H2SW
1998091800432	19980918	00432		1998	9	18	HEEA0016022      	4	19980911	G	3422	2891ESR	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50182					45242				DIRECTIONAL GYRO INDICATOR PRECESSES AND DOES NOT SLAVE CORRECTLY.						1	G	7	1 	3U				H2SW
1998091800433	19980918	00433	SW  	1998	9	18	HEEA0016023      	4	19980911	G	3421	206075607103	GYRO            			BELL  	206   	206L1       	1182107	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21240					45647				ATTITUDE GYRO PRECESSES AND HAS EXCESSIVE BAR DROP IN RIGHT TURN.						1	G	7	1 	3U				H2SW
1998091800434	19980918	00434		1998	9	18	HEEA0016024      	4	19980911	G	3421	206075607103	GYRO            			BELL  	206   	206L3       	1182108	SW  										COCKPIT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				CAGING SHAFT PULLS OUT, BUT WILL NOT CAGE UNIT.						1	G	7	1 	3U				H2SW
1998091800435	19980918	00435	SW  	1998	9	18	HEEA0016025      	1	19980911	G	7722	206375007103	INDICATOR       			BELL  	206   	206L3       	1182108	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	41791					51465				TOT HAS NO INDICATION ON START-UP, NEEDLE STICKS AT ZERO.						1	G	7	1 	3U				H2SW
1998091800436	19980918	00436	SW  	1998	9	18	HEEA0016026      	1	19980911	G	2841	393008047	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL QTY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				WHEN TRYING TO CALIBRATE INDICATOR, FOUND TO BE OFF AT ZERO USING EMPTY ADJUSTMENT SCREW TO CALIBRATE AT ZERO, NEEDLE PE	GGED TO THE RIGHT OF ZERO AND STAYED.  CHECKED FULL SIDE, NEEDLE WOULD ONLY GO TO 1000 POUNDS.					1	G	7	2 	4U				H4SW
1998091800437	19980918	00437	SW  	1998	9	18	HEEA0016027      	1	19980911	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		10659								BLADE TIP TOO HEAVY FROM VENDOR.						1	G	7	2 	4U				H4SW
1998091800439	19980918	00439	SW  	1998	9	18	HEEA0016029      	1	19980911	G	3212	206373902103	VALVE           			BELL  	407   	407         		SW  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	447PH					53114				RELIEF VALVE LEAKING.						1	G	7	1 	3U			O	H2SW
1998091800446	19980918	00446	EU  	1998	9	18	HEEA0016030      	1	19980911	G	2435	23032048	STARTER         			BOLKMS	105   	BO105S      	5626006	EU  										START/GEN	OVERHEATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	91070	12647				S145				EVIDENCE OF OVERHEATING ON TERMINAL BLOCK.						1	G	7	2 	3U				H3EU
1998091800447	19980918	00447	GL  	1998	9	18	HEEA0016031      	2	19980911	G	7322	252464430	FUEL CONTROL    			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL SYSTEM	OUT OF ADJUST   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B	2935 				S673	CAE836331			ON FIRST START AFTER INSTALLATION IN THE AIRCRAFT, TOT ROSE RAPIDLY.  FOUND START/ACCEL AND START/DERICH ADJUSTMENTS TUR	NED TO MINIMUM, NO MORE ADJUSTMENT AVAILABLE.  RECEIVED UNIT IN SHOP WITH START DERICHMENT AND START ACCELERATION ADJUST	MENTS BOTH ADJUSTED TO THE CCW STOP.   TESTED UNITS START DERICH OPERATION IN SHOP, TESTED SATISFACTORY.  TESTED START D	ERICH AND START ACCEL. IN FLOW ROOM, BOTH TESTED SATISFACTORY.  COMPLETED TESTING OF UNIT PER TEST SPEC. NR 12529-01, UN	IT TESTED OK.		1	G	7	2 	3U	3	U		H3EU    	E4CE
1998091800408	19980918	00408	NE  	1998	9	18	HEEA0016032      	1	19980911	G	6410	7610105101042	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X	4909 				760050				PADDLE 'A'  HAS A HOLE IN THE LEADING EDGE ABRASION STRIP.						1	G	7	2 	3U				H1NE
1998091800440	19980918	00440		1998	9	18	HEEA0016033      	4	19980911	G	2350	AFT25B	AMPLIFIER       			BELL  	407   	407         		SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				AUDIO AMPLIFIER INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998091800409	19980918	00409		1998	9	18	HEEA0016034      	4	19980911	G	3442	7009330901	RADAR           																	COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RADAR HAS NO RETURNS AFTER 1-2 HOURS OF OPERATION.
1998091800441	19980918	00441		1998	9	18	HEEA0016035      	4	19980911	G	3416	13011001	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				PILOT REPORTED ALTIMETER UNIT READS 125 FEET HIGH OUT OF TOLERANCE.  WHEN RECEIVED UNIT, IT HAD LOOSE PARTS INSIDE.						1	G	7	2 	4U				H4SW
1998091800410	19980918	00410		1998	9	18	HEEA0016036      	2	19980911	G	7250	08E782	BEARING         		763080790210	SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E	2358 			12840277	760155				BEARING FAILURE, FOUND METAL SHAVING ON SEALS AND ROUGH ROTATION.  REPLACED WITH SERVICEABLE BEARINGS.						1	G	7	2 	3U				H1NE
1998091800411	19980918	00411		1998	9	18	HEEA0016037      	4	19980911	G	3416	8503S20LW5V	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				NEEDLE STICKING AND HAS EXCESSIVE LEAKAGE WHEN BARO KNOB IS TURNED AT 18,000 FEET.						1	G	7	2 	3U				H1NE
1998091800442	19980918	00442	SW  	1998	9	18	HEEA0016038      	1	19980911	G	6710	412010182101	BEARING         			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L	1551 				33006				MAIN ROTOR BEARING WORN BEYOND LIMITS AND FACE OF INNER BALL ALSO SHOWS SIGNS OF WEAR.  REPLACED WITH SERVICEABLE ROD EN	D ASSY.					1	G	7	2 	4U				H4SW
1998091800443	19980918	00443	SW  	1998	9	18	HEEA0016039      	1	19980911	G	6320	206040530001	CASE            		206040004107	BELL  	206   	206L3       	1182108	SW  										M/R GEARBOX	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6610E				B51719	51424				CRACK INDICATION ON BOTTOM OF MAIN CASE, INSIDE AND OUT, IN SAME PLACE.  SCRAPPED CASE AND REPLACED WITH NEW CASE.						1	G	7	1 	3U				H2SW
1998092500170	19980925	00170	SW  	1998	9	25	HEEA0016042      	1	19980915	G	3212	206050247138	COVER           			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				FLOAT COVER WORN AND TORN.						1	G	7	1 	3U			O	H2SW
1998092500177	19980925	00177	EU  	1998	9	25	HEEA0016043      	1	19980915	G	3213	350A41107921	SHOE            			SNIAS 	350   	AS350B2     	8680813	EU  										SKID	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z					2820				SKID SHOE WORN.						1	G	7	1 	3U				H9EU
1998092500171	19980925	00171	SW  	1998	9	25	HEEA0016045      	1	19980916	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										START/GEN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805	793  				28141				STARTER PREMATURELY DISENGAGES.						2	G	7	2 	4U				H10SW
1998092500164	19980925	00164	GL  	1998	9	25	HEEA0016046      	2	19980916	G	7250	23001967	WHEEL           		6898735     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					3RD STAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	7136H				CAT36701	S833	CAE820965F			RECEIVING INSPECTION REVEALED:  MEASURED .010 INCH OVER SPECS (7.506 INCH - 7.508 INCH) ON NR 3 WHEEL OUTSIDE DIAMETER. 	 INSTALLED A NEW NR 3 WHEEL.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998092500165	19980925	00165	GL  	1998	9	25	HEEA0016047      	2	19980917	G	7250	23033185	TURBINE         								ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MALFUNCTIONED   	E			HEEA	O				OTHER                   				B			SMOKE/FUMES/ODORS/SPARKS  			LD	LANDING        	1			SW	03		14663								SMOKE ON LANDING AND SHUT DOWN.  PART TOTAL CYCLES, 1,687.											3	U			E1GL
1998092500166	19980925	00166	GL  	1998	9	25	HEEA0016048      	2	19980918	G	7230	23056634	SPLINES         		23033191    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					SPUR GEAR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	10778	814  			CAC70762	45391	CAE860550			ENGINE REMOVED DUE TO SMOKE ON SHUT DOWN.  INSPECTION OF COMPRESSOR REVEALED:  STEP WEAR BEYOND SERVICEABLE LIMITS ON SP	UR GEAR SPLINES.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998092500167	19980925	00167	GL  	1998	9	25	HEEA0016049      	2	19980918	G	7230	23056634	SPUR GEAR       		23033191    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	16938	581  			CAC70027	45157	CAE860015			ENGINE REMOVED DUE TO LOW POWER.  INSPECTION OF COMPRESSOR REVEALED:  WORN BEYOND SERVICEABLE LIMITS ON SHAFT SPLINES.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998092500168	19980925	00168	GL  	1998	9	25	HEEA0016050      	2	19980918	G	7230	23056634	SPUR GEAR       		23051643    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X	708  			CAC90504	760050	CAE890670S			ENGINE REMOVED DUE TO IMPELLER TIME.  INSPECTION OF COMPRESSOR PARTS NOTED: STEP WEAR BEYOND SERVICEABLE LIMITS ON SHAFT	 SPLINES.					1	G	7	2 	3U	3	U		H1NE    	E1GL
1998092500169	19980925	00169	GL  	1998	9	25	HEEA0016051      	2	19980918	G	7230	23056634	SPUR GEAR       		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31077	458  			CAC91597	51520	CAE895576			ENGINE REMOVED DUE TO TURBINE OVERHAUL.  INSPECTION OF COMPRESSOR PARTS NOTED: SPLINE WEAR BEYOND SERVICEABLE LIMITS ON 	SHAFT SPLINES.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998092500178	19980925	00178	EU  	1998	9	25	HEEA0016053      	1	19980918	G	2110	5A535024	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										AIR COMPRESSOR	SEIZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				AIR COMPRESSOR BEARING FROZEN UP.						1	G	7	1 	3U				H9EU
1998092500179	19980925	00179	EU  	1998	9	25	HEEA0016054      	1	19980918	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				WORN ROD END BEARINGS.  SERIAL NUMBERS REMOVED ARE PMA33051 AND PMA1403.						1	G	7	1 	3U				H9EU
1998092500172	19980925	00172	SW  	1998	9	25	HEEA0016055      	1	19980918	G	3212	407350302101	BAG             			BELL  	407   	407         		SW  										FLOAT	PUNCTURED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				HOLE IN FLOAT BAG.						1	G	7	1 	3U			O	H2SW
1998092500173	19980925	00173	SW  	1998	9	25	HEEA0016056      	1	19980918	G	6510	406040340101	DISK            			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				TWO EACH CRACKED DISKS IN TAIL ROTOR.						1	G	7	1 	3U			O	H2SW
1998092500174	19980925	00174	SW  	1998	9	25	HEEA0016057      	1	19980918	G	5610	407030643101	HINGE           			BELL  	407   	407         		SW  										COCKPIT WINDOW	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				HOLES WORN ON HINGE.						1	G	7	1 	3U			O	H2SW
1998092500175	19980925	00175	SW  	1998	9	25	HEEA0016058      	1	19980918	G	5610	407030643102	HINGE           			BELL  	407   	407         		SW  										COCKPIT WINDOW	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				HOLES WORN ON HINGE.						1	G	7	1 	3U			O	H2SW
1998092500176	19980925	00176	SW  	1998	9	25	HEEA0016059      	1	19980918	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				BLOWER HOUSING CRACKED AT ATTACHED POINTS.						1	G	7	1 	3U			O	H2SW
1998100900474	19981009	00474	SW  	1998	10	9	HEEA0016062      	1	19980921	G	6340	214074280107	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH				MR255	33197				NR 1 ENGINE WARNING LIGHT COMES ON INTERMITTENTLY IN-FIGHT.						1	G	7	2 	4U				H4SW
1998100900475	19981009	00475	SW  	1998	10	9	HEEA0016063      	1	19980921	G	6420	222012701119	HUB             			BELL  	230   	230         	1182149	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	2405 			A294	23009				HUB REMOVED FOR 2500 HOUR OVERHAUL.  FOUR EACH BLADE BEARINGS CRACKED.						1	G	7	2 	3U			NC	H9SW
1998100900476	19981009	00476	SW  	1998	10	9	HEEA0016064      	1	19980921	G	6420	222312753103	BEARING         		222012701117	BELL  	230   	230         	1182149	SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN	2405 			A292	23009				HUB REMOVED FOR 2500 HOUR OVERHAUL.  FOUR EACH BLADE BEARINGS CRACKED.						1	G	7	2 	3U			NC	H9SW
1998100900465	19981009	00465	NE  	1998	10	9	HEEA0016065      	1	19980925	G	2510	A1077B	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H				CD22512	760233				TRANSFORMER RECTIFIER NOT SUPPLYING POWER TO EMS EQUIP.   CONTACTS B2 AND B3 SHOULD HAVE CONTINUITY WITH RELAY AT REST T	O ALLOW EMS TRANSFORMER RECTIFIER TO SUPPLY POWER TO EMS SYSTEMS.  THIS RELAY DOES NOT.  REMOVED AND REPLACED WITH SERVI	CEABLE RELAY.				1	G	7	2 	3U				H1NE
1998100900466	19981009	00466	NE  	1998	10	9	HEEA0016066      	1	19980925	G	2510	A1077B	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	3122H				CJ61870	760233				BAD FROM STOCK - MICROSWITCH STUCK 12 AND 13 DOES NOT OPEN WHEN RELAY IS PULLED.  REMOVED AND REPLACED WITH SERVICEABLE 	RELAY.					1	G	7	2 	3U				H1NE
1998100900467	19981009	00467	NE  	1998	10	9	HEEA0016067      	1	19980925	G	6321	7665009803103	ROTOR BRAKE     			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V				286	760158				ROTOR BRAKE MOTOR RUNS CONTINUOUSLY AND NEVER BUILDS UP PRESSURE (SUSPECT VALVE STUCK CLOSED).  UNIT INSPECTED BY ACCESS	ORY OVERHAUL SHOP.  THERE WAS NO PROBLEM FOUND WITH UNIT.					1	G	7	2 	3U				H1NE
1998100900468	19981009	00468	NE  	1998	10	9	HEEA0016068      	1	19980925	G	6321	7665009803103	ROTOR BRAKE     			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V				368	760158				WITH ROTOR BRAKE ON AND ROTOR SPOOLING DOWN (STILL TURNING)...WINDSHIELD HOT  BUS TIE OPEN TFMR RECT AND DOOR OPEN WARNI	NG LIGHTS CYCLE ON AND OFF ON MASTER CAUTION PANEL UNTIL ROTOR COMES TO A COMPLETE STOP.  ROTOR BRAKE FUNCTION NORMAL. U	NIT CURRENTLY IN ACCESSORY OVERHAUL SHOP FOR REPAIRS.				1	G	7	2 	3U				H1NE
1998100900469	19981009	00469	NE  	1998	10	9	HEEA0016069      	1	19980925	G	6321	7665009803103	ROTOR BRAKE     			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				ROTOR BRAKE INOPERATIVE.  REPLACED WITH SERVICEABLE UNIT.						1	G	7	2 	3U				H1NE
1998100900470	19981009	00470	NE  	1998	10	9	HEEA0016070      	1	19980925	G	6321	7665009803105	MODULE          			SKRSKY	S76   	S76A        	8143006	NE  										ROTOR BRAKE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				MODULE CYCLES CONTINUOUSLY WHEN ON.  UNIT INSPECTED BY ACCESSORY OVERHAUL SHOP.   REPLACED O-RINGS AND BEARINGS DUE TO C	ONTAMINATION.					1	G	7	2 	3U				H1NE
1998100900471	19981009	00471		1998	10	9	HEEA0016072      	1	19980925	G	5320	6896407	SUPPORT         																	FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					47707					RECEIVING INSPECTION REVEALED:   WELDMENT NOT MACHINED IN FRONT SUPPORT SCAVENGE PORT.
1998100900472	19981009	00472		1998	10	9	HEEA0016073      	1	19980925	G	5320	6896407	SUPPORT         																	FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					47701					RECEIVING INSPECTION REVEALED:  WELDMENT NOT MACHINED IN FRONT SUPPORT SCAVENGE PORT.
1998100900473	19981009	00473		1998	10	9	HEEA0016074      	1	19980925	G	5320	6896407	SUPPORT         																	FUSELAGE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					47699					RECEIVING INSPECTION REVEALED:  WELDMENT NOT MACHINED IN FRONT SUPPORT SCAVENGE PORT.
1998100900477	19981009	00477	SW  	1998	10	9	HEEA0016075      	1	19980925	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH				NHFS3045	53207				TAIL ROTOR LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW
1998100900478	19981009	00478	SW  	1998	10	9	HEEA0016076      	1	19980925	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH				NHFS3049	53207				TAIL ROTOR LINK HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW
1998100900479	19981009	00479	SW  	1998	10	9	HEEA0016077      	1	19980925	G	3212	206050247132	COVER           			BELL  	407   	407         		SW  										FLOAT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				CAP MISSING FROM FLOAT.						1	G	7	1 	3U			O	H2SW
1998100900480	19981009	00480	SW  	1998	10	9	HEEA0016078      	1	19980925	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				ONE DISC CRACKED AND REMAINDER CORRODED OR RUSTY.   LOCATION 2ND FROM T/R GEARBOX.						1	G	7	1 	3U			O	H2SW
1998100900481	19981009	00481	SW  	1998	10	9	HEEA0016079      	1	19980925	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				DISK CRACKED 2ND FROM T/R GEARBOX.						1	G	7	1 	3U			O	H2SW
1998100900482	19981009	00482	EU  	1998	10	9	HEEA0016080      	1	19980925	G	6710	SC5083	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	60951	1263 				2771				MAIN ROTOR SERVO LEAKING.						1	G	7	1 	3U				H9EU
1998100900483	19981009	00483	EU  	1998	10	9	HEEA0016081      	1	19980925	G	2121	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  										AIR DIST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				BLOWER MOTOR DOESN'T RUN, AIR FINS UNBOUNDED.						1	G	7	1 	3U				H9EU
1998100900484	19981009	00484	EU  	1998	10	9	HEEA0016082      	1	19980925	G	6322	9696	MOTOR           			SNIAS 	350   	AS350B2     	8680813	EU  										BLOWER	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L					2873				BLOWER MOTOR HAS BEARING NOISE.						1	G	7	1 	3U				H9EU
1998100900485	19981009	00485	EU  	1998	10	9	HEEA0016083      	1	19980925	G	7712	305731365	INDICATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				COCKPIT INDICATOR STICKING.						1	G	7	1 	3U				H9EU
1998100900486	19981009	00486	SW  	1998	10	9	HEEA0016087      	1	19980928	G	2435	206062200123	STARTER         			BELL  	407   	407         		SW  										STARTER/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				STARTER/GENERATOR FAILED 300 HOUR INSPECTION.						1	G	7	1 	3U			O	H2SW
1998100900487	19981009	00487	SW  	1998	10	9	HEEA0016088      	1	19980929	G	2435	206062200113	STARTER         			BELL  	407   	407         		SW  										STARTER/GEN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	501  				53199				STARTER HAD DEAD SPOT AND WILL NOT MOTOR INTERMITTENTLY.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND BRUSHES EXCESSI	VELY WORN, PITTED COMMUTATOR AND SHORTED STATOR.  INSPECTED AND REPAIRED.					1	G	7	1 	3U			O	H2SW
1998100900488	19981009	00488	EU  	1998	10	9	HEEA0016089      	1	19980929	G	6510	112131521	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM	6190 			669	S683				TAIL ROTOR SHAFT HAS WORN BEARINGS OR SLEEVES.						1	G	7	2 	3U				H3EU
1998100900489	19981009	00489	EU  	1998	10	9	HEEA0016090      	1	19980929	G	6510	112131521	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM				550	S683				CORROSION ON SHAFT.						1	G	7	2 	3U				H3EU
1998102300233	19981023	00233	EU  	1998	10	23	HEEA0016093      	1	19981005	G	6420	350A33211905	BODY            			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				EXCESSIVE CORROSION AROUND BEARING BORE HOLE AND HINGE BEARING.  RUBBER SEPARATION BEARING P/N 350A33-2153-00, TT 650:35	 HOURS.					1	G	7	1 	3U				H9EU
1998102300234	19981023	00234	EU  	1998	10	23	HEEA0016094      	1	19981005	G	6321	350A32050002	BRAKE ASSY      			SNIAS 	350   	AS350B2     	8680813	EU  										ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4000L	1026 				2873				BRAKE ASSEMBLY WORN.						1	G	7	1 	3U				H9EU
1998102300235	19981023	00235	EU  	1998	10	23	HEEA0016095      	1	19981005	G	6420	350A33200405	SPIDER          			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	RATCHETING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				TAIL ROTOR HAS RATCHETING BEARINGS.						1	G	7	1 	3U				H9EU
1998102300236	19981023	00236	EU  	1998	10	23	HEEA0016096      	1	19981005	G	2435	150SG122Q	STARTER         			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PART RECEIVED DAMAGED, STARTER CRACKED.						1	G	7	1 	3U				H9EU
1998102300237	19981023	00237	EU  	1998	10	23	HEEA0016097      	1	19981005	G	6720	350A27195011	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				BEARINGS RUSTED OUT (BALL BEARINGS FALLING OUT)						1	G	7	1 	3U				H9EU
1998102300238	19981023	00238	EU  	1998	10	23	HEEA0016099      	1	19981005	G	2121	420800001	BLOWER          			SNIAS 	350   	AS350B2     	8680813	EU  										AIR DIST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				BLADE BROKEN AND WILL NOT RUN.						1	G	7	1 	3U				H9EU
1998102300239	19981023	00239	EU  	1998	10	23	HEEA0016100      	1	19981005	G	5350	350A31201621	FAIRING         			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				FAIRING CRACKED AT MOUNT HOLE.						1	G	7	1 	3U				H9EU
1998102300240	19981023	00240		1998	10	23	HEEA0016101      	1	19981005	G	2510	57521810	SEAT BELT       																	COCKPIT	IMPROPER PART   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										UNITS ARE NOT CERTIFIED FOR USE IN THE UNITED STATES.
1998102300210	19981023	00210	SW  	1998	10	23	HEEA0016102      	1	19981005	G	7910	206061505115	OIL TANK        			BELL  	407   	407         		SW  										ENGINE OIL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	510PH					53209				TANKS ASSEMBLY CRACKED AT VENT FITTING.						1	G	7	1 	3U			O	H2SW
1998102300211	19981023	00211	SW  	1998	10	23	HEEA0016104      	1	19981005	G	3212	206050247132	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				VELCRO ON AFT CAP WORN, STICKING ON VELCRO/FABRIC HAS TORN OUT.						1	G	7	1 	3U			O	H2SW
1998102300212	19981023	00212	SW  	1998	10	23	HEEA0016105      	1	19981005	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				FUEL TRANSFER LIGHT EXTINGUISHES ON SHUT DOWN.						1	G	7	1 	3U			O	H2SW
1998102300213	19981023	00213	SW  	1998	10	23	HEEA0016106      	1	19981005	G	6210	407012101105	BLADE           			BELL  	407   	407         		SW  										MAIN ROTOR	IMPROPER PART   	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										THIS BLADE CANNOT BE USED ON A/C S/N 53159 PER PER T.B. 407-98-8.						1	G	7	1 	3U			O	H2SW
1998102300214	19981023	00214	SW  	1998	10	23	HEEA0016107      	1	19981005	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				FLOAT COVER HAS TORN CAP.						1	G	7	1 	3U			O	H2SW
1998102300215	19981023	00215	SW  	1998	10	23	HEEA0016109      	1	19981005	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				COUPLING HAS CRACKED DISC.						1	G	7	1 	3U			O	H2SW
1998102300216	19981023	00216	SW  	1998	10	23	HEEA0016110      	1	19981005	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	2304 				53070				BEARINGS WORN.  SERIAL NUMBERS REMOVED ARE RXFS-2032 AND RXFS-2003.						1	G	7	1 	3U			O	H2SW
1998102300217	19981023	00217	SW  	1998	10	23	HEEA0016111      	1	19981005	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										M/R DRIVE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				MGT INDICATOR PEGS OUT INTERMITTENTLY.						1	G	7	1 	3U			O	H2SW
1998102300218	19981023	00218	SW  	1998	10	23	HEEA0016112      	1	19981005	G	2841	407375006101	INDICATOR       			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				FUEL GAUGE FAILED.						1	G	7	1 	3U			O	H2SW
1998102300219	19981023	00219	SW  	1998	10	23	HEEA0016113      	1	19981005	G	7931	407375004101	INDICATOR       			BELL  	407   	407         		SW  										ENGINE OIL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				ENGINE OIL PRESSURE DROPPED TO ZERO DURING GROUND RUN.						1	G	7	1 	3U			O	H2SW
1998102300220	19981023	00220	SW  	1998	10	23	HEEA0016114      	1	19981005	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										MGB TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH	191  				53266				MGT INDICATOR STICKS ON START-UP  (WILL NOT REGISTER TEMP INDICATION UNTIL WELL INTO START).						1	G	7	1 	3U			O	H2SW
1998102300221	19981023	00221	SW  	1998	10	23	HEEA0016115      	1	19981005	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										MGB	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				MGT INDICATOR WILL NOT INTERFACE WITH TERMINAL SOFTWARE.						1	G	7	1 	3U			O	H2SW
1998102300222	19981023	00222	SW  	1998	10	23	HEEA0016116      	1	19981005	G	7714	407375002103	INDICATOR       			BELL  	407   	407         		SW  										ENGINE NG	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	141MA					53016				NG INDICATOR WILL NOT SELF-TEST.						1	G	7	1 	3U			O	H2SW
1998102300223	19981023	00223	SW  	1998	10	23	HEEA0016117      	1	19981005	G	3212	407350302101	FLOAT BAG       			BELL  	407   	407         		SW  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	612PH	525  				53199				RIGHT AFT FLOAT BAG LEAKING.						1	G	7	1 	3U			O	H2SW
1998102300224	19981023	00224	SW  	1998	10	23	HEEA0016118      	1	19981005	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				STARTER WILL NOT  MOTOR OR ENGAGE.						2	G	7	2 	4U				H10SW
1998102300199	19981023	00199		1998	10	23	HEEA0016119      	2	19981006	G	7230	6851430	REAR DIFFUSER   		6890550     															TURBINE	PITTED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAC38464					RECEIVING INSPECTION REVEALED:  PITS ON REAR DIFFUSER MAJOR AND MINOR SEALS.  PART OVERHAULED W/O LF3102.
1998102300200	19981023	00200	GL  	1998	10	23	HEEA0016120      	2	19981006	G	7250	23034775	SUPPORT         		23035128    	BELL  	206   	206L4       	1182110	SW  	ALLSN 	250C  	250C30P     	03013	GL  					GP SECTION	BENT            	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	7077B				CAT90463	52037	CAE895606			RECEIVING INSPECTION REVEALED:  BEND BEYOND SERVICEABLE LIMITS ON G.P. SUPPORT PRESSURE OIL STRUT.  PART OVERHAULED W/O 	16671.					1	G	7	1 	3U	3	U	NC	H2SW    	E1GL
1998102300201	19981023	00201	GL  	1998	10	23	HEEA0016121      	2	19981006	G	7230	6876667	TUBE            			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FIREWALL	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  TUBE UNABLE TO FIT INTO SCROLL.  PART OVERHAULED ON W/O NR L169384.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998102300202	19981023	00202	GL  	1998	10	23	HEEA0016122      	2	19981006	G	7240	6895800	TUBE            			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  PISTON RING AREA OVERSIZED.    PART OVERHAULED ON WO NR L1742524.						1	G	7	1 	3U	3	U		H2SW    	E1GL
1998102300203	19981023	00203	GL  	1998	10	23	HEEA0016123      	2	19981006	G	7250	6851531	NOZZLE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					4TH STAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	967MB					S737				RECEIVING INSPECTION REVEALED:  VOIDS IN NR 4 NOZZLE TIP PATHS.  PART OVERHAULED ON WO NR L174496.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998102300204	19981023	00204	GL  	1998	10	23	HEEA0016124      	2	19981006	G	7250	6879879	COLLECTOR       			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED:  MEASURED .085 INCH OVER BP SPECS (.105 INCH - .110 INCH) ON EXHAUST COLLECTOR FLANGE.  P	ART OVERHAULED ON  W/O NR  15644.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998102300225	19981023	00225	SW  	1998	10	23	HEEA0016126      	1	19981006	G	6520	PHI407112	BOOT            			BELL  	407   	407         		SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	407MM	1970 				53060				BOOT SWOLLEN AND LEAKING GREASE.  ALSO REMOVED TRUNNION ASSY P/N 206-011-728-001, DUE TO SPINDLES WORN BEYOND LIMITS.  A	LSO REMOVED BEARINGS P/N MS27641-5 DUE TO TRUNNION SPINDLE SEAT WORN BEYOND LIMITS.					1	G	7	1 	3U			O	H2SW
1998102300226	19981023	00226	GL  	1998	10	23	HEEA0016127      	1	19981006	G	7922	23063392	VALVE           			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					ENG OIL TEMP	FAILED          	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	141MA	454  				53016				REPAIR DUE TO OIL TEMPERATURE EXCEEDED 120 DEGREES.  CAUSE FOR OIL TEMP - OIL TEMP THERMAL VALVE P/N 724155, S/N 6056.						1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998102300227	19981023	00227	GL  	1998	10	23	HEEA0016128      	2	19981006	G	7200	23063392	ENGINE          			BELL  	407   	407         		SW  	ALLSN 	250C  	250C47B     		GL  					POWER SECT	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH	519  				53038				REPAIR DUE TO ENGINE OIL PRESSURE DROPPED TO ZERO AND METAL IN OIL.  CAUSE FOR LOSS OF OIL PRESSURE - A CRACKED SLEEVE O	N AIRCRAFT LINE P/N 407-062-532-01.					1	G	7	1 	3U	3	U	O	H2SW    	E1GL
1998102300228	19981023	00228	SW  	1998	10	23	HEEA0016129      	1	19981007	G	2434	214175150105	GENERATOR       			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	1626 				28102				GENERATOR BURNED AND SHAFT GRINDS.						2	G	7	2 	4U				H10SW
1998102300205	19981023	00205	GL  	1998	10	23	HEEA0016130      	2	19981007	G	7313	6879867	NOZZLE          			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					NR 3	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				ENGINE REMOVED DUE TO LOW POWER AND SMOKE ON DECELERATION.  REPLACED NR 3 NOZZLE, POWER INCREASED 6 PERCENT.  TRIED NR 3	 NOZZLE ON ANOTHER TURBINE.  LOW POWER ON TEST CELL.   REPLACED NOZZLE AND HAD A 3 PERCENT INCREASE IN POWER.  INSTALLED	 A STANDARD AERO OVERHAULED NR 3 NOZZLE.				1	G	7	2 	3U	3	U		H3EU    	E4CE
1998102300206	19981023	00206	GL  	1998	10	23	HEEA0016131      	2	19981007	G	7230	6899170	SUPPORT         			BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C28B     	03013	GL  					ENGINE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	5748Q					45499				ENGINE REMOVED DUE TO CRACKED SCROLL.  FRONT SUPPORT WAS TRANSFERRED TO COMPRESSOR S/N CAC70646.  ENGINE FAILED CELL TES	T DUE TO HIGH COMPRESSOR VIBS.  REPLACED FRONT SUPPORT.   CURED PROBLEM.  TRANSFERRED FRONT SUPPORT TO COMPRESSOR S/N CA	C70016.  ENGINE FAILED DUE TO HIGH COMPRESSOR VIBS.  REPLACED FRONT SUPPORT.				1	G	7	1 	3U	3	U		H2SW    	E1GL
1998102300229	19981023	00229	SW  	1998	10	23	HEEA0016132      	1	19981007	G	6300	230025819101	BRACKET         			BELL  	230   	230         	1182149	SW  										M/R DRIVE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BRACKET MIS-MANUFACTURED.   NOT FORMED WITH ENOUGH BEND.						1	G	7	2 	3U			NC	H9SW
1998102300230	19981023	00230	SW  	1998	10	23	HEEA0016133      	1	19981007	G	2435	206062200123	STARTER         			BELL  	407   	407         		SW  										START/GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH	754  				53198				300 HOUR INSPECTION.  FOUND BRUSHES WERE EXCESSIVELY WORN AND END BELL HAD SURFACE CORROSION.						1	G	7	1 	3U			O	H2SW
1998102300231	19981023	00231	SW  	1998	10	23	HEEA0016134      	1	19981007	G	2435	206062200113	STARTER         			BELL  	407   	407         		SW  										START/GEN	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	719PH	237  				53266				GENERATOR FAILED IN-FLIGHT AND STARTER WOULD NOT TURN OVER.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND BRUSHES EXCE	SSIVELY WORN AND BURNED.					1	G	7	1 	3U			O	H2SW
1998102300232	19981023	00232	SW  	1998	10	23	HEEA0016135      	1	19981007	G	2432	28SP100	CELL            		31908001    	BELL  	407   	407         		SW  										BATTERY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416				9703851	53070				CELL BURNT WHILE BATTERY WAS ON FINAL CHARGE. REPLACED CELL WITH NEW ONE, COMPLETED CHARGE AND RETURNED BATTERY TO SERVI	CE.					1	G	7	1 	3U			O	H2SW
1998102300207	19981023	00207	GL  	1998	10	23	HEEA0016136      	2	19981008	G	7210	6894171	GEARBOX         			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ENGINE	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81992	3242 				S827	CAE835682			ENGINE REMOVED DUE TO METAL.  INSPECTION OF GEARBOX REVEALED:  PULLED COMPRESSOR MOUNT INSERT AS MARKED AND BRONZE LIFTI	NG ON GEARBOX FORWARD AND AFT PTO BORES.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998102300208	19981023	00208	GL  	1998	10	23	HEEA0016137      	2	19981008	G	7210	23037419	COVER           		6894171     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH				CAG34140	S557	CAE834061			ENGINE REMOVED DUE TO LOW POWER.  UPON DISASSEMBLY OF ENGINE NOTED:  DETACHED SPARE CAGE IN GEARBOX.  GEARBOX DISASSEMBL	Y REVEALED:  DETACHED SPARE CAGE AND LOOSE CAGES AS MARKED ON GEARBOX COVER.  INSTALLED  OVERHAULED COVER.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998102300209	19981023	00209	GL  	1998	10	23	HEEA0016138      	2	19981008	G	7210	23008021	HOUSING         		6894171     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					GEARBOX	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH				CAG34140	S557	CAE834061			ENGINE REMOVED DUE TO LOW POWER.  UPON DISASSEMBLY OF ENGINE NOTED:  DETACHED SPARE CAGE IN GEARBOX.  GEARBOX DISASSEMBL	Y REVEALED: LOOSE P.T.O. CAGE IN GEARBOX HOUSING. INSTALLED A OVERHAULED GEARBOX HOUSING.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998103000143	19981030	00143	SW  	1998	10	30	HEEA0016139      	1	19981013	G	6220	206011118001	BEARING         			BELL  	206   	206L1       	1182107	SW  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										CLEANED MAIN ROTOR BEARING AND FOUND TO BE RUSTED AND PITTED.						1	G	7	1 	3U				H2SW
1998103000162	19981030	00162	EU  	1998	10	30	HEEA0016144      	1	19981013	G	6220	704A33633109	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										SPHERICAL THRUST	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	1228 				2653				RUBBER PUSHING OUT OF  SPHERICAL THRUST BEARING.						1	G	7	1 	3U				H9EU
1998103000144	19981030	00144	SW  	1998	10	30	HEEA0016147      	1	19981013	G	2150	2730502	VALVE           			BELL  	230   	230         	1182149	SW  										AIR COND	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				VALVE HAS INTERMITTENT OPERATION.						1	G	7	2 	3U			NC	H9SW
1998103000145	19981030	00145	SW  	1998	10	30	HEEA0016148      	1	19981013	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				COOLER HAS METAL CONTAMINATION.						1	G	7	1 	3U			O	H2SW
1998103000146	19981030	00146	SW  	1998	10	30	HEEA0016149      	1	19981013	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				COOLER LEAKING.						1	G	7	1 	3U			O	H2SW
1998103000147	19981030	00147	SW  	1998	10	30	HEEA0016150      	1	19981013	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				TAIL ROTOR DISK COUPLING CRACKED ON AFT FACING SIDE NR 6 SEGMENT.						1	G	7	1 	3U			O	H2SW
1998103000148	19981030	00148	SW  	1998	10	30	HEEA0016151      	1	19981013	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				AFT O/C BLOWER COUPLING CRACKED AND HAS CORROSION.						1	G	7	1 	3U			O	H2SW
1998103000149	19981030	00149	SW  	1998	10	30	HEEA0016152      	1	19981013	G	6500	406040339111	BEARING         		406040320101	BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH				AFS118	53278				TAIL ROTOR HAS ROUGH BEARINGS.  SERIAL NUMBERS REMOVED ARE 98-0495 AND 98-0435.  REPLACEMENT PART SERIAL NUMBERS ARE 98-	0637 AND 98-0665.					1	G	7	1 	3U			O	H2SW
1998103000150	19981030	00150	SW  	1998	10	30	HEEA0016153      	1	19981013	G	7931	222375019009	TRANSDUCER      			BELL  	230   	230         	1182149	SW  										OIL PRESSURE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				TRANSDUCER READS HIGH.						1	G	7	2 	3U			NC	H9SW
1998103000151	19981030	00151		1998	10	30	HEEA0016154      	4	19981013	G	3434	FM1012	ANTENNA         			BELL  	230   	230         	1182149	SW  										MARKER BEACON	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				BEACON INTERMITTENT, INOPERATIVE.						1	G	7	2 	3U			NC	H9SW
1998103000152	19981030	00152	SW  	1998	10	30	HEEA0016155      	1	19981013	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				EXHAUST DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1998103000153	19981030	00153	SW  	1998	10	30	HEEA0016156      	1	19981013	G	5302	206032305127	FRAME           			BELL  	407   	407         		SW  										TAIL BOOM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				TAIL BOOM FRAME CRACKED.						1	G	7	1 	3U			O	H2SW
1998103000154	19981030	00154	SW  	1998	10	30	HEEA0016157      	1	19981013	G	5320	206032305129A	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				ANGLE CRACKED.						1	G	7	1 	3U			O	H2SW
1998103000155	19981030	00155	SW  	1998	10	30	HEEA0016158      	1	19981013	G	7714	214175251107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										TRIPLE TACH	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				TRIPLE TACHOMETER ON NR 2 ENGINE ERRATIC.						2	G	7	2 	4U				H10SW
1998103000156	19981030	00156		1998	10	30	HEEA0016159      	4	19981014	G	2340	PM212302	SWITCH          			BELL  	407   	407         		SW  										COCKPIT	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				ICS LEG BROKEN.						1	G	7	1 	3U			O	H2SW
1998103000157	19981030	00157	SW  	1998	10	30	HEEA0016160      	1	19981014	G	6340	407375001105	INDICATOR       			BELL  	407   	407         		SW  										MGT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	406PH					53198				MGT FAILED IN FLIGHT, FULL DEFLECTION.						1	G	7	1 	3U			O	H2SW
1998103000158	19981030	00158		1998	10	30	HEEA0016161      	4	19981014	G	3120	M803B205VBATT	CLOCK           			BELL  	407   	407         		SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				CLOCK INACCURATE, ALSO HAS EXCESSIVE CORROSION.						1	G	7	1 	3U			O	H2SW
1998103000163	19981030	00163	EU  	1998	10	30	HEEA0016162      	1	19981014	G	5610	04011340990	HANDLE          			SNIAS 	350   	AS350B2     	8680813	EU  										RT WINDOW	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				SLIDE WINDOW HANDLE CRACKED, SLIDE WINDOW CRACKED.						1	G	7	1 	3U				H9EU
1998103000164	19981030	00164	EU  	1998	10	30	HEEA0016164      	1	19981014	G	2435	150SG122Q	STARTER         			SNIAS 	350   	AS350B2     	8680813	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	9445 				2771				STARTER/GENERATOR ARCING AND WILL NOT MOTOR ENGINE.						1	G	7	1 	3U				H9EU
1998103000165	19981030	00165	EU  	1998	10	30	HEEA0016165      	1	19981014	G	6220	ELT302301	FREQ ADAPTER    			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				FREQUENCY ADAPTER HAS RUBBER SEPARATION BEYOND LIMITS.  SERIAL NUMBERS REMOVED ARE 4056, 4075, AND 4080.						1	G	7	1 	3U				H9EU
1998103000166	19981030	00166	EU  	1998	10	30	HEEA0016166      	1	19981014	G	6420	350A33200405	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R SPIDER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				TAIL ROTOR SPIDER'S BEARINGS ROUGH.						1	G	7	1 	3U				H9EU
1998103000159	19981030	00159	SW  	1998	10	30	HEEA0016167      	1	19981016	G	6320	204040386001	CASE ASSY       			BELL  	412   	412         	1182202	SW  										TRANSMISSION	DEFECTIVE       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRANSMISSION UNABLE TO OBTAIN PROPER BACKLASH ON QUILLS.  POSSIBLE DEFECTIVE PART.						1	G	7	2 	4U				H4SW
1998103000141	19981030	00141	GL  	1998	10	30	HEEA0016168      	2	19981016	G	7230	23051122	REAR DIFFUSER   		23051643    	BELL  	206   	206L1       	1182107	SW  	ALLSN 	250C  	250C30P     	03013	GL  					ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5005B				CAC91619	45175	CAE890024			ENGINE REMOVED DUE TO F.O.D.   UPON INSPECTION OF COMPRESSOR PARTS NOTED:   CRACKING AND LIFTING BEYOND SERVICEABLE LIMI	TS ON REAR DIFFUSER MAJOR SEAL.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998103000142	19981030	00142		1998	10	30	HEEA0016169      	2	19981016	G	7250	23032264	NOZZLE          																	ENGINE	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVING INSPECTION REVEALED: UNABLE TO OBTAIN RUNOUTS IN LIMITS WHEN INSTALLED IN FIXTURE.  OBTAINED .005 TIR ON BOTH 	TIP PATHS.
1998103000160	19981030	00160	SW  	1998	10	30	HEEA0016171      	1	19981016	G	7930	407375004101	INDICATOR       			BELL  	407   	407         		SW  										ENGINE OIL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				TEMPERATURE SEGMENT ON INDICATOR INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998103000161	19981030	00161	SW  	1998	10	30	HEEA0016172      	1	19981016	G	2430	214175131103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				INTERMITTENT START PROBLEMS.						2	G	7	2 	4U				H10SW
1998103000167	19981030	00167	EU  	1998	10	30	HEEA0016174      	1	19981016	G	2930	MA12401	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  										HYDRAULIC SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				HYDRAULIC LOW PRESSURE LIGHT REMAINED OFF DURING SHUTDOWN.						1	G	7	1 	3U				H9EU
1998111300001	19981113	00001	GL  	1998	11	13	HEEA0016176      	2	19981019	G	7230	23056634	SPUR GEAR       		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SPUR ADAPTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	979BH	472  			CAC91903	51403	CAE895816			ENGINE REMOVED DUE TO TURBINE OVERHAUL.  VISUAL INSPECTION OF COMPRESSOR REVEALED:  STEP WEAR BEYOND SERVICEABLE LIMITS 	ON SHAFT AFT SPLINES.  INSTALLED A NEW SHAFT.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998111300002	19981113	00002	GL  	1998	11	13	HEEA0016177      	2	19981019	G	7230	23031922	SHAFT           		6890550     	BELL  	206   	206B3       	1181506	SW  	ALLSN 	250C  	250C20B     	03013	GL  					COMPRESSOR	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2270G	108  			CAC40329	3610	CAE834578			ENGINE REMOVED DUE TO METAL.  UPON INSPECTION OF COMPRESSOR PARTS NOTED:  SPALLING ON SHAFT GEAR TEETH.  INSTALLED A NEW	 SHAFT.					1	G	7	1 	3U	3	U		H2SW    	E4CE
1998111300003	19981113	00003	GL  	1998	11	13	HEEA0016178      	2	19981019	G	7210	23034787	BEARING         		6894171     	BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					2.5 BEARING	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J	231  			CAG38747	S826	CAE836341			ENGINE REMOVED DUE TO METAL.  UPON INSPECTION OF GEARBOX PARTS NOTED:  SPALLED ON NR 2 1/2 BEARING OUTER RACE AND ROLLER	S. INSTALLE D A NEW BEARING.					1	G	7	2 	3U	3	U		H3EU    	E4CE
1998111300004	19981113	00004	GL  	1998	11	13	HEEA0016179      	2	19981019	G	7230	23056634	SPUR GEAR       		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					SPUR ADAPTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X	953  			CAC91648	51494	CAE895603			ENGINE REMOVED DUE TO CRACKED SCROLL.   DISASSEMBLY INSPECTION REVEALED:  STEP WEAR BEYOND SERVICEABLE LIMITS ON SPUR GE	AR SHAFT AFT SPLINES.  FAILED NO-GO GAUGE.  INSTALLED A NEW SPUR GEAR.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998111300005	19981113	00005	GL  	1998	11	13	HEEA0016180      	2	19981019	G	7230	23035262	BEARING         		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 1	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X	953  			CAC91648	51494	CAE895603			ENGINE REMOVED DUE TO CRACKED SCROLL.  DISASSEMBLY INSPECTION REVEALED:  SPALLING ON NR 1 BEARING ROLLER.  INSTALLED A N	EW NR 1 BEARING.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998111300006	19981113	00006	GL  	1998	11	13	HEEA0016181      	2	19981019	G	7230	23009626	CARBON SEAL     		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					MATING SURFACE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X	953  			CAC91648	51494	CAE895603			ENGINE REMOVED DUE TO CRACKED SCROLL.   DISASSEMBLY INSPECTION REVEALED:  PITTED BEYOND SERVICEABLE LIMITS ON CARBON SEA	L MATING SURFACE.  INSTALLED A NEW CARBON SEAL.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998111300007	19981113	00007	GL  	1998	11	13	HEEA0016182      	2	19981019	G	7230	23004514	MATING RING     		23051643    	BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					NR 1 BEARING	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8590X	953  			CAC91648	51494	CAE895603			ENGINE REMOVED DUE TO CRACKED SCROLL.   DISASSEMBLY INSPECTION REVEALED:  PITTED BEYOND SERVICEABLE LIMITS ON MATING RIN	G MATING SURFACE.  INSTALLED A NEW MATING RING.					1	G	7	1 	3U	3	U		H2SW    	E1GL
1998111300128	19981113	00128	SW  	1998	11	13	HEEA0016183      	1	19981020	G	6230	407040011101	MAST ASSY       			BELL  	407   	407         		SW  										MAIN ROTOR	FLAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	2428 				53070				FOUND PRIMER ON INSIDE OF MAST FLAKING OFF DURING 12 MONTH INSPECTION.						1	G	7	1 	3U			O	H2SW
1998111300129	19981113	00129	SW  	1998	11	13	HEEA0016184      	1	19981021	G	5260	SYLC502281	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	SEIZED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				STEP ACTUATOR SEIZED.						1	G	7	2 	4U				H4SW
1998111300130	19981113	00130	SW  	1998	11	13	HEEA0016185      	1	19981021	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				STEP ACTUATOR WILL NOT ACTUATE.						1	G	7	2 	4U				H4SW
1998111300131	19981113	00131	SW  	1998	11	13	HEEA0016186      	1	19981021	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH	9899 				33150				LEADING EDGE STRIP OUTBOARD SEPARATED BEYOND LIMITS.  ALSO HAS EROSION HOLE ON THE OUTBOARD END.  THE TOP AFT FRETTING P	AD IS UNBONDED.					1	G	7	2 	4U				H4SW
1998111300132	19981113	00132	SW  	1998	11	13	HEEA0016187      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				STEP ACTUATOR WILL NOT EXTEND.						1	G	7	2 	4U				H4SW
1998111300133	19981113	00133	SW  	1998	11	13	HEEA0016188      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				STEP ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998111300134	19981113	00134	SW  	1998	11	13	HEEA0016189      	1	19981021	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	GRINDING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				STEP ACTUATOR HAS GRINDING NOISE AND STOPS WHEN STEP IS HALF WAY UP.						1	G	7	2 	4U				H4SW
1998111300135	19981113	00135	SW  	1998	11	13	HEEA0016190      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				STEP ACTUATOR STICKS INTERMITTENTLY.						1	G	7	2 	4U				H4SW
1998111300136	19981113	00136	SW  	1998	11	13	HEEA0016191      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				STEP ACTUATOR STUCK IN DOWN POSITION.  SHAFT BROKEN DURING REMOVAL.						1	G	7	2 	4U				H4SW
1998111300137	19981113	00137	SW  	1998	11	13	HEEA0016192      	1	19981021	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	SLOW            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				STEP ACTUATOR ACTUATES SLOWLY.						1	G	7	2 	4U				H4SW
1998111300138	19981113	00138	SW  	1998	11	13	HEEA0016193      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				STEP ACTUATOR WILL NOT EXTEND.						1	G	7	2 	4U				H4SW
1998111300139	19981113	00139	SW  	1998	11	13	HEEA0016194      	1	19981021	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				STEP ACTUATOR STUCK.						1	G	7	2 	4U				H4SW
1998111300140	19981113	00140	SW  	1998	11	13	HEEA0016195      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				STEP ACTUATOR INOPERATIVE WILL NOT RETRACT.						1	G	7	2 	4U				H4SW
1998111300141	19981113	00141	SW  	1998	11	13	HEEA0016196      	1	19981021	G	5260	212075418103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				STEP ACTUATOR UNIT TRAVELED APPROXIMATELY 1/2 STROKE AND STOPPED WITH SPARKS COMING FROM UNIT.						1	G	7	2 	4U				H4SW
1998111300142	19981113	00142	SW  	1998	11	13	HEEA0016197      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				STEP ACTUATOR WILL NOT ACTUTATE.  SERIAL NUMBERS REMOVED ARE BP9920 AND T28916.						1	G	7	2 	4U				H4SW
1998111300143	19981113	00143	SW  	1998	11	13	HEEA0016198      	1	19981021	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	RATCHETING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				STEP ACTUATOR RATCHETING MID-RANGE OF TRAVEL.						1	G	7	2 	4U				H4SW
1998111300144	19981113	00144	SW  	1998	11	13	HEEA0016199      	1	19981021	G	5260	212075418105	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				STEP ACTUATOR WILL NOT ACTUATE.						1	G	7	2 	4U				H4SW
1998111300145	19981113	00145	SW  	1998	11	13	HEEA0016200      	1	19981021	G	5260	SYLC502283	ACTUATOR        			BELL  	412   	412         	1182202	SW  										STEP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				STEP ACTUATOR WILL NOT ACTIVATE, INOPERATIVE.						1	G	7	2 	4U				H4SW
1998111300244	19981113	00244	EU  	1998	11	13	HEEA0016201      	1	19981021	G	6420	350A33200405	BEARING         			SNIAS 	350   	AS350B2     	8680813	EU  										T/R SPIDER	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6100R					2862				TAIL ROTOR BEARINGS ROUGH AND SEALS HARD.						1	G	7	1 	3U				H9EU
1998111300245	19981113	00245	EU  	1998	11	13	HEEA0016202      	1	19981021	G	6210	355A11002011	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6097Z	4610 				2820				MAIN ROTOR BLADE CRACKED.						1	G	7	1 	3U				H9EU
1998111300246	19981113	00246	EU  	1998	11	13	HEEA0016203      	1	19981021	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S					2777				PITCH CONTROL HAS PLAY IN BEARINGS.  SERIAL NUMBERS REMOVED ARE S1894 AND S1952.  REPLACEMENT PART SERIAL NUMBERS ARE S2	250 AND S2217.					1	G	7	1 	3U				H9EU
1998111300146	19981113	00146	SW  	1998	11	13	HEEA0016204      	1	19981021	G	6230	406310411101	BOOT            			BELL  	407   	407         		SW  										MAIN ROTOR	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MAIN ROTOR MAST BOOT TORN.						1	G	7	1 	3U			O	H2SW
1998111300147	19981113	00147	SW  	1998	11	13	HEEA0016205      	1	19981021	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1998111300148	19981113	00148	SW  	1998	11	13	HEEA0016206      	1	19981021	G	7910	206061505115	TANK            			BELL  	407   	407         		SW  										ENGINE OIL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				TANK ASSEMBLY CRACKED.						1	G	7	1 	3U			O	H2SW
1998111300149	19981113	00149	SW  	1998	11	13	HEEA0016207      	1	19981021	G	6510	407040321101	BRACKET         			BELL  	407   	407         		SW  										T/R DRIVE SHAFT	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BRACKET CRACKED.						1	G	7	1 	3U			O	H2SW
1998111300150	19981113	00150	SW  	1998	11	13	HEEA0016208      	1	19981021	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				LINK HAS WORN BEARINGS.  SERIAL NUMBERS REMOVED ARE NHFS-2711 AND NHFS-2446.  REPLACEMENT PART SERIAL NUMBERS ARE NHFS-3	742 AND NHFS-3784.					1	G	7	1 	3U			O	H2SW
1998111300151	19981113	00151	SW  	1998	11	13	HEEA0016209      	1	19981021	G	7920	407040623101	OIL TUBE        			BELL  	407   	407         		SW  										FLARE	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				OIL TUBE CORRODED AT FLARE.						1	G	7	1 	3U			O	H2SW
1998111300152	19981113	00152	SW  	1998	11	13	HEEA0016210      	1	19981021	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	125  				53070				UPPER MAIN ROTOR UNIVERSAL BEARING WORN.						1	G	7	1 	3U			O	H2SW
1998111300153	19981113	00153	SW  	1998	11	13	HEEA0016212      	1	19981021	G	6321	206340301103	PUCK            			BELL  	407   	407         		SW  										ROTOR BRAKE	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1622 				53114				ROTOR BRAKE PUCK UNBONDED FROM AFT PAD ASSEMBLY.						1	G	7	1 	3U			O	H2SW
1998111300154	19981113	00154	SW  	1998	11	13	HEEA0016213      	1	19981021	G	6230	214040118101	TRIPLEX BEARING 			BELL  	214   	214ST       	1182106	SW  										SWASHPLATE	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805	286  				28141				RECEIVED INPUT QUILL ASSEMBLY P/N 214-040-019-101 INTO OVERHAUL SHOP DUE TO METAL.  FOUND TRIPLEX BEARING SET TO BE SPAL	LING, CAUSING METAL IN OIL.					2	G	7	2 	4U				H10SW
1998111300008	19981113	00008		1998	11	13	HEEA0016214      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1547D					760077				ROCKS IN-FLIGHT.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND NR 1 POTENTIOMETER IS INOPERATIVE.						1	G	7	2 	3U				H1NE
1998111300009	19981113	00009		1998	11	13	HEEA0016215      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342	1704 				760096				PILOT REPORTED ACTUATOR TO BE INOPERATIVE.  INSPECTED BY ACCESSORY OVERHAUL SHOP AND FOUND POTENTIOMETERS HAD NO INDICAT	ION.					1	G	7	2 	3U				H1NE
1998111300010	19981113	00010		1998	11	13	HEEA0016216      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546K					760082				ACTUATOR CHATTERS AND SHAKES CYCLIC.						1	G	7	2 	3U				H1NE
1998111300011	19981113	00011	NE  	1998	11	13	HEEA0016217      	4	19981021	G	2200	8241631	POTENTIOMETER   		769000180210	SKRSKY	S76   	S76A        	8143006	NE  										YAW AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G				79025986	760076				NR 2 YAW AFCS CHANNEL INOPERATIVE.  POTS WERE SCRAPPED.						1	G	7	2 	3U				H1NE
1998111300012	19981113	00012		1998	11	13	HEEA0016218      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	KICKS           	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342	9764 				760096				ACTUATOR KICKS IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300013	19981113	00013		1998	11	13	HEEA0016219      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	KICKS           	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546K	3499 				760082				ACTUATOR KICKS IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300014	19981113	00014		1998	11	13	HEEA0016220      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	4253S	8796 				760035				ACTUATOR CHATTERS WHEN ENGAGED.						1	G	7	2 	3U				H1NE
1998111300015	19981113	00015		1998	11	13	HEEA0016221      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G	10226				760076				ACTUATOR CHATTERS IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300016	19981113	00016		1998	11	13	HEEA0016222      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	706AE	10377				760275				ACTUATOR CHATTERS, JERKS.						1	G	7	2 	3U				H1NE
1998111300017	19981113	00017		1998	11	13	HEEA0016223      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3122H					760233				ACTUATOR CHATTERING.						1	G	7	2 	3U				H1NE
1998111300018	19981113	00018		1998	11	13	HEEA0016224      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	792CH	9540 				760193				ACTUATOR CHATTERING.						1	G	7	2 	3U				H1NE
1998111300019	19981113	00019		1998	11	13	HEEA0016225      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	792CH					760193				AFCS ACTUATOR CHATTERING.						1	G	7	2 	3U				H1NE
1998111300020	19981113	00020		1998	11	13	HEEA0016226      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342	12107				760096				ACTUATOR TRAVELS TO THE RIGHT AND BACK TO CENTER, BUT WILL NOT TRAVEL TO THE LEFT.						1	G	7	2 	3U				H1NE
1998111300021	19981113	00021		1998	11	13	HEEA0016227      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3122G	9604 				760232				ACTUATOR CHATTERS.						1	G	7	2 	3U				H1NE
1998111300022	19981113	00022		1998	11	13	HEEA0016228      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	KICKS           	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342	5158 				760096				ACTUATOR KICKING IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300023	19981113	00023		1998	11	13	HEEA0016229      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5426U	10998				760167				NR 1 ROLL CHATTERING.						1	G	7	2 	3U				H1NE
1998111300024	19981113	00024		1998	11	13	HEEA0016230      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	5426U	8026 				760167				NR 2 PITCH CHATTERING.						1	G	7	2 	3U				H1NE
1998111300025	19981113	00025		1998	11	13	HEEA0016231      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	22342					760096				AFCS ACTUATOR CHATTERING AND ALSO KICKING IN FLIGHT.						1	G	7	2 	3U				H1NE
1998111300026	19981113	00026		1998	11	13	HEEA0016232      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	3122G					760232				ACTUATOR CHATTERS.						1	G	7	2 	3U				H1NE
1998111300027	19981113	00027		1998	11	13	HEEA0016233      	4	19981021	G	2210	7690001802106	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										AFCS	RATCHETS        	E			HEEA	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	1546G					760076				ACTUATOR STICKY AND RATCHETY.						1	G	7	2 	3U				H1NE
1998111300028	19981113	00028	NE  	1998	11	13	HEEA0016234      	1	19981021	G	2421	7655009005105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H1NE
1998111300029	19981113	00029	NE  	1998	11	13	HEEA0016235      	1	19981021	G	2421	7655009005105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H1NE
1998111300030	19981113	00030	NE  	1998	11	13	HEEA0016236      	1	19981021	G	2421	7655009005105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H1NE
1998111300031	19981113	00031	NE  	1998	11	13	HEEA0016237      	1	19981021	G	2421	7655009005105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H1NE
1998111300032	19981113	00032	NE  	1998	11	13	HEEA0016238      	1	19981021	G	2421	7655009005105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				GENERATOR INOPERATIVE.   AIRCRAFT HAS NO CURRENT.						1	G	7	2 	3U				H1NE
1998111300033	19981113	00033	NE  	1998	11	13	HEEA0016239      	1	19981021	G	2421	7655009005105	GENERATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H1NE
1998111300034	19981113	00034	NE  	1998	11	13	HEEA0016240      	1	19981021	G	6220	7610608000050	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				MAIN ROTOR WEAK.						1	G	7	2 	3U				H1NE
1998111300035	19981113	00035	NE  	1998	11	13	HEEA0016241      	1	19981021	G	6220	7610608000047	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				MAIN ROTOR DAMPER WEAK.						1	G	7	2 	3U				H1NE
1998111300036	19981113	00036	NE  	1998	11	13	HEEA0016242      	1	19981021	G	6220	7610608000049	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				MAIN ROTOR DAMPER WEAK.						1	G	7	2 	3U				H1NE
1998111300037	19981113	00037	NE  	1998	11	13	HEEA0016243      	1	19981021	G	6220	7610608000050	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				MAIN ROTOR DAMPER WEAK.						1	G	7	2 	3U				H1NE
1998111300038	19981113	00038	NE  	1998	11	13	HEEA0016244      	1	19981021	G	6220	7610608000049	DAMPER          			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				MAIN ROTOR DAMPER WEAK.						1	G	7	2 	3U				H1NE
1998111300039	19981113	00039	NE  	1998	11	13	HEEA0016245      	1	19981021	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	ERODED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G	8703 				760076				TAIL ROTOR BLADE PRIMARY RUBBER ERODED THROUGH ON BOTH PADDLES.						1	G	7	2 	3U				H1NE
1998111300040	19981113	00040	NE  	1998	11	13	HEEA0016246      	1	19981021	G	6410	7610105101041	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										TAIL ROTOR	ERODED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342	6337 				760096				PRIMARY RUBBER ERODED THROUGH AND ELIPTICAL PLUG UNBONDED.						1	G	7	2 	3U				H1NE
1998111300041	19981113	00041	NE  	1998	11	13	HEEA0016247      	1	19981021	G	6210	7615009100051A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K	11728				760082				FIBERGLASS TORN AT STA 120 ON THE UPPER SURFACE JUST AFT OF THE LEADING EDGE STRIP.  THE NICKEL STRIP HAS NUMEROUS AMOUN	T OF CRACKS.					1	G	7	2 	3U				H1NE
1998111300042	19981113	00042	NE  	1998	11	13	HEEA0016248      	1	19981021	G	6210	7615009100042A	BLADE           			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		12229								TRIM TAB UNBONDED DURING TRACKING AND BALANCING OF AIRCRAFT.						1	G	7	2 	3U				H1NE
1998111300043	19981113	00043	NE  	1998	11	13	HEEA0016249      	1	19981021	G	2913	7665009808102	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  										HYDRAULIC SYS	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1545X					760050				HYDRAULIC PUMP LEAKS FROM SEAL DRAIN.						1	G	7	2 	3U				H1NE
1998111300044	19981113	00044	NE  	1998	11	13	HEEA0016250      	1	19981021	G	2913	AP1V111	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  										HYDRAULIC SYS	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2743E					760155				HYDRAULIC PUMP LEAKS FROM SEAL DRAIN.						1	G	7	2 	3U				H1NE
1998111300045	19981113	00045	NE  	1998	11	13	HEEA0016251      	1	19981021	G	2913	7665009808102	PUMP            			SKRSKY	S76   	S76A        	8143006	NE  										HYDRAULIC SYS	FAILED          	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1545K					760047				O-RING FAILURE ON PLUG ON PUMP HOUSING.  SYSTEM LOST OIL AND PRESSURE.						1	G	7	2 	3U				H1NE
1998111300046	19981113	00046	NE  	1998	11	13	HEEA0016252      	1	19981021	G	7921	7630807901105	OIL COOLER      			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	707AE					760276				OIL COOLER HAS HIGH OIL TEMPERATURE.						1	G	7	2 	3U				H1NE
1998111300047	19981113	00047	NE  	1998	11	13	HEEA0016253      	1	19981021	G	7921	7636209203102	OIL COOLER      			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2743E					760155				OIL COOLER LEAKING.						1	G	7	2 	3U				H1NE
1998111300048	19981113	00048	NE  	1998	11	13	HEEA0016254      	1	19981021	G	6322	10E931	SHAFT ASSY      		763080790210	SKRSKY	S76   	S76A        	8143006	NE  										BLOWER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342				926	760096				SHAFT ASSY WORN BEYOND LIMITS.  CORROSION FOUND ON SHAFT.  REPLACED WITH SERVICEABLE SHAFT.						1	G	7	2 	3U				H1NE
1998111300049	19981113	00049	NE  	1998	11	13	HEEA0016255      	1	19981021	G	7921	5F155105	OIL COOLER      			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				M			OVER TEMP                 			IN	INSP/MAINT     	1			SW	03	707AE					760276				OIL COOLER HAS HIGH OIL TEMPERATURE.						1	G	7	2 	3U				H1NE
1998111300050	19981113	00050	NE  	1998	11	13	HEEA0016256      	1	19981021	G	3150	7655001001103	CAUTION PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X					760050				BATTERY TEMP WARNING LIGHT INOPERATIVE.						1	G	7	2 	3U				H1NE
1998111300051	19981113	00051	NE  	1998	11	13	HEEA0016257      	1	19981021	G	3150	7655001001103	CAUTION PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				NO MASTER CAUTION LIGHT WITH POWER ON.						1	G	7	2 	3U				H1NE
1998111300052	19981113	00052	NE  	1998	11	13	HEEA0016258      	1	19981021	G	3150	7655001001103	CAUTION PANEL   			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				CAUTION PANEL UNIT HAS BLOWN CIRCUIT TRACE GOING TO H AND J P2.						1	G	7	2 	3U				H1NE
1998111300053	19981113	00053		1998	11	13	HEEA0016259      	4	19981022	G	2312	064100900	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				TRANSCEIVER HAS NO TRANSMIT OR RECEIVE.						1	G	7	2 	3U				H1NE
1998111300054	19981113	00054		1998	11	13	HEEA0016260      	4	19981022	G	3431	066107800	RECEIVER        			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				RMI BAD AND COMPASS CARD NOT FOLLOWING CORRECTLY.						1	G	7	2 	3U				H1NE
1998111300055	19981113	00055		1998	11	13	HEEA0016261      	4	19981022	G	3420	1113025	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										HSI	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				COMPASS CARD STICKS INTERMITTENTLY.  PAINT ON CARD AND NEEDLE STICKING.						1	G	7	2 	3U				H1NE
1998111300056	19981113	00056		1998	11	13	HEEA0016262      	4	19981022	G	3420	1113025	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										HSI	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217					760229				HSI NAVIGATOR FLAG STICKS.						1	G	7	2 	3U				H1NE
1998111300057	19981113	00057		1998	11	13	HEEA0016263      	4	19981022	G	3420	1113025	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				HSI COURSE DIGITIZER WILL NOT ZERO.						1	G	7	2 	3U				H1NE
1998111300058	19981113	00058		1998	11	13	HEEA0016264      	4	19981022	G	3420	1113025	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				HSI COURSES SET KNOB INOPERATIVE.						1	G	7	2 	3U				H1NE
1998111300059	19981113	00059		1998	11	13	HEEA0016265      	4	19981022	G	3420	1113034	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				ATTITUDE INDICATOR WILL NOT SHOW CORRECT ATTITUDE AND GS POINTER STUCK.						1	G	7	2 	3U				H1NE
1998111300060	19981113	00060		1998	11	13	HEEA0016266      	4	19981022	G	3416	1003511326	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FRICTION        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				ALTIMETER EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H1NE
1998111300061	19981113	00061		1998	11	13	HEEA0016267      	4	19981022	G	3416	10163511839	ALTIMETER       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	707AE					760276				FAILED FUNCTION ERROR CHECK, ENCODER OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE
1998111300062	19981113	00062		1998	11	13	HEEA0016268      	4	19981022	G	3421	125780	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT ADI	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				ADI INDICATOR PRECESSES IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300063	19981113	00063	NE  	1998	11	13	HEEA0016269      	1	19981022	G	3510	10C001616T	OXY CONVERTER   			SKRSKY	S76   	S76A        	8143006	NE  										OXYGEN SYS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				OXYGEN CONVERTER VENTS CONTINUOUSLY PRESSURE CLOSING, VALVE NOT SETTING.						1	G	7	2 	3U				H1NE
1998111300064	19981113	00064		1998	11	13	HEEA0016270      	4	19981022	G	3414	2002011293	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AIRSPEED	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				AIRSPEED INDICATOR'S NEEDLE STICKS AT LOW END OF SCALE.						1	G	7	2 	3U				H1NE
1998111300065	19981113	00065	NE  	1998	11	13	HEEA0016271      	1	19981022	G	7540	2820	SWITCH          			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				BLEED CAUTION LIGHT INTERMITTENTLY COMES ON.						1	G	7	2 	3U				H1NE
1998111300066	19981113	00066	NE  	1998	11	13	HEEA0016272      	1	19981022	G	2611	30231R7B	SMOKE DETECTOR  			SKRSKY	S76   	S76A        	8143006	NE  										CARGO BAY	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1546K					760082				SMOKE DETECTOR WILL NOT TEST.						1	G	7	2 	3U				H1NE
1998111300067	19981113	00067	NE  	1998	11	13	HEEA0016273      	1	19981022	G	2435	200SGL115Q	STARTER         			SKRSKY	S76   	S76A        	8143006	NE  										START/GEN	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K	4819 				760082				STARTER/GENERATOR HAS INTERMITTENT STARTING AND LOUD CLANKING NOISE.						1	G	7	2 	3U				H1NE
1998111300068	19981113	00068		1998	11	13	HEEA0016274      	4	19981022	G	3416	8140BS20LW	ENCODER         			SKRSKY	S76   	S76A        	8143006	NE  										ALTIMETER	FRICTION        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	15460					760223				ENCODING ALTIMETER HAS EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H1NE
1998111300069	19981113	00069		1998	11	13	HEEA0016275      	4	19981022	G	3416	212070238003	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ALTIMETER	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				INDICATOR HAS EXCESSIVE CASE LEAKAGE.						1	G	7	2 	3U				H1NE
1998111300070	19981113	00070		1998	11	13	HEEA0016276      	4	19981022	G	2210	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS PITCH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				VERTICAL GYRO SPINS UP SLOWLY, ADI WILL NOT STAY ERECT.						1	G	7	2 	3U				H1NE
1998111300071	19981113	00071		1998	11	13	HEEA0016277      	4	19981022	G	2210	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS PITCH	CHATTERS        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				ROLL CHANNEL CHATTERS IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300072	19981113	00072		1998	11	13	HEEA0016278      	4	19981022	G	2210	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS PITCH	KICKS           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				PITCH KICKS IN-FLIGHT.						1	G	7	2 	3U				H1NE
1998111300073	19981113	00073		1998	11	13	HEEA0016279      	4	19981022	G	2210	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS PITCH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546G					760076				ATT INDICATOR INOPERATIVE.						1	G	7	2 	3U				H1NE
1998111300074	19981113	00074		1998	11	13	HEEA0016280      	4	19981022	G	3421	7660002113103	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS PITCH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				VERTICAL GYRO SLOW TO PULL, FLAG PRECESSES AFTER SEVERAL MINUTES.						1	G	7	2 	3U				H1NE
1998111300075	19981113	00075		1998	11	13	HEEA0016281      	4	19981022	G	2210	7660002113102	VERTICAL GYRO   			SKRSKY	S76   	S76A        	8143006	NE  										AFCS PITCH	PRECESSES       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				GYRO PRECESSES.  TIME SINCE REPAIR 459:10 HOURS.						1	G	7	2 	3U				H1NE
1998111300076	19981113	00076	NE  	1998	11	13	HEEA0016282      	1	19981022	G	2430	7655009006105	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E					760155				DC CONTROL WOULD NOT TEST ON START-UP.						1	G	7	2 	3U				H1NE
1998111300077	19981113	00077	NE  	1998	11	13	HEEA0016283      	1	19981022	G	2430	7655009006105	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				DC CONTROL WILL NOT COME ON-LINE AFTER START.						1	G	7	2 	3U				H1NE
1998111300078	19981113	00078	NE  	1998	11	13	HEEA0016284      	1	19981022	G	2430	7655009006106	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E					760155				DC CONTROL - GROUND FAULT WOULD NOT TEST.						1	G	7	2 	3U				H1NE
1998111300079	19981113	00079	NE  	1998	11	13	HEEA0016285      	1	19981022	G	2931	7645001078104	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				HYDRAULIC PRESSURE INDICATOR'S NR 2 NEEDLE PEGS OUT ON HIGH SIDE.						1	G	7	2 	3U				H1NE
1998111300080	19981113	00080	NE  	1998	11	13	HEEA0016286      	1	19981022	G	7720	7645001078101	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE TEMP	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				ENGINE OIL TEMPERATURE NEEDLE CONTINUOUSLY FLUCTUATES.						1	G	7	2 	3U				H1NE
1998111300081	19981113	00081	NE  	1998	11	13	HEEA0016287      	1	19981022	G	7712	7645001078106	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										DUAL TORQUE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				DUAL TORQUE INDICATOR INOPERATIVE.						1	G	7	2 	3U				H1NE
1998111300082	19981113	00082	NE  	1998	11	13	HEEA0016288      	1	19981022	G	7931	7645001078112	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE OIL	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				PRESSURE INDICATES LOW TEMPERATURE, NEEDLE STICKS.						1	G	7	2 	3U				H1NE
1998111300083	19981113	00083	NE  	1998	11	13	HEEA0016289      	1	19981022	G	7931	7645001078112	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE OIL	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5128					760181				TEMPERATURE NEEDLE FLUCTUATES.						1	G	7	2 	3U				H1NE
1998111300084	19981113	00084	NE  	1998	11	13	HEEA0016290      	1	19981022	G	7334	7645001078118	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										FUEL PRESSURE	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				PRESSURE TRANSMITTER TRANSMITS LOW OUT OF TOLERANCE THROUGHOUT SCALE.						1	G	7	2 	3U				H1NE
1998111300085	19981113	00085	NE  	1998	11	13	HEEA0016291      	1	19981022	G	7334	7645001078118	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										FUEL PRESSURE	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				PRESSURE TRANSMITTER TRANSMITS LOW OUT OF TOLERANCE THROUGHOUT SCALE.						1	G	7	2 	3U				H1NE
1998111300086	19981113	00086	NE  	1998	11	13	HEEA0016292      	1	19981022	G	7334	7645001078118	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										FUEL PRESSURE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				PRESSURE TRANSMITTER READS HIGH, ABOVE 100 PSI.						1	G	7	2 	3U				H1NE
1998111300087	19981113	00087	NE  	1998	11	13	HEEA0016293      	1	19981022	G	2932	7645001078121	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										HYDRAULIC	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				HYDRAULIC TRANSMITTER READS HIGH OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE
1998111300088	19981113	00088	NE  	1998	11	13	HEEA0016294      	1	19981022	G	7931	7645001078120	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										OIL PRESSURE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				ENGINE OIL TRANSMITTER NOT TRANSMITTING CORRECTLY.						1	G	7	2 	3U				H1NE
1998111300089	19981113	00089	NE  	1998	11	13	HEEA0016295      	1	19981022	G	2932	7645001078121	TRANSMITTER     			SKRSKY	S76   	S76A        	8143006	NE  										HYDRAULIC	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1547D					760077				REPORTED HYDRAULIC TRANSMITTER READS LOW OUT OF TOLERANCE.						1	G	7	2 	3U				H1NE
1998111300090	19981113	00090	NE  	1998	11	13	HEEA0016296      	1	19981022	G	2841	7645001078103	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										FUEL QUANTITY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				FUEL QUANTITY NEEDLE STICKS AND WILL NOT READ ZERO.						1	G	7	2 	3U				H1NE
1998111300091	19981113	00091	NE  	1998	11	13	HEEA0016297      	1	19981022	G	2841	7645001078103	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										FUEL QUANTITY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				F1 ADJUSTER NOT EFFECTIVE ON FUEL QUANTITY INDICATOR, AND CANNOT CALIBRATE.						1	G	7	2 	3U				H1NE
1998111300092	19981113	00092		1998	11	13	HEEA0016298      	4	19981022	G	3413	RC30VIL	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911MJ					760231				RATE OF CLIMB INDICATOR CANNOT CALIBRATE TO ZERO.						1	G	7	2 	3U				H1NE
1998111300093	19981113	00093		1998	11	13	HEEA0016299      	4	19981022	G	3413	RC30VIL	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V					760158				RATE OF CLIMB NEEDLE STICKS, SLOW TO RETURN TO ZERO.						1	G	7	2 	3U				H1NE
1998111300094	19981113	00094	NE  	1998	11	13	HEEA0016300      	1	19981022	G	2842	7630702900104	SENSOR          			SKRSKY	S76   	S76A        	8143006	NE  										FUEL CELL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				TANK UNIT'S LOW LEVEL LIGHT STAYS ILLUMINATED WHILE AIRCRAFT IS RUNNING.						1	G	7	2 	3U				H1NE
1998111300095	19981113	00095	NE  	1998	11	13	HEEA0016301      	1	19981022	G	2842	7630702900104	SENSOR          			SKRSKY	S76   	S76A        	8143006	NE  										FUEL CELL	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				TANK UNIT WILL NOT CALIBRATE.						1	G	7	2 	3U				H1NE
1998111300096	19981113	00096	NE  	1998	11	13	HEEA0016302      	1	19981022	G	7810	7630507003044	EJECTOR         			SKRSKY	S76   	S76A        	8143006	NE  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				EJECTOR HAS EXCESSIVE CRACKING.						1	G	7	2 	3U				H1NE
1998111300097	19981113	00097	NE  	1998	11	13	HEEA0016303      	1	19981022	G	7810	7630507003044	EJECTOR         			SKRSKY	S76   	S76A        	8143006	NE  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				EJECTOR HAS PROGRESSIVE CRACKS.						1	G	7	2 	3U				H1NE
1998111300098	19981113	00098		1998	11	13	HEEA0016304      	4	19981022	G	2210	7690001812102	BRAKE           			SKRSKY	S76   	S76A        	8143006	NE  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				F			FLT CONT AFFECTED         			IN	INSP/MAINT     	1			SW	03	1547D					760077				BRAKE WILL NOT HOLD CONTROLS.						1	G	7	2 	3U				H1NE
1998111300099	19981113	00099	NE  	1998	11	13	HEEA0016305      	1	19981022	G	3212	7625101102101	FLOAT BAG       			SKRSKY	S76   	S76A        	8143006	NE  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	1545X	3781 				760050				FLOAT BAG LEAKING.						1	G	7	2 	3U				H1NE
1998111300100	19981113	00100	NE  	1998	11	13	HEEA0016306      	1	19981022	G	3040	7620001011104	CONVERTER       			SKRSKY	S76   	S76A        	8143006	NE  										WIPER	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				CONVERTER WILL NOT OPERATE AND OUTPUT HOUSING CRACKED.						1	G	7	2 	3U				H1NE
1998111300101	19981113	00101		1998	11	13	HEEA0016307      	4	19981022	G	2210	7690001822103	ACTUATOR        			SKRSKY	S76   	S76A        	8143006	NE  										CYCLIC TRIM	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K					760047				TRIM ACTUATOR SLOW WITH INTERMITTENT OPERATION.						1	G	7	2 	3U				H1NE
1998111300102	19981113	00102	NE  	1998	11	13	HEEA0016308      	1	19981022	G	6320	7635109500043	TRANSMISSION    			SKRSKY	S76   	S76A        	8143006	NE  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5435V	4836 				760158				TRANSMISSION HAS METAL IN OIL.						1	G	7	2 	3U				H1NE
1998111300103	19981113	00103	NE  	1998	11	13	HEEA0016309      	1	19981022	G	6710	7690001880106	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										DROOP COMP	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				DROOP COMP HAS NTERMITTENT OPERATION.						1	G	7	2 	3U				H1NE
1998111300104	19981113	00104	NE  	1998	11	13	HEEA0016310      	1	19981022	G	6710	7690001880106	AMPLIFIER       			SKRSKY	S76   	S76A        	8143006	NE  										DROOP COMP	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				DROOP COMP INOPERATIVE.						1	G	7	2 	3U				H1NE
1998111300105	19981113	00105	NE  	1998	11	13	HEEA0016311      	1	19981022	G	7714	7645001076101	TACH            			SKRSKY	S76   	S76A        	8143006	NE  										GAS GENERATOR	FAILED          	E			HEEA	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	707AE					760276				GAS GENERATOR TACHOMETER SMOKES WHEN TURNED ON.						1	G	7	2 	3U				H1NE
1998111300106	19981113	00106	NE  	1998	11	13	HEEA0016312      	1	19981022	G	2160	7650007903102	VALVE           			SKRSKY	S76   	S76A        	8143006	NE  										AIR SHUTOFF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545K	6444 				760047				SHUT OFF VALVE INOPERATIVE.  WILL NOT ACTUATE.						1	G	7	2 	3U				H1NE
1998111300107	19981113	00107	NE  	1998	11	13	HEEA0016313      	1	19981022	G	3040	7655001013103	MOTOR           			SKRSKY	S76   	S76A        	8143006	NE  										WIPER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				WIPER MOTOR SLOWS DOWN WITH LOAD.						1	G	7	2 	3U				H1NE
1998111300108	19981113	00108	NE  	1998	11	13	HEEA0016314      	1	19981022	G	2422	7655003007105	INVERTER        			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				INVERTER DOES NOT COME ON LINE EVERY TIME.						1	G	7	2 	3U				H1NE
1998111300109	19981113	00109	NE  	1998	11	13	HEEA0016315      	1	19981022	G	6230	7610408011041	RING            			SKRSKY	S76   	S76A        	8143006	NE  										SWASHPLATE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5426U					760167				SWASHPLATE'S OUTBOARD DIAMETER LINERS WORN.						1	G	7	2 	3U				H1NE
1998111300110	19981113	00110		1998	11	13	HEEA0016316      	4	19981022	G	3414	7645000801101	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										AIR SPEED	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31217					760229				AIRSPEED NEEDLE DOES NOT RETURN TO ZERO.						1	G	7	2 	3U				H1NE
1998111300111	19981113	00111	NE  	1998	11	13	HEEA0016317      	1	19981022	G	6220	7640002900104	ARM             			SKRSKY	S76   	S76A        	8143006	NE  										VISCOUS DAMPER	MISINSTALLED    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										DAMPER ARM IMPROPERLY INSTALLED.						1	G	7	2 	3U				H1NE
1998111300112	19981113	00112		1998	11	13	HEEA0016318      	4	19981022	G	3420	1113034	INDICATOR       			SKRSKY	S76   	S76A        	8143006	NE  										ATTITUDE	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	31219					760230				ATTITUDE INDICATOR HAS JERKY MOVEMENT AND PRECESSES.						1	G	7	2 	3U				H1NE
1998111300113	19981113	00113	NE  	1998	11	13	HEEA0016319      	1	19981022	G	2430	7655009006106	GCU             			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1546K					760082				DC CONTROL UNIT WILL NOT ALLOW NR 1 DC GENERATOR TO COME ON-LINE.						1	G	7	2 	3U				H1NE
1998111300247	19981113	00247	EU  	1998	11	13	HEEA0016320      	1	19981022	G	7714	DL41239	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE RPM	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	133AE					S800				RPM INDICATOR ERRATIC UP TO 30 PERCENT, AND HAS WATER CONTAMINATION.						1	G	7	2 	3U				H3EU
1998111300114	19981113	00114	NE  	1998	11	13	HEEA0016321      	1	19981022	G	7330	PC820101	SIGNAL COND     			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122G					760232				TOTALIZER DOESN'T COUNT DOWN.						1	G	7	2 	3U				H1NE
1998111300115	19981113	00115	NE  	1998	11	13	HEEA0016322      	1	19981022	G	2422	SPS1607A	STATIC INVERTER 			SKRSKY	S76   	S76A        	8143006	NE  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	792CH					760193				STATIC INVERTER INOPERATIVE.  POWER IN, NOTHING OUT.						1	G	7	2 	3U				H1NE
1998111300116	19981113	00116	NE  	1998	11	13	HEEA0016323      	1	19981022	G	6230	SB5007102	BEARING         			SKRSKY	S76   	S76A        	8143006	NE  										SWASHPLATE	UNBONDED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4253S					760035				BEARING SHIM UNBONDED ON OUTER RACE.						1	G	7	2 	3U				H1NE
1998111300117	19981113	00117		1998	11	13	HEEA0016324      	4	19981022	G	2312	071121525	CONTROL UNIT    			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22342					760096				CONTROL UNIT'S DIGITS ARE UNREADABLE.						1	G	7	2 	3U				H1NE
1998111300118	19981113	00118	NE  	1998	11	13	HEEA0016325      	1	19981022	G	7120	7630907017044	TRIPOD MOUNT    			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE BAY	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	706AE					760275				EXCESSIVE WEAR AT BUSHING HOLES ON LOWER LEGS.  REPLACED WITH NEW TRIPOD MOUNT.						1	G	7	2 	3U				H1NE
1998111300119	19981113	00119	NE  	1998	11	13	HEEA0016326      	1	19981022	G	5350	7660002110102	RADOME          			SKRSKY	S76   	S76A        	8143006	NE  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	31217					760229				RADOME MOUNT HOLES MISALIGNED.						1	G	7	2 	3U				H1NE
1998111300120	19981113	00120		1998	11	13	HEEA0016327      	4	19981022	G	2312	7001840913	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1546G					760076				RECEIVER/TRANSMITTER DOES NOT TEST 50-250-400 AND 1200 LEDS GOES OFF.						1	G	7	2 	3U				H1NE
1998111300121	19981113	00121		1998	11	13	HEEA0016328      	4	19981022	G	2370	9806020023	CVR             			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	1545K					760047				CVR TEST LIGHT WILL NOT ILLUMINATE.						1	G	7	2 	3U				H1NE
1998111300122	19981113	00122		1998	11	13	HEEA0016329      	4	19981022	G	2312	4000103000	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				STATIC NOISE IN HEADSET, LOW POWER OUT.						1	G	7	2 	3U				H1NE
1998111300123	19981113	00123	NE  	1998	11	13	HEEA0016330      	2	19981022	G	7320	7630103004043	TORQUE SHAFT    			SKRSKY	S76   	S76A        	8143006	NE  										ENGINE CONTROL	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3122H					760233				TORQUE SHAFT'S BALL HAS GROOVE AND HANGS UP ON GROOVE, ALSO ROUGH IN MOVEMENT.						1	G	7	2 	3U				H1NE
1998111300124	19981113	00124		1998	11	13	HEEA0016331      	4	19981022	G	2312	064100900	TRANSCEIVER     			SKRSKY	S76   	S76A        	8143006	NE  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1545X					760050				TRANSMIT SIDETONE GARBLED.  TESTED, CLEANED CORROSION, BENCH CHECK GOOD.						1	G	7	2 	3U				H1NE
1998111300125	19981113	00125	NE  	1998	11	13	HEEA0016332      	1	19981022	G	6220	7640002900101	ARM             			SKRSKY	S76   	S76A        	8143006	NE  										DAMPENER	MISINSTALLED    	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	1545K					760047				DAMPENER ARM IMPROPERLY INDEXED.						1	G	7	2 	3U				H1NE
1998111300155	19981113	00155		1998	11	13	HEEA0016333      	4	19981022	G	3442	40005040301	DRIVE ASSY      			BELL  	214   	214ST       	1182106	SW  										RADAR ANNTENA	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				TILT INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300156	19981113	00156		1998	11	13	HEEA0016334      	4	19981022	G	3442	40005040301	DRIVE ASSY      			BELL  	214   	214ST       	1182106	SW  										RADAR ANNTENA	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				TILT CONTROL HAS NO EFFECT ON ANTENNA.						2	G	7	2 	4U				H10SW
1998111300157	19981113	00157		1998	11	13	HEEA0016335      	4	19981022	G	3442	40005040301	DRIVE ASSY      			BELL  	214   	214ST       	1182106	SW  										RADAR ANNTENA	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				DRIVE ASSY INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300158	19981113	00158		1998	11	13	HEEA0016336      	4	19981022	G	2312	40008310103	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				TRANSCEIVER'S GAIN INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300159	19981113	00159		1998	11	13	HEEA0016337      	4	19981022	G	2312	071121540	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	59805					28141				NO DISPLAY, ELECTRICAL BURNING SMELL WHEN TURNED ON.						2	G	7	2 	4U				H10SW
1998111300160	19981113	00160		1998	11	13	HEEA0016338      	4	19981022	G	2312	071121540	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				COMM CONTROL INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300161	19981113	00161	SW  	1998	11	13	HEEA0016339      	1	19981022	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	172  				28102				STARTER WOULD NOT CROSS START WITHOUT TRIPPING NR 1 GENERATOR.						2	G	7	2 	4U				H10SW
1998111300162	19981113	00162	SW  	1998	11	13	HEEA0016340      	1	19981022	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				B			SMOKE/FUMES/ODORS/SPARKS  			IN	INSP/MAINT     	1			SW	03	6957Y	2198 				28139				CLUTCH FAILED SLIPPAGE TORQUE TEST, EXCEEDS MAXIMUM LIMITS, DRIVE AND BEARING ABOVE CLUTCH SPINS IN RACER, WIRES BURNT, 	AND INSULATION IS MELTED OFF WIRES GOING TO CURRENT LIMITING RESISTOR.					2	G	7	2 	4U				H10SW
1998111300163	19981113	00163	SW  	1998	11	13	HEEA0016341      	1	19981022	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				STARTER CLUTCH IS SLIPPING.						2	G	7	2 	4U				H10SW
1998111300164	19981113	00164	SW  	1998	11	13	HEEA0016342      	1	19981022	G	6320	214040845103	PUMP            			BELL  	214   	214ST       	1182106	SW  										GEARBOX OIL	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				PORT PLATE CORRODED.						2	G	7	2 	4U				H10SW
1998111300165	19981113	00165	SW  	1998	11	13	HEEA0016343      	1	19981023	G	3340	01077028521	STROBE          			BELL  	214   	214ST       	1182106	SW  										EXTERNAL LIGHTS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59805					28141				STROBE LIGHT INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300166	19981113	00166	SW  	1998	11	13	HEEA0016344      	1	19981023	G	3340	01077028521	STROBE          			BELL  	214   	214ST       	1182106	SW  										EXTERNAL LIGHTS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6957Y					28139				STROBE LIGHT HAS NO OUTPUT, WILL NOT FLASH.						2	G	7	2 	4U				H10SW
1998111300167	19981113	00167	SW  	1998	11	13	HEEA0016345      	1	19981023	G	3340	01077028521	STROBE          			BELL  	214   	214ST       	1182106	SW  										EXTERNAL LIGHTS	INOPERATIVE     	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	6957Y					28139				STROBE LIGHT HAS NO OUTPUT, WILL NOT FLASH.						2	G	7	2 	4U				H10SW
1998111300168	19981113	00168		1998	11	13	HEEA0016346      	4	19981023	G	2312	064102300	TRANSCIEVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT VHF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				VHF TRANSCEIVER DRAWS EXCESSIVE CURRENT.						2	G	7	2 	4U				H10SW
1998111300169	19981113	00169		1998	11	13	HEEA0016347      	4	19981023	G	3451	066106602	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT DME	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				TRANSCEIVER HAS BURNED COMPONENTS INTERNALLY.						2	G	7	2 	4U				H10SW
1998111300170	19981113	00170		1998	11	13	HEEA0016348      	4	19981023	G	3431	066107800	RECEIVER        			BELL  	214   	214ST       	1182106	SW  										COCKPIT NAV	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				NOT RECEIVING ON VOR/LOC AND GS.						2	G	7	2 	4U				H10SW
1998111300171	19981113	00171		1998	11	13	HEEA0016349      	4	19981023	G	3454	066401000	RECEIVER        			BELL  	214   	214ST       	1182106	SW  										NAVIGATION	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				RECEIVER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300172	19981113	00172		1998	11	13	HEEA0016350      	4	19981023	G	3455	071121009	ADF CONTROL     			BELL  	214   	214ST       	1182106	SW  										DISPLAY	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				ADF INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300173	19981113	00173		1998	11	13	HEEA0016351      	4	19981023	G	3420	1113025	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				RADIO MAGNETIC INDICATOR WILL NOT SLAVE, GLIDE SCOPE FLAG STICKS.						2	G	7	2 	4U				H10SW
1998111300174	19981113	00174	SW  	1998	11	13	HEEA0016352      	1	19981023	G	2435	2CM272B1	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y	449  				28139				STARTER/GENERATOR SLOW TO START AND 250 HOUR INSPECTION DUE.						2	G	7	2 	4U				H10SW
1998111300175	19981113	00175		1998	11	13	HEEA0016353      	4	19981023	G	3420	258719343	GYRO            			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				GYRO INTERMITTENTLY WILL NOT BECOME VALID.						2	G	7	2 	4U				H10SW
1998111300176	19981113	00176		1998	11	13	HEEA0016354      	4	19981023	G	3422	2594484	TRANSMITTER     			BELL  	214   	214ST       	1182106	SW  										FLUX VALVE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				TRANSMITTER WILL NOT SLAVE IN MAG.						2	G	7	2 	4U				H10SW
1998111300177	19981113	00177	SW  	1998	11	13	HEEA0016355      	1	19981023	G	2430	51576003	CONTROL UNIT    			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				DC CONTROL UNIT WILL NOT COME ON LINE.						2	G	7	2 	4U				H10SW
1998111300178	19981113	00178		1998	11	13	HEEA0016356      	4	19981023	G	3442	40008310105	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										RADAR SYSTEM	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				TRANSCEIVER INTERMITTENT AND STAYS IN RT FAULT TOO LONG.						2	G	7	2 	4U				H10SW
1998111300179	19981113	00179	SW  	1998	11	13	HEEA0016357      	1	19981023	G	2435	36B510954G2	CLUTCH          			BELL  	214   	214ST       	1182106	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				CLUTCH SLIPPAGE EXCEED LIMITS.						2	G	7	2 	4U				H10SW
1998111300180	19981113	00180	SW  	1998	11	13	HEEA0016358      	1	19981023	G	2435	36B510954G2	CLUTCH          			BELL  	214   	214ST       	1182106	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				FAILS CLUTCH TORQUE SLIPPAGE TEST OVER 400 INCHES/POUNDS.						2	G	7	2 	4U				H10SW
1998111300181	19981113	00181	SW  	1998	11	13	HEEA0016359      	1	19981023	G	2421	222375033107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				ATTITUDE INDICATOR PRECESSES AND IS SLOW TO ERECT.						2	G	7	2 	4U				H10SW
1998111300182	19981113	00182	SW  	1998	11	13	HEEA0016360      	1	19981023	G	2421	222375033107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				ATTITUDE INDICATOR SLOW TO ERECT AND FALLS OFF-LINE AFTER 10 MINUTES.						2	G	7	2 	4U				H10SW
1998111300183	19981113	00183	SW  	1998	11	13	HEEA0016361      	1	19981023	G	7712	222375077111	TRANSMITTER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				TRANSMITER READS HIGH WITH NO PRESSURE APPLIED.						2	G	7	2 	4U				H10SW
1998111300184	19981113	00184	SW  	1998	11	13	HEEA0016362      	1	19981023	G	2730	214001970107	ACTUATOR ASSY   			BELL  	214   	214ST       	1182106	SW  										ELEVATOR SYS	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	59805					28141				ACTUATOR ASSY WILL NOT MONITOR TEST AND KEEPS KICKING OFF-LINE.						2	G	7	2 	4U				H10SW
1998111300185	19981113	00185	SW  	1998	11	13	HEEA0016363      	1	19981023	G	2730	214001970107	ACTUATOR ASSY   			BELL  	214   	214ST       	1182106	SW  										ELEVATOR SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				ACTUATOR ASSY ELEVATOR WILL NOT STAY ON-LINE.						2	G	7	2 	4U				H10SW
1998111300186	19981113	00186	SW  	1998	11	13	HEEA0016364      	1	19981023	G	2730	214001970107	ACTUATOR ASSY   			BELL  	214   	214ST       	1182106	SW  										ELEVATOR SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				ACTUATOR ASSY CAUSES NR 1 FBW ELEVATOR TO DROP OFF-LINE.						2	G	7	2 	4U				H10SW
1998111300187	19981113	00187	SW  	1998	11	13	HEEA0016365      	1	19981023	G	5347	214031277129S	TRACK           			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										LOWER OUTBOARD FLANGE TOO NARROW TO PICK UP FASTENERS.						2	G	7	2 	4U				H10SW
1998111300188	19981113	00188	SW  	1998	11	13	HEEA0016366      	1	19981023	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	497  				28102				STARTER WILL NOT CROSS START.						2	G	7	2 	4U				H10SW
1998111300189	19981113	00189	SW  	1998	11	13	HEEA0016367      	1	19981023	G	2841	214066212101	PROBE           			BELL  	214   	214ST       	1182106	SW  										FUEL QUANTITY	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				TRANSMITS INACCURATE READINGS.						2	G	7	2 	4U				H10SW
1998111300190	19981113	00190	SW  	1998	11	13	HEEA0016368      	1	19981023	G	3212	214073936104	BAG             			BELL  	214   	214ST       	1182106	SW  										FLOAT	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805	242  				28141				FLOAT BAG LEAKS.						2	G	7	2 	4U				H10SW
1998111300191	19981113	00191	SW  	1998	11	13	HEEA0016369      	1	19981023	G	3040	214073932110	CONVERTER       			BELL  	214   	214ST       	1182106	SW  										WIPER MOTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				CONVERTER INOPERATIVE.						2	G	7	2 	4U				H10SW
1998111300192	19981113	00192		1998	11	13	HEEA0016370      	4	19981023	G	2210	214074104101	SENSOR          			BELL  	214   	214ST       	1182106	SW  										SCAS SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				SCAS WILL NOT STAY ENGAGED.						2	G	7	2 	4U				H10SW
1998111300193	19981113	00193		1998	11	13	HEEA0016371      	4	19981023	G	3414	214074152101	TRANSDUCER      			BELL  	214   	214ST       	1182106	SW  										AIRSPEED	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				CAUSES ELEVATORS TO KICK OFF-LINE.						2	G	7	2 	4U				H10SW
1998111300194	19981113	00194	SW  	1998	11	13	HEEA0016372      	1	19981023	G	6240	214074280105	DETECTOR        			BELL  	214   	214ST       	1182106	SW  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				RPM DETECTOR - ROTOR WARNING LIGHT EARLY.						2	G	7	2 	4U				H10SW
1998111300195	19981113	00195		1998	11	13	HEEA0016373      	4	19981023	G	2210	214074301105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										SCAS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				SCAS AMPLIFIER'S LAST DIGIT UNREADABLE.						2	G	7	2 	4U				H10SW
1998111300196	19981113	00196		1998	11	13	HEEA0016374      	4	19981023	G	2210	214074303115	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										AUTOFLIGHT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				COULD NOT ADJUST ROLL CHANNEL TO PROPER VOLTAGE, PITCH WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW
1998111300197	19981113	00197		1998	11	13	HEEA0016375      	4	19981023	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										FBWE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				WILL NOT MOTION TEST NOR WILL ELEVATORS STAY EMERGED.						2	G	7	2 	4U				H10SW
1998111300198	19981113	00198		1998	11	13	HEEA0016376      	4	19981023	G	2210	214074305105	AMPLIFIER       			BELL  	214   	214ST       	1182106	SW  										FBWE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				ELEVATOR WILL NOT STAY ENGAGED.						2	G	7	2 	4U				H10SW
1998111300199	19981113	00199	SW  	1998	11	13	HEEA0016377      	1	19981023	G	2913	214076033101	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYDRAULIC SYS	FLUCTUATING     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				HYDRAULIC PUMP FLUCTUATING PRESSURE WITH CONTROL MOVEMENT.						2	G	7	2 	4U				H10SW
1998111300200	19981113	00200	SW  	1998	11	13	HEEA0016378      	1	19981023	G	2430	214175133103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				RELAY CONTACT 13 AND 14 HAS TOO MUCH RESISTANCE.						2	G	7	2 	4U				H10SW
1998111300201	19981113	00201	SW  	1998	11	13	HEEA0016379      	1	19981023	G	2434	214175150105	GENERATOR       			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M	1780 				28102				GENERATOR WILL NOT COME ON LINE.						2	G	7	2 	4U				H10SW
1998111300202	19981113	00202	SW  	1998	11	13	HEEA0016380      	1	19981023	G	2434	214175150105	SHAFT           			BELL  	214   	214ST       	1182106	SW  										GENERATOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				GENERATOR SHAFT BROKEN.						2	G	7	2 	4U				H10SW
1998111300203	19981113	00203	SW  	1998	11	13	HEEA0016381      	1	19981023	G	2430	214175171103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				RELAY WILL NOT ENGAGE.						2	G	7	2 	4U				H10SW
1998111300204	19981113	00204	SW  	1998	11	13	HEEA0016382      	1	19981023	G	2430	214175171103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				RELAY WILL NOT CARRY LOAD, GETS HOT.						2	G	7	2 	4U				H10SW
1998111300205	19981113	00205	SW  	1998	11	13	HEEA0016383      	1	19981023	G	2430	214175171103	RELAY           			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				BATTERY SWITCH WILL NOT TRIP WHEN BUS. SWITCH TURNED OFF.						2	G	7	2 	4U				H10SW
1998111300206	19981113	00206		1998	11	13	HEEA0016384      	4	19981023	G	3414	214175299107	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				INDICATOR STICKS AT 40 TO 50 KNOTS.						2	G	7	2 	4U				H10SW
1998111300207	19981113	00207	SW  	1998	11	13	HEEA0016385      	1	19981023	G	2432	214175379103	CHARGER         			BELL  	214   	214ST       	1182106	SW  										BATTERY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				CHARGER WILL NOT CHARGE BATTERY.						2	G	7	2 	4U				H10SW
1998111300208	19981113	00208	SW  	1998	11	13	HEEA0016386      	1	19981023	G	2432	214175379103	CHARGER         			BELL  	214   	214ST       	1182106	SW  										BATTERY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				CHARGER WILL NOT CHARGE BATTERY.						2	G	7	2 	4U				H10SW
1998111300209	19981113	00209		1998	11	13	HEEA0016387      	4	19981023	G	3417	214175421101	ADC             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				FAIL 5 LIGHT AND A/S 3 LIGHT.						2	G	7	2 	4U				H10SW
1998111300210	19981113	00210		1998	11	13	HEEA0016388      	4	19981023	G	2312	064100900	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				RECEIVER WEAK, SQUELCH CANNOT BE TUNED OUT.						1	G	7	1 	4U				H4SW
1998111300211	19981113	00211		1998	11	13	HEEA0016389      	4	19981023	G	2310	064101600	CONTROL         			BELL  	212   	212         	1181420	SW  										COCKPIT HF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				LEDS LIGHT UP, DISPLAY BAD.						1	G	7	1 	4U				H4SW
1998111300212	19981113	00212		1998	11	13	HEEA0016390      	4	19981023	G	3452	066104100	TRANSPONDER     			BELL  	212   	212         	1181420	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				TRANSPONDER HAS LOW POWER.  TIME SINCE REPAIR 0:00 HOURS.						1	G	7	1 	4U				H4SW
1998111300213	19981113	00213		1998	11	13	HEEA0016391      	4	19981023	G	3452	066104100	TRANSPONDER     			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				NO CODE TRANSMITTER.  NO REPLY LIGHT.  NO TEST LIGHT.  TIME SINCE REPAIR 0:00 HOURS.						1	G	7	1 	4U				H4SW
1998111300214	19981113	00214		1998	11	13	HEEA0016392      	4	19981023	G	3420	1113025	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT HSI	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	27805					31106				HSI INDICATOR'S COMPASS CARD STICKS.						1	G	7	1 	4U				H4SW
1998111300215	19981113	00215		1998	11	13	HEEA0016393      	4	19981023	G	3420	1113025	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT HSI	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				HSI INDICATOR'S TO/FROM FLAG STICKS, NR 2 BEARING POINTER RATCHETS.						1	G	7	1 	4U				H4SW
1998111300216	19981113	00216		1998	11	13	HEEA0016394      	4	19981023	G	3420	1113025	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				GS FLAG WILL NOT PULL.						1	G	7	1 	4U				H4SW
1998111300217	19981113	00217	SW  	1998	11	13	HEEA0016395      	1	19981023	G	2931	124043	INDICATOR       			BELL  	212   	212         	1181420	SW  										HYDRAULIC SYS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				HYDRAULIC PRESSURE NEEDLE WILL NOT RETURN TO ZERO.						1	G	7	1 	4U				H4SW
1998111300218	19981113	00218		1998	11	13	HEEA0016396      	4	19981023	G	3425	1258103	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				NO ADF POINTER INFO DISPLAYED.						1	G	7	1 	4U				H4SW
1998111300219	19981113	00219	SW  	1998	11	13	HEEA0016397      	1	19981023	G	2422	1A2501D	INVERTER        			BELL  	212   	212         	1181420	SW  										AC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				INVERTER HAS LOW VOLTAGE OUTPUT.						1	G	7	1 	4U				H4SW
1998111300220	19981113	00220	SW  	1998	11	13	HEEA0016398      	1	19981023	G	5320	205031832006P	SUPPORT         			BELL  	212   	212         	1181420	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										SUPPORT MISMANUFACTURED.  AREA THAT BUTTS TO CAP ANGLE NEEDS TO BE ONE INCH.  SUBMITTER STATED FLAT SURFACE NOT .75 INCH	.					1	G	7	1 	4U				H4SW
1998111300221	19981113	00221	SW  	1998	11	13	HEEA0016399      	1	19981023	G	3211	205050400101	SADDLE ASSY     		205050400106	BELL  	212   	212         	1181420	SW  										SKID	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3131S				NA	30953				INBOARD SECTION OF SADDLE ASSEMBLY CRACKED.  CRACK EXTENDS FORE - AFT .75 INCH, ONE INCH BELOW THE INBOARD LOWER BOLT HO	LE WITH THE LOWER INBOARD BOLT HOLE BEING THE CENTER POINT. REPLACED WITH SERVICEABLE SKID TUBE ASSEMBLY.					1	G	7	1 	4U				H4SW
1998111300222	19981113	00222	SW  	1998	11	13	HEEA0016400      	1	19981023	G	7933	209070262009	INDICATOR       			BELL  	212   	212         	1181420	SW  										ENGINE OIL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	102PH					30899				ON INITIAL INSTALLATION, TEMPERATURE INDICATION PEGS TO THE HIGH SIDE WITH POWER APPLIED.  REPLACED WITH A SERVICEABLE I	NDICATOR.					1	G	7	1 	4U				H4SW
1998111300223	19981113	00223	SW  	1998	11	13	HEEA0016401      	1	19981023	G	7931	209070262101	INDICATOR       			BELL  	212   	212         	1181420	SW  										ENGINE OIL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				ENGINE OIL TEMPERATURE STAYS AT ZERO.						1	G	7	1 	4U				H4SW
1998111300224	19981113	00224	SW  	1998	11	13	HEEA0016402      	1	19981023	G	2437	209070264003	DUAL AMMETER    			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				DUAL AMMETER NEEDLE STICKING.						1	G	7	1 	4U				H4SW
1998111300225	19981113	00225	SW  	1998	11	13	HEEA0016403      	1	19981023	G	3150	209075325045	CAUTION PANEL   			BELL  	212   	212         	1181420	SW  										INST PANEL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1082G					31109				PANEL ASSY LIGHTS FLICKER INTERMITTENTLY.						1	G	7	1 	4U				H4SW
1998111300226	19981113	00226	SW  	1998	11	13	HEEA0016404      	1	19981023	G	6240	209075326101	DETECTOR        			BELL  	212   	212         	1181420	SW  										MAIN ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				RPM INDICATOR ACTIVATES ALARM AT RANDOM.						1	G	7	1 	4U				H4SW
1998111300227	19981113	00227		1998	11	13	HEEA0016405      	4	19981023	G	3416	212070238003	ALTIMETER       			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736D					31135				INDICATOR - INTERNAL FAILURE, LOOSE PARTS.						1	G	7	1 	4U				H4SW
1998111300228	19981113	00228	SW  	1998	11	13	HEEA0016406      	1	19981023	G	7712	212075037101	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				N1 NEEDLE ERRATIC AND STICKS.						1	G	7	1 	4U				H4SW
1998111300229	19981113	00229	SW  	1998	11	13	HEEA0016407      	1	19981023	G	7722	212075067109	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT ITT	FLUCTUATING     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										ITT INDICATOR GAUGE FLUCTUATING.						1	G	7	1 	4U				H4SW
1998111300230	19981113	00230	SW  	1998	11	13	HEEA0016408      	1	19981023	G	7722	212075562003	INDICATOR       			BELL  	212   	212         	1181420	SW  										COCKPIT ITT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				ITT INDICATOR STICKS AT 580 DEGREES.						1	G	7	1 	4U				H4SW
1998111300231	19981113	00231		1998	11	13	HEEA0016409      	4	19981023	G	3421	214075244001	GYRO            			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				RT FLAG ON ADI NOT PULLED.						1	G	7	1 	4U				H4SW
1998111300232	19981113	00232	SW  	1998	11	13	HEEA0016410      	1	19981023	G	2435	23046020	GENERATOR       			BELL  	212   	212         	1181420	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				STARTER/GENERATOR WILL NOT COME ON-LINE.						1	G	7	1 	4U				H4SW
1998111300233	19981113	00233		1998	11	13	HEEA0016411      	4	19981023	G	2210	2593996333	TARSYN          			BELL  	212   	212         	1181420	SW  										AUTOFLIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				TARSYN FAILS TEST 8.5 ON SST.						1	G	7	1 	4U				H4SW
1998111300234	19981113	00234		1998	11	13	HEEA0016412      	4	19981023	G	2210	2593996333	TARSYN          			BELL  	212   	212         	1181420	SW  										AUTOFLIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				TARSYN - PIN C OF BOTTOM CONNECTOR HAS PINS BACKING OUT OF CONNECTOR.						1	G	7	1 	4U				H4SW
1998111300235	19981113	00235		1998	11	13	HEEA0016413      	4	19981023	G	3422	2594484	FLUX VALVE      			BELL  	212   	212         	1181420	SW  										WING	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				COMPASS IS INOPERATIVE, IT HAS ERRATIC OUTPUT.						1	G	7	1 	4U				H4SW
1998111300126	19981113	00126	SW  	1998	11	13	HEEA0016414      	2	19981023	G	7230	3017600	COMPRESSOR      			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1082G	15935				31109				NOISE COMING FROM COMPRESSOR.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998111300236	19981113	00236	SW  	1998	11	13	HEEA0016415      	1	19981023	G	7722	3030083	TRIM COMPENSATOR			BELL  	212   	212         	1181420	SW  										ENGINE TIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				TRIM COMPENSATOR ADJUSTED TO 100.  WILL NOT LOWER TEMP INDICATION TO WITHIN RANGE.						1	G	7	1 	4U				H4SW
1998111300127	19981113	00127	EA  	1998	11	13	HEEA0016416      	2	19981023	G	7321	32447066	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  	PWA   	PT6T  	PT6T3       	52045	EA  					NR 2 ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5736J					31140				TORQUE CONTROL UNIT CAUSES TORQUE OSCILLATION ON NR 2 ENGINE.						1	G	7	1 	4U	4	U		H4SW    	E22EA
1998111300237	19981113	00237		1998	11	13	HEEA0016417      	4	19981023	G	2312	4000044000	TRANSCEIVER     			BELL  	212   	212         	1181420	SW  										COCKPIT VHF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1082G					31109				VHF TRANSCEIVER HAS STATIC, HARD TO RECEIVE.						1	G	7	1 	4U				H4SW
1998111300238	19981113	00238	SW  	1998	11	13	HEEA0016418      	1	19981023	G	2430	51509002R	CONTROL UNIT    			BELL  	212   	212         	1181420	SW  										DC CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				CONTROL UNIT WILL NOT COME ON LINE.						1	G	7	1 	4U				H4SW
1998111300239	19981113	00239		1998	11	13	HEEA0016419      	4	19981023	G	3422	656520	VALVE           			BELL  	212   	212         	1181420	SW  										COMPASS	INCORRECT       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				COMPASS HAS INCORRECT HEADINGS, OUTPUT UNRELIABLE.						1	G	7	1 	4U				H4SW
1998111300240	19981113	00240		1998	11	13	HEEA0016420      	4	19981023	G	3422	664543	FLUX VALVE      			BELL  	212   	212         	1181420	SW  										COMPASS	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				READING IS OFF 80 DEGREES.						1	G	7	1 	4U				H4SW
1998111300241	19981113	00241		1998	11	13	HEEA0016421      	4	19981023	G	3457	80265000311	RECEIVER        			BELL  	212   	212         	1181420	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1082G					31109				GPS RECEIVER WILL NOT HOLD SATELLITES.						1	G	7	1 	4U				H4SW
1998111300242	19981113	00242	SW  	1998	11	13	HEEA0016422      	1	19981023	G	2422	ASH5845	INVERTER        			BELL  	212   	212         	1181420	SW  										AC SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				INVERTER TRIPS CIRCUIT BREAKER.						1	G	7	1 	4U				H4SW
1998111300243	19981113	00243	SW  	1998	11	13	HEEA0016423      	1	19981023	G	2422	ASH5845	INVERTER        			BELL  	212   	212         	1181420	SW  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				INVERTER WOULD NOT COME ON LINE AT INITIAL INSTALLATION FROM STOCK.						1	G	7	1 	4U				H4SW
1998112000138	19981120	00138	SW  	1998	11	20	HEEA0016424      	1	19981026	G	7931	APTE13850G	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										OIL PRESSURE	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				TRANSMITTER READS HIGH OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998112000139	19981120	00139		1998	11	20	HEEA0016425      	4	19981026	G	2562	ELT1104	ELT             			BELL  	412   	412         	1182202	SW  										FUSELAGE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03		1468 								ELT G-SWITCH OPERATION DOES NOT FUNCTION CORRECTLY, WILL NOT ACTIVATE PROPERLY.						1	G	7	2 	4U				H4SW
1998112000140	19981120	00140		1998	11	20	HEEA0016426      	4	19981026	G	2562	ELT910	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										ELT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				ELT SELF-ACTIVATES INTERMITTENTLY.						1	G	7	2 	4U				H4SW
1998112000141	19981120	00141		1998	11	20	HEEA0016427      	4	19981026	G	2562	ELT910	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										ELT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				ELT PERIODICALLY SELF-ACTIVATES WITHOUT REASON.						1	G	7	2 	4U				H4SW
1998112000142	19981120	00142		1998	11	20	HEEA0016428      	4	19981026	G	2562	ELT910	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										ELT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				INTERMITTENT ACTIVATION MALFUNCTIONING SWITCH ON ELT.						1	G	7	2 	4U				H4SW
1998112000143	19981120	00143	SW  	1998	11	20	HEEA0016429      	1	19981026	G	2823	L88010501	VALVE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ONE OF THE FITTING PLATES LEAKING FUEL.						1	G	7	2 	4U				H4SW
1998112000144	19981120	00144		1998	11	20	HEEA0016430      	4	19981026	G	3442	MI585467	ANTENNA PEDESTAL			BELL  	412   	412         	1182202	SW  										RADAR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				RADAR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000145	19981120	00145	SW  	1998	11	20	HEEA0016431      	1	19981026	G	7722	SELOC19EJ	ITT INDICATOR   			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				ITT INDICATION NEEDLE STICKS.						1	G	7	2 	4U				H4SW
1998112000146	19981120	00146		1998	11	20	HEEA0016432      	4	19981026	G	2312	064100900	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				TRANSCEIVER'S SQUELCH TEST STICKS, RECEIVER WEAK.						1	G	7	2 	4U				H4SW
1998112000147	19981120	00147		1998	11	20	HEEA0016433      	4	19981026	G	3452	066104100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z					33077				TRANSPONDER DOES NOT TRANSMIT, FLEX CABLE BURNT.						1	G	7	2 	4U				H4SW
1998112000148	19981120	00148		1998	11	20	HEEA0016434      	4	19981026	G	3434	066104400	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				INTERMITTENT, DISTORTED AUDIO.						1	G	7	2 	4U				H4SW
1998112000149	19981120	00149		1998	11	20	HEEA0016435      	4	19981026	G	3455	066104701	RECEIVER        			BELL  	412   	412         	1182202	SW  										ADF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				RECEIVER WEAK SCRATCHY 1799 KHZ NOT POINTING CORRECTLY IN ADF.						1	G	7	2 	4U				H4SW
1998112000150	19981120	00150		1998	11	20	HEEA0016436      	4	19981026	G	3455	066104701	RECEIVER        			BELL  	412   	412         	1182202	SW  										ADF	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				BFO INOPERATIVE AND VERY WEAK RECEIVE.						1	G	7	2 	4U				H4SW
1998112000151	19981120	00151	SW  	1998	11	20	HEEA0016437      	1	19981027	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	189  				53278				TRUNNION BEARING HAS EXCESSIVE AXIAL PLAY.						1	G	7	1 	3U			O	H2SW
1998112000152	19981120	00152	SW  	1998	11	20	HEEA0016438      	1	19981027	G	3212	206050247132	COVER           			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				FRONT RIGHT FLOAT COVER WORN ON ENDS AND VELCRO IS WORN, COMING OFF AND NO LONGER HOLDS BACK END FLAP DOWN.						1	G	7	1 	3U			O	H2SW
1998112000153	19981120	00153	SW  	1998	11	20	HEEA0016439      	1	19981027	G	3212	206050247132	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				FLOAT COVER HAS TORN END COVERS.						1	G	7	1 	3U			O	H2SW
1998112000154	19981120	00154	SW  	1998	11	20	HEEA0016440      	1	19981027	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				BLOWER HOUSING HAS WORKING RIVETS.						1	G	7	1 	3U			O	H2SW
1998112000155	19981120	00155	SW  	1998	11	20	HEEA0016441      	1	19981027	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				BLOWER HOUSING HAS WORKING RIVETS.						1	G	7	1 	3U			O	H2SW
1998112000156	19981120	00156	SW  	1998	11	20	HEEA0016442      	1	19981027	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				BLOWER HOUSING WORKING RIVETS.						1	G	7	1 	3U			O	H2SW
1998112000157	19981120	00157	SW  	1998	11	20	HEEA0016443      	1	19981027	G	7120	407060111101	MOUNT           			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				MOUNT HAS WORN BEARINGS.						1	G	7	1 	3U			O	H2SW
1998112000158	19981120	00158	SW  	1998	11	20	HEEA0016444      	1	19981027	G	6230	406310411101	BOOT            			BELL  	407   	407         		SW  										MAIN ROTOR	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				BOOT TORN.						1	G	7	1 	3U			O	H2SW
1998112000159	19981120	00159	SW  	1998	11	20	HEEA0016445      	1	19981027	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				PRESSURE SWITCH WILL NOT ILLUMINATE LIGHT.						1	G	7	1 	3U			O	H2SW
1998112000160	19981120	00160	SW  	1998	11	20	HEEA0016446      	1	19981027	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				COUPLING HAS CRACKED DISC.						1	G	7	1 	3U			O	H2SW
1998112000161	19981120	00161	SW  	1998	11	20	HEEA0016447      	1	19981027	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	FAULTY          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	103  				53267				DISK COUPLING - BOLTS AND NUTS LOST TORQUE.						1	G	7	1 	3U			O	H2SW
1998112000162	19981120	00162	SW  	1998	11	20	HEEA0016448      	1	19981027	G	7930	407375004101	INDICATOR       			BELL  	407   	407         		SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				ENGINE OIL TEMPERATURE INDICATION GOES TO ZERO EVERY 2 MINUTES THEN RETURNS TO NORMAL.						1	G	7	1 	3U			O	H2SW
1998112000163	19981120	00163	SW  	1998	11	20	HEEA0016449      	1	19981027	G	7921	406360500101	COOLER          			BELL  	407   	407         		SW  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	467PH					53142				OIL COOLER LEAKING.						1	G	7	1 	3U			O	H2SW
1998112000164	19981120	00164	SW  	1998	11	20	HEEA0016450      	1	19981027	G	6322	222001388101	COVER           			BELL  	230   	230         	1182149	SW  										M/R GEARBOX	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	230UN					23009				COVER CRACKED AND BROKEN.  MOUNT FLANGE MISSING.						1	G	7	2 	3U			NC	H9SW
1998112000327	19981120	00327	EU  	1998	11	20	HEEA0016451      	1	19981027	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										PITCH CONTROL	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				ROD, PITCH CONTROL HAS BEARINGS WORN.						1	G	7	1 	3U				H9EU
1998112000328	19981120	00328	EU  	1998	11	20	HEEA0016452      	1	19981027	G	6220	350A31190703	STARFLEX        			SNIAS 	350   	AS350B2     	8680813	EU  										ARM	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6095S	2015 				2777				STARFLEX CRACKED IN ONE ARM.						1	G	7	1 	3U				H9EU
1998112000165	19981120	00165		1998	11	20	HEEA0016454      	4	19981027	G	3455	066104701	RECEIVER        			BELL  	412   	412         	1182202	SW  										ADF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				UPON INSTALLATION TRANSCEIVER, ADF WOULD NOT TEST OR IDENT AND WEAK SIGNAL.						1	G	7	2 	4U				H4SW
1998112000166	19981120	00166		1998	11	20	HEEA0016455      	4	19981027	G	3444	066104800	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										RADAR ALT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	21498					36003				RADAR ALTIMETER WOULD NOT TEST ON GROUND.						1	G	7	2 	4U				H4SW
1998112000167	19981120	00167		1998	11	20	HEEA0016456      	4	19981027	G	2312	066106600	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				TRANSCEIVER INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000168	19981120	00168		1998	11	20	HEEA0016457      	4	19981027	G	3451	066106602	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT DME	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				TRANSCEIVER INOPERATIVE.  TIME SINCE REPAIR 117:40 HOURS.						1	G	7	2 	4U				H4SW
1998112000169	19981120	00169		1998	11	20	HEEA0016458      	4	19981027	G	3451	066106602	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT DME	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				TRANSCEIVER INOPERATIVE, NO TRACKING.						1	G	7	2 	4U				H4SW
1998112000170	19981120	00170		1998	11	20	HEEA0016459      	4	19981027	G	3452	066107100	TRANSPONDER     			BELL  	412   	412         	1182202	SW  										COCKPIT ATC	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				TRANSPONDER LOSES CODE MEMORY WHEN TURNED OFF.						1	G	7	2 	4U				H4SW
1998112000171	19981120	00171		1998	11	20	HEEA0016460      	4	19981027	G	3455	066107700	RECEIVER        			BELL  	412   	412         	1182202	SW  										ADF	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				ADF RECEIVER HAS NO POWER OUTPUT TO CONTROL HEAD.						1	G	7	2 	4U				H4SW
1998112000172	19981120	00172		1998	11	20	HEEA0016461      	4	19981027	G	3431	066107800	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				VHF NAV RECEIVER READS 177 OFF, NOT FOLLOWING COMPASS.						1	G	7	2 	4U				H4SW
1998112000173	19981120	00173		1998	11	20	HEEA0016462      	4	19981027	G	3454	066107810	RECEIVER        			BELL  	412   	412         	1182202	SW  										COCKPIT NAV	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				GLIDESLOPE INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000174	19981120	00174		1998	11	20	HEEA0016463      	4	19981027	G	3452	071119218	DISPLAY         			BELL  	412   	412         	1182202	SW  										COCKPIT XPONDER	DAMABED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				TRANSPONDER CONTROL HAS SEVERE BURN HOLE IN DISPLAY BOARD.						1	G	7	2 	4U				H4SW
1998112000175	19981120	00175		1998	11	20	HEEA0016464      	4	19981027	G	3450	071121570	DISPLAY         			BELL  	412   	412         	1182202	SW  										COCKPIT COMM	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				COMM 2 CONTROL HAS NO DISPLAY, BURNED SPOTS ON DISPLAY BOARD.						1	G	7	2 	4U				H4SW
1998112000176	19981120	00176		1998	11	20	HEEA0016465      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				HSI DOES NOT SLAVE WHEN OTHER HSI IS IN COMMAND.						1	G	7	2 	4U				H4SW
1998112000177	19981120	00177		1998	11	20	HEEA0016466      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03						36003				HSI INDICATOR - OFF FLAG AND HEADING CARD STICKS.						1	G	7	2 	4U				H4SW
1998112000178	19981120	00178		1998	11	20	HEEA0016467      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				G/S FLAG WILL NOT PULL.						1	G	7	2 	4U				H4SW
1998112000179	19981120	00179		1998	11	20	HEEA0016468      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				VOR FLAG WILL NOT COME IN VIEW.						1	G	7	2 	4U				H4SW
1998112000180	19981120	00180		1998	11	20	HEEA0016469      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				HSI INDICATOR - COURSE DIGITS UNREADABLE 140-180.						1	G	7	2 	4U				H4SW
1998112000181	19981120	00181		1998	11	20	HEEA0016470      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				HSI INDICATOR - NR 1 POINTER 30-50 OFF.						1	G	7	2 	4U				H4SW
1998112000182	19981120	00182		1998	11	20	HEEA0016471      	4	19981027	G	3420	1113025	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				NAV VALID FLAG WILL NOT PULL.						1	G	7	2 	4U				H4SW
1998112000183	19981120	00183		1998	11	20	HEEA0016472      	4	19981027	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				TURN IN BANK, BALL JUMPS INTERMITTENTLY IN ATTITUDE INDICATOR.						1	G	7	2 	4U				H4SW
1998112000184	19981120	00184		1998	11	20	HEEA0016473      	4	19981027	G	3421	1113034	INDICATOR       			BELL  	412   	412         	1182202	SW  										ATTITUDE	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				ADI INDICATION PRECESSES, FD FLAG STUCK.						1	G	7	2 	4U				H4SW
1998112000185	19981120	00185	SW  	1998	11	20	HEEA0016474      	1	19981027	G	2844	124044	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL PRESSURE	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				INSTRUMENTS INDICATES HIGH ON FUEL PRESSURE INDICATOR.						1	G	7	2 	4U				H4SW
1998112000186	19981120	00186	SW  	1998	11	20	HEEA0016475      	1	19981027	G	2842	2003600000102	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FUEL QUANTITY	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				SHOWS 120 POUNDS FUEL WHEN TANK EMPTY.						1	G	7	2 	4U				H4SW
1998112000187	19981120	00187	SW  	1998	11	20	HEEA0016476      	1	19981027	G	2435	200SG119Q	STARTER GEN     			BELL  	412   	412         	1182202	SW  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH	4530 				33197				GENERATOR IS INOPERATIVE AND STARTER IS DRAGGING.						1	G	7	2 	4U				H4SW
1998112000188	19981120	00188	SW  	1998	11	20	HEEA0016477      	1	19981027	G	6700	204001376003	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										FLT CONTROL	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				PEDALS STIFF AND BINDING ON BRAKE ASSEMBLY.						1	G	7	2 	4U				H4SW
1998112000189	19981120	00189	SW  	1998	11	20	HEEA0016478      	1	19981027	G	6700	204001376003	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										FLT CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				SHAFT DISENGAGED ON BRAKE ASSEMBLY.						1	G	7	2 	4U				H4SW
1998112000190	19981120	00190	SW  	1998	11	20	HEEA0016479      	1	19981027	G	6710	204060762005	LINEAR ACTUATOR 			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				LINEAR ACTUATOR INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000191	19981120	00191	SW  	1998	11	20	HEEA0016480      	1	19981027	G	5230	205032809035A	PANEL ASSY      			BELL  	412   	412         	1182202	SW  										CARGO DOOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PANEL ASSEMBLY SEPARATED.						1	G	7	2 	4U				H4SW
1998112000192	19981120	00192	SW  	1998	11	20	HEEA0016481      	1	19981027	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										BOOST	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				PUMP INOPERATIVE, WAS VERY NOISY BEFORE IT QUIT.						1	G	7	2 	4U				H4SW
1998112000193	19981120	00193	SW  	1998	11	20	HEEA0016482      	1	19981027	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										BOOST	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				PUMP HAS INTERMITTENT OPERATION AND NO PRESSURE.						1	G	7	2 	4U				H4SW
1998112000194	19981120	00194	SW  	1998	11	20	HEEA0016483      	1	19981027	G	2822	205060606003	PUMP            			BELL  	412   	412         	1182202	SW  										BOOST	REVERSED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				PUMP RUNS BACKWARDS, TRIPS CIRCUIT BREAKER IN FORWARD.						1	G	7	2 	4U				H4SW
1998112000195	19981120	00195	SW  	1998	11	20	HEEA0016484      	1	19981027	G	7160	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  										INTAKE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				ACTUATOR WOULD NOT OPERATE DOOR.						1	G	7	2 	4U				H4SW
1998112000196	19981120	00196	SW  	1998	11	20	HEEA0016485      	1	19981027	G	7160	209062214001	ACTUATOR        			BELL  	412   	412         	1182202	SW  										INTAKE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				ACTUATOR WILL NOT ACTUATE.						1	G	7	2 	4U				H4SW
1998112000197	19981120	00197	SW  	1998	11	20	HEEA0016486      	1	19981027	G	6240	209075326005	WARNING BOX     			BELL  	412   	412         	1182202	SW  										M/R RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				RPM WARNING BOX TURN NEEDLE INDICATES FULL RIGHT.						1	G	7	2 	4U				H4SW
1998112000198	19981120	00198		1998	11	20	HEEA0016487      	4	19981027	G	3425	71252	GYRO            			BELL  	212   	212         	1181420	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5010F					30936				GYRO INOPERATIVE.						1	G	7	1 	4U				H4SW
1998112000199	19981120	00199	SW  	1998	11	20	HEEA0016488      	1	19981027	G	2422	ASH5845	INVERTER        			BELL  	212   	212         	1181420	SW  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1079U					31122				INVERTER INOPERATIVE.						1	G	7	1 	4U				H4SW
1998112000200	19981120	00200	SW  	1998	11	20	HEEA0016489      	1	19981027	G	6410	212010750105	BLADE           			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH	1509 				33150				LEADING EDGE OF BLADE DAMAGED, HOLE IN END CAP AREA.						1	G	7	2 	4U				H4SW
1998112000201	19981120	00201	SW  	1998	11	20	HEEA0016490      	1	19981027	G	6520	212040003023	GEARBOX         			BELL  	412   	412         	1182202	SW  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	141PH	4029 				33197				SEAL LEAKS, EXCESSIVE CORROSION ON MAIN CASE.						1	G	7	2 	4U				H4SW
1998112000202	19981120	00202	SW  	1998	11	20	HEEA0016491      	1	19981027	G	7810	212061201012	EJECTOR         			BELL  	412   	412         	1182202	SW  										EXHAUST	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				SEAL ON EJECTOR ASSY TORN AND SEVERAL MISSING RIVETS.						1	G	7	2 	4U				H4SW
1998112000203	19981120	00203	SW  	1998	11	20	HEEA0016492      	1	19981027	G	6320	212070116009	INDICATOR       			BELL  	412   	412         	1182202	SW  										XMSN OIL	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				OIL TRANSMITTER INDICATION INTERMITTENTLY STICKS AND READS HIGH.						1	G	7	2 	4U				H4SW
1998112000204	19981120	00204		1998	11	20	HEEA0016493      	4	19981027	G	3416	212070238003	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				INDICATOR SLOW TO RESPOND TO ALTITUDE CHANGES, FAILED FRICTION ERROR TEST.						1	G	7	2 	4U				H4SW
1998112000205	19981120	00205		1998	11	20	HEEA0016494      	4	19981027	G	3416	212070238007	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				ALTIMETER INDICATION READS 50 HIGH AT 1,000 FEET.						1	G	7	2 	4U				H4SW
1998112000206	19981120	00206		1998	11	20	HEEA0016495      	4	19981027	G	3416	212070238007	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023	601  				33080				INDICATOR HAS EXCESSIVE FRICTION ERROR - NEEDLE SLOW TO RESPOND.						1	G	7	2 	4U				H4SW
1998112000207	19981120	00207		1998	11	20	HEEA0016496      	4	19981027	G	3416	212070238003	ALTIMETER       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				INDICATOR FAILED SCALE ACCURACY AND FRICTION ERROR CHECKS ON HIGH END.						1	G	7	2 	4U				H4SW
1998112000208	19981120	00208		1998	11	20	HEEA0016497      	4	19981027	G	3413	212070239001	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				RATE OF CLIMB INDICATOR HAS UNRELIABLE READINGS, CANNOT CALIBRATE.						1	G	7	2 	4U				H4SW
1998112000209	19981120	00209	SW  	1998	11	20	HEEA0016498      	1	19981027	G	7712	212075037101	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				N1 INDICATOR HAS STICKING NEEDLES.						1	G	7	2 	4U				H4SW
1998112000210	19981120	00210	SW  	1998	11	20	HEEA0016499      	1	19981027	G	7722	212075037105	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				INDICATOR FLUCTUATES ON START, WILL NOT RUN-UP.						1	G	7	2 	4U				H4SW
1998112000211	19981120	00211	SW  	1998	11	20	HEEA0016500      	1	19981027	G	7722	212075067105	INDICATOR       			BELL  	412   	412         	1182202	SW  										ITT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ITT INDICATION FLUCTUATES 550-800C IN-FLIGHT.						1	G	7	2 	4U				H4SW
1998112000212	19981120	00212	SW  	1998	11	20	HEEA0016501      	1	19981027	G	7722	212075067109	INDICATOR       			BELL  	412   	412         	1182202	SW  										ITT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				ITT INDICATION NEEDLE STICKS.						1	G	7	2 	4U				H4SW
1998112000213	19981120	00213	SW  	1998	11	20	HEEA0016502      	1	19981027	G	7722	212075067109	INDICATOR       			BELL  	412   	412         	1182202	SW  										ITT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				ITT INDICATION NEEDLE STICKS ON ENGINE STARTS.						1	G	7	2 	4U				H4SW
1998112000214	19981120	00214	SW  	1998	11	20	HEEA0016503      	1	19981027	G	7722	212075067109	INDICATOR       			BELL  	412   	412         	1182202	SW  										ITT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				ITT INDICATION NEEDLE STICKS.						1	G	7	2 	4U				H4SW
1998112000215	19981120	00215	SW  	1998	11	20	HEEA0016504      	1	19981027	G	6730	212076005103	ACTUATOR        			BELL  	412   	412         	1182202	SW  										CYCLIC	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X	13804				33115				ACTUATOR PISTON IS SCORED.						1	G	7	2 	4U				H4SW
1998112000216	19981120	00216	SW  	1998	11	20	HEEA0016505      	1	19981027	G	2915	212076006007	VALVE           			BELL  	412   	412         	1182202	SW  										HYD PRESSURE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				REMOTE BYPASS INDICATION TRIPS.						1	G	7	2 	4U				H4SW
1998112000217	19981120	00217	SW  	1998	11	20	HEEA0016506      	1	19981028	G	5320	205030889016	BRACKET         			BELL  	412   	412         	1182202	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				CRACKED AT ATTACHMENT NUT PLATE FOR ELEVATOR HORN RETAINER BRACKET.  REPLACED WITH SERVICEABLE BRACKET.						1	G	7	2 	4U				H4SW
1998112000218	19981120	00218	SW  	1998	11	20	HEEA0016507      	1	19981028	G	5320	205030889016	BRACKET         			BELL  	412   	412         	1182202	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				BRACKET CRACKED AT LOWER AFT CORNER.  REPLACED WITH SERVICEABLE BRACKET.						1	G	7	2 	4U				H4SW
1998112000219	19981120	00219	SW  	1998	11	20	HEEA0016508      	1	19981028	G	5320	206033110229	STIFFENER       			BELL  	206   	206L3       	1182108	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8591X					51495				STIFFENER CRACKED FROM RADIUS TO HOLE FOR FASTENER.  REPLACED WITH SERVICEABLE BRACKET.						1	G	7	1 	3U				H2SW
1998112000220	19981120	00220	SW  	1998	11	20	HEEA0016509      	1	19981028	G	5320	206032308005	ANGLE           			BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	2245Y					45751				ANGLE MISMANUFACTURED.  NO EDGE DISTANCE TO INSTALL NUT PLATES ON ANGLE.  THE ANGLE REMOVED IS .9375 INCH WIDE, NEW ANGL	E IS .8125 INCH WIDE.					1	G	7	1 	3U				H2SW
1998112000221	19981120	00221	SW  	1998	11	20	HEEA0016510      	1	19981028	G	2822	212076010001	BOLT            			BELL  	412   	412         	1182202	SW  										HYD PUMP	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				BOLT BROKEN ON PUMP.						1	G	7	2 	4U				H4SW
1998112000222	19981120	00222	SW  	1998	11	20	HEEA0016511      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				CYCLIC FORE AND AFT FORCE STICKING AFTER 30-40 MINUTES OF FLIGHT.						1	G	7	2 	4U				H4SW
1998112000223	19981120	00223	SW  	1998	11	20	HEEA0016512      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				ROTARY ACTUATOR NOT RELEASING, STICKING.						1	G	7	2 	4U				H4SW
1998112000224	19981120	00224	SW  	1998	11	20	HEEA0016513      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				ROTARY ACTUATOR STICKING WITH FORCE, TRIM OFF.						1	G	7	2 	4U				H4SW
1998112000225	19981120	00225	SW  	1998	11	20	HEEA0016514      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				AFCS WOULD NOT TEST IN PITCH.						1	G	7	2 	4U				H4SW
1998112000226	19981120	00226	SW  	1998	11	20	HEEA0016515      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				ROTARY ACTUATOR HAS INTERMITTENT OPERATION.						1	G	7	2 	4U				H4SW
1998112000227	19981120	00227	SW  	1998	11	20	HEEA0016516      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				AFTER 3 TO 4 HOURS OF FLIGHT, ROTARY ACTUATOR  STICKS INTERMITTENTLY.						1	G	7	2 	4U				H4SW
1998112000228	19981120	00228	SW  	1998	11	20	HEEA0016517      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ROTARY ACTUATOR WILL NOT TRIM FORCE AND AFT.						1	G	7	2 	4U				H4SW
1998112000229	19981120	00229	SW  	1998	11	20	HEEA0016518      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ROTARY ACTUATOR STICKS AND BINDS WILL NOT RELEASE.						1	G	7	2 	4U				H4SW
1998112000230	19981120	00230	SW  	1998	11	20	HEEA0016519      	1	19981028	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				ACTUATOR/LATERAL CYCLIC STICKING.						1	G	7	2 	4U				H4SW
1998112000231	19981120	00231	SW  	1998	11	20	HEEA0016520      	1	19981028	G	6240	214074280103	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				RPM LIMIT DETECTOR NOT FUNCTIONING.						1	G	7	2 	4U				H4SW
1998112000232	19981120	00232		1998	11	20	HEEA0016521      	4	19981028	G	3424	214075244001	GYRO            			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				RATE GYRO TURN SPEED INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000233	19981120	00233		1998	11	20	HEEA0016522      	4	19981028	G	3416	214175278101	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				ALTIMETER INDICATION NEEDLES STICK THROUGHOUT RANGE.						1	G	7	2 	4U				H4SW
1998112000234	19981120	00234	SW  	1998	11	20	HEEA0016523      	1	19981028	G	2435	23046020	STARTER         			BELL  	412   	412         	1182202	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2298Z	19694				33077				STARTER/GENERATOR FAILS TO MOTOR, DUE OVERHAUL.						1	G	7	2 	4U				H4SW
1998112000235	19981120	00235	SW  	1998	11	20	HEEA0016524      	1	19981028	G	2435	23046020	STARTER         			BELL  	412   	412         	1182202	SW  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH	6308 				33197				STARTER WILL NOT ENGAGE ENGINE.						1	G	7	2 	4U				H4SW
1998112000236	19981120	00236		1998	11	20	HEEA0016525      	4	19981028	G	2211	222305007101	TRIM COMPUTER   			BELL  	412   	412         	1182202	SW  										E/E BAY	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				AFCS WILL NOT BEEP LEFT OR RIGHT.						1	G	7	2 	4U				H4SW
1998112000237	19981120	00237		1998	11	20	HEEA0016526      	4	19981028	G	2200	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										E/E BAY	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				ATTITUDE INDICATOR PRECESSES.						1	G	7	2 	4U				H4SW
1998112000238	19981120	00238		1998	11	20	HEEA0016527      	4	19981028	G	2200	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										E/E BAY	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	108X					33115				DG FAILS TEST 8.5 ON SST.						1	G	7	2 	4U				H4SW
1998112000239	19981120	00239		1998	11	20	HEEA0016528      	4	19981028	G	2200	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										E/E BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				RECO LIGHT DOES NOT ILLUMINATE AFTER FAST ERECTS RELEASED.						1	G	7	2 	4U				H4SW
1998112000240	19981120	00240		1998	11	20	HEEA0016529      	4	19981028	G	2200	2593996333	TARSYN333       			BELL  	412   	412         	1182202	SW  										E/E BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				CAUSES KICK IN AFCS YAW.  VG SPIKES IN ROLL AFTER WARM-UP.						1	G	7	2 	4U				H4SW
1998112000241	19981120	00241		1998	11	20	HEEA0016530      	4	19981028	G	3422	2594484	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FLUX VALVE	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7128R					36007				TRANSMITTER FLUCTUATES WHEN VIBRATES.						1	G	7	2 	4U				H4SW
1998112000242	19981120	00242		1998	11	20	HEEA0016531      	4	19981028	G	3422	2594484	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FLUX VALVE	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2261D					33076				FLANGE LOOSE FROM HOUSING.						1	G	7	2 	4U				H4SW
1998112000243	19981120	00243		1998	11	20	HEEA0016532      	4	19981028	G	3422	2594484	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										FLUX VALVE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				PILOTS RMI WILL NOT SLAVE TO MAG COMPASS.						1	G	7	2 	4U				H4SW
1998112000131	19981120	00131	NE  	1998	11	20	HEEA0016533      	2	19981028	G	7250	3017600	POWER SECTION   			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					ENGINE	CHAFED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X	9243 				33113				POWER SECTION CHAFED ON GEARBOX.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998112000244	19981120	00244	SW  	1998	11	20	HEEA0016534      	1	19981028	G	2611	302319	SMOKE DETECTOR  			BELL  	412   	412         	1182202	SW  										CABIN	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	3893P					33012				SMOKE DETECTOR WILL NOT TEST PROPERLY.						1	G	7	2 	4U				H4SW
1998112000245	19981120	00245	SW  	1998	11	20	HEEA0016535      	1	19981028	G	2611	302319	SMOKE DETECTOR  			BELL  	412   	412         	1182202	SW  										CABIN	MALFUNCTIONED   	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	142PH					33150				SMOKE DETECTOR INTERMITTENT DURING TEST.						1	G	7	2 	4U				H4SW
1998112000132	19981120	00132	NE  	1998	11	20	HEEA0016536      	2	19981028	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING GRBOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K	2563 				36001				GEARBOX MAKING METAL.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998112000133	19981120	00133	NE  	1998	11	20	HEEA0016537      	2	19981028	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING GRBOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T	3554 				33112				GEARBOX MAKING METAL.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998112000134	19981120	00134	NE  	1998	11	20	HEEA0016538      	2	19981028	G	7210	3024780	GEARBOX         			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					COMBINING BOX	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH	4911 				33197				GEARBOX MAKING METAL.						1	G	7	2 	4U	4	U		H4SW    	E22EA
1998112000246	19981120	00246	SW  	1998	11	20	HEEA0016539      	1	19981028	G	7722	3030083	TRIM COMPENSATOR			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				ITT FLUCTUATES AND CANNOT ADJUST BIAS.						1	G	7	2 	4U				H4SW
1998112000247	19981120	00247	SW  	1998	11	20	HEEA0016540      	1	19981028	G	7722	3030083	TRIM COMPENSATOR			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				IN-FLIGHT ITT FLUCTUATES OK ON GROUND.						1	G	7	2 	4U				H4SW
1998112000248	19981120	00248	SW  	1998	11	20	HEEA0016541      	1	19981028	G	7722	3030083	TRIM COMPENSATOR			BELL  	412   	412         	1182202	SW  										COCKPIT	FLUCTUATES      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				TRIM COMPENSATOR'S INDICATOR FLUCTUATES.						1	G	7	2 	4U				H4SW
1998112000249	19981120	00249	SW  	1998	11	20	HEEA0016542      	1	19981028	G	7722	3030083	TRIM COMPENSATOR			BELL  	412   	412         	1182202	SW  										COCKPIT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				ITT READING TOO HIGH.						1	G	7	2 	4U				H4SW
1998112000250	19981120	00250	SW  	1998	11	20	HEEA0016543      	1	19981028	G	7722	3030083	TRIM COMPENSATOR			BELL  	412   	412         	1182202	SW  										COCKPIT	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				TRIM COMPENSATOR INOPERATIVE ONLY 10 DIFFERENCE.						1	G	7	2 	4U				H4SW
1998112000135	19981120	00135	NE  	1998	11	20	HEEA0016544      	2	19981028	G	7532	312320201	VALVE           			BELL  	412   	412         	1182202	SW  	PWA   	PT6T  	PT6T3B      	52045	NE  					BLEED AIR SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	2148K					36001				VALVE MADE ENGINE HOWL.  TESTED BY ACCESSORY SHOP AND UNIT LEAKED AT THE SPLITLINE.  UNIT ALSO LEAKED AROUND PISTON AREA	, INDICATING A RUPTURED DIAPHRAGM.					1	G	7	2 	4U	4	U		H4SW    	E22EA
1998112000251	19981120	00251	SW  	1998	11	20	HEEA0016545      	1	19981028	G	2840	391046197	PROBE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				FUEL PROBE READS HIGH OUT OF TOLERANCE ON CAP METER.						1	G	7	2 	4U				H4SW
1998112000252	19981120	00252	SW  	1998	11	20	HEEA0016546      	1	19981028	G	2840	391046199	PROBE           			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				FUEL PROBE READS HIGH OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998112000253	19981120	00253	SW  	1998	11	20	HEEA0016547      	1	19981028	G	2841	393008047	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL QUANTITY	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				INDICATOR WILL NOT ADJUST TO ZERO WHEN EMPTY.						1	G	7	2 	4U				H4SW
1998112000254	19981120	00254	SW  	1998	11	20	HEEA0016548      	1	19981028	G	2841	393008047	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL QUANTITY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				INDICATION CONSTANTLY FLUCTUATES 50 POUNDS ON TEST, LEFT TO RIGHT.						1	G	7	2 	4U				H4SW
1998112000255	19981120	00255		1998	11	20	HEEA0016549      	4	19981028	G	3450	40001452500	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT VHF	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				POWER-OUT HESITATING WHEN KEYED.						1	G	7	2 	4U				H4SW
1998112000256	19981120	00256		1998	11	20	HEEA0016550      	4	19981028	G	2210	4020936903	TARSYN333       			BELL  	412   	412         	1182202	SW  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				ATTITUDE GYRO ERRATIC IN PITCH.  TIME SINCE REPAIR 10:40 HOURS.						1	G	7	2 	4U				H4SW
1998112000257	19981120	00257	SW  	1998	11	20	HEEA0016551      	1	19981028	G	6730	4025008918	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				NO POWER OUTPUT ON PITCH MODE.						1	G	7	2 	4U				H4SW
1998112000258	19981120	00258		1998	11	20	HEEA0016552      	4	19981028	G	2211	4033089901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COMPUTER FAILS ROLL CHANNEL TEST.						1	G	7	2 	4U				H4SW
1998112000259	19981120	00259	SW  	1998	11	20	HEEA0016553      	1	19981028	G	6220	412010190103	SPINDLE         			BELL  	412   	412         	1182202	SW  										DAMPER	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P	2666 				33012				DAMPER BEARING SEPARATED FROM SPINDLE.						1	G	7	2 	4U				H4SW
1998112000260	19981120	00260	SW  	1998	11	20	HEEA0016554      	1	19981028	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T	8809 				33112				BLADE TIP EXTREMELY HEAVY, SUSPECT WATER IN BLADE.						1	G	7	2 	4U				H4SW
1998112000261	19981120	00261	SW  	1998	11	20	HEEA0016555      	1	19981028	G	6210	412015300109	BLADE           			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T	5349 				33112				BLADE TIP EXTREMELY HEAVY, SUSPECT WATER IN BLADE.						1	G	7	2 	4U				H4SW
1998112000262	19981120	00262		1998	11	20	HEEA0016556      	4	19981028	G	3414	412075009105	INDICATOR       			BELL  	412   	412         	1182202	SW  										AIRSPEED	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				AIRSPEED INDICATION INDICATES LOW OUT OF TOLERANCE THROUGHOUT.						1	G	7	2 	4U				H4SW
1998112000263	19981120	00263		1998	11	20	HEEA0016557      	4	19981028	G	3414	412075009105	INDICATOR       			BELL  	412   	412         	1182202	SW  										AIRSPEED	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				AIRSPEED INDICATOR READS 15 KNOTS TOO FAST.						1	G	7	2 	4U				H4SW
1998112000264	19981120	00264		1998	11	20	HEEA0016558      	4	19981028	G	3414	412075009105	INDICATOR       			BELL  	412   	412         	1182202	SW  										AIRSPEED	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				AIRSPEED NEEDLE READS HIGH OUT OF TOLERANCE.						1	G	7	2 	4U				H4SW
1998112000265	19981120	00265	SW  	1998	11	20	HEEA0016559      	1	19981028	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				TRIPLE TACHOMETER INSTRUMENT INDICATES OUT OF TOLERANCE 100 PERCENT.						1	G	7	2 	4U				H4SW
1998112000266	19981120	00266	SW  	1998	11	20	HEEA0016560      	1	19981028	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				TRIPLE TACHOMETER HAS SEVERE NEEDLE SPLIT.						1	G	7	2 	4U				H4SW
1998112000267	19981120	00267	SW  	1998	11	20	HEEA0016561      	1	19981028	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				TRIPLE TACHOMETER HAS NEEDLE SPLIT, JERK MOVEMENT.						1	G	7	2 	4U				H4SW
1998112000268	19981120	00268	SW  	1998	11	20	HEEA0016562      	1	19981028	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				NEEDLES NR 1 AND NR 2 STUCK AND ERRATIC.						1	G	7	2 	4U				H4SW
1998112000269	19981120	00269	SW  	1998	11	20	HEEA0016563      	1	19981028	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				TRIPLE TACHOMETER'S NR 1 NEEDLE READS HIGH AND STICKS.						1	G	7	2 	4U				H4SW
1998112000270	19981120	00270	SW  	1998	11	20	HEEA0016564      	1	19981028	G	7714	412075010109	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				NR 1 INDICATION NEEDLE STICKS.  ROTOR NEEDLE READS 2 PERCENT  LOW.						1	G	7	2 	4U				H4SW
1998112000271	19981120	00271	SW  	1998	11	20	HEEA0016565      	1	19981028	G	7714	412075010111	INDICATOR       			BELL  	412   	412         	1182202	SW  										TRIPLE TACH	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				NR 1 ENGINE INDICATION WILL NOT GO TO 100 PERCENT.						1	G	7	2 	4U				H4SW
1998112000272	19981120	00272	SW  	1998	11	20	HEEA0016566      	1	19981028	G	2422	412075101101	INVERTER        			BELL  	412   	412         	1182202	SW  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				NR 2 INVERTER INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000273	19981120	00273	SW  	1998	11	20	HEEA0016567      	1	19981028	G	2422	412075101101	INVERTER        			BELL  	412   	412         	1182202	SW  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				INVERTER WILL NOT COME ON LINE, INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000274	19981120	00274	SW  	1998	11	20	HEEA0016568      	1	19981028	G	7712	412075205101	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										ENGINE TORQUE	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				TORQUE TRANSMITTER STICKING.						1	G	7	2 	4U				H4SW
1998112000275	19981120	00275	SW  	1998	11	20	HEEA0016569      	1	19981028	G	7712	412075205101	TRANSMITTER     			BELL  	412   	412         	1182202	SW  										ENGINE TORQUE	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				TORQUE TRANSMITTER INDICATES LOW POWER.						1	G	7	2 	4U				H4SW
1998112000276	19981120	00276	SW  	1998	11	20	HEEA0016570      	1	19981028	G	2841	412375001101	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL QUANTITY	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	33008					36004				RIGHT READING 100  PERCENT LOWER THAN LEFT ON FUEL QUANTITY INDICATOR.						1	G	7	2 	4U				H4SW
1998112000277	19981120	00277	SW  	1998	11	20	HEEA0016571      	1	19981028	G	2841	412375001101	INDICATOR       			BELL  	412   	412         	1182202	SW  										FUEL QUANTITY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				UNRELIABLE ANALOG INDICATION READS 250 POUNDS ON RIGHT SIDE LESS THAN LEFT SIDE ON FUEL QUANTITY INDICATOR.						1	G	7	2 	4U				H4SW
1998112000278	19981120	00278		1998	11	20	HEEA0016572      	4	19981028	G	3453	453105004	LORAN           			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	107X					33113				ENTER BUTTON UNREADABLE ON LORAN.						1	G	7	2 	4U				H4SW
1998112000279	19981120	00279	SW  	1998	11	20	HEEA0016573      	1	19981028	G	2840	473203003	SIGNAL COND     			BELL  	412   	412         	1182202	SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				FUEL QUANTITY INDICATOR INTERMITTENTLY DROPS TO ZERO (LEFT).						1	G	7	2 	4U				H4SW
1998112000280	19981120	00280		1998	11	20	HEEA0016574      	4	19981028	G	3416	5035P2P42	ENCODER         			BELL  	412   	412         	1182202	SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2258F					33073				HUNDREDS NEEDLE HAS INTERMITTENT OPERATION ON ALTIMETER.						1	G	7	2 	4U				H4SW
1998112000281	19981120	00281		1998	11	20	HEEA0016575      	4	19981028	G	3416	5035P2P44	ENCODER         			BELL  	412   	412         	1182202	SW  										ALTIMETER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6559Z					36019				EXCESSIVE CASE LEAKAGE, LOOSE PARTS INSIDE ENCODING ALTIMETER.						1	G	7	2 	4U				H4SW
1998112000282	19981120	00282		1998	11	20	HEEA0016576      	4	19981028	G	3416	5035P2P44	ENCODER         			BELL  	412   	412         	1182202	SW  										ALTIMETER	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22608					33075				ENCODER READOUTS ERRATIC AND INDICATES HIGH.						1	G	7	2 	4U				H4SW
1998112000283	19981120	00283		1998	11	20	HEEA0016577      	4	19981028	G	3421	5040045901	GYRO            			BELL  	412   	412         	1182202	SW  										ATTITUDE	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										GYRO HAS ERRATIC ERECTION ON ATTITUDE INDICATION.						1	G	7	2 	4U				H4SW
1998112000284	19981120	00284	SW  	1998	11	20	HEEA0016578      	1	19981028	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				BATTERY BUS SWITCH WILL NOT STAY LOCKED.  TIME SINCE REPAIR 1,096:00 HOURS.						1	G	7	2 	4U				H4SW
1998112000285	19981120	00285	SW  	1998	11	20	HEEA0016579      	1	19981028	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023					33080				GENERATOR DID NOT COME ON-LINE.						1	G	7	2 	4U				H4SW
1998112000286	19981120	00286	SW  	1998	11	20	HEEA0016580      	1	19981028	G	2430	51509002R	CONTROL UNIT    			BELL  	412   	412         	1182202	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	1202T					33112				GENERATOR WILL NOT COME ON-LINE.  TIME SINCE REPAIR 0:00.						1	G	7	2 	4U				H4SW
1998112000287	19981120	00287		1998	11	20	HEEA0016581      	4	19981028	G	2210	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				COMPUTER SLOW TO TRIM IN ROLL.						1	G	7	2 	4U				H4SW
1998112000288	19981120	00288		1998	11	20	HEEA0016582      	4	19981028	G	2210	7000298901	COMPUTER        			BELL  	412   	412         	1182202	SW  										AFCS	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	21498					36003				NR 2 HELIPILOT KICKS OFF 14 FIT = SAS ATT MODE LIGHTS REMAIN ON AT SAME TIME.						1	G	7	2 	4U				H4SW
1998112000289	19981120	00289		1998	11	20	HEEA0016583      	4	19981028	G	2210	7000299901	CONTROLLER      			BELL  	412   	412         	1182202	SW  										AUTOFLIGHT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893P					33012				ATT SAS SEGMENT CHIPPED.						1	G	7	2 	4U				H4SW
1998112000290	19981120	00290		1998	11	20	HEEA0016584      	4	19981028	G	3444	7000839901	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADIO ALT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3911L					33023				NO DH INDICATION, EITHER LIGHT OR ORAL.						1	G	7	2 	4U				H4SW
1998112000291	19981120	00291		1998	11	20	HEEA0016585      	4	19981028	G	3444	7000839904	INDICATOR       			BELL  	412   	412         	1182202	SW  										RADAR ALT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RADAR INDICATION READS LOW AT 200 FEET.						1	G	7	2 	4U				H4SW
1998112000292	19981120	00292	SW  	1998	11	20	HEEA0016586      	1	19981028	G	6720	7001484	ACTUATOR        			BELL  	412   	412         	1182202	SW  										YAW CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5759N					33002				ACTUATOR STUCK IN FULL RIGHT HARD POSITION.						1	G	7	2 	4U				H4SW
1998112000293	19981120	00293		1998	11	20	HEEA0016587      	4	19981028	G	2312	7001840913	TRANSCEIVER     			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RECEIVER/TRANSMITTER OUTPUT WILL NOT ADJUST TO .450 VDC.						1	G	7	2 	4U				H4SW
1998112000294	19981120	00294	SW  	1998	11	20	HEEA0016588      	1	19981028	G	3340	7028501	LIGHT           			BELL  	412   	412         	1182202	SW  										STROBE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	22347					36005				STROBE LIGHT INOPERATIVE, UNIT FULL OF WATER.						1	G	7	2 	4U				H4SW
1998112000295	19981120	00295	SW  	1998	11	20	HEEA0016589      	1	19981028	G	2841	71122002	INDICATOR       			BELL  	412   	412         	1182202	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893N					33010				FUEL QUANTITY INDICATION NEEDLE FLUCTUATES.						1	G	7	2 	4U				H4SW
1998112000296	19981120	00296		1998	11	20	HEEA0016590      	4	19981028	G	3425	71252	GYRO            			BELL  	412   	412         	1182202	SW  										HSI	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	23023	643  				33080				POINTER ON BOTTOM OF ATTITUDE GAUGE NOT CENTERED.						1	G	7	2 	4U				H4SW
1998112000297	19981120	00297	SW  	1998	11	20	HEEA0016591      	1	19981028	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										ENGINE OIL	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2148K					36001				C-BOX MAKING METAL.						1	G	7	2 	4U				H4SW
1998112000298	19981120	00298	SW  	1998	11	20	HEEA0016592      	1	19981028	G	7921	8538100	OIL COOLER      			BELL  	412   	412         	1182202	SW  										XMSN OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA									TRANS. OIL TEMP HIGH.						1	G	7	2 	4U				H4SW
1998112000299	19981120	00299	SW  	1998	11	20	HEEA0016593      	1	19981028	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				BRAKE ASSEMBLY HAS WORN LININGS.						1	G	7	2 	4U				H4SW
1998112000300	19981120	00300	SW  	1998	11	20	HEEA0016594      	1	19981028	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MALFUCNTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2149S					36002				BRAKE ASSEMBLY SWITCHES INOPERATIVE.						1	G	7	2 	4U				H4SW
1998112000301	19981120	00301	SW  	1998	11	20	HEEA0016595      	1	19981028	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	3893N					33010				BRAKE ASSEMBLY LEAKING AND LININGS WORN.						1	G	7	2 	4U				H4SW
1998112000302	19981120	00302	SW  	1998	11	20	HEEA0016596      	1	19981028	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893L					33006				BRAKE ASSEMBLY HAS WORN LININGS.						1	G	7	2 	4U				H4SW
1998112000303	19981120	00303	SW  	1998	11	20	HEEA0016597      	1	19981028	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141PH					33197				BRAKE ASSEMBLY HAS BROKEN SWITCH ASSY.						1	G	7	2 	4U				H4SW
1998112000304	19981120	00304	SW  	1998	11	20	HEEA0016598      	1	19981028	G	6321	94501031	BRAKE ASSY      			BELL  	412   	412         	1182202	SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3893S					33022				BRAKE ASSEMBLY HAS WORN LININGS.						1	G	7	2 	4U				H4SW
1998112000305	19981120	00305	SW  	1998	11	20	HEEA0016603      	1	19981031	G	7712	407375003107	INDICATOR       			BELL  	407   	407         		SW  										ENGINE TORQUE	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				TORQUE INDICATOR'S DIGITAL DISPLAY HAS CONTINUOUS ROTATION AND ERRATIC NUMBERS.						1	G	7	1 	3U			O	H2SW
1998112000306	19981120	00306	SW  	1998	11	20	HEEA0016604      	1	19981031	G	6410	406016100119	BLADE           			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1277 				53114				SEPARATION AT BLADE TIP, SUSPECTED INVOLVED IN AN OVERSPEED INCIDENT (118.4 PERCENT).						1	G	7	1 	3U			O	H2SW
1998112000307	19981120	00307	SW  	1998	11	20	HEEA0016606      	1	19981031	G	6510	407040302103	DRIVE SHAFT     			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	134  				53278				TAIL ROTOR DRIVESHAFT BEARINGS CAUSING HIGH FREQUENCY VIBRATION.						1	G	7	1 	3U			O	H2SW
1998112000308	19981120	00308	SW  	1998	11	20	HEEA0016609      	1	19981031	G	6310	406040500123	FREEWHEEL UNIT  			BELL  	407   	407         		SW  										MAIN ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	510PH	937  				53209				FREEWHEEL UNIT'S FORWARD SEAL LEAKS.						1	G	7	1 	3U			O	H2SW
1998112000309	19981120	00309	SW  	1998	11	20	HEEA0016615      	1	19981031	G	7921	406360500101	OIL COOLER      			BELL  	407   	407         		SW  										ENGINE OIL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				HIGH OIL TEMP (ENGINE).						1	G	7	1 	3U			O	H2SW
1998112000310	19981120	00310	SW  	1998	11	20	HEEA0016616      	1	19981031	G	3212	206050247137	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW
1998112000311	19981120	00311	SW  	1998	11	20	HEEA0016617      	1	19981031	G	2822	407362013101	SWITCH          			BELL  	407   	407         		SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				PRESSURE SWITCH LIGHT DOESN'T COME ON, INTERMITTENT.						1	G	7	1 	3U			O	H2SW
1998112000312	19981120	00312	SW  	1998	11	20	HEEA0016619      	1	19981031	G	7810	407063001101	EXHAUST STACK   			BELL  	407   	407         		SW  										ENGINE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH					53114				EXHAUAST STACK CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000313	19981120	00313	SW  	1998	11	20	HEEA0016620      	1	19981031	G	5320	206032305129A	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1644 				53114				ANGLE CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000314	19981120	00314	SW  	1998	11	20	HEEA0016621      	1	19981031	G	5320	206032305127	CHANNEL         			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1644 				53114				CHANNEL CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000315	19981120	00315	SW  	1998	11	20	HEEA0016622      	1	19981031	G	5320	206032305129A	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	578  				53199				ANGLE CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000316	19981120	00316	SW  	1998	11	20	HEEA0016623      	1	19981031	G	5320	206032305127	CHANNEL         			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	578  				53199				CHANNEL CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000317	19981120	00317	SW  	1998	11	20	HEEA0016624      	1	19981031	G	5320	206032305129A	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	133  				53278				ANGLE CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000318	19981120	00318	SW  	1998	11	20	HEEA0016625      	1	19981031	G	5320	206032305127	CHANNEL         			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	133  				53278				CHANNEL CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000319	19981120	00319	SW  	1998	11	20	HEEA0016626      	1	19981031	G	5320	206064902105	FIREWALL        			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH	133  				53278				FIREWALL CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000320	19981120	00320	SW  	1998	11	20	HEEA0016627      	1	19981031	G	7120	407060111101	BIPOD MOUNT     			BELL  	407   	407         		SW  										ENGINE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MOUNT BEARINGS WORN.						1	G	7	1 	3U			O	H2SW
1998112000321	19981120	00321	SW  	1998	11	20	HEEA0016628      	1	19981031	G	6300	406012129101	LINK ASSEMBLY   			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				LINK ASSEMBLY BEARINGS WORN.						1	G	7	1 	3U			O	H2SW
1998112000322	19981120	00322	SW  	1998	11	20	HEEA0016629      	1	19981031	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000323	19981120	00323	SW  	1998	11	20	HEEA0016630      	1	19981031	G	6510	206061432118	INLET           			BELL  	407   	407         		SW  										TAIL ROTOR	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				INLET CRACKED AND BROKEN OFF.						1	G	7	1 	3U			O	H2SW
1998112000324	19981120	00324	SW  	1998	11	20	HEEA0016631      	1	19981031	G	7910	206061505115	TANK            			BELL  	407   	407         		SW  										ENGINE OIL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				TANK ASSY CRACKED.						1	G	7	1 	3U			O	H2SW
1998112000329	19981120	00329	EU  	1998	11	20	HEEA0016632      	1	19981031	G	6720	350A33214501	ROD             			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466					3004				ROD, PITCH CONTROL HAS WORN BEARINGS.						1	G	7	1 	3U				H9EU
1998112000136	19981120	00136	GL  	1998	11	20	HEEA0016633      	2	19981031	G	7250	23055438	NOZZLE          								ALLSN 	250C  	250C30P     	03013	GL  					2ND STAGE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					CAT90463		CAE895554			TURBINE DISASSEMBLED DUE TO N1 DRAG ON TEST CELL.  UPON INSPECTION OF TURBINE PARTS NOTED:   TIP DRAG ON NR 2 NOZZLE 1ST	 STAGE TIP PATH.  INSTALLED AN OVERHAULED NR 2 NOZZLE.										3	U			E1GL
1998112000137	19981120	00137	GL  	1998	11	20	HEEA0016634      	2	19981031	G	7250	23055438	NOZZLE          		23035128    	SKRSKY	S76   	S76A        	8143006	NE  	ALLSN 	250C  	250C30S     	03013	GL  					2ND STAGE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5128	637  			CAT97610	760181	CAE890460S			ENGINE REMOVED DUE TO NR 1 AND NR 2 WHEEL CYCLES.  UPON INSPECTION OF TURBINE PARTS NOTED:   RUNOUT EXCEED SERVICEABLE L	IMITS ON NR 2 NOZZLE TIP PATHS .002 INCH RUNOUT OVER SPECS ON NR 1 TIP PATH.  .001 INCH RUNOUT OVER SPECS ON NR 2 TIP PA	TH.  INSTALLED OVERHAULED NR 2 NOZZLE.				1	G	7	2 	3U	3	U		H1NE    	E1GL
1998112000325	19981120	00325	SW  	1998	11	20	HEEA0016635      	1	19981031	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA	2071 				53016				STARTER/GENERATOR BRUSHES WORN BEYOND LIMITS.						1	G	7	1 	3U			O	H2SW
1998112000326	19981120	00326	SW  	1998	11	20	HEEA0016636      	1	19981031	G	2435	206062200113	STARTER         			BELL  	407   	407         		SW  										START/GEN	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH	735  				53228				STARTER/GENERATOR INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998112000330	19981120	00330	SW  	1998	11	20	HEEA0016639      	1	19981104	G	6710	206062721109	ACTUATOR        			BELL  	206   	206L1       	1182107	SW  										DROOP COMP	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2770Y					45291				ACTUATOR SHAFT CRACKED.						1	G	7	1 	3U				H2SW
1998112000331	19981120	00331		1998	11	20	HEEA0016641      	4	19981105	G	3422	060001500	GYRO            			BOLKMS	105   	BO105S      	5626006	EU  										HSI	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				GYRO HAS INTERMITTENT OUTPUT TO HSI INDICATOR.						1	G	7	2 	3U				H3EU
1998112000332	19981120	00332		1998	11	20	HEEA0016642      	4	19981105	G	3444	066104800	TRANSCEIVER     			BOLKMS	105   	BO105S      	5626006	EU  										RADAR ALT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	818SH					S753				FLAG WILL NOT PULL OR NEEDLE MOVE WITH POWER ON.						1	G	7	2 	3U				H3EU
1998112000333	19981120	00333		1998	11	20	HEEA0016643      	4	19981105	G	3452	066106200	TRANSPONDER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	9190Y					S669				TRANSPONDER  WILL NOT TRANSMIT.						1	G	7	2 	3U				H3EU
1998112000334	19981120	00334		1998	11	20	HEEA0016644      	4	19981105	G	3452	066106200	TRANSPONDER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				TRANSCEIVER WILL NOT TRANSMIT AFTER ONE HOUR OF FLIGHT.						1	G	7	2 	3U				H3EU
1998112000335	19981120	00335		1998	11	20	HEEA0016645      	4	19981105	G	3452	066106200	TRANSPONDER     			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911EB					S812				REPLY LIGHT BLINKS CONTINUOUSLY.						1	G	7	2 	3U				H3EU
1998112000336	19981120	00336		1998	11	20	HEEA0016646      	4	19981105	G	3452	066106200	TRANSPONDER     			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	217UC					7152				IDENTIFIER LIGHT IS INOPERATIVE.						1	G	7	2 	3U				H13EU
1998112000337	19981120	00337		1998	11	20	HEEA0016647      	4	19981105	G	3452	066107100	TRANSPONDER     			BOLKMS	117   	BK117A3     	5626015	EU  										ATC	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				TRANSPONDER DISPLAY COMES UP 7777 WHEN UNIT IS TURNED ON.						1	G	7	2 	3U				H13EU
1998112000338	19981120	00338		1998	11	20	HEEA0016648      	4	19981105	G	3444	066305401	INDICATOR       			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911LK					7068				DH LIGHT OUT OF SPECS , R210 AND R304 BAD.						1	G	7	2 	3U			NC	H13EU
1998112000339	19981120	00339	EU  	1998	11	20	HEEA0016649      	1	19981105	G	6420	10531713	GRIP BEARING    			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T	10085				S539				TAIL ROTOR ASSEMBLY'S GRIP BEARING WORN.						1	G	7	2 	3U				H3EU
1998112000340	19981120	00340	EU  	1998	11	20	HEEA0016650      	1	19981105	G	6510	1053180301	DRIVE SHAFT     			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B					S673				CRACKS AND FLAKING ON INBOARD JOURNAL FLAME SPRAY COATING.						1	G	7	2 	3U				H3EU
1998112000341	19981120	00341	EU  	1998	11	20	HEEA0016651      	1	19981105	G	6510	1053180301	DRIVE SHAFT     			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				TAIL ROTOR HAS CRACKS IN PLATING.						1	G	7	2 	3U				H3EU
1998112000342	19981120	00342	EU  	1998	11	20	HEEA0016652      	1	19981105	G	6510	1053180301	DRIVE SHAFT     			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911EB					S812				TAIL ROTOR WORN BEYOND LIMITS.						1	G	7	2 	3U				H3EU
1998112000343	19981120	00343	EU  	1998	11	20	HEEA0016653      	1	19981105	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H					S833				TAIL ROTOR BLADE'S RUBBER COAT DETERIORATING AT BLADE TIP.						1	G	7	2 	3U				H3EU
1998112000344	19981120	00344	EU  	1998	11	20	HEEA0016654      	1	19981105	G	6410	10531980	BLADE           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	DETERIORATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H					S833				TAIL ROTOR BLADE'S RUBBER COAT DETERIORATING AT BLADE TIP.						1	G	7	2 	3U				H3EU
1998112000345	19981120	00345	EU  	1998	11	20	HEEA0016655      	1	19981105	G	6710	10541488	CONTROL ROD     			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				EXCESSIVE CORROSION UNDER COLLAR OF CONTROL TUBE.  REPLACED WITH SERVICEABLE CONTROL TUBE.						1	G	7	2 	3U				H3EU
1998112000346	19981120	00346	EU  	1998	11	20	HEEA0016656      	1	19981105	G	6710	10545361	CONTROL ROD     			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				EXCESSIVE CORROSION ON COLLAR AT ROD END MOUNT AREA OF CONTROL TUBE.  REPLACED WITH SERVICEABLE CONTROL TUBE.						1	G	7	2 	3U				H3EU
1998112000347	19981120	00347	EU  	1998	11	20	HEEA0016657      	1	19981105	G	7100	10560386	BUSHING         			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE MOUNT	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				ELASTOMERIC SEPARATING FROM BUSHING.  REPLACED WITH SERVICEABLE CONTROL TUBE.						1	G	7	2 	3U				H3EU
1998112000348	19981120	00348	EU  	1998	11	20	HEEA0016658      	1	19981105	G	7722	10590947	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				TOT INDICATOR CANNOT CALIBRATE.  NON-LINEAR THROUGH SCALE.						1	G	7	2 	3U				H3EU
1998112000349	19981120	00349	EU  	1998	11	20	HEEA0016659      	1	19981105	G	7722	10590947	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TOT INDICATOR OUT OF CALIBRATION.  40 DEGREES LOW AT 900 DEGREES.						1	G	7	2 	3U				H3EU
1998112000350	19981120	00350	EU  	1998	11	20	HEEA0016660      	1	19981105	G	7722	10590947	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TOT INDICATOR UNABLE TO CALIBRATE.						1	G	7	2 	3U				H3EU
1998112000351	19981120	00351	EU  	1998	11	20	HEEA0016661      	1	19981105	G	7722	10590947	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										READING 100 DEGREES WITH ENGINE RUNNING.						1	G	7	2 	3U				H3EU
1998112000352	19981120	00352	EU  	1998	11	20	HEEA0016662      	1	19981105	G	7722	10590947	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR					S719				TOT INDICATION NEEDLE FLUCTUATES WHEN VIBRATED.						1	G	7	2 	3U				H3EU
1998112000353	19981120	00353	EU  	1998	11	20	HEEA0016663      	1	19981105	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				MAST MOMENT INDICATION HAS ERRATIC OPERATION AT INDICATOR IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998112000354	19981120	00354	EU  	1998	11	20	HEEA0016664      	1	19981105	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				TORQUE TRANSMISSION ERRATIC OPERATION AT INDICATOR IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998112000355	19981120	00355	EU  	1998	11	20	HEEA0016665      	1	19981105	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	135AE					S838				TORQUE TRANSMISSION INTERMITTENT, NEEDLE STICKS.						1	G	7	2 	3U				H3EU
1998112000356	19981120	00356	EU  	1998	11	20	HEEA0016666      	1	19981105	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	135AE					S838				MAST MOMENT INDICATION INTERMITTENT, NEEDLE STICKS.						1	G	7	2 	3U				H3EU
1998112000357	19981120	00357	EU  	1998	11	20	HEEA0016667      	1	19981105	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8197X					S808				TORQUE TRANSMITTER WOULD NOT TEST.						1	G	7	2 	3U				H3EU
1998112000358	19981120	00358		1998	11	20	HEEA0016668      	4	19981105	G	3400	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	8197X					S808				MAST MOMENT INDICATOR WOULD NOT TEST.						1	G	7	2 	3U				H3EU
1998112000359	19981120	00359	EU  	1998	11	20	HEEA0016669      	1	19981105	G	6240	10594564	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	137AE					S851				MAST MOMENT WILL NOT INDICATE WITH ROTOR RUNNING.						1	G	7	2 	3U				H3EU
1998112000360	19981120	00360	EU  	1998	11	20	HEEA0016670      	1	19981105	G	6240	10594575	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										MAST MOMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	137AE					S851				TORQUE TRANSMITTER WILL NOT INDICATE WITH ROTOR RUNNING.						1	G	7	2 	3U				H3EU
1998112000361	19981120	00361	GL  	1998	11	20	HEEA0016671      	2	19981105	G	7510	1092T1002W	ACTUATOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					ANTI ICE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81982					S818				ACTUATOR WILL NOT ACTUATE.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998112000362	19981120	00362	EU  	1998	11	20	HEEA0016672      	1	19981105	G	6510	112131521	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				SHAFT ASSY HAS CORROSION ON TUBE.						1	G	7	2 	3U				H3EU
1998112000363	19981120	00363	EU  	1998	11	20	HEEA0016673      	1	19981105	G	6510	112131521	SHAFT           			BOLKMS	105   	BO105S      	5626006	EU  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM					S683				SHAFT ASSEMBLY HAS WORN BEARING.						1	G	7	2 	3U				H3EU
1998112000364	19981120	00364	EU  	1998	11	20	HEEA0016674      	1	19981105	G	2842	1176415203	TRANSMITTER     			BOLKMS	117   	BK117A4     	5626017	EU  										FUEL QUANTITY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				FUEL QUANTITY TRANSMITTER STICKING.						1	G	7	2 	3U				H13EU
1998112000365	19981120	00365	EU  	1998	11	20	HEEA0016675      	1	19981105	G	3310	1179203103	CONTROL UNIT    			BOLKMS	117   	BK117B2     	5626013	EU  										LIGHTS	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911LK					7068				CONTROL UNIT TRIPS CIRCUIT BREAKER AS SOON AS LIGHT SWITH TURNED ON.						1	G	7	2 	3U			NC	H13EU
1998112000366	19981120	00366	EU  	1998	11	20	HEEA0016676      	1	19981105	G	3150	1179405207	ANNUNCIATOR     			BOLKMS	117   	BK117B2     	5626013	EU  										MASTER CAUTION	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	191BK					7146				ANNUNCIATOR PANEL'S TOP TWO SEGMENTS LEFT WILL NOT LIGHT.						1	G	7	2 	3U			NC	H13EU
1998112000367	19981120	00367	EU  	1998	11	20	HEEA0016677      	1	19981105	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117B2     	5626013	EU  										ENGINE N1	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	136AE					7234				N1 INDICATOR INOPERATIVE.						1	G	7	2 	3U			NC	H13EU
1998112000368	19981120	00368	EU  	1998	11	20	HEEA0016678      	1	19981105	G	7714	1179405603	INDICATOR       			BOLKMS	117   	BK117B2     	5626013	EU  										ENGINE N1	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	136AE					7234				N1 INDICATOR INSTRUMENT READS HIGH AFTER WARM-UP.						1	G	7	2 	3U			NC	H13EU
1998112000369	19981120	00369	GL  	1998	11	20	HEEA0016679      	2	19981105	G	7320	1564T1005	ACTUATOR        			BOLKMS	105   	BO105S      	5626006	EU  	ALLSN 	250C  	250C20B     	03013	GL  					FUEL CONTROL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721MB					S752				ACTUATOR  WILL NOT ACTUATE.						1	G	7	2 	3U	3	U		H3EU    	E4CE
1998112000370	19981120	00370	EU  	1998	11	20	HEEA0016680      	1	19981105	G	2810	20C00212	FILLER VALVE    			BOLKMS	117   	BK117B1     	5626012	EU  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	134AE					7237				FILLER VALVE HAS SEAL TORN, LEAKS.						1	G	7	2 	3U				H13EU
1998112000371	19981120	00371	EU  	1998	11	20	HEEA0016681      	1	19981105	G	2150	20475591	ECU TURBINE     			BOLKMS	105   	BO105S      	5626006	EU  										ECU	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				ECU TURBINE HAS ROUGH BEARING.						1	G	7	2 	3U				H3EU
1998112000372	19981120	00372	EU  	1998	11	20	HEEA0016682      	1	19981105	G	7923	209072433101	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										OIL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR					S719				VALVE INTERMITTENTLY WILL NOT CLOSE.						1	G	7	2 	3U				H3EU
1998112000373	19981120	00373	EU  	1998	11	20	HEEA0016683      	1	19981105	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	967MB					S737				RPM LIGHT AND HORN COMES ON INTERMITTENTLY.						1	G	7	2 	3U				H3EU
1998112000374	19981120	00374	EU  	1998	11	20	HEEA0016684      	1	19981105	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RPM AND AUDIO DOES NOT COME ON WHEN 12 PERCENT N1 SPLIT.						1	G	7	2 	3U				H3EU
1998112000375	19981120	00375	EU  	1998	11	20	HEEA0016685      	1	19981105	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	9190Y					S669				RPM WARNING LIGHT COMES ON IN FLIGHT CRUISE WITH NO AUDIO.						1	G	7	2 	3U				H3EU
1998112000376	19981120	00376	EU  	1998	11	20	HEEA0016686      	1	19981105	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721MB					S752				RPM WARNING, INTERMITTENT LIGHT.						1	G	7	2 	3U				H3EU
1998112000377	19981120	00377	EU  	1998	11	20	HEEA0016687      	1	19981105	G	6240	KDW021	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3071K					S859				RPM WARNING, INTERMITTENT LIGHT.						1	G	7	2 	3U				H3EU
1998112000378	19981120	00378	EU  	1998	11	20	HEEA0016688      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RPM WARNING, INTERMITTENT AUDIO AND LIGHT.						1	G	7	2 	3U				H3EU
1998112000379	19981120	00379	EU  	1998	11	20	HEEA0016689      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	135AE					S838				RPM WARNING, INTERMITTENT DURING CRUISE FLIGHT.						1	G	7	2 	3U				H3EU
1998112000380	19981120	00380	EU  	1998	11	20	HEEA0016690      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RPM WARNING CAUSES AUDIO AND RPM LIGHT TO COME ON.						1	G	7	2 	3U				H3EU
1998112000381	19981120	00381	EU  	1998	11	20	HEEA0016691      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RPM WARNING, LIGHT COMING ON AT 100 PERCENT.						1	G	7	2 	3U				H3EU
1998112000382	19981120	00382	EU  	1998	11	20	HEEA0016692      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4302G					S853				RPM WARNING LIGHT AND AUDIO COMES ON AT 100 PERCENT N2.						1	G	7	2 	3U				H3EU
1998112000383	19981120	00383	EU  	1998	11	20	HEEA0016693      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RPM WARNING, AUDIO LIGHT CAME ON IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998112000384	19981120	00384	EU  	1998	11	20	HEEA0016694      	1	19981105	G	6240	KDW021A	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										ROTOR RPM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				RPM WARNING LIGHT COMING ON IN-FLIGHT.						1	G	7	2 	3U				H3EU
1998112000385	19981120	00385	EU  	1998	11	20	HEEA0016695      	1	19981106	G	6240	2202A1002	WARNING BOX     			BOLKMS	105   	BO105S      	5626006	EU  										RPM WARNING	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB	1    				S756				RPM WARNING CAUSES TRIM CIRCUIT BREAKER TO TRIP.						1	G	7	2 	3U				H3EU
1998112000386	19981120	00386	EU  	1998	11	20	HEEA0016696      	1	19981106	G	2435	23032022	STARTER         			BOLKMS	117   	BK117A3     	5626015	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH	10546				7050				STARTER WOULD NOT MOTOR ENGINE.						1	G	7	2 	3U				H13EU
1998112000387	19981120	00387	EU  	1998	11	20	HEEA0016697      	1	19981106	G	2435	23032048	STARTER         			BOLKMS	105   	BO105S      	5626006	EU  										START/GEN	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	131AE					S787				STARTER/GENERATOR DOES NOT START.						1	G	7	2 	3U				H3EU
1998112000388	19981120	00388		1998	11	20	HEEA0016698      	4	19981106	G	3422	2594484	TRANSMITTER     			BOLKMS	117   	BK117B1     	5626012	EU  										FLUX VALVE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL					7198				TRANSMITER WILL NOT SLAVE.						1	G	7	2 	3U				H13EU
1998112000389	19981120	00389	EU  	1998	11	20	HEEA0016699      	1	19981106	G	2400	30248001	BATTERY         			BOLKMS	105   	BO105S      	5626006	EU  										BATTERY BOX	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03	7170D					S840				INSTALLED BATTERY IN AIRCRAFT.  WHEN BATTERY SWITCH TURNED ON BOTH BATTERY HOT LIGHTS CAME ON.  REPLACED WITH SERVICEABL	E BATTERY.					1	G	7	2 	3U				H3EU
1998112000390	19981120	00390	EU  	1998	11	20	HEEA0016700      	1	19981106	G	7921	37010200004	OIL COOLER      			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE OIL	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	624MB					S751				OIL COOLER LEAKING FROM CENTER OF COOLER ASSY.						1	G	7	2 	3U				H3EU
1998112000391	19981120	00391		1998	11	20	HEEA0016701      	4	19981106	G	2312	4000103000	TRANSCEIVER     			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	WEAK            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				TRANSCEIVER TRANSMITS VERY WEAK OR NOT AT ALL.						1	G	7	2 	3U				H13EU
1998112000392	19981120	00392		1998	11	20	HEEA0016702      	4	19981106	G	2312	40001278500	TRANSCEIVER     			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	217UC					7152				TRANSCEIVER BREAKING IN TRANSMISSION.						1	G	7	2 	3U				H13EU
1998112000393	19981120	00393	EU  	1998	11	20	HEEA0016703      	1	19981106	G	2913	4002001	PUMP            			BOLKMS	117   	BK117B2     	5626013	EU  										HYDRAULIC SYS	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	134AE					7237				HYDRAULIC PUMP CASE DRAIN LEAKING.						1	G	7	2 	3U			NC	H13EU
1998112000394	19981120	00394	EU  	1998	11	20	HEEA0016704      	1	19981106	G	7714	4011001	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	FLUCTUATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B					S673				OIL INDICATION FLUCTUATES, NR 1 NEEDLE STICKS AT ZERO.						1	G	7	2 	3U				H3EU
1998112000395	19981120	00395	EU  	1998	11	20	HEEA0016705      	1	19981106	G	7714	4011001	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	624MB					S751				OIL INDICATION'S NR 2 NEEDLE INTERMITTENTLY STICKS ON ZERO.						1	G	7	2 	3U				H3EU
1998112000396	19981120	00396	EU  	1998	11	20	HEEA0016706      	1	19981106	G	7714	4011001	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	FLUCTUATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81832					S828				NR 2 ENGINE OIL PRESSURE FLUCTUATES.						1	G	7	2 	3U				H3EU
1998112000397	19981120	00397	EU  	1998	11	20	HEEA0016707      	1	19981106	G	7714	4011001	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50293					S677				TRANSMISSION PRESSURE INDICATOR STICKING.						1	G	7	2 	3U				H3EU
1998112000398	19981120	00398		1998	11	20	HEEA0016708      	4	19981106	G	3100	4021001	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										DUAL FUEL PRESS	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911PF					S718				FUEL PRESSURE INDICATION NEEDLE STICKS.						1	G	7	2 	3U				H3EU
1998112000399	19981120	00399	EU  	1998	11	20	HEEA0016709      	1	19981106	G	2840	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESSURE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				INDICATOR DROPS TO ZERO AFTER TRANSMITTER WARMS UP.						1	G	7	2 	3U				H3EU
1998112000400	19981120	00400		1998	11	20	HEEA0016710      	4	19981106	G	3421	40205773	GYRO            			BOLKMS	117   	BK117B1     	5626012	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911TL					7198				DIRECTIONAL GYRO NOT SLAVING, HEADING SYNCHRO OUTPUT PRECESSES.						1	G	7	2 	3U				H13EU
1998112000401	19981120	00401		1998	11	20	HEEA0016711      	4	19981106	G	3421	40205773	GYRO            			BOLKMS	117   	BK117B2     	5626013	EU  										COCKPIT	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE					7238				DIRECTIONAL GYRO'S HEADING SYNCHRO OUTPUTS ERRATIC.  TIME SINCE REPAIR 227:35 HOURS.						1	G	7	2 	3U			NC	H13EU
1998112000402	19981120	00402		1998	11	20	HEEA0016712      	4	19981106	G	3421	4021541671	GYRO            			BOLKMS	117   	BK117B2     	5626013	EU  										ARTIFICIAL HORIZ	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	136AE					7234				GYRO TUMBLED ONE TIME AND RECOVERED ON SPOOL DOWN-CSAS PITCH AND ROLL KICKING AND GOING OFF LINE INTERMITTENTLY.						1	G	7	2 	3U			NC	H13EU
1998112000403	19981120	00403	NE  	1998	11	20	HEEA0016713      	2	19981106	G	7310	430128601	MANIFOLD        			BOLKMS	117   	BK117B2     	5626013	EU  	LYC   	LTS101	LTS101750B1 	41560	NE  					ENGINE FUEL	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911LK	3556 				7168				AFTER FLIGHT, FOUND FUEL MANIFOLD LEAKING ON PINHOLE OR CRACK IN ONE TUBE AT 4:30 POSITION.						1	G	7	2 	3U	3	U	NC	H13EU   	E5NE10
1998112000404	19981120	00404	EU  	1998	11	20	HEEA0016714      	1	19981106	G	6320	4638305028	BEARING         		4638001001  	BOLKMS	105   	BO105S      	5626006	EU  										TRANSMISSION	SPALLED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H				618	S833				MAKING METAL. FOUND MAST BEARING SPALDING AND WAS CAUSE OF METAL.  REPAIRED TRANSMISSION AND INSTALLED NEW MAST BEARING.						1	G	7	2 	3U				H3EU
1998112000405	19981120	00405	EU  	1998	11	20	HEEA0016715      	1	19981106	G	6320	4619304033	RING GEAR       		4638001004  	BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM				155	S683				MAKING METAL.  FOUND RING GEAR CRACKED AT ALIGNMENT BOLT HOLE FORWARD POSITION.  ALSO FOUND COLLECTOR WHEEL, SUNGEAR , 2	 EACH INTERMEDIATE SHAFT, 5 EACH PLANETARY GEARS SPALLING.   REPAIRED TRANSMISSION AND INSTALLED SERVICEABLE PARTS.					1	G	7	2 	3U				H3EU
1998112000406	19981120	00406	EU  	1998	11	20	HEEA0016716      	1	19981106	G	6320	4638001004	TRANSMISSION    			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911PF	7214 				S718				MAKING METAL.  INSPECT AND REPAIR DUE TO METAL IN OIL AND EXCESSIVE CORROSION ON TOP OF MAST.  ALSO SENDING ROTOR BRAKE 	AND DISK, MAST DRIVE ADAPTER ASSY, (2) PITCH LINKS, (2) CONTROL LEVERS, (1) CONTROL FORK ASSY AND (1) BEARING BLOCK, (1)	 HINGED SUPPORT.				1	G	7	2 	3U				H3EU
1998112000407	19981120	00407	EU  	1998	11	20	HEEA0016717      	1	19981106	G	6320	4638001004	TRANSMISSION    			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	MAKING METAL    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	81992	4769 				S827				TRANSMISSION MAKING METAL.						1	G	7	2 	3U				H3EU
1998112000408	19981120	00408	EU  	1998	11	20	HEEA0016718      	1	19981106	G	6400	4638201003	CENTER CASE     			BOLKMS	105   	BO105S      	5626006	EU  										M/R TRANSMISSION	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM					S683				TAIL ROTOR BORE WORN, ACCY BORE WORN, NOZZLE RING BORE WORN.						1	G	7	2 	3U				H3EU
1998112000409	19981120	00409	EU  	1998	11	20	HEEA0016719      	1	19981106	G	6320	4638201004	LOWER HOUSING   			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM					S683				INTERNAL SHAFT SEAT WORN.						1	G	7	2 	3U				H3EU
1998112000410	19981120	00410	EU  	1998	11	20	HEEA0016720      	1	19981106	G	6320	4638201005	UPPER HOUSING   			BOLKMS	105   	BO105S      	5626006	EU  										M/R GEARBOX	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7136H					S833				TOP CASE LINER LOOSE AND DAMAGED						1	G	7	2 	3U				H3EU
1998112000411	19981120	00411	EU  	1998	11	20	HEEA0016721      	1	19981106	G	6320	4639311008	BEARING BUSHING 			BOLKMS	117   	BK117A4     	5626017	EU  										MAIN ROTOR	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										BUSHING P/N 4639-310-007 WAS SENT PACKAGED IN A BOX TAGGED P/N 4639-311-008.						1	G	7	2 	3U				H13EU
1998112000412	19981120	00412	EU  	1998	11	20	HEEA0016722      	1	19981106	G	7722	50061036	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				INSTRUMENT INDICATION DROPS OFF TO ZERO.						1	G	7	2 	3U				H3EU
1998112000413	19981120	00413		1998	11	20	HEEA0016723      	4	19981106	G	3416	5035P2P44	ENCODER         			BOLKMS	105   	BO105S      	5626006	EU  										ALTIMETER	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911FL					S717				ENCODER READS HIGH.						1	G	7	2 	3U				H3EU
1998112000414	19981120	00414		1998	11	20	HEEA0016724      	4	19981106	G	3416	5035P2P44	ENCODER         			BOLKMS	117   	BK117A3     	5626015	EU  										ALTIMETER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				ENCODER SKIPPING ELEVATORS IN REPORTING MODE.						1	G	7	2 	3U				H13EU
1998112000415	19981120	00415		1998	11	20	HEEA0016725      	4	19981106	G	3421	5040017901	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	133AE					S800				LIGHT INOPERATIVE.  UNIT WAS TAGGED 412 USE ONLY, CAUTION 5V LIGHTS AND WERE INSTALLED IN A BO105 WHICH IS A 8V LIGHTS, 	NOW LIGHTS ARE INOPERATIVE - REPLACED 2 EACH 5-VOLT LAMPS P/N 7152, RECALIBRATED, BENCH CHECK GOOD (10-27-98)					1	G	7	2 	3U				H3EU
1998112000416	19981120	00416	EU  	1998	11	20	HEEA0016726      	1	19981106	G	2424	51565000R	REGULATOR       			BOLKMS	105   	BO105S      	5626006	EU  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J					S826				NR 1 GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H3EU
1998112000417	19981120	00417	EU  	1998	11	20	HEEA0016727      	1	19981106	G	2424	51565000R	REGULATOR       			BOLKMS	105   	BO105S      	5626006	EU  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	624MB					S751				GENERATOR WILL NOT COME ON-LINE.						1	G	7	2 	3U				H3EU
1998112000418	19981120	00418	EU  	1998	11	20	HEEA0016728      	1	19981106	G	2424	51565000R	REGULATOR       			BOLKMS	105   	BO105S      	5626006	EU  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3071K					S859				GENERATOR DROPS OFF-LINE.						1	G	7	2 	3U				H3EU
1998112000419	19981120	00419		1998	11	20	HEEA0016729      	4	19981106	G	3416	61031016	ALTIMETER       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	50293					S677				ALTIMETER FAILED FRICTION ERROR TEST.						1	G	7	2 	3U				H3EU
1998112000420	19981120	00420		1998	11	20	HEEA0016730      	4	19981106	G	2312	6222093001	POWER SUPPLY    			BOLKMS	105   	BO105S      	5626006	EU  										COMM EQUIPMENT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3520T					S539				NO TRANSMIT LIGHT ON ROL VHF WHEN KEYED.						1	G	7	2 	3U				H3EU
1998112000421	19981120	00421	EU  	1998	11	20	HEEA0016731      	1	19981106	G	2110	62561411	ECU CONTROLLER  			BOLKMS	117   	BK117B1     	5626012	EU  										E/E BAY	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	217UC					7152				ECU CONTROLLER SENSOR, INTERMITTENTLY, OHMS BAD.						1	G	7	2 	3U				H13EU
1998112000422	19981120	00422	EU  	1998	11	20	HEEA0016732      	1	19981106	G	6720	741C000005	ACTUATOR        			BOLKMS	117   	BK117B1     	5626012	EU  										TAIL ROTOR	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	911TL					7198				T/R ACTUATOR - LEAKING OUT SEALS.						1	G	7	2 	3U				H13EU
1998112000423	19981120	00423	EU  	1998	11	20	HEEA0016733      	1	19981106	G	7600	97914211	VALVE           			BOLKMS	105   	BO105S      	5626006	EU  										BLEED AIR SOV	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR					S719				VALVE INTERMITTENTLY STICKS.						1	G	7	2 	3U				H3EU
1998112000424	19981120	00424		1998	11	20	HEEA0016734      	4	19981106	G	2340	ACS1278	AUDIO CONTROL   			BOLKMS	117   	BK117A4     	5626017	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				AUDIO CONTROL PANEL WILL NOT TRANSMIT ON EITHER VHF RADIO.  RECEPTION WAS GOOD.						1	G	7	2 	3U				H13EU
1998112000425	19981120	00425		1998	11	20	HEEA0016735      	4	19981106	G	2340	AA95758	AUDIO CONTROL   			BOLKMS	117   	BK117A3     	5626015	EU  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH	15   				7050				NO SIDETONE WHEN TRANSMITTING ON VHF OR FM.						1	G	7	2 	3U				H13EU
1998112000426	19981120	00426	EU  	1998	11	20	HEEA0016736      	1	19981106	G	6340	DL40438	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	FLUCTUATED      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J					S826				RPM ROTOR NEEDLE FLUCTUATES, COULD NOT VERIFY COMPLAINT, HOWEVER, NR 1 AND NR 2 NEEDLES HAVE ABOUT 2 PERCENT SPLIT IN MO	VEMENT.					1	G	7	2 	3U				H3EU
1998112000427	19981120	00427	EU  	1998	11	20	HEEA0016737      	1	19981106	G	2800	BSE20660G1	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	OUT OF TOLERANCE	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	7170D					S840				FUEL PRESSURE TRANSMITTER LOW OUT OF TOLERANCE						1	G	7	2 	3U				H3EU
1998112000428	19981120	00428	EU  	1998	11	20	HEEA0016738      	1	19981106	G	2844	BSE206150G3	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4573B					S673				TRANSDUCER - OUTPUT DOES NOT CHANGE WITH PRESSURE APPLIED.						1	G	7	2 	3U				H3EU
1998112000429	19981120	00429	EU  	1998	11	20	HEEA0016739      	1	19981106	G	2844	BSE206150G3	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR					S719				TRANSDUCER FLUCTUATES AND FAILS TO ZERO INTERMITTENTLY.						1	G	7	2 	3U				H3EU
1998112000430	19981120	00430	EU  	1998	11	20	HEEA0016740      	1	19981106	G	2844	BSE206150G3	TRANSDUCER      			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	135AE					S838				TRANSDUCER - FLUCTUATING READINGS.						1	G	7	2 	3U				H3EU
1998112000431	19981120	00431	EU  	1998	11	20	HEEA0016741      	1	19981106	G	3212	D24873101	COVER           			BOLKMS	105   	BO105S      	5626006	EU  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8197X					S808				TORN FLOAT BAG COVER.						1	G	7	2 	3U				H3EU
1998112000432	19981120	00432	EU  	1998	11	20	HEEA0016742      	1	19981106	G	2800	DK042	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL PRESSURE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PRESSURE TRANSMITTER - EXCESSIVE FRICTION ERROR.						1	G	7	2 	3U				H3EU
1998112000433	19981120	00433	EU  	1998	11	20	HEEA0016743      	1	19981106	G	6240	DL40440	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	133AE					S800				TRIPLE RPM INDICATION - NR 2 NEEDLE FLUCTUATING AND READS LOW.						1	G	7	2 	3U				H3EU
1998112000434	19981120	00434	EU  	1998	11	20	HEEA0016744      	1	19981106	G	7714	DL41240	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	133AE					S800				RPM INDICATION, SLOW REACTION ON START.						1	G	7	2 	3U				H3EU
1998112000435	19981120	00435	EU  	1998	11	20	HEEA0016745      	1	19981106	G	6240	DL43638	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8199J					S826				TRIPLE RPM INDICATION, NEEDLES INOPERATIVE.						1	G	7	2 	3U				H3EU
1998112000436	19981120	00436	EU  	1998	11	20	HEEA0016746      	1	19981106	G	6240	DL43638	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TRIPLE TACH	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	137AE					S851				TRIPLE RPM INDICATION - ALL THREE NEEDLES INOPERATIVE.						1	G	7	2 	3U				H3EU
1998112000437	19981120	00437		1998	11	20	HEEA0016747      	4	19981106	G	2562	ELT910	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										ELT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	724MB					S756				ELT SELF-ACTIVATES INTERMITTENTLY.						1	G	7	2 	3U				H3EU
1998112000438	19981120	00438		1998	11	20	HEEA0016748      	4	19981106	G	2562	ELT910	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										ELT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6607K					S841				ELT TRANSMITS WHILE IN ARM POSITION.						1	G	7	2 	3U				H3EU
1998112000439	19981120	00439	EU  	1998	11	20	HEEA0016749      	1	19981106	G	2810	FTA017521E	FUEL CELL       			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	50293					S677				FUEL CELL LEAKING.						1	G	7	2 	3U				H3EU
1998112000440	19981120	00440		1998	11	20	HEEA0016750      	4	19981106	G	3100	G555674	TRANSDUCER      			BOLKMS	117   	BK117B2     	5626013	EU  										ENGINE TORQUE	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	132AE					7238				PRESSURE TRANDUCER - ERRATIC INDICATIONS.						1	G	7	2 	3U			NC	H13EU
1998112000441	19981120	00441	EU  	1998	11	20	HEEA0016751      	1	19981106	G	6300	SKCP24563	DRIVESHAFT      			BOLKMS	105   	BO105S      	5626006	EU  										MAIN ROTOR	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	205UC	2275 				S668				DRIVESHAFT'S INNER SURFACE CORRODED.						1	G	7	2 	3U				H3EU
1998112000442	19981120	00442	EU  	1998	11	20	HEEA0016752      	1	19981106	G	2422	SPS1607A	STATIC INVERTER 			BOLKMS	105   	BO105S      	5626006	EU  										AC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911DD					S830				STATIC INVERTER TRIPS CIRCUIT BREAKER.						1	G	7	2 	3U				H3EU
1998112000443	19981120	00443	EU  	1998	11	20	HEEA0016753      	1	19981106	G	2422	SS120	STATIC INVERTER 			BOLKMS	117   	BK117A3     	5626015	EU  										AC SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	401PH					7050				STATIC INVERTER INOPERATIVE, NO POWER.						1	G	7	2 	3U				H13EU
1998112000444	19981120	00444	EU  	1998	11	20	HEEA0016754      	1	19981106	G	7933	TM41039	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										ENGINE OIL TEMP	STICKING        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911BR					S719				NR 1 ENGINE SIDE TEMPERATURE INDICATOR STICKS, REFLECTIVE PAINT FLAKING.						1	G	7	2 	3U				H3EU
1998112000445	19981120	00445	EU  	1998	11	20	HEEA0016755      	1	19981106	G	7722	TM42739	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	86CH					S557				EXHAUST TEMPERATURE INDICATION READS 15 HIGH.						1	G	7	2 	3U				H3EU
1998112000446	19981120	00446	EU  	1998	11	20	HEEA0016756      	1	19981106	G	7722	TM42739	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	READS LOW       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5031U					S678				EXHAUST TEMPERATURE INDICATOR CANNOT CALIBRATE.  READS LOW.						1	G	7	2 	3U				H3EU
1998112000447	19981120	00447	EU  	1998	11	20	HEEA0016757      	1	19981106	G	7722	TM42739	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										TOT	READS HIGH      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911HM					S683				EXHAUST TEMPERATURE INDICATION, 20 HIGH THROUGHOUT SCALE.						1	G	7	2 	3U				H3EU
1998112000448	19981120	00448	EU  	1998	11	20	HEEA0016758      	1	19981106	G	2841	VT42641	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										FUEL LEVEL	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5421E					S806				FUEL LEVEL GAUGE SUPPLY INDICATOR ERRATIC.						1	G	7	2 	3U				H3EU
1998112000449	19981120	00449	EU  	1998	11	20	HEEA0016759      	1	19981106	G	2841	VT42641	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										FUEL LEVEL	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	9190Y					S669				FUEL LEVEL GAUGE SUPPLY SIDE INDICATION OFF.						1	G	7	2 	3U				H3EU
1998112000450	19981120	00450	EU  	1998	11	20	HEEA0016760      	1	19981106	G	2841	VT42641	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										FUEL LEVEL	ERRATIC         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911EB					S812				FUEL LEVEL GAUGE, ERRATIC INDICATION READINGS.						1	G	7	2 	3U				H3EU
1998112000451	19981120	00451	EU  	1998	11	20	HEEA0016761      	1	19981106	G	2841	VT42641	INDICATOR       			BOLKMS	105   	BO105S      	5626006	EU  										FUEL LEVEL	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5029H					S670				GAUGE INOPERATIVE, WILL NOT INDICATE FUEL LEVEL.						1	G	7	2 	3U				H3EU
1998112000452	19981120	00452	EU  	1998	11	20	HEEA0016762      	1	19981106	G	2841	VT42641	INDICATOR       			BOLKMS	117   	BK117A4     	5626017	EU  										FUEL LEVEL	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	911RZ					7092				FUEL LEVEL GAUGE INTERMITTENT OPERATION ON BOTH SIDES.  FRICTION ERROR BOTH NEEDLES.						1	G	7	2 	3U				H13EU
1998112001134	19981120	01134	EU  	1998	11	20	HEEA0016763      	1	19981109	G	3213	350A08220721	SHOE            			SNIAS 	350   	AS350B2     	8680813	EU  										SKID	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				HOLES WORN THROUGH SHOE.  SCRAPPED.						1	G	7	1 	3U				H9EU
1998112001135	19981120	01135	EU  	1998	11	20	HEEA0016765      	1	19981109	G	2822	1C454	PUMP            			SNIAS 	350   	AS350B2     	8680813	EU  										ENGINE	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	40466	1238 				3004				FUEL PUMP DOESN'T OPERATE - TRIPS FUSE.						1	G	7	1 	3U				H9EU
1998112001111	19981120	01111	SW  	1998	11	20	HEEA0016771      	1	19981109	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH	578  				53199				OIL COOLER BLOWER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1998112001112	19981120	01112	SW  	1998	11	20	HEEA0016772      	1	19981109	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				OIL COOLER BLOWER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1998112001113	19981120	01113	SW  	1998	11	20	HEEA0016773      	1	19981109	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				OIL COOLER BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW
1998112001114	19981120	01114	SW  	1998	11	20	HEEA0016774      	1	19981109	G	6322	206061432121	HOUSING         			BELL  	407   	407         		SW  										COOLER BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				BLOWER HOUSING CRACKED IN TWO PLACES.						1	G	7	1 	3U			O	H2SW
1998112001115	19981120	01115	SW  	1998	11	20	HEEA0016775      	1	19981109	G	6510	406040340101	DISK PACK       			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				CRACKED DISK, NR 7 THOMAS COUPLING.						1	G	7	1 	3U			O	H2SW
1998112001116	19981120	01116	SW  	1998	11	20	HEEA0016776      	1	19981109	G	3300	407362005103	SWITCH          			BELL  	407   	407         		SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	719PH					53266				FUEL LOW LEVEL LIGHT WAS ON WHEN BATTERY TURNED ON FOR PRE-FLIGHT.  AIRCRAFT HAD 245 POUNDS OF FUEL.						1	G	7	1 	3U			O	H2SW
1998112001117	19981120	01117	SW  	1998	11	20	HEEA0016777      	1	19981109	G	3212	407350301101	FLOATBAG        			BELL  	407   	407         		SW  										FLOAT SYS	MISMARKED       	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										FLOATBAG PART RECEIVED AS A 407-350-301-101, S/N 0045; BUT IN REALITY ,THE PART NUMBER ON THE BAG WAS 407-350-300-101.						1	G	7	1 	3U			O	H2SW
1998112001118	19981120	01118	SW  	1998	11	20	HEEA0016778      	1	19981109	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										STARTER	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1041 				53114				BRUSHES WERE EXCESSIVELY WORN AND BURNT ON EDGES.						1	G	7	1 	3U			O	H2SW
1998112001119	19981120	01119	SW  	1998	11	20	HEEA0016779      	1	19981111	G	3212	206050247131	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				CAP TORN OFF, END CAP WORN.						1	G	7	1 	3U			O	H2SW
1998112001120	19981120	01120	SW  	1998	11	20	HEEA0016780      	1	19981111	G	6320	406340100101	PUMP            			BELL  	407   	407         		SW  										TRANMISSION OIL	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	437PH					53072				TRANSMISSION OIL PUMP LEAKING.						1	G	7	1 	3U			O	H2SW
1998112001121	19981120	01121	SW  	1998	11	20	HEEA0016783      	1	19981111	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	406PH					53198				LINK BEARINGS WORN BEYOND LIMITS.  SERIAL NUMBERS REMOVED ARE NHFS-3122 AND NHFS-3123.						1	G	7	1 	3U			O	H2SW
1998112001122	19981120	01122	SW  	1998	11	20	HEEA0016784      	1	19981111	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				CORROSION AND FACE STAINED ON PRESSURE GAUGE.						1	G	7	1 	3U			O	H2SW
1998112001123	19981120	01123	SW  	1998	11	20	HEEA0016785      	1	19981111	G	6320	206040530001	MAIN CASE       			BELL  	206   	206L3       	1182108	SW  										M/R GEARBOX	MISMANUFACTURED 	E			HEEA	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	03										RECEIVED CASE FROM BELL, NO PLUG INSTALLED.						1	G	7	1 	3U				H2SW
1998112001124	19981120	01124	SW  	1998	11	20	HEEA0016786      	1	19981111	G	6321	406010429101	PIN             			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MAIN ROTOR PIN WORN.						1	G	7	1 	3U			O	H2SW
1998112001125	19981120	01125	SW  	1998	11	20	HEEA0016787      	1	19981111	G	6321	406010429101	PIN             			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH					53003				MAIN ROTOR PIN WORN.						1	G	7	1 	3U			O	H2SW
1998112001126	19981120	01126	SW  	1998	11	20	HEEA0016788      	1	19981111	G	6410	214015700115	CAP             			BELL  	214   	214ST       	1182106	SW  										T/R BLADE	SEPARATED       	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y	339  				28139				TIP CAP SEPARATED.						2	G	7	2 	4U				H10SW
1998112001110	19981120	01110	NE  	1998	11	20	HEEA0016789      	1	19981112	G	2430	A1077D	RELAY           			SKRSKY	S76   	S76A        	8143006	NE  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2743E					760155				RELAY INSTALLED ON AIRCRAFT.  FOUND TERMINALS 12 AND 13 AND TERMINALS 22 AND 23 HAD NO CONTINUITY IN REST POSITION.  WHE	N POWER IS APPLIED TO X1 AND X2, THEY HAVE CONTINUITY.  FUNCTIONAL CHECKED RELAY AS RECEIVED.  CONFIRMED PROBLEM.  RELAY	 WAS INADVERTENTLY WIRED IN REVERSE.  HOWEVER, RELAY WAS SCRAPPED DUE TO TWO MOUNTING FLANGES WERE CUT OFF TO FACILITATE	 EASE OF INSTALLATION.			1	G	7	2 	3U				H1NE
1998112001127	19981120	01127	SW  	1998	11	20	HEEA0016790      	1	19981112	G	3212	407350301101	FLOATBAG        			BELL  	407   	407         		SW  										FLOAT SYS	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	437PH					53072				LEFT FLOATBAG LEAKING.   DATE OF MFG 6-25-96.						1	G	7	1 	3U			O	H2SW
1998112001129	19981120	01129	SW  	1998	11	20	HEEA0016792      	1	19981112	G	6330	406010425107	LEVER ASSEMBLY  			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	570  				53003				LEVER ASSEMBLY BUSHINGS WORN.  SERIAL NUMBERS REMOVED ARE A1742 AND A1695.  REPLACEMENT PART SERIAL NUMBERS ARE A2487 AN	D A2485.					1	G	7	1 	3U			O	H2SW
1998112001130	19981120	01130	SW  	1998	11	20	HEEA0016793      	1	19981112	G	6230	406010428109	BUSHING         			BELL  	407   	407         		SW  										M/R HUB	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	570  				53003				MAIN ROTOR HUB BUSHING WORN.						1	G	7	1 	3U			O	H2SW
1998112001131	19981120	01131	SW  	1998	11	20	HEEA0016794      	1	19981112	G	6230	406010426101	LINK ASSEMBLY   			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	2478 				53003				LINK ASSEMBLY BUSHING WORN.  SERIAL NUMBERS REMOVED ARE AFS 1491 AND AFS 1467.  REPLACEMENT SERIAL NUMBERS ARE AFS 2073 	AND AFS 2068.					1	G	7	1 	3U			O	H2SW
1998112001132	19981120	01132	SW  	1998	11	20	HEEA0016795      	1	19981112	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH	124  				53283				EXCESSIVE PLAY IN ONE POSITION ONLY.						1	G	7	1 	3U			O	H2SW
1998112001133	19981120	01133	SW  	1998	11	20	HEEA0016796      	1	19981112	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	723PH	124  				53283				EXCESSIVE PLAY IN ONE POSITION ONLY.						1	G	7	1 	3U			O	H2SW
1998121100280	19981211	00280	SW  	1998	12	11	HEEA0016825      	1	19981124	G	5312	206033401113S	BULKHEAD        		206033004045	BELL  	206   	206L1       	1182107	SW  										FUSELAGE	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	2761N				AOKP01014	45277				BULKHEAD MISMANUFACTURED.  NUMEROUS GROOVES AROUND PERIMETER OF PART, ON AFT FACE AND FLANGE.  REMOVED THE PRIMER TO MAK	E SURE IT WAS NOT A PROBLEM WITH JUST THE PRIMER COAT.					1	G	7	1 	3U				H2SW
1998121100281	19981211	00281	SW  	1998	12	11	HEEA0016826      	1	19981124	G	5320	206033412001A	BRACKET         		206033004045	BELL  	206   	206L1       	1182107	SW  										TAIL BOOM	MISMANUFACTURED 	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03					A0001038					MISMANUFACTURED.  NEW SUPPORT BRACKET DOES NOT FIT CONTOUR OF TAILBOOM SKIN.  IT HAS A TWIST TO IT, THAT CAUSES IT TO RO	CK WHEN PLACED ON THE TAILBOOM UPPER SKIN SURFACE WHERE IT IS TO BE INSTALLED.  WITH BRACKET PLACED ON A FLAT SURFACE, T	HERE IS APPROXIMATELY A .0312 INCH GAP UNDER THE RIGHT FORWARD CORNER.				1	G	7	1 	3U				H2SW
1998121100314	19981211	00314	EU  	1998	12	11	HEEA0016827      	1	19981124	G	7931	1130021089	SWITCH          			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				PRESSURE SWITCH INTERMITTENT.						1	G	7	1 	3U				H9EU
1998121100315	19981211	00315	EU  	1998	12	11	HEEA0016828      	1	19981124	G	6210	355A11002011	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	2343 				2653				CRACK ON THE LOWER SIDE OF BLADE.						1	G	7	1 	3U				H9EU
1998121100316	19981211	00316	EU  	1998	12	11	HEEA0016829      	1	19981124	G	6210	355A11002011	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	3225 				2653				CRACK ON THE LOWER SIDE OF BLADE.						1	G	7	1 	3U				H9EU
1998121100317	19981211	00317	EU  	1998	12	11	HEEA0016830      	1	19981124	G	6210	355A11002011	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	2433 				2653				CRACK ON THE LOWER SIDE OF BLADE.						1	G	7	1 	3U				H9EU
1998121100318	19981211	00318	EU  	1998	12	11	HEEA0016831      	1	19981124	G	7160	350A54024200	ELBOW           			SNIAS 	350   	AS350B2     	8680813	EU  										INTAKE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	4036H					2919				UNION WORN.						1	G	7	1 	3U				H9EU
1998121100319	19981211	00319	EU  	1998	12	11	HEEA0016832      	1	19981124	G	2821	432B124	FILTER          			SNIAS 	350   	AS350B2     	8680813	EU  										FUEL SYSTEM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ					2653				BOWL NUT WORN AND CORRODED IN FUEL SYSTEM.						1	G	7	1 	3U				H9EU
1998121100320	19981211	00320	EU  	1998	12	11	HEEA0016833      	1	19981124	G	2435	150SG122Q	GENERATOR       			SNIAS 	350   	AS350B2     	8680813	EU  										START/GENERATOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951					2771				STARTER/GENERATOR HAS FLAT SPOT AND WILL NOT ENERGIZE.						1	G	7	1 	3U				H9EU
1998121100282	19981211	00282	SW  	1998	12	11	HEEA0016834      	1	19981124	G	6720	406312103101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				WORN BEARINGS AND LINK.  SERIAL NUMBERS REMOVED ARE NHFS-2820 AND NHFS-2163.						1	G	7	1 	3U			O	H2SW
1998121100283	19981211	00283	SW  	1998	12	11	HEEA0016835      	1	19981124	G	6720	406012129101	LINK            			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	467PH					53142				T/R PITCH CHANGE CONTROL ROD HAS WORN BEARINGS AND IS BINDING.						1	G	7	1 	3U			O	H2SW
1998121100284	19981211	00284		1998	12	11	HEEA0016836      	4	19981124	G	3416	5934D3	ALTIMETER       			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	467PH	1131 				53142				INDICATION SHOWS 100 FOOT DIFFERENCE BETWEEN ALTIMETER SETTING AND FIELD ELEVATION.						1	G	7	1 	3U			O	H2SW
1998121100285	19981211	00285	SW  	1998	12	11	HEEA0016837      	1	19981124	G	3212	212073905001	GAUGE           			BELL  	407   	407         		SW  										FLOAT	CONTAMINATED    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				GAUGE IS STICKING AND HAS A BUILD UP OF UNKNOWN SUBSTANCE INSIDE OF GAUGE.  SCRAPPED IN-HOUSE DUE TO NON-REPAIRABLE.						1	G	7	1 	3U			O	H2SW
1998121100286	19981211	00286	SW  	1998	12	11	HEEA0016838      	1	19981124	G	3212	407350301101	FLOATBAG        			BELL  	407   	407         		SW  										FLOAT SYSTEM	LEAKING         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				LEFT FLOAT LEAKING.						1	G	7	1 	3U			O	H2SW
1998121100287	19981211	00287	SW  	1998	12	11	HEEA0016839      	1	19981124	G	6220	407010150103	FRAHM ASSY      			BELL  	407   	407         		SW  										MAIN ROTOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				FOUND A BROKEN SPRING ON DAMPENER IN MAIN ROTOR.						1	G	7	1 	3U			O	H2SW
1998121100288	19981211	00288	SW  	1998	12	11	HEEA0016840      	1	19981124	G	7910	206061505115	TANK            			BELL  	407   	407         		SW  										ENGINE OIL	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				OIL TANK CRACKED AT TOP WHERE VENT CONNECTS.						1	G	7	1 	3U			O	H2SW
1998121100289	19981211	00289		1998	12	11	HEEA0016841      	4	19981124	G	3416	206070263101	ALTIMETER       			BELL  	407   	407         		SW  										COCKPIT	INACCURATE      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				ALTIMETER INDICATION READS 100 FEET OFF.						1	G	7	1 	3U			O	H2SW
1998121100290	19981211	00290	SW  	1998	12	11	HEEA0016843      	1	19981124	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										MAIN ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH	203  				53288				EXCESSIVE LATERAL PLAY IN BEARINGS IN MAIN ROTOR.						1	G	7	1 	3U			O	H2SW
1998121100291	19981211	00291	SW  	1998	12	11	HEEA0016844      	1	19981124	G	3212	206050247131	FLOAT COVER     			BELL  	407   	407         		SW  										FLOAT	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	457PH					53147				FORWARD CUP WORN.						1	G	7	1 	3U			O	H2SW
1998121100292	19981211	00292	SW  	1998	12	11	HEEA0016845      	1	19981124	G	6220	407001524105	PIVOT BEARING   			BELL  	407   	407         		SW  										M/R HEAD	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	2624 				53070				PIVOT BEARING FAILED.						1	G	7	1 	3U			O	H2SW
1998121100321	19981211	00321	EU  	1998	12	11	HEEA0016846      	1	19981124	G	2840	DK042	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										PRESSURE TRANSMITTER INOPERATIVE.						1	G	7	2 	3U				H3EU
1998121100322	19981211	00322	EU  	1998	12	11	HEEA0016847      	1	19981125	G	2840	DK042	TRANSMITTER     			BOLKMS	105   	BO105S      	5626006	EU  										FUEL SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721MB					S752				PRESSURE TRANSMITTER FLUCTUATES, UNIT FUNCTION CHECKED BAD, INTERMITTENTLY FLUCTUATES AT LOW PRESSURE.						1	G	7	2 	3U				H3EU
1998121100293	19981211	00293	SW  	1998	12	11	HEEA0016848      	1	19981125	G	6340	214074280107	DETECTOR        			BELL  	412   	412         	1182202	SW  										RPM LIMIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	142PH					33150				NR 1 ENGINE OUT REMAINS ILLUMINATED AND NR 1 PARTICLE SEPARATOR LIGHT REMAINS ILLUMINATED AT GROUND IDLE.						1	G	7	2 	4U				H4SW
1998121100294	19981211	00294	SW  	1998	12	11	HEEA0016849      	1	19981125	G	5210	214070541104	TRACK           			BELL  	214   	214ST       	1182106	SW  										DOOR	BROKEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										TRACK BROKEN.  WHEN PACKAGE WAS OPENED FOUND TRACK SPLIT.						2	G	7	2 	4U				H10SW
1998121100295	19981211	00295	SW  	1998	12	11	HEEA0016850      	1	19981201	G	6710	214001347005	ACTUATOR        			BELL  	412   	412         	1182202	SW  										ROTARY	STICKS          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	293CA					33005				ROTOR ACTUATOR STICKS INTERMITTENTLY.  DATE OF MFG 10-29-98.						1	G	7	2 	4U				H4SW
1998121100296	19981211	00296	SW  	1998	12	11	HEEA0016853      	1	19981202	G	3212	064105430	TRANSCEIVER     			BELL  	407   	407         		SW  										VHF COMM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	417PH					53038				TRANSCEIVER WILL NOT CHANGE FREQUENCY.						1	G	7	1 	3U			O	H2SW
1998121100297	19981211	00297		1998	12	11	HEEA0016854      	4	19981202	G	2312	064105430	TRANSCEIVER     			BELL  	407   	407         		SW  										VHF COMM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	612PH					53199				TRANSCEIVER DOES NOT TRANSMIT OR RECEIVE.   PERFORMED PRELIMINARY INSPECTION, FOUND C195 AND ASSOCIATED CIRCUITS SEVEREL	Y BURNT.					1	G	7	1 	3U			O	H2SW
1998121100298	19981211	00298		1998	12	11	HEEA0016855      	4	19981202	G	2312	066106103	TRANSCEIVER     			BELL  	407   	407         		SW  										COCKPIT	INTERMITTENT    	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				TRANSCEIVER UNIT IS INTERMITTENT.						1	G	7	1 	3U			O	H2SW
1998121100299	19981211	00299		1998	12	11	HEEA0016856      	4	19981202	G	3452	066106200	TRANSPONDER     			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	404PH					53188				TRANSPONDER  REPLY LIGHT BLINKS CONSTANTLY.						1	G	7	1 	3U			O	H2SW
1998121100300	19981211	00300		1998	12	11	HEEA0016857      	4	19981202	G	3444	071111401	ANTENNA         			BELL  	407   	407         		SW  										RADAR ALTIMETER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				RADAR ALTIMETER DISPLAY INACCURATE.						1	G	7	1 	3U			O	H2SW
1998121100301	19981211	00301		1998	12	11	HEEA0016858      	4	19981202	G	3444	071111401	ANTENNA         			BELL  	407   	407         		SW  										RADAR ALTIMETER	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				AVI ANTENNA INTERMITTENT IN-FLIGHT.						1	G	7	1 	3U			O	H2SW
1998121100302	19981211	00302		1998	12	11	HEEA0016859      	4	19981202	G	3422	102005403	GYRO            			BELL  	407   	407         		SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				HORIZONTAL GYRO DOES NOT CAGE.						1	G	7	1 	3U			O	H2SW
1998121100303	19981211	00303		1998	12	11	HEEA0016860      	4	19981202	G	3457	13824120234	RECEIVER        			BELL  	407   	407         		SW  										COCKPIT GPS	INOPERATIVE     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	403PH					53177				GPS RECEIVER INOPERATIVE.						1	G	7	1 	3U			O	H2SW
1998121100304	19981211	00304	SW  	1998	12	11	HEEA0016861      	1	19981202	G	3246	206053184121	SKID TUBE       			BELL  	407   	407         		SW  										MLG	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	402PH					53159				ACCELERATED WEAR ON EXTREME HEEL OF SKID TUBES.  DUE TO THE TAIL LOW ALTITUDE OF THIS AIRCRAFT MODEL IN A HOVER AND LAND	ING, THE EXTREME HEEL OF THE SKID OFTEN CONTACTS THE GROUND FIRST.  THIS AREA DOESN'T HAVE SKID SHOES OR OTHER PROTECTIV	E DEVICES.  WITH 800 HOURS TOTAL TIME ON THE AIRCRAFT, THE HEEL OF THE SKIDS HAS WORN 0.020 INCH.  THE LIMIT FOR THIS AR	EA IS 0.025 INCH PER THE BHT 407 MAINTENANCE MANUAL.   INSPECTION OF OTHER AIRCRAFT OF THIS MODEL ALSO EXHIBIT THIS ACCE	LLERATED WEAR.  REPORTING TO MANUFACTURER OF THIS PROBLEM.  SUBMITTER SUGGESTED CLOSE INSPECTION TO THIS AREA MAY BE REQ	UIRED.	1	G	7	1 	3U			O	H2SW
1998121100305	19981211	00305		1998	12	11	HEEA0016862      	4	19981202	G	3421	206075607103	GYRO            			BELL  	407   	407         		SW  										ATTITUDE	PRECESSING      	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				ATTITUDE GYRO PRECESSES.						1	G	7	1 	3U			O	H2SW
1998121100306	19981211	00306	SW  	1998	12	11	HEEA0016863      	1	19981202	G	6210	406016043101	COVER           		407015001107	BELL  	407   	407         		SW  										M/R BLADE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416	2487 			A437A442A3	53070				POTTING COMPOUND ON BOTTOM OF BLADES TRAILING EDGE WEIGHT POCKET CRACKING AND FLAKING OFF AND CAUSING COVER TO CORRODE. 	 (3 EACH BLADES).   REMOVED OLD POTTING COMPOUND AND CLEANED CORROSION ON COVER.  TREATED AREA AND PRIMED AREA.  FILLED 	LOW AREAS OF COVER WITH COMPOUND FILLER AND BLENDED SMOOTH.  TOUCHED UP AREA WITH PAINT AS REQUIRED.				1	G	7	1 	3U			O	H2SW
1998121100307	19981211	00307		1998	12	11	HEEA0016864      	4	19981202	G	2350	AMS44	ICS             			BELL  	407   	407         		SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	720PH					53277				PASSENGER NR 5 NO SIDETONE OR RECEIVE.						1	G	7	1 	3U			O	H2SW
1998121100308	19981211	00308		1998	12	11	HEEA0016865      	4	19981202	G	3416	D120P2T	ENCODER         			BELL  	407   	407         		SW  										ALTIMETER	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	427PH					53059				EXCESSIVE CASE LEAKAGE IN ALTIMETER.						1	G	7	1 	3U			O	H2SW
1998121100309	19981211	00309	SW  	1998	12	11	HEEA0016866      	1	19981202	G	2435	214060056103	STARTER         			BELL  	214   	214ST       	1182106	SW  										ENGINE	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				DURING 250 HOUR INSPECTION, FAILED CLUTCH SLIPPAGE TORQUE TEST.  BREAKAWAY WAS AT AROUND 450 INCH/POUNDS, LIMITS ARE 325	 TO 375 INCH/POUNDS.					2	G	7	2 	4U				H10SW
1998121100310	19981211	00310	SW  	1998	12	11	HEEA0016867      	1	19981204	G	3212	206050247135	COVER           			BELL  	407   	407         		SW  										FLOAT	TORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	141MA					53016				FRONT END OF FLOAT COVER TORN.						1	G	7	1 	3U			O	H2SW
1998121100311	19981211	00311	SW  	1998	12	11	HEEA0016868      	1	19981204	G	7810	407062021101	DUCT            			BELL  	407   	407         		SW  										EXHAUST	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1998121100312	19981211	00312	SW  	1998	12	11	HEEA0016869      	1	19981204	G	6420	407012101107	HUB             			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	177  				53267				T/R HUB ASSEMBLY UNABLE TO KEEP BALANCED.						1	G	7	1 	3U			O	H2SW
1998121100313	19981211	00313	SW  	1998	12	11	HEEA0016870      	1	19981204	G	6410	406016100119	BLADE           			BELL  	407   	407         		SW  										TAIL ROTOR	DAMAGED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	177  				53267				T/R BLADE - UNABLE TO KEEP BALANCED.						1	G	7	1 	3U			O	H2SW
1999011500381	19990115	00381	SW  	1999	1	15	HEEA059894       	1	19981222	G	5320	407250015	AIR DEFLECTOR   			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X					53267				TOP CORNER OF PLASTIC AIR DEFLECTOR BREAKING OFF WHERE BOLT HOLE IS.  THE KNURL NUT TIGHTENS UP WHEN DEFLECTOR IS PUSHED	 OUT, WHEN TRYING TO STOW DEFLECTOR, YOU CANNOT LOOSEN THE KNURL NUT BY HAND.  THEREFORE, THE CUSTOMER PULLS ON DEFLECTO	R BREAKINGTHE TOP.  APPLIED 0.025 INCH ALUMINUM DOUBLER TO EACH SIDE OF THE DEFLECTOR, USING 890 PROSEAL AND 7 EACH AN47	0AD-6 RIVETS.			1	G	7	1 	3U			O	H2SW
1999011500377	19990115	00377	SW  	1999	1	15	HEEA059896       	1	19981221	G	2435	206062200113	BRUSHES         			BELL  	407   	407         		SW  										START/GEN	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407PH	1459 				53003				STARTER/GENERATOR HAD EXCESSIVELY WORN BRUSHES.  REPAIRED.						1	G	7	1 	3U			O	H2SW
1999011500382	19990115	00382		1999	1	15	HEEA059897       	4	19981222	G	3451	066106602	TRANSCEIVER     			BELL  	214   	214ST       	1182106	SW  										E/E BAY	INOP            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				PILOT REPORTS DME INOPERATIVE.						2	G	7	2 	4U				H10SW
1999011500383	19990115	00383		1999	1	15	HEEA059898       	4	19981222	G	3452	066107100	TRANSPONDER     			BELL  	214   	214ST       	1182106	SW  										ATC	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				ATC TRANSPONDER REPORTED AS NOT SQUAWKING.  PERFORMED PRELIMINARY INSPECTION.  REPLACED TRANSISTOR Q104, Q502, AND TWO E	ACH SPACERS, REPAIRED.  BEGAN BENCH CHECK AND FOUND WEAK TRANSMIT POWER.   ALIGNED TRANSMITTER AND GOT 100 WATTS OUT.					2	G	7	2 	4U				H10SW
1999011500384	19990115	00384		1999	1	15	HEEA059899       	4	19981222	G	3422	066401000	HSI             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				HSI LOCKS UP IN ARNAV MODE, C/S NEEDLES PEG ON BOTH HSI.  TIME SINCE REPAIR 84:50 HOURS.						2	G	7	2 	4U				H10SW
1999011500385	19990115	00385		1999	1	15	HEEA059900       	4	19981222	G	3441	066401018	RNAV            			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOP            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				RNAV INOPERATIVE.						2	G	7	2 	4U				H10SW
1999011500386	19990115	00386		1999	1	15	HEEA059901       	4	19981222	G	3441	066401018	RNAV            			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				NO TO-FROM FLAG INDICATION ON AIRCRAFT.						2	G	7	2 	4U				H10SW
1999011500387	19990115	00387		1999	1	15	HEEA059902       	4	19981222	G	3454	071107600	VOR             			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				VOR NEEDLE 10-60 DEGREES OFF.						2	G	7	2 	4U				H10SW
1999011500388	19990115	00388		1999	1	15	HEEA059903       	4	19981222	G	3452	071119218	TRANSPONDER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOP            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				TRANSPONDER WILL NOT COME ON.						2	G	7	2 	4U				H10SW
1999011500389	19990115	00389		1999	1	15	HEEA059904       	4	19981222	G	3452	071119218	TRANSPONDER     			BELL  	214   	214ST       	1182106	SW  										COCKPIT	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				TRANSPONDER CONTROL HAS NO DISPLAY.						2	G	7	2 	4U				H10SW
1999011500390	19990115	00390		1999	1	15	HEEA059905       	4	19981222	G	3455	071121009	CONTROL UNIT    			BELL  	214   	214ST       	1182106	SW  										ADF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59806					28140				ADF CONTROL'S DISPLAY UNREADABLE.						2	G	7	2 	4U				H10SW
1999011500391	19990115	00391		1999	1	15	HEEA059906       	4	19981222	G	3455	071121009	CONTROL UNIT    			BELL  	214   	214ST       	1182106	SW  										ADF SYSTEM	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				ADF CONTROL'S PHOTO CELL WEAK AND KNOB MISSING.						2	G	7	2 	4U				H10SW
1999011500392	19990115	00392	SW  	1999	1	15	HEEA059908       	1	19981222	G	2140	209072433103	VALVE           			BELL  	214   	214ST       	1182106	SW  										AIR DIST	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				CIRCUIT BREAKER TRIPS IN AIR DISTRIBUTION SYSTEM.						2	G	7	2 	4U				H10SW
1999011500393	19990115	00393	SW  	1999	1	15	HEEA059909       	1	19981222	G	6720	214001540109	ACTUATOR        			BELL  	214   	214ST       	1182106	SW  										TAIL ROTOR	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				ACTUATOR KICKS AFCS PITCH OFFLINE.						2	G	7	2 	4U				H10SW
1999011500394	19990115	00394	SW  	1999	1	15	HEEA059910       	1	19981222	G	5330	214031614127	PLATE           			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				ELASTOMER CRACKED.						2	G	7	2 	4U				H10SW
1999011500395	19990115	00395	SW  	1999	1	15	HEEA059911       	1	19981222	G	5330	214031614128	PLATE           			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	5748M					28102				ELASTOMER CRACKED.						2	G	7	2 	4U				H10SW
1999011500396	19990115	00396	SW  	1999	1	15	HEEA059912       	1	19981222	G	6220	214031615106	CLEVIS ASSY     			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	6957Y					28139				ELASTOMER DETERIORATED AND DEBONDED.						2	G	7	2 	4U				H10SW
1999011500397	19990115	00397	SW  	1999	1	15	HEEA059913       	1	19981222	G	6330	214031617113	SPRING          			BELL  	214   	214ST       	1182106	SW  										MAIN ROTOR	FAILED          	E			HEEA	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			SW	03	6957Y					28139				ELASTOMER CUT.						2	G	7	2 	4U				H10SW
1999011500398	19990115	00398	SW  	1999	1	15	HEEA059914       	1	19981222	G	3213	214052053101	SKID TUBE ASSY  			BELL  	214   	214ST       	1182106	SW  										MLG	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RIV NUTS SPINNING AT CROSS-TUBE MOUNT.  REPLACED WITH SERVICEABLE PART.						2	G	7	2 	4U				H10SW
1999011500399	19990115	00399	SW  	1999	1	15	HEEA059915       	1	19981222	G	3213	214052053105	SKID TUBE ASSY  			BELL  	214   	214ST       	1182106	SW  										MLG	LOOSE           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										RIV NUTS SPINNING AT CROSS-TUBE MOUNT.  REPLACED WITH SERVICEABLE PART.						2	G	7	2 	4U				H10SW
1999011500400	19990115	00400	SW  	1999	1	15	HEEA059916       	1	19981222	G	3212	214052200107	FLOAT           			BELL  	214   	214ST       	1182106	SW  										AFT END	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				AFT FLOAT FAILED 6-MONTH INSPECTION.						2	G	7	2 	4U				H10SW
1999011500401	19990115	00401	SW  	1999	1	15	HEEA059917       	1	19981222	G	2810	214066256103	FUEL CELL       			BELL  	214   	214ST       	1182106	SW  										FUSELAGE	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	59806					28140				LEAKING THROUGH FUEL CELL WALL.						2	G	7	2 	4U				H10SW
1999011500402	19990115	00402		1999	1	15	HEEA059918       	4	19981222	G	2220	214074104101	SENSOR          			BELL  	214   	214ST       	1182106	SW  										SCAS SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				SCAS PITCH PROBLEM.						2	G	7	2 	4U				H10SW
1999011500403	19990115	00403		1999	1	15	HEEA059919       	4	19981222	G	3424	214075244001	RATE TRANSMITTER			BELL  	214   	214ST       	1182106	SW  										COCKPIT	INOP            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03										COPILOT TURN RATE COORDINATE INOPERATIVE.						2	G	7	2 	4U				H10SW
1999011500404	19990115	00404		1999	1	15	HEEA059920       	4	19981222	G	3416	214075268101	INDICATOR       			BELL  	214   	214ST       	1182106	SW  										COCKPIT	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	3897N					28106				INDICATOR SPINS.						2	G	7	2 	4U				H10SW
1999011500405	19990115	00405	SW  	1999	1	15	HEEA059921       	1	19981222	G	2913	214076033001	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYDRAULIC SYSTEM	LEAKING         	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	6957Y					28139				HYDRAULIC PUMP LEAKING AND NOISY.						2	G	7	2 	4U				H10SW
1999011500406	19990115	00406	SW  	1999	1	15	HEEA059922       	1	19981222	G	2913	214076033001	PUMP            			BELL  	214   	214ST       	1182106	SW  										HYDRAULIC SYSTEM	NOISY           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				HYDRAULIC PUMP NOISY.						2	G	7	2 	4U				H10SW
1999011500407	19990115	00407	SW  	1999	1	15	HEEA059923       	1	19981222	G	2430	214175150105	GENERATOR       			BELL  	214   	214ST       	1182106	SW  										DC SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	59805					28141				GENERATOR HAS NO OUTPUT.						2	G	7	2 	4U				H10SW
1999011500408	19990115	00408	SW  	1999	1	15	HEEA059924       	1	19981222	G	2424	214175153105	REGULATOR       			BELL  	214   	214ST       	1182106	SW  										AC SYSTEM	INOP            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				VOLTAGE REGULATOR INOPERATIVE.						2	G	7	2 	4U				H10SW
1999011500409	19990115	00409	SW  	1999	1	15	HEEA059925       	1	19981222	G	2432	214175379103	CHARGER         			BELL  	214   	214ST       	1182106	SW  										E/E BAY	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8045T					28101				BATTERY CHARGER WILL NOT TOP CHARGE BATTERY.						2	G	7	2 	4U				H10SW
1999011500410	19990115	00410	SW  	1999	1	15	HEEA059926       	1	19981228	G	6310	206040525001	FILTER          			BELL  	206   	206L1       	1182107	SW  										TRANSMISSION	LOOSE           	E			HEEA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			SW	03	5019F					45244				STUD PULLED FROM HOUSING.  LOST TRANSMISSION OIL DURING OPS CHECK FLIGHT DUE TO ONE EACH STUD FOR OIL FILTER CAP PULLING	 THREADS OUT OF HOUSING, ALLOWING FILTER BOWL TO COCK AND BLOW OIL BY BOWL O-RING.					1	G	7	1 	3U				H2SW
1999011500411	19990115	00411	SW  	1999	1	15	HEEA059927       	1	19981229	G	2823	47127	VALVE           			BELL  	407   	407         		SW  										FUEL SYSTEM	FAILED          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	57416					53070				SHUT-OFF VALVE TRIPS CIRCUIT BREAKER.						1	G	7	1 	3U			O	H2SW
1999011500412	19990115	00412	SW  	1999	1	15	HEEA059928       	1	19981229	G	6340	222375077117	TRANSMITTER     			BELL  	407   	407         		SW  										MAIN ROTOR	MALFUNCTIONED   	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH					53228				OIL PRESSURE LIGHT DOESN'T COME ON AT SHUTDOWN.						1	G	7	1 	3U			O	H2SW
1999011500413	19990115	00413	SW  	1999	1	15	HEEA059929       	1	19981229	G	6300	406310405101	UNIVERSAL       			BELL  	407   	407         		SW  										M/R DRIVE	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	408PH	888  				53228				MAIN ROTOR DRIVE HAS EXCESSIVE AXIAL PLAY.						1	G	7	1 	3U			O	H2SW
1999011500414	19990115	00414	SW  	1999	1	15	HEEA059930       	1	19981229	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										T/R DRIVE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500415	19990115	00415	SW  	1999	1	15	HEEA059931       	1	19981229	G	6420	406040339111	BEARING         		407040303101	BELL  	407   	407         		SW  										TAIL ROTOR	ROUGH           	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	8595X	173  			AFS1049	53267				TAIL ROTOR BEARINGS ROUGH.  SERIAL NUMBERS REMOVED ARE A98-0445 AND A98-0506.						1	G	7	1 	3U			O	H2SW
1999011500416	19990115	00416	SW  	1999	1	15	HEEA059932       	1	19981229	G	6420	406312100101	BEARING         			BELL  	407   	407         		SW  										TAIL ROTOR	WORN            	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	447PH	1401 				53114				TAIL ROTOR HAS WORN FEATHERING BEARINGS.						1	G	7	1 	3U			O	H2SW
1999011500417	19990115	00417	SW  	1999	1	15	HEEA059933       	1	19981229	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500418	19990115	00418	SW  	1999	1	15	HEEA059934       	1	19981229	G	5312	206064902105	BULKHEAD        			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				BULKHEAD CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500419	19990115	00419	SW  	1999	1	15	HEEA059935       	1	19981229	G	5320	206032305129A	ANGLE           			BELL  	407   	407         		SW  										FUSELAGE	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	405PH					53207				FUSELAGE ANGLE CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500420	19990115	00420	SW  	1999	1	15	HEEA059936       	1	19981229	G	7921	407062021101	DUCT            			BELL  	407   	407         		SW  										OIL COOLER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				OIL COOLER DUCT CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500421	19990115	00421	SW  	1999	1	15	HEEA059937       	1	19981229	G	6510	206061432121	HOUSING         			BELL  	407   	407         		SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	407MM					53060				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500422	19990115	00422	SW  	1999	1	15	HEEA059938       	1	19981229	G	6510	206061432121	HOUSING         			BELL  	407   	407         		SW  										BLOWER	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	437PH					53072				BLOWER HOUSING CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500423	19990115	00423	SW  	1999	1	15	HEEA059939       	1	19981229	G	6720	406012129101	LINK ASSY       			BELL  	407   	407         		SW  										T/R PITCH	FROZEN          	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				LINK ASSEMBLY BEARING FROZEN.						1	G	7	1 	3U			O	H2SW
1999011500424	19990115	00424	SW  	1999	1	15	HEEA059940       	1	19981229	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	721PH					53278				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500425	19990115	00425	SW  	1999	1	15	HEEA059941       	1	19981229	G	6510	406040340101	DISK COUPLING   			BELL  	407   	407         		SW  										TAIL ROTOR	CRACKED         	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	722PH					53288				DISK COUPLING CRACKED.						1	G	7	1 	3U			O	H2SW
1999011500378	19990115	00378	EU  	1999	1	15	HEEA059944       	1	19981221	G	2910	SC50711	SERVO           			SNIAS 	350   	AS350B2     	8680813	EU  										HYDRAULIC SYSTEM	CORRODED        	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	350BZ	2937 				2653				PART IS CORRODED.  (CORROSION ON SERVO BODY)						1	G	7	1 	3U				H9EU
1999011500379	19990115	00379	EU  	1999	1	15	HEEA059946       	1	19981221	G	3310	704A46814049	LIGHT           			SNIAS 	350   	AS350B2     	8680813	EU  										COCKPIT	INOP            	E			HEEA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			SW	03	60951					2771				GRADUATOR LIGHT WILL NOT COME ON.						1	G	7	1 	3U				H9EU
1999011500380	19990115	00380	EU  	1999	1	15	HEEA059948       	1	19981221	G	6410	355A12004008	BLADE           			SNIAS 	350   	AS350B2     	8680813	EU  										TAIL ROTOR	DELAMINATED     	E			HEEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			SW	03	60951	280  				2771				SEPARATION AT TRAILING EDGE TIP OF ONE BLADE.						1	G	7	1 	3U				H9EU
1998121700004	19981217	00004	WP  	1998	12	17	IH987518001      	1	19981207	G	3213	3598295	STRUT           	DOUG        	5759145506  	DOUG  	DC8   	DC862       	3021970	WP  										RT MLG	DAMAGED         	B			IH3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	07	1804	4312 			AA901025	45896				UPON DISASSEMBLY OF RT MLG STRUT FOR SEAL CHANGE, P/N 3598295 FOLLOWER FOUND TO BE FRACTURED CAUSING DAMAGE TO P/N 37673	709-501 ADAPTER ASSY PACKING, P/N 3598375 SPACER.  UPPER BEARING SPLIT, P/N 3598297 HEAD, PISTON, AND P/N 3598296 VALVE,	 REBOUND CHECK.  VISUALLY INSPECTED THE CYLINDER WITH NO DAMAGE NOTED.  REPLACED DAMAGED PARTS.  REF DIMENSION AVIATION 	WORK ORDER 7518-12-M044.			2	L	7	4 	4F				4A25
1998051500294	19980515	00294	SW  	1998	5	15	KBTR482F         	1	19980430	G	5313	206031341123	LONGERON        			BELL  	206   	206L1       	1182107	SW  										LT ENG LEG	CRACKED         	B			KBTR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	07	5746N	7631 				45461				INSPECTION FOUND 4 INCH CRACK RUNNING LONGITUDINALLY .3 INCH BELOW CENTER LEFT HAND ENGINE LEG ATTACHMENT BOLT HOLE.  SU	BMITTER RECOMMENDATIONS TO PREVENT RECURRENCE:  INCREASE FOOT PRINT OF CUP P/N 206-032-315-113.  (X)					1	G	7	1 	3U				H2SW
1998062600290	19980626	00290	NE  	1998	6	26	M9QR564N         	2	19980521	G	7250	762425	AIRSEAL         								PWA   	JT8   	JT8*        	52044	NE  					LP TURBINE	CRACKED         	B			M9QR	K				NONE                    				W			INADEQUATE Q C            			IN	INSP/MAINT     	1			SW	17										WHILE RE-EVALUATING THE DATA FOR TI-JT8D-117 ON WELDING OF THE KNIFE EDGE AIRSEALS ON 2ND, 3RD, AND 4TH STAGE ROTATING A	IRSEALS, CRACKING WAS DETECTED IN THE PEDESTAL RADIUS.  THE PART WAS DAMAGED AS THE RESULT OF THE LASER WELDING PROCESS.	   THE INVESTIGATION IS CONTINUING.  REF:  OPERATOR CONTROL NR 98ZZZX2242 AND 98ZZZX2243.       (X)									4	F			E2EA
1999092400177	19990924	00177		1999	9	24	MVH0064186       	4	19980129	G	2312	4000102000	TRANSCEIVER     			AEROSP	SA365 	SA365N      	8680669	EU  										COCKPIT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				TRANSCEIVER REMOVED OFF FREQUENCY.						1	G	7	2 	3U				H10EU
1999092400178	19990924	00178		1999	9	24	MVH0064187       	4	19980226	G	3442	071131800	ANTENNA         			AEROSP	SA365 	SA365N      	8680669	EU  										WEATHER RADAR	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				ANTENNAE FAULT.						1	G	7	2 	3U				H10EU
1999092400179	19990924	00179		1999	9	24	MVH0064189       	4	19980310	G	2210	41800468800	AMPLIFIER       			AEROSP	SA365 	SA365N      	8680669	EU  										AUTO PILOT	INOPERATIVE     	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				ALTITUDE HOLD AND AIRSPEED HOLD INOPERABLE.						1	G	7	2 	3U				H10EU
1999092400180	19990924	00180		1999	9	24	MVH0064191       	2	19980310	G	7412	9580113800	HE GENERATOR    			AEROSP	SA365 	SA365N      	8680669	EU  										ENGINE	INOPERATIVE     	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	820  				6068				HE GENERATOR INOPERABLE.						1	G	7	2 	3U				H10EU
1999092400181	19990924	00181	EU  	1999	9	24	MVH0064193       	1	19980414	G	6730	8031A	SERVO CONTROL   			AEROSP	SA365 	SA365N      	8680669	EU  										CYCLIC	INTERMITTENT    	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				INTERMITTENT SERVO LIGHT IN SYSTEM.						1	G	7	2 	3U				H10EU
1999092400182	19990924	00182	EU  	1999	9	24	MVH0064194       	1	19980501	G	2822	P94C16601	PUMP            			AEROSP	SA365 	SA365N      	8680669	EU  										FUEL BOOST	MALFUNCTIONED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	1033 				6068				BOOSTER PUMP REMOVED DUE TO LOW PRESSURE.						1	G	7	2 	3U				H10EU
1999092400183	19990924	00183		1999	9	24	MVH0064196       	4	19980514	G	2210	41800468106	AMPLIFIER       			AEROSP	SA365 	SA365N      	8680669	EU  										AUTO PILOT	FAILED          	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF					6068				AMPLIFIER UNIT, SN 170,  LANE 1 COMPARATOR INOPERABLE.  WILL NOT HOLD ROLL, LANE 1.						1	G	7	2 	3U				H10EU
1999092400184	19990924	00184	EU  	1999	9	24	MVH0064197       	1	19980520	G	2435	524031B	BEARING         			AEROSP	SA365 	SA365N      	8680669	EU  										STARTER/GEN	DISINTEGRATED   	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	4524 				6068				BEARING HAS SLOP, GETTING HIGH VIBRATIONS FROM GENERATOR.						1	G	7	2 	3U				H10EU
1999092400185	19990924	00185	EU  	1999	9	24	MVH0064198       	1	19980614	G	6720	SC4161B	SERVO CONTROL   			AEROSP	SA365 	SA365N      	8680669	EU  										CYCLIC	LEAKING         	H			BAQA	K				NONE                    				K			FLUID LOSS                			IN	INSP/MAINT     	1			EA	03	63CF	949  				6068				SERVO CONTROL LEAKING AT SHAFT SEAL.						1	G	7	2 	3U				H10EU
1999092400186	19990924	00186	EU  	1999	9	24	MVH0064199       	1	19980618	G	2435	524031B	BEARING         			AEROSP	SA365 	SA365N      	8680669	EU  										STARTER/GEN	WORN            	H			BAQA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			EA	03	63CF	890  				6068				STARTER/GENERATOR HAD BEARING PLAY.						1	G	7	2 	3U				H10EU
1998032600610	19980326	00610	CE  	1998	3	26	NI2R032L         	1	19980201	G	5210		LATCH PIN ARM   			LEAR  	55    	55C         	5170706	CE  										CABIN DOOR	CRACKED         	B			NI2R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			CE	03	40CR					144				PERFORMED EDDY CURRENT TEST PER LEAR NDT MANUAL PART 3 52-10-01.  DETECTED LINEAR INDICATION AT AREA 'F' AT APPROX 4 O'C	LOCK POSITION.  REFERENCE ST LOUIS TEST LAB 98F-0350.  ACFT LANDINGS:  1,621.  ACFT TT:  2,372 HOURS.  TEST PERFORMED MA	RCH 2, 1998.  (X)				2	L	7	2 	4F			RT	A10CE
1998101600525	19981016	00525	EU  	1998	10	16	QXEA9801426      	1	19980911	G	5330		SKIN            			FOKKER	F28   	F28MK4000   	4990810	EU  										FRAME 6305-6805	DENTED          	A			QXEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	491US					11156				PDX - THERE IA DENT ON THE LEFT FUSELAGE SKIN BETWEEN FRAME 6305 AND 6805, STRINGER 16.  REPAIRED IAW FOKKER SRM 53-02-0	6 PAGE 4, FIGURE 2.					2	L	7	2 	4F			RT	A20EU
1998112600332	19981126	00332	EU  	1998	11	26	QXEA9801689      	1	19981107	G	5753		SKIN            			FOKKER	F28   	F28MK4000   	4990810	EU  										LT TE FLAP	DAMAGED         	A			QXEA	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NM	09	484US					11234				LEFT-HAND INBOARD FLAP LOWER INBOARD TRAILING EDGE HAS LARGE AREAS OF ROCK DAMAGE FROM MAIN TIRES.  REPAIRED IAW FOKKER 	SRM 51-20-0, PARAGRAPH 4.					2	L	7	2 	4F			RT	A20EU
1998022600065	19980226	00065	NE  	1998	2	26	SADF9801         	2	19980121	G	7200		ENGINE          			BAC   	146   	AVRO146RJ100	1500096	EU  	LYC   	LF507 	LF5071F     		NE  					NR 4	BIRD STRIKE     	A			SADF	E	A	F		ENGINE SHUTDOWN         	UNSCHED LANDING         	ACTIVATE FIRE EXT.      		C			F.O.D.                    			CL	CLIMB          	1			SO	23	508MM	6074 				E3247	LF07361			FLT 166 AIR TURN TO BAQ - FOD (BIRD) DURING TAKEOFF ENGINE NR 4.  ENGINE WAS SHUT DOWN ACCORDING TO CHECK LIST.  EXTINGU	ISHER NR 1 WAS DISCHARGED DUE TO POSSIBLE STRUCTURAL DAMAGE.  OVERWIEGHT LOG WAS PERFORMED AT 93,500 POUNDS.  CHANGED EN	GINE NR 4 IAW AMM 71-00-00.  IT WAS PERFORMED OVERWEIGHT CONDITIONAL INSPECTION IAW AMM 05-50-11 AND WAS FOUND IN NORMAL	 CONDITION.			2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998072400719	19980724	00719	NE  	1998	7	24	SADF9803         	2	19980607	G	7200		ENGINE          			BAC   	146   	AVRO146RJ100	1500096	EU  	LYC   	LF507 	LF5071F     		NE  					NR 1	VIBRATION       	A			SADF	C	D			ABORTED TAKEOFF         	RETURN TO BLOCK         			E			VIBRATION/BUFFET          			TO	TAKEOFF        	1			SO	23	505MM					E3242	LF07262			BOG/VUP - FLT 594 - REJECTED TAKEOFF DUE TO HIGH VIBRATION (MAX TRUST 1.0 INCHREASING DURING RUNNING TO 1.2) ENGINE NR 1	 REJECTED WAS DONE AT 65 KNOTS.  IT WAS CLEANED AND ADJUSTED.  VIBRATION PICKUP P246 CONNECTOR WAS CHECKED, AND FOUND OK	.  ENGINE NR 1 RUN-UP.  N1 SET 95.1 AND VIBRATION WAS 0.5 IAW AMM 72-00-00.  (X)				2	H	7	4 	4F	4	F	RT	A49EU   	E6NE
1998091100022	19980911	00022	EU  	1998	9	11	SADF9807         	1	19980725	G	2731		TRIM TAB        			BAC   	146   	AVRO146RJ100	1500096	EU  										ELEVATOR	LOOSE           	A		A	SADF	B				EMER. DESCENT           				F			FLT CONT AFFECTED         			CR	CRUISE         	1			SO	23	504MM					E3221				CLO/ADZ - FLT 176 - DURING CRUISE AT FL 240 IN ICING CONDITIONS USING ENGINE WING AND TAIL ANTI-ICE ALONG WITH CONT IGN,	 AND SPEED REDUCED TO M 0,60, THE AIRPLANE ENTERED IN ABRUPT PITCH OSCILLATIONS.  PROCEDURE (CHECK LIST) WAS FOLLOWED AN	D THE OSCILLATIONS CEASED AT 208 KNOTS.  DESCEND WAS INITIATED DOWN TO FL 200 AND STILL DURING DESCENT THE OSCILLATIONS 	CONTINUED.  ELEVATOR WAS INSPECTED VISUALLY IAW  AMM05-21-13.  ALL DRAIN ORIFICES WERE CLEAR.  CONTROL CABLES WERE INSPE	CTED AND FOUND OK.  ELEVATOR APPEARS NORMAL.  THE TRIM TAB ON THE RIGHT SIDE SEEMS TO BE A LITTLE LOOSE.  IT WAS ADJUSTE	D.  PLEASE KEEP UNDER OBSERVATION AND REPORT.  (X)	2	H	7	4 	4F			RT	A49EU
1998021900009	19980219	00009	NE  	1998	2	19	SI3R98001        	2	19980127	G	7210	7757602	BEARING         	HAMSTD      	6044T35P01  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					GC 49 GRBOX	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13732			7378		GEE367295			DURING DISASSEMBLY OF GEARBOX, THE RIGHT FORWARD IDLER GEAR BEARING RACE WAS FOUND CRACKED.  PN 775760-2, FIG 8 ITEM 85.	  HSS SO NR 75533SG.  CUST:  SKYWAYS A/L.  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6
1998022600868	19980226	00868	NE  	1998	2	26	SI3R98002        	2	19980203	G	7210	7757571	BEARING         	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARBOX	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		14350			9191		GEE785342			DURING DISASSEMBLY OF GEARBOX, THE FORWARD ROLLER BEARING INNER RACE WAS FOUND CRACKED, PN 775757-1, FIG 7, ITEM 60.  (X	)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998022600869	19980226	00869	NE  	1998	2	26	SI3R98003        	2	19980213	G	7210	7757704	RETAIN NUT      	HAMSTD      	5074T51G10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARBOX	LOOSE           	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		8381 			1H100188		GEE785506			DURING DISASSEMBLY OF GEARBOX, THE DRIVE GEAR RETENTION NUT WAS REMOVED WITH NO TORQUE REQUIRED.  INSTALLATION TORQUE IS	 1,550 - 1,600 FEET/POUNDS.  NUT P/N 775770-4, FIG 7 ITEM 25.  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998031200739	19980312	00739	NE  	1998	3	12	SI3R98004        	2	19980218	G	7210	7757602	IDLER BEARING   	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GEARBOX	CRACKED         	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		17027			7316		GEE785371			DURING DISASSSEMBLY OF GEARBOX, THE FORWARD IDLER GEAR BEARING INNER RACE WAS FOUND CRACKED.  P/N 775760-2, FIG 8 ITEM 8	5.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998031900270	19980319	00270	NE  	1998	3	19	SI3R98005        	2	19980223	G	7210	7895781	TAB WASHER      		5074T16G10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC 49 GRBOX IDLR	FAILED          	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		11623			1H100033		GEE785623			DISASSEMBLY OF GEARCASE REVEALED THE MAIN PUMP SEIZED, THE TAB WASHER ON THE FORWARD RIGHT IDLER GEAR BROKEN.  METAL CON	TAMINATION THROUGHOUT THE CASE AND IN PUMP.  THIS GEARCASE IS NOT REPAIRABLE AND IS CONSIDERED FOR SCRAP DISPOSITION.					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998031900269	19980319	00269	NE  	1998	3	19	SI3R98006        	2	19980224	G	7210	7757704	RETAIN NUT      		7758001     	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GC49 GEARBOX	LOOSE           	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					UDAG0214					DURING DISASSEMBLY OF GEARBOX, THE DRIVE GEAR RETENTION NUT WAS REMOVED WITH NO TORQUE REQUIRED.  INSTALLATION TORQUE IS	 1550-1600 FEET/POUNDS.  (NUT P/N 775770-4, FIG 7 ITEM 25).  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998042400099	19980424	00099	NM  	1998	4	24	SI3R98007        	1	19980408	G	2140	8102082	HEAT EXCHANGER  	HAMSTD      		BOEING	777   	777222      	1385219	NM  										DUCT	FAILED          	B	P		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03	766UA	9861 			0007					THE HEAT EXCHANGER WAS RECEIVED WITH THE PRIMARY INLET DUCT CRACKED THE FULL LENGTH AND PEALED BACK.						2	L	7	2 	4F			RT	T0001SE
1998061900926	19980619	00926	NE  	1998	6	19	SI3R98008        	2	19980520	G	7210	6044T35P10	GEARBOX         	HAMSTD      	GC49        	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  						DAMAGED         	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		14611	788  		UDAG0843					DISASSEMBLY OF GEARBOX REVEALED SEVERE DAMAGE TO THE DAMPER RING ON THE RIGHT FORWARD IDLER GEAR.  ALSO, RIGHT FORWARD I	DLER GEAR WEB CRACKED (P/N 792207-3) BULKHEAD (P/N 775754-13) HAS 0.060 INCH - 0.080 INCH GROOVE WORN IN.  RECOMMEND SCR	AP DISPOSITION.  (P/N 775760-2, FIG 8 ITEM 85).  HSS SO NR 85198SE.  CUST:  SIMMONS A/L.				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998080700225	19980807	00225	NE  	1998	8	7	SI3R98009        	2	19980605	G	7210	5074T51G10	GEARBOX         		GC49        	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					ENGINE	WORN            	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		10542			1H100219		GEE785434			DISASSEMBLY OF GEAR CASE REVEALED THE TAB WASHER AND RETAINING RING ON THE FORWARD RIGHT IDLER GEAR BROKEN.  BROKEN BEAR	ING (P/N 775765-2) IN SLIDER BLOCK ASSY.  INPUT PINION GEAR WORN.  METAL CONTAMINATION LOCAL TO THIS AREA.  HSS SO NR 86	314 SE.  CUST:  WINGS WEST A/L				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998080700247	19980807	00247	NM  	1998	8	7	SI3R98010        	1	19980615	G	3610	774910909	HOUSING         	HAMSTD      	77385619    	BOEING	747   	747*        		NM  										IP CHECK VLV	FRACTURED       	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03					890431					UPON RECEIPT OF UNIT, THE FOLLOWING CONDITIONS WERE NOTED AT INCOMING INSPECTION.  FOR DESCRIPTION, (REF:  CMM 36-12-06 	PG 602).  VALVE CAP WORN, ANTI-ROTATION TEETH BROKEN OFF, CHECK VALVE STOP WORN OFF.  GUIDE TUBE FRACTURED INTO 2 PIECES	.  POPPET SHAFT TEETH WORN OFF (REF:  CMM 36-12-06 PG 511).  CUSTOMER P.O, 50A-88013-24667-7.  S.O. 87373SE.  (X)				2	L	7	4 	4F			RT	A20WE
1998081400176	19980814	00176	NM  	1998	8	14	SI3R98012        	1	19980707	G	2150	7274504	HOUSING         	HAMSTD      	7192389     	BOEING	747   	747*        		NM  										ACM	PERFORMATED     	B	P		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		13663			KC10C83					UPON RECEIPT OF THE COMPESSOR HOUSING, THE FOLLOWING CONDITIONS WERE NOTED AT TEAR-DOWN:  COMPRESSOR HOUSING HAS A 1 INC	H PERFORATION IN WALL NEAR DUCT.  (REF:  CMM 21-51-03 PAGE 436A).  SHAFT, WHICH IS MATED TO ROTOR, SNAPPED AND PIECES OF	 ROTOR SNAPPED OFF DUE TO CONTACT WITH HOUSING.  (REF:  CMM 21-51-03 PAGE 516). ONE PIECE OF THE ROTOR APPEARS TO HAVE G	ONE THROUGH THE HOUSING WALL.  CUSTOMER P.O. 481W41761.  S.O. NR 88383SG.  (X)			2	L	7	4 	4F			RT	A20WE
1998082800062	19980828	00062	NE  	1998	8	28	SI3R98013        	2	19980721	G	7210	7757704	RETAIN NUT      		6044T35P01  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A2      	30030	NE  					GC49 GEARBOX	LOOSE           	B	S		SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		23562			UDAG0043		GEE367307			DURING DISASSEMBLY OF GEARBOX, THE DRIVE GEAR RETENTION NUT WAS REMOVED WITH NO TORQUE REQUIRED. INSTALLATION TORQUE IS 	1550 - 1600 FEET/POUNDS.  (NUT P/N 775770-4, FIG 7 ITEM 25).  HSS SO NR 86355SE.  CUST:  AIR OSTRAVA/GE. CMM 72-11-02. (	X)				2	L	7	2 	4T	4	T	RT	A52EU   	E8NE6
1998121800027	19981218	00027	EU  	1998	12	18	SI3R98015        	1	19981109	G	6120		PUMP            	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT75A       	30030	NE  					PROP CONTROL	DAMAGED         	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		21765			UDAG0021		GEE367372			DISSASSEMBLY OF GEAR CASE REVEALED OIL PUMP (P/N 775798-1) WITH BROKEN OFF INPUT SHAFT.  ALSO, SPRAY BAR BROKEN FORWARD 	RIGHT IDLER ROLLER BEARING SPALLED (S/N 10, P/N 775760-2).  HSS SO NR 208555 SO  CUST:  BUSINESS EXPRESS A/L.  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998121800028	19981218	00028	NE  	1998	12	18	SI3R98016        	2	19981109	G	7210	7757602	BEARING         	HAMSTD      	6044T35P10  	SAAB  	SF340 	SF340A      	7850100	EU  	GE    	CT7TP 	CT79B       	30030	NE  					GEARBOX	SPALLED         	B			SI3R	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			NE	03		15239			7435		GEE785625			DURING DISASSEMBLY OF GEARBOX, THE LT FORWARD IDLER GEAR ROLLER BEARING WAS FOUND TO HAVE A SPALLED INNER RACE AND ROLLE	RS.  HSS SO NR 210197 SO.  CUST:  AMR.  (X)					2	L	7	2 	4T	4	T	RT	A52EU   	E8NE
1998061200602	19980612	00602	NM  	1998	6	12	TWRA9825         	1	19980425	G	3397		WIRE            			BOEING	747   	747212B     	1384886	NM  										CABIN	FAILED          	A			TWRA	K				NONE                    				L			NO TEST                   			IN	INSP/MAINT     	1			EA	15	6186					21439				'A' ZONE EGRESS LIGHTING INOP.  REPAIRED 'Z' ZONE EGRESS LIGHTING WIRES, OPS CHECK OK PER MM 33-51-00.  (M)						2	L	7	4 	4F			 	A20WE
1998060500022	19980605	00022	GL  	1998	6	5	UTVR98001        	2	19980423	G	7250		BEARING         			BELL  	206   	206L3       	1182108	SW  	ALLSN 	250C  	250C30P     	03013	GL  					GP NR 8	FAILED          	B			UTVR	K				NONE                    				O			OTHER                     			IN	INSP/MAINT     	1			WP	09	791CA					51455	CAE895523			AFTER CAREFUL INSPECTION OF THE GP TURBINE AND RELATED COMPONENTS, OBSERVED THE NR 8 BEARING HAD CATASTROPHICALLY FAILED	 CAUSING THE CHIP DETECTOR IN THE COCKPIT TO INDICATE.  THE AIRCRAFT WAS IMMEDIATELY GROUNDED.  THE SUBSEQUENT INSPECTIO	N REVEALED NO TELLTALE SIGNS OF THE CAUSE OF THE BEARING FAILURE.  ALL OIL LINES WERE TESTED AND FOUND FREE OF OBSTRUCTI	ONS.  ALL RELATED COMPONENTS AND SYSTEMS DID NOT SHOW SIGNS OF FAILURE, PREMATURE WEAR, OR ABNORMAL STRESSES.  SUBMITTER	'S OPINION IS THE NR 8 BEARING HAD INHERENT UNDETECTABLE DEFECTS WHICH RESULTED IN THE FAILURE.		1	G	7	1 	3U	3	U		H2SW    	E1GL
1998041700103	19980417	00103	SO  	1998	4	17	XC4R1546         	1	19980403	G	3242	1331096	STATOR DISK     	BFGOODRICH  	21585       	EMB   	120   	EMB120ER    	3260203	SO  										NR 1 BRAKE	CRACKED         	B			XC4R	K				NONE                    				O			OTHER                     			NR	NOT REPORTED   	1			SO	19	2FOR	3684 	1193 		1636	120302				BRAKE NR 1 STATOR FAILED (CRACKED), JAMMING WHEEL BRAKE ASSEMBLY WHICH DAMAGED BOTH WHEEL AND BRAKE TORQUE TUBES.						2	L	7	2 	4T			RT	A31SO
1999030500457	19990305	00457	CE  	1999	3	5	XEFR855K         	1	19981202	G	7830	635405159	BELLCRANK       			CESSNA	525   	525         	2076601	CE  										LT ATTENUATOR	CRACKED         	B			XEFR	O				OTHER                   				O			OTHER                     			NR	NOT REPORTED   	1			GL	03	41EB					5250116				PILOT REPORTED LEFT HAND ATTENUATOR LIGHT STAYS ON WHEN DEPLOYED.  FOUND LEFT HAND ATTENUATOR BELLCRANK CRACKED AT ACTUA	TOR END.  REMOVED P/N 6354051-59 AND REPLACED WITH P/N 6354051-59.  TIGHTENED HARDWARE IAW CHAPTER 20 OF CITATION MM.  O	PS CHECK GOOD.  (X)				1	L	7	2 	4F			RT	A1WI